Numerical Study of Film Cooling in Oxygen/Methane Thrust Chambers
|
|
- Job Rich
- 8 years ago
- Views:
Transcription
1 4 TH EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES Numerical Study of Film Cooling in Oxygen/Methane Thrust Chambers B. Betti, E. Martelli, F. Nasuti and M. Onofri Università di Roma La Sapienza Dipartimento di Ingegneria Meccanica e Aerospaziale, via Eudossiana 18, Roma 00184, Italy Seconda Università di Napoli Dipartimento di Ingegneria Aerospaziale e Meccanica, Via Roma 29, Aversa 81131, Italy Abstract Oxygen/methane propellant combination has recently gained interest for space propulsion as proved by the inclusion of its study in the European Community 7 th Framework Program (FP7) project In-Space Propulsion 1 (ISP-1). In the rocket engine design phase, the different available options for thrust chamber cooling have to be studied. In this framework, the thermo-fluid dynamic analysis of film-cooled thrust chambers is one of the necessary steps for the reliable development of liquid rocket engines. In the present study, thrust chamber film cooling efficiency is analyzed by means of a multi-component Reynolds-Averaged Navier-Stokes (RANS) equations solver. After validation of the simplified approach against available data for oxygen/hydrogen thrust chambers, a preliminary numerical study of the oxygen/methane film-cooled thrust chamber which will be tested in the ISP-1 project is carried out. 1. Introduction The In-Space Propulsion 1 (ISP-1) project founded by the European Community 7 th Framework Program (FP7) has the objective of improving the knowledge of future space mission cryogenic propulsion [1]. One of the goals of this project is to acquire a basic knowledge of low thrust cryogenic oxygen/methane propulsion. Methane as a fuel can provide a higher specific impulse, together with better cooling abilities and less soot deposition than kerosene. Differently than oxygen/hydrogen propellant combination, oxygen/methane can be considered as space storable and is favored by higher density [2], although it gives lower specific impulse. The adequate understanding and accurate prediction of heat transfer characteristics and wall temperature distribution in presence of film cooling are considered key features for the development of reliable oxygen/methane engines. Film cooling in the hot-gas side of thrust chambers is an important technique which can relieve the regenerative cooling system requirements. Film cooling is obtained by injecting a cold gas or liquid tangentially to the wall to protect it from the hot combustion products in the core of the chamber and to keep it under the safe operative temperature. Film injection is provided by a single circumferential slot (curtain cooling) or through a number of finite width slots (slot film cooling). This active cooling technique has been widely adopted for high performance thrust chamber such as Space Shuttle main engine (SSME) and Vulcain 2 for the European launcher Ariane 5. For these engines thermal and structural loads are reduced by the combined use of film and regenerative cooling. The influence of main governing parameters on film cooling efficiency has been included in several analytical models [3, 4, 5, 6]. Air-air and foreign gas-air film cooling have been widely investigated by experimental studies [3], [7] and numerical simulations [8, 9, 10]. Recently, film cooling in oxygen/hydrogen thrust chambers has been investigated by experimental studies [11, 12, 13, 14] and numerical simulations [15, 16, 17, 18]. Film cooling efficiency has been also experimentally investigated for oxygen/kerosene [19] and oxygen/methane [20] propellant combinations. The aim of the present study is to assess the capability of a simplified approach to capture peculiar features of film-cooled thrust chambers in terms of wall heat flux and film cooling efficiency. The simplified approach consists of considering only the main geometrical aspects of the injection plate without introducing any modeling of atomization, vaporization, mixing and combustion. Before analyzing film cooling test cases, a benchmark experimental test case of a nozzle operated with hot air is reproduced to validate the imposed wall temperature boundary condition implemented Copyright 2011 by B. Betti, E. Martelli, F. Nasuti and M. Onofri. Published by the EUCASS association with permission.
2 PP LIQUID PROPULSION ISP 1 in a in-house CFD numerical code. Then, a detailed film cooling experimental test case is reproduced to assess the capability of the simplified approach to evaluate wall heat flux in a liquid oxygen/gaseous hydrogen subscale combustion chamber with and without film cooling. Finally, methane film cooling capability is analyzed reproducing an experimental test case which will be carried out in the frame of the ISP-1 project [1]. 2. Numerical approach The present approach relies on an in-house 3D multi-block finite volume Reynolds-Averaged Navier-Stokes (RANS) equations solver [21], modified to simulate multi-component mixtures of thermally perfect gases. Multi-component diffusion has been validated [22] reproducing two experimental test cases retrieved in open literature. Turbulence is described by means of the Spalart-Allmaras one equation model [23]. A constant turbulent Schmidt number is adopted to model turbulent diffusivity. 3. Validation test cases 3.1 Hot-gas side heat transfer Hot-gas side boundary condition has been validated by reproducing the benchmark experimental test case No. 313 of [24] where wall temperature and wall heat flux measurements are collected. The test case is characterized by a supersonic nozzle where compressed and heated air flows with a stagnation pressure of bar and a stagnation temperature of K. Wall temperature and wall heat flux measurement uncertainties are ±1% and ±8%, respectively. The numerical reproduction of the experimental test case has been carried out by axis-symmetric computations with grid and boundary conditions shown in Fig. 1. Three grid levels were employed to ensure grid convergence, with the Figure 1: Convergent-divergent nozzle [24]: grid (medium grid level) and boundary conditions enforced. fine grid having 200x180 cells in the axial and radial directions, respectively. The medium grid is obtained by removing one node out of two, in each coordinate direction, from the fine grid. In the same way the coarse grid is obtained from the medium grid. Axial velocity profile in section x = mm and wall heat flux along the nozzle obtained with coarse, medium and fine grids are shown in Fig. 2(a) and Fig. 2(b), respectively. Asymptotic grid convergence is reached and Richardson extrapolated numerical solution [25] is evaluated and plotted. To evaluate the grid independence of the numerical solution, percentage errors of each grid level solution referred to the Richardson extrapolated solution are plotted. Axial velocity profiles show errors lower than 0.5% even with the coarse grid, whereas wall heat flux profiles show errors up to 5% with the coarse grid in the region near the inlet section where boundary layer develops. Comparison 2
3 B. Betti, E. Martelli, F. Nasuti and M. Onofri - NUMERICAL STUDY OF FILM COOLING IN OXYGEN/METHANE THRUST CHAMBERS (a) Axial velocity profile in section x = mm. (b) Wall heat flux along the chamber Figure 2: Convergent-divergent nozzle [24]: grid verification. Figure 3: Convergent-divergent nozzle [24]: comparison between experimental data and numerical solution. Interpolated wall temperature profile is enforced as a boundary condition. with experimental data [24] is shown in Fig. 3. Note that the wall temperature enforced has been interpolated with a polynomial function in order to have a smooth temperature profile at the wall. The corresponding numerical evaluation of wall heat flux follows the experimental data within the maximum total error (±8%) estimated in the reference work. The comparison shows the capability of the solver to reproduce properly thermal boundary layers near the wall and thus to be employed in the following to evaluate wall heat flux from the hot gases in a combustion chamber to the wall with and without film cooling. 3
4 PP LIQUID PROPULSION ISP Wall heat flux in subscale combustion chambers with film cooling The simplified approach to study film cooled thrust chamber is first assessed by reproducing a well documented experimental test case [18, 26, 14]. This test case consists in a water-cooled high pressure subscale combustion chamber operated with liquid oxygen (LOX) and gaseous hydrogen (H 2 ). The combustion chamber features are summarized in Tab. 1. Hydrogen film is injected tangentially to the chamber wall through slots which are arranged in the same azimuthal position of the outer ring injectors. Main parameters of the chosen load point are summarized in Tab. 2. In order to have a reference solution with the same chamber pressure and hot-gas mixture ratio, the same load point is investigated with and without film cooling. Due to the small amount of film injected in the chamber compared to the overall mass flow rate, the difference between the chamber pressure in the case with and without the film is negligible. In the numerical simulations, the three dimensional configuration of Chamber Film Length, L (mm) 200 Inner radius, r c (mm) 25 Throat radius, r th (mm) 16.5 Slot number, N slot 10 Slot height, s (mm) 0.40 Slot width, b (mm) 3.50 With Film Cooling Without Film Cooling p c (MPa) ṁ LOX (kg/s) ṁ H2 (kg/s) ṁ f ilm /(ṁ LOX + ṁ H2 ) (%) T f ilm (K) Table 1: Subscale combustion chamber and film cooling geometrical features [14] Table 2: Film cooling experimental load point [14] with and without film cooling the chamber has been reduced to a two dimensional axis-symmetric configuration as shown in Fig. 4. The simplified approach adopted for the numerical simulations is described in the following. The injector plate near field is not resolved in details and atomization, vaporization, mixing and combustion phenomena are not modeled assuming they are confined near the injector plate. A mixture of equilibrium combustion products is injected in the chamber through the inlet section which is evaluated as the section with the maximum radius covered by the injectors on the injector plate design (hot gas injection section is highlighted in red in Fig. 4). Hydrogen film is injected through the blue section of Fig. 4, which is obtained matching the experimental film cooling slot height and imposing 2D axis-symmetry. With this assumption, experimental film inlet velocity and inlet temperature are matched, whereas experimental film mass flow rate is not reproduced. Goal of the simplified approach is to preserve the main geometrical features of the injector plate such as the distance between outer injector ring and film slot and the film slot height. Figure 4: LOX/H 2 film cooling experimental test bench: from the 3D configuration (experimental setup) to the 2D axis-symmetric configuration (numerical simulation). Hot gas injection : red section; film cooling injection: blue section. (Adapted from [14]). The numerical simulation is carried out on a grid divided into three blocks with different features (Fig. 5). In the first block, cells are clustered radially near the chamber wall and axially near the plate between the hot gas injection and the film injection to resolve boundary layers, cells are also clustered inside the flowfield in the radial direction to resolve 4
5 B. Betti, E. Martelli, F. Nasuti and M. Onofri - NUMERICAL STUDY OF FILM COOLING IN OXYGEN/METHANE THRUST CHAMBERS Figure 5: LOX/H 2 film cooling experimental test bench [14]: multi-block numerical grid and boundary conditions enforced. Enlargement of the injection block with enforced boundary conditions in the case with and without film cooling. Grid Levels No. of Volumes Block 1 Block 2 Block 3 y min Coarse grid 25x45 15x30 20x µm Medium grid 50x90 30x60 40x µm Fine grid 100x180 60x120 80x µm Table 3: LOX/H 2 film cooling test case [14]: multi-block grid verification. the mixing layer between the film injection and the hot gas injection. In the second and third blocks, cells are clustered radially near the wall to resolve the boundary layer. A similar grid has been employed for the case without film cooling in which the first block has been modified to take into account only for the hot gas injection, whereas blocks 2 and 3 have been left unchanged. Injection block boundary conditions in the case with and without film cooling are shown in Fig. 5. In the subsonic inflow, mass flow rate per unit area, stagnation temperature, velocity direction and mixture composition are imposed for hot gas and film. Hot gas mass flow rate is the sum of oxidizer and fuel mass flow rate from the injectors. The mixture composition and the stagnation temperature at the hot-gas inlet are calculated by the NASA Chemical Equilibrium and Applications (CEA) code, which is a one-dimensional chemical equilibrium calculation program [27], imposing the overall mixture ratio and the chamber pressure and assuming the stagnation temperature equal to the adiabatic flame temperature. Hydrogen film mass flow rate is evaluated by preserving the experimental inlet temperature and velocity considering a 2D axis-symmetric injection. Stagnation temperature is evaluated with an isentropic assumption from film inlet temperature and inlet Mach number. Experimental surface temperatures interpolated along the chamber are enforced at no-slip walls boundaries. In the nozzle, the isothermal wall temperature of 700 K is assigned due to the lack of experimental measurements in this region. Grid asymptotic convergence has been verified with three grid levels whose volumes are summarized per block in Tab. 3. Medium grid size numerical solution differs from Richardson extrapolated solution by an error lower than 1%. The computed temperature field is shown in Fig. 6 for both cases with (top) and without (bottom) film cooling. Enlargements of the inlet section highlight the flowfield structure near the injection region. Large recirculation occurs near the wall in the case without film cooling, whereas a pair of counter rotating vortices takes place between hot gas 5
6 PP LIQUID PROPULSION ISP 1 Figure 6: LOX/H 2 film cooling test case [14]: temperature field in the case with (top) and without (bottom) film cooling. Enlargements of the inlet region with streamlines. and film injection in the case with film cooling as shown by the superimposed streamlines. Wall heat flux along the chamber with and without film cooling is shown in Fig. 7(a). Filled and empty dots represent wall heat flux experimental measurements by gradient method with and without film cooling, respectively. Error bars (±8%) are included with the estimated error evaluated in [18]. Numerical evaluation for wall heat flux are plotted in solid red and black lines for the case with and without film cooling, respectively. Numerical wall heat flux without film cooling over-predicts experimental measurements near the injector plate (first two measurement points) whereas downstream follows experimental values within experimental errors. On the contrary, wall heat flux with film cooling is largely underestimated due to the larger amount of film injected in the numerical simulation with respect to the experimental value. Nevertheless, numerical solution reproduces the experimental trend as can be seen comparing the red dashed line which represents the experimental trend of the last four measurement points and the red dot-dashed line which represent the numerical trend in the same spatial region. To take into account the three dimensional configuration of the film slots, wall heat flux along the chamber with film cooling has been evaluated by a weighted average ( q w,av ) (blue solid line) between the numerical results obtained in the 2D axis-symmetric configuration with film ( q w,w f ilm ) (red solid line) and without film ( qw,wo f ilm ) (black solid line). Weights are ɛ and (1 ɛ) where ɛ is the surface ratio between total slot width and the overall chamber perimeter per unit length as shown in Eq. 1. Weights adopted in Eq. 1 neglect spanwise diffusion and give an estimation of the maximum wall heat flux achievable with a three dimensional configuration. q w,av = ɛ q w,w f ilm + (1 ɛ) q w,wo f ilm with: ɛ = N slotb 2πr c (1) In both cases (black and blue line), up to the second measurement point numerical solutions largely over-predict experimental data because injector plate near field phenomena are not modeled. In the numerical solution without the film cooling, wall heat flux reflects a backward facing step configuration with two peaks linked to the hot gas recirculation region shown in Fig. 6. In the experimental test, the recirculation region near the injector plate encompasses cold gases and thus wall heat flux smoothly grows along the chamber without peaks. Previous analysis of this simplified approach [22] underlined that after the flow reattachment point, wall heat flux along the chamber follows experimental trend in a similar way. For this reason, the present analysis is focused on the numerical wall heat flux after the flow reattachment point on the wall (located after the second wall heat flux peak). After this point, in both cases numerical 6
7 B. Betti, E. Martelli, F. Nasuti and M. Onofri - NUMERICAL STUDY OF FILM COOLING IN OXYGEN/METHANE THRUST CHAMBERS (a) Experimental measurements [18] (filled dots with film cooling, empty dots without film cooling) vs numerical solution with (red solid line) and without (black solid line) film cooling. Experimental trend (dashed red line) is evaluated with the last four measurement points. (b) Experimental measurements [18] (filled dots with film cooling; empty dots without film cooling) vs numerical solution with (red) and without (black) film cooling, and weighted averaged numerical solution with film cooling (blue). Error bars in numerical solutions quantify the maximum radiative heat flux. Figure 7: LOX/H 2 film cooling wall heat flux [14] wall heat flux follows experimental data within the experimental error along the chamber. Moreover, a rough estimation of the radiative heat flux coming from the flame has been added to the convective wall heat flux and is shown in Fig. 7(b) as error bars over the solid lines. The maximum radiative heat flux from the hot gas to the wall has been evaluated with Eq. 2 valid for transparent gas and non-emitting walls: q wall, rad = ε g σt 4 Hot Gas (2) where ε g is the effective emissivity of hot gas, σ is the Stefan-Boltzmann constant and T Hot Gas is the maximum temperature in each section. Hot gas is supposed to be transparent in order to evaluate the maximum radiative heat flux coming to the wall from hot gas assuming for each section the maximum gas temperature. Walls are supposed to be non-emitting because in thrust chambers wall temperature is always much lower than hot gas temperature. In high pressure oxygen/hydrogen rocket thrust chambers, combustion products mixture is mainly composed by water vapor and the effective emissivity of this mixture has been evaluated in [28] and is assumed here to be equal to With this test case, the capability of the adopted simplified approach to capture peculiar features of film cooled thrust chambers in terms of heat flux has been assessed. This simplified approach is employed in the following section to analyze film cooling efficiency of an oxygen/methane subscale thrust chamber. 4. Film cooling in oxygen/methane thrust chambers In the frame of the 7 th Framework Program within the In-Space Propulsion 1 project, film cooling in oxygen/methane thrust chamber will be studied in terms of experiments and numerical simulations. In particular, the experimental test case [1] consists in a low pressure calorimetric subscale combustion chamber where gaseous oxygen (O 2 ) and gaseous methane (CH 4 ) at ambient temperature are injected. Film cooling is realized with gaseous methane injected through a 2D axis-symmetric circular slot (Tab. 4). In the experimental test campaign, different chamber pressure, mixture ratio and film slot height will be investigated providing axial distribution of heat pick-up based on detailed water mass flow rate and surface temperatures. A preliminary numerical analysis of the wall heat flux and the film cooling efficiency is conducted in the present work of ISP-1 project as a support to the experimental test. In particular, the simplified approach described and verified in Sec. 3.2 is employed to evaluate the film cooling efficiency in the subscale combustion chamber whose test campaign is foreseen to end by the end of the year. One experimental load 7
8 PP LIQUID PROPULSION ISP 1 Chamber Lenght, L (mm) 200 Inner radius, r c (mm) 25 Throat radius, r th (mm) 14 Chamber Injectors p c 10 bar O/F 3.4 ṁ O2 ṁ CH kg/s kg/s Film Slot height, s (mm) 0.46 Film ṁ f ilm /ṁ O2 +CH 4 20% Table 4: O 2 /CH 4 subscale chamber and film cooling geometrical features Table 5: O 2 /CH 4 Film Cooling: experimental load point point whose main parameters are summarized in Tab. 5 has been selected within the design test matrix as a reference test case to evaluate film cooling efficiency. Film cooling capabilities of keeping the thrust chamber wall in a safe operative mode are quantified by film cooling efficiency which can be defined [3] as: η = T aw T cc T 2 T cc (3) where T aw is the adiabatic wall temperature, T cc and T 2 are the hot gas and the film cooling temperature, respectively. As can be seen in Fig. 8, numerical grid and boundary conditions are similar to those employed in Sec. 3.2 and described in Fig. 5. The only difference is in the wall boundary condition where for the validation test case in Sec. 3.2 wall temperature was prescribed as an interpolation of experimental surface temperature measurements, whereas in this analysis no-slip walls are treated as adiabatic walls to evaluate film cooling efficiency. The multi-block numerical grid Figure 8: O 2 /CH 4 film cooling experimental test bench: multi-block numerical grid and boundary conditions enforced. Enlargement of the injection block with enforced boundary conditions in the case with and without film cooling. is composed by three blocks with the same features described in Sec. 3.2 for the injection region, the middle region and the nozzle with 70x80, 30x60 and 50x40 volumes, respectively. Temperature field with and without film cooling is described in Fig. 9, with an enlargement of the inlet section whose peculiar flows features are highlighted by superimposed streamlines. In Fig. 10, wall adiabatic temperature has been evaluated with (solid red line) and without (solid green line) film cooling. Film cooling efficiency (solid blue line) is evaluated with Eq. 3. 8
9 B. Betti, E. Martelli, F. Nasuti and M. Onofri - NUMERICAL STUDY OF FILM COOLING IN OXYGEN/METHANE THRUST CHAMBERS The initial plateau of efficiency near the film injection where wall temperature equals film temperature is so little that cannot be seen in Fig. 10. Then efficiency begins to decrease up to the nozzle. As can be seen adiabatic wall temperatures even with film cooling exceeds by far material allowable temperatures. For this reason, in these experimental configurations convective cooling represents the only way to cool the chamber enough to keep it under safe conditions for the overall test campaign. Figure 9: O 2 /CH 4 film cooling: temperature field with (top) and without (bottom) film cooling. Figure 10: O 2 /CH 4 film cooling: adiabatic wall temperature with (red line) and without (green line) film cooling and film cooling efficiency η f ilm (blue line). 9
10 PP LIQUID PROPULSION ISP 1 5. Conclusions In this work, the ability of a simplified approach to evaluate numerically wall heat flux in film-cooled rocket thrust chamber is assessed. After validation of the wall boundary condition by reproducing a benchmark test case, the simplified approach is applied to a film cooled LOX/H 2 subscale combustion chamber to evaluate wall heat flux with and without film cooling. In reproducing this test case, a mixture of equilibrium combustion products is injected in the chamber surrounded by a 2D axis-symmetric film cooling. Experimental film injection velocity and temperature, and slot height are reproduced whereas film mass flow rate is higher than the experimental value. Experimental data and numerical solutions for wall heat flux with and without film cooling are in good agreement within the experimental error. Due to the three dimensional configuration of the film injection, numerical wall heat flux has been obtained by a weighted average of 2D axis-symmetric wall heat fluxes with and without film cooling. In addition, the maximum radiative heat transfer from the hot gases has been roughly estimated. Comparison with experimental data gives confidence in the present simplified approach as a tool for a first evaluation of thermal environment of film cooled thrust chambers. Finally, film cooling efficiency in oxygen/methane thrust chambers has been analyzed reproducing a test case designed in the frame of the ISP-1 project. 6. Acknowledgments The present study is being performed within the In-Space Propulsion 1 project coordinated by SNECMA and supported by the European Community 7 th Framework Program for Research and Technology, Grant agreement No Part of the numerical simulations presented were done at the CASPUR High Performance Computing (HPC) facilities within the Standard HPC grant of References [1] Ordonneau, G., Haidn, O., Soller, S., and Onofri, M., Oxygen-methane Combustion Studies in In Space Propulsion Programme, 4th European Conference for Aerospace Sciences, EUCASS, Saint Petersburg, Russia, 3-7 July, [2] Preuss, A., Preclik, D., Mading, C., Gorgen, J., Soller, S., Haidn, O., Oschwald, M., Clauss, W., Arnold, R., and Sender, J., LOX/Methane Technology Efforts for Future Liquid Rocket Engines, 5th International Spacecraft Propulsion Conference and 2nd International Symposium on Propulsion for Space Transportation, [3] Goldstein, R. J., Film Cooling, Advances in Heat Transfer, Vol. 7, pp , [4] Simon, F. F., Jet Model for Slot Film Cooling with Effect of Free-stream and Coolant Turbulence, NASA-TP- 2655, [5] Dellimore, K. H., Cruz, C., Marshall, A. W., and Cadou, C. P., Influence of a Streamwise Pressure Gradient on Film-Cooling Effectiveness, Journal of Thermophysics and Heat Transfer, Vol.23, No.1, Jan-Mar [6] Dellimore, K. H., Marshall, A. W., and Cadou, C. P., Influence of Compressibility on Film-Cooling Effectiveness, Journal of Thermophysics and Heat Transfer, Vol.24, No.3, Jul-Sep [7] Cruz, C. A. and Marshall, A. W., Surface and Gas Measurements Along a Film-Cooled Wall, Journal of Thermophysics and Heat Transfer, Vol. 21, No. 1, Jan-Mar [8] Dellimore, K. H., Marshall, A. W., Trouvé, A., and Cadou, C. P., Numerical Simulation of Subsonic Slot-Jet Film Cooling of an Adiabatic Wall, 47th AIAA Aerospace Science Meeting Including The New Horizons Forum and Aerospace Exposition, 5-8 Jan 2009, Orlando, Florida. AIAA [9] Dellimore, K. H., Modeling and Simulation of Mixing Layer Flows For Rocket Engine Film Cooling, Ph.D. Dissertation, University of Maryland,
11 B. Betti, E. Martelli, F. Nasuti and M. Onofri - NUMERICAL STUDY OF FILM COOLING IN OXYGEN/METHANE THRUST CHAMBERS [10] Voegele, A. P., Trouvé, A., Cadou, C., and Marshall, A., RANS Modeling of 2D Adiabatic Slot Film Cooling, 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 2010, Nashville, TN - AIAA [11] Kim, J. G., Lee, K. J., Seo, S., Han, Y. M., Kim, H. J., and Choi, H. S., Film Cooling Effects on Wall Heat Flux of a Liquid Propellant Combustion Chamber, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 9-12 July 2006, Sacramento, CA. AIAA [12] Arnold, R., Suslov, D., Haidn, O. J., and Weigand, B., Circumferential Behavior of Tangential Film Cooling and Injector Wall Compatibility in a High Pressure LOX/GH 2 Subscale Combustion Chamber, 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 2008, Hartford, CT, AIAA [13] Arnold, R., Suslov, D., and Haidn, O. J., Film Cooling of Accelerated Flow in a Subscale Combustion Chamber, Journal of Propulsion and Power Vol.25, No. 2, Mar-Apr [14] Arnold, R., Suslov, D., and Haidn, O. J., Film Cooling in a High-Pressure Subscale Combustion Chamber, Journal of Propulsion and Power, Vol.26, No. 3, May-Jun [15] Han, P. G., Namkoung, H. J., Kim, K. H., and Yoon, Y. B., A Study on the Cooling Mechanism in Liquid Rocket Engines, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 2004, Fort Laudardale, FL. AIAA [16] Zhang, H. W., Tao, W. Q., He, Y. L., and Zhang, W., Numerical Study of Liquid Film Cooling in a Rocket Combustion Chamber, International Journal of Heat and Mass Transfer, Vol. 49, pp , [17] Zhang, H. W., He, Y. L., and Tao, W. Q., Numerical Study of Film and Regenerative Cooling in a Thrust Chamber at High Pressure, Numerical Heat Transfer, Part A, Vol.52, pp , [18] Arnold, R., Suslov, D., Oschwald, M., Haidn, O. J., Aichner, T., Ivancic, B., and Frey, M., Experimentally and Numerically Investigated Film Cooling in a Subscale Rocket Combustion Chamber, 3rd European Conference for Aerospace Sciences (EUCASS), July [19] Kirchberger, C., Schlieben, G., Hupfer, A., Kau, H., Martin, P., and Soller, S., Investigation on Film Cooling in a Kerosene/GOX Combustion Chamber, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2-5 August 2009, Denver, CO. AIAA [20] Arnold, R., Suslov, S., and Haidn, O. J., Experimental Investigation of Film Cooling with Tangential Slot Injection in a LOX/CH4 Subscale Rocket Combustion Chamber, 26th International Symposium on Space Technology and Science (ISTS), [21] Pizzarelli, M., Nasuti, F., Paciorri, R., and Onofri, M., Numerical Analysis of Three-Dimensional Flow of Supercritical Fluid in Cooling Channels, AIAA Journal, Vol. 47, No. 11 ( ), [22] Betti, B., Martelli, E., and Nasuti, F., Heat Flux Evaluation in Oxygen/Methane Thrust Chambers by RANS Approach, 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, July 2010, Nashville, TN - AIAA [23] Spalart, P. and Allmaras, S., A One-equation Turbulence Model for Aerodynamic Flows, La Recherche Aerospatiale 1, 5-23, [24] Back, L. H., Massier, P. F., and Gier, H. L., Convective Heat Transfer in a Convergent-Divergent Nozzle, NASA Technical Report No , [25] Roy, C. J., McWherter-Payne, M. A., and Oberkampf, W. L., Verification and Validation for Laminar Hypersonic Flowfields, Part 1: Verification, AIAA Journal, Vol. 41, No. 10, October, [26] Suslov, D. I., Arnold, R., and Haidn, O. J., Investigation of Two Dimensional Thermal Loads in the Region near the Injector Head of a High Pressure Subscale Combustion Chamber, 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum And Aerospace Exposition 5-8 January 2009, Orlando, FL. AIAA
12 PP LIQUID PROPULSION ISP 1 [27] McBride, B. J. and Gordon, S., Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications, NASA Reference Publication 1311, [28] Wang, Q., Wu, F., Zeng, M., Luo, L., and Sun, J., Numerical Simulation and Optimization on Heat Transfer and Fluid Flow in Cooling Channel of Liquid Rocket Engine Thrust Chamber, Engineering Computations: International Journal for Computed-Aided Engineering and Software. Vol. 23 No. 8, pp ,
3D Numerical Simulation on Rotating Detonation Engine : Effects of Converging-Diverging-Nozzle on Thrust Performance
25 th ICDERS August 2 7, 2015 Leeds, UK 3D Numerical Simulation on Rotating Detonation Engine : Effects of Converging-Diverging-Nozzle on Thrust Performance Seiichiro ETO 1, Yusuke WATANABE 1, Nobuyuki
More informationHYBRID ROCKET TECHNOLOGY IN THE FRAME OF THE ITALIAN HYPROB PROGRAM
8 th European Symposium on Aerothermodynamics for space vehicles HYBRID ROCKET TECHNOLOGY IN THE FRAME OF THE ITALIAN HYPROB PROGRAM M. Di Clemente, R. Votta, G. Ranuzzi, F. Ferrigno March 4, 2015 Outline
More informationCFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation
Page1 CFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation ABSTRACT Alan Vincent E V P G Scholar, Nehru Institute of Engineering and Technology, Coimbatore Tamil Nadu A high
More informationPushing the limits. Turbine simulation for next-generation turbochargers
Pushing the limits Turbine simulation for next-generation turbochargers KWOK-KAI SO, BENT PHILLIPSEN, MAGNUS FISCHER Computational fluid dynamics (CFD) has matured and is now an indispensable tool for
More informationLecture 6 - Boundary Conditions. Applied Computational Fluid Dynamics
Lecture 6 - Boundary Conditions Applied Computational Fluid Dynamics Instructor: André Bakker http://www.bakker.org André Bakker (2002-2006) Fluent Inc. (2002) 1 Outline Overview. Inlet and outlet boundaries.
More informationEffect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD
Universal Journal of Mechanical Engineering 1(4): 122-127, 2013 DOI: 10.13189/ujme.2013.010403 http://www.hrpub.org Effect of Pressure Ratio on Film Cooling of Turbine Aerofoil Using CFD Vibhor Baghel
More informationGraduate Certificate Program in Energy Conversion & Transport Offered by the Department of Mechanical and Aerospace Engineering
Graduate Certificate Program in Energy Conversion & Transport Offered by the Department of Mechanical and Aerospace Engineering Intended Audience: Main Campus Students Distance (online students) Both Purpose:
More informationPart IV. Conclusions
Part IV Conclusions 189 Chapter 9 Conclusions and Future Work CFD studies of premixed laminar and turbulent combustion dynamics have been conducted. These studies were aimed at explaining physical phenomena
More informationAbaqus/CFD Sample Problems. Abaqus 6.10
Abaqus/CFD Sample Problems Abaqus 6.10 Contents 1. Oscillatory Laminar Plane Poiseuille Flow 2. Flow in Shear Driven Cavities 3. Buoyancy Driven Flow in Cavities 4. Turbulent Flow in a Rectangular Channel
More informationHEAT TRANSFER ANALYSIS IN A 3D SQUARE CHANNEL LAMINAR FLOW WITH USING BAFFLES 1 Vikram Bishnoi
HEAT TRANSFER ANALYSIS IN A 3D SQUARE CHANNEL LAMINAR FLOW WITH USING BAFFLES 1 Vikram Bishnoi 2 Rajesh Dudi 1 Scholar and 2 Assistant Professor,Department of Mechanical Engineering, OITM, Hisar (Haryana)
More informationGT2011 46090 ANALYSIS OF A MICROGASTURBINE FED BY NATURAL GAS AND SYNTHESIS GAS: MGT TEST BENCH AND COMBUSTOR CFD ANALYSIS
ASME Turbo Expo 2011 June 6 10, 2011 Vancouver, Canada GT 2011 46090 ANALYSIS OF A MICROGASTURBINE FED BY NATURAL GAS AND SYNTHESIS GAS: MGT TEST BENCH AND COMBUSTOR CFD ANALYSIS M. Cadorin 1,M. Pinelli
More informationNUMERICAL ANALYSIS OF THE EFFECTS OF WIND ON BUILDING STRUCTURES
Vol. XX 2012 No. 4 28 34 J. ŠIMIČEK O. HUBOVÁ NUMERICAL ANALYSIS OF THE EFFECTS OF WIND ON BUILDING STRUCTURES Jozef ŠIMIČEK email: jozef.simicek@stuba.sk Research field: Statics and Dynamics Fluids mechanics
More informationThe soot and scale problems
Dr. Albrecht Kaupp Page 1 The soot and scale problems Issue Soot and scale do not only increase energy consumption but are as well a major cause of tube failure. Learning Objectives Understanding the implications
More informationProblem Statement In order to satisfy production and storage requirements, small and medium-scale industrial
Problem Statement In order to satisfy production and storage requirements, small and medium-scale industrial facilities commonly occupy spaces with ceilings ranging between twenty and thirty feet in height.
More informationDifferential Relations for Fluid Flow. Acceleration field of a fluid. The differential equation of mass conservation
Differential Relations for Fluid Flow In this approach, we apply our four basic conservation laws to an infinitesimally small control volume. The differential approach provides point by point details of
More informationCO 2 41.2 MPa (abs) 20 C
comp_02 A CO 2 cartridge is used to propel a small rocket cart. Compressed CO 2, stored at a pressure of 41.2 MPa (abs) and a temperature of 20 C, is expanded through a smoothly contoured converging nozzle
More informationME 239: Rocket Propulsion. Over- and Under-expanded Nozzles and Nozzle Configurations. J. M. Meyers, PhD
ME 239: Rocket Propulsion Over- and Under-expanded Nozzles and Nozzle Configurations J. M. Meyers, PhD 1 Over- and Underexpanded Nozzles Underexpanded Nozzle Discharges fluid at an exit pressure greater
More informationME6130 An introduction to CFD 1-1
ME6130 An introduction to CFD 1-1 What is CFD? Computational fluid dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions, and related phenomena by solving numerically
More informationCFD STUDY OF TEMPERATURE AND SMOKE DISTRIBUTION IN A RAILWAY TUNNEL WITH NATURAL VENTILATION SYSTEM
CFD STUDY OF TEMPERATURE AND SMOKE DISTRIBUTION IN A RAILWAY TUNNEL WITH NATURAL VENTILATION SYSTEM J. Schabacker, M. Bettelini, Ch. Rudin HBI Haerter AG Thunstrasse 9, P.O. Box, 3000 Bern, Switzerland
More informationExpress Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology
Express Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology Dimitrios Sofialidis Technical Manager, SimTec Ltd. Mechanical Engineer, PhD PRACE Autumn School 2013 - Industry
More informationCFD SIMULATION OF SDHW STORAGE TANK WITH AND WITHOUT HEATER
International Journal of Advancements in Research & Technology, Volume 1, Issue2, July-2012 1 CFD SIMULATION OF SDHW STORAGE TANK WITH AND WITHOUT HEATER ABSTRACT (1) Mr. Mainak Bhaumik M.E. (Thermal Engg.)
More informationForces on the Rocket. Rocket Dynamics. Equation of Motion: F = Ma
Rocket Dynamics orces on the Rockets - Drag Rocket Stability Rocket Equation Specific Impulse Rocket otors Thrust orces on the Rocket Equation of otion: = a orces at through the Center of ass Center of
More informationFlow in data racks. 1 Aim/Motivation. 3 Data rack modification. 2 Current state. EPJ Web of Conferences 67, 02070 (2014)
EPJ Web of Conferences 67, 02070 (2014) DOI: 10.1051/ epjconf/20146702070 C Owned by the authors, published by EDP Sciences, 2014 Flow in data racks Lukáš Manoch 1,a, Jan Matěcha 1,b, Jan Novotný 1,c,JiříNožička
More informationIntegration of a fin experiment into the undergraduate heat transfer laboratory
Integration of a fin experiment into the undergraduate heat transfer laboratory H. I. Abu-Mulaweh Mechanical Engineering Department, Purdue University at Fort Wayne, Fort Wayne, IN 46805, USA E-mail: mulaweh@engr.ipfw.edu
More informationIntroduction to CFD Analysis
Introduction to CFD Analysis 2-1 What is CFD? Computational Fluid Dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions, and related phenomena by solving numerically
More informationA SILICON-BASED MICRO GAS TURBINE ENGINE FOR POWER GENERATION. Singapore Institute of Manufacturing Technology, Singapore 658075
Stresa, Italy, 26-28 April 2006 A SILICON-BASED MICRO GAS TURBINE ENGINE FOR POWER GENERATION X. C. Shan 1, Z. F. Wang 1, R. Maeda 2, Y. F. Sun 1 M. Wu 3 and J. S. Hua 3 1 Singapore Institute of Manufacturing
More informationFluid Mechanics Prof. S. K. Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur
Fluid Mechanics Prof. S. K. Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur Lecture - 20 Conservation Equations in Fluid Flow Part VIII Good morning. I welcome you all
More informationRESEARCH PROJECTS. For more information about our research projects please contact us at: info@naisengineering.com
RESEARCH PROJECTS For more information about our research projects please contact us at: info@naisengineering.com Or visit our web site at: www.naisengineering.com 2 Setup of 1D Model for the Simulation
More informationNUCLEAR ENERGY RESEARCH INITIATIVE
NUCLEAR ENERGY RESEARCH INITIATIVE Experimental and CFD Analysis of Advanced Convective Cooling Systems PI: Victor M. Ugaz and Yassin A. Hassan, Texas Engineering Experiment Station Collaborators: None
More informationA. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic
AiMT Advances in Military Technology Vol. 8, No. 1, June 2013 Aerodynamic Characteristics of Multi-Element Iced Airfoil CFD Simulation A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty
More informationHigh Speed Aerodynamics Prof. K. P. Sinhamahapatra Department of Aerospace Engineering Indian Institute of Technology, Kharagpur
High Speed Aerodynamics Prof. K. P. Sinhamahapatra Department of Aerospace Engineering Indian Institute of Technology, Kharagpur Module No. # 01 Lecture No. # 06 One-dimensional Gas Dynamics (Contd.) We
More informationComparison of Heat Transfer between a Helical and Straight Tube Heat Exchanger
International Journal of Engineering Research and Technology. ISSN 0974-3154 Volume 6, Number 1 (2013), pp. 33-40 International Research Publication House http://www.irphouse.com Comparison of Heat Transfer
More informationCFD Analysis of a MILD Low-Nox Burner for the Oil and Gas industry
CFD Analysis of a MILD Low-Nox Burner for the Oil and Gas industry Alessandro Atzori Supervised by: Vincent Moreau Framework: Industria 2015 Bill on competitiveness and industrial policy, approved on 22
More informationLecture 3 Fluid Dynamics and Balance Equa6ons for Reac6ng Flows
Lecture 3 Fluid Dynamics and Balance Equa6ons for Reac6ng Flows 3.- 1 Basics: equations of continuum mechanics - balance equations for mass and momentum - balance equations for the energy and the chemical
More informationINTERNATIONAL JOURNAL OF MECHANICAL ENGINEERING AND TECHNOLOGY (IJMET)
INTERNATIONAL JOURNAL OF MECHANICAL ENGINEERING AND TECHNOLOGY (IJMET) Proceedings of the 2 nd International Conference on Current Trends in Engineering and Management ICCTEM -2014 ISSN 0976 6340 (Print)
More informationComparative Analysis of Gas Turbine Blades with and without Turbulators
Comparative Analysis of Gas Turbine Blades with and without Turbulators Sagar H T 1, Kishan Naik 2 1 PG Student, Dept. of Studies in Mechanical Engineering, University BDT College of Engineering, Davangere,
More informationGEOMETRIC, THERMODYNAMIC AND CFD ANALYSES OF A REAL SCROLL EXPANDER FOR MICRO ORC APPLICATIONS
2 nd International Seminar on ORC Power Systems October 7 th & 8 th, 213 De Doelen, Rotterdam, NL GEOMETRIC, THERMODYNAMIC AND CFD ANALYSES OF A REAL SCROLL EXPANDER FOR MICRO ORC APPLICATIONS M. Morini,
More informationAirbreathing Rotating Detonation Wave Engine Cycle Analysis
46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 5-8 July 010, Nashville, TN AIAA 010-7039 Airbreathing Rotating Detonation Wave Engine Cycle Analysis Eric M. Braun, Frank K. Lu, Donald R.
More informationEffect of design parameters on temperature rise of windings of dry type electrical transformer
Effect of design parameters on temperature rise of windings of dry type electrical transformer Vikas Kumar a, *, T. Vijay Kumar b, K.B. Dora c a Centre for Development of Advanced Computing, Pune University
More informationCFD SUPPORT FOR JET NOISE REDUCTION CONCEPT DESIGN AND EVALUATION FOR F/A 18 E/F AIRCRAFT
CFD SUPPORT FOR JET NOISE REDUCTION CONCEPT DESIGN AND EVALUATION FOR F/A 18 E/F AIRCRAFT S.M. Dash, D.C. Kenzakowski, and C. Kannepalli Combustion Research and Flow Technology, Inc. (CRAFT Tech ) 174
More informationNUMERICAL ANALYSIS OF AERO-SPIKE NOZZLE FOR SPIKE LENGTH OPTIMIZATION
IMPACT: International Journal of Research in Engineering & Technology (IMPACT: IJRET) ISSN(E): 2321-8843; ISSN(P): 2347-4599 Vol. 1, Issue 6, Nov 2013, 1-14 Impact Journals NUMERICAL ANALYSIS OF AERO-SPIKE
More informationModelling and Computation of Compressible Liquid Flows with Phase Transition
JASS 2009 - Joint Advanced Student School, Saint Petersburg, 29. 03. - 07. 04. 2009 Modelling and Simulation in Multidisciplinary Engineering Modelling and Computation of Compressible Liquid Flows with
More informationIntroduction to CFD Analysis
Introduction to CFD Analysis Introductory FLUENT Training 2006 ANSYS, Inc. All rights reserved. 2006 ANSYS, Inc. All rights reserved. 2-2 What is CFD? Computational fluid dynamics (CFD) is the science
More informationNumerical analysis of size reduction of municipal solid waste particles on the traveling grate of a waste-to-energy combustion chamber
Numerical analysis of size reduction of municipal solid waste particles on the traveling grate of a waste-to-energy combustion chamber Masato Nakamura, Marco J. Castaldi, and Nickolas J. Themelis Earth
More informationSimulation of Fluid-Structure Interactions in Aeronautical Applications
Simulation of Fluid-Structure Interactions in Aeronautical Applications Martin Kuntz Jorge Carregal Ferreira ANSYS Germany D-83624 Otterfing Martin.Kuntz@ansys.com December 2003 3 rd FENET Annual Industry
More informationEffect of Aspect Ratio on Laminar Natural Convection in Partially Heated Enclosure
Universal Journal of Mechanical Engineering (1): 8-33, 014 DOI: 10.13189/ujme.014.00104 http://www.hrpub.org Effect of Aspect Ratio on Laminar Natural Convection in Partially Heated Enclosure Alireza Falahat
More informationVapor Chambers. Figure 1: Example of vapor chamber. Benefits of Using Vapor Chambers
Vapor Chambers A vapor chamber is a high-end thermal management device that can evenly dissipate heat from a small source to a large platform of area (see Figure 1). It has a similar construction and mechanism
More informationCFD MODELLING OF TOP SUBMERGED LANCE GAS INJECTION
CFD MODELLING OF TOP SUBMERGED LANCE GAS INJECTION Nazmul Huda PhD Student Faculty of Engineering and Industrial Science Swinburne University of Technology Melbourne, Australia Supervised by Dr. Jamal
More informationCONVERGE Features, Capabilities and Applications
CONVERGE Features, Capabilities and Applications CONVERGE CONVERGE The industry leading CFD code for complex geometries with moving boundaries. Start using CONVERGE and never make a CFD mesh again. CONVERGE
More informationLES SIMULATION OF A DEVOLATILIZATION EXPERIMENT ON THE IPFR FACILITY
LES SIMULATION OF A DEVOLATILIZATION EXPERIMENT ON THE IPFR FACILITY F. Donato*, G. Rossi**, B. Favini**, E. Giacomazzi*, D. Cecere* F.R. Picchia*, N.M.S. Arcidiacono filippo.donato@enea.it * ENEA-UTTEI/COMSO
More informationINLET AND EXAUST NOZZLES Chap. 10 AIAA AIRCRAFT ENGINE DESIGN R01-07/11/2011
MASTER OF SCIENCE IN AEROSPACE ENGINEERING PROPULSION AND COMBUSTION INLET AND EXAUST NOZZLES Chap. 10 AIAA AIRCRAFT ENGINE DESIGN R01-07/11/2011 LECTURE NOTES AVAILABLE ON https://www.ingegneriaindustriale.unisalento.it/scheda_docente/-/people/antonio.ficarella/materiale
More informationCFD Analysis of Swept and Leaned Transonic Compressor Rotor
CFD Analysis of Swept and Leaned Transonic Compressor Nivin Francis #1, J. Bruce Ralphin Rose *2 #1 Student, Department of Aeronautical Engineering& Regional Centre of Anna University Tirunelveli India
More informationNUMERICAL SIMULATION OF FLOW FIELDS IN CASE OF FIRE AND FORCED VENTILATION IN A CLOSED CAR PARK
FACULTY OF ENGINEERING NUMERICAL SIMULATION OF FLOW FIELDS IN CASE OF FIRE AND FORCED VENTILATION IN A CLOSED CAR PARK Xavier Deckers, Mehdi Jangi, Siri Haga and Bart Merci Department of Flow, Heat and
More informationNumerical Simulation of Thermal Stratification in Cold Legs by Using OpenFOAM
Progress in NUCLEAR SCIENCE and TECHNOLOGY, Vol. 2, pp.107-113 (2011) ARTICLE Numerical Simulation of Thermal Stratification in Cold Legs by Using OpenFOAM Jiejin CAI *, and Tadashi WATANABE Japan Atomic
More informationCOMBUSTION SYSTEMS - EXAMPLE Cap. 9 AIAA AIRCRAFT ENGINE DESIGN www.amazon.com
CORSO DI LAUREA MAGISTRALE IN Ingegneria Aerospaziale PROPULSION AND COMBUSTION COMBUSTION SYSTEMS - EXAMPLE Cap. 9 AIAA AIRCRAFT ENGINE DESIGN www.amazon.com LA DISPENSA E DISPONIBILE SU www.ingindustriale.unisalento.it
More informationHeat Transfer Prof. Dr. Aloke Kumar Ghosal Department of Chemical Engineering Indian Institute of Technology, Guwahati
Heat Transfer Prof. Dr. Aloke Kumar Ghosal Department of Chemical Engineering Indian Institute of Technology, Guwahati Module No. # 02 One Dimensional Steady State Heat Transfer Lecture No. # 05 Extended
More informationUniversity Turbine Systems Research 2012 Fellowship Program Final Report. Prepared for: General Electric Company
University Turbine Systems Research 2012 Fellowship Program Final Report Prepared for: General Electric Company Gas Turbine Aerodynamics Marion Building 300 Garlington Rd Greenville, SC 29615, USA Prepared
More informationRavi Kumar Singh*, K. B. Sahu**, Thakur Debasis Mishra***
Ravi Kumar Singh, K. B. Sahu, Thakur Debasis Mishra / International Journal of Engineering Research and Applications (IJERA) ISSN: 48-96 www.ijera.com Vol. 3, Issue 3, May-Jun 3, pp.766-77 Analysis of
More informationFundamentals of Pulse Detonation Engine (PDE) and Related Propulsion Technology
Fundamentals of Pulse Detonation Engine (PDE) and Related Propulsion Technology Dora E. Musielak, Ph.D. Aerospace Engineering Consulting Arlington, TX All rights reserved. No part of this publication may
More informationIAC-12-C4.1.11 PRELIMINARY DESIGN STUDY OF STAGED COMBUSTION CYCLE ROCKET ENGINE FOR SPACELINER HIGH-SPEED PASSENGER TRANSPORTATION CONCEPT
PRELIMINARY DESIGN STUDY OF STAGED COMBUSTION CYCLE ROCKET ENGINE FOR SPACELINER HIGH-SPEED PASSENGER TRANSPORTATION CONCEPT Ryoma Yamashiro JAXA, Space Transportation System Research and Development Center,
More informationAN EXPERIMENTAL STUDY OF EXERGY IN A CORRUGATED PLATE HEAT EXCHANGER
International Journal of Mechanical Engineering and Technology (IJMET) Volume 6, Issue 11, Nov 2015, pp. 16-22, Article ID: IJMET_06_11_002 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=6&itype=11
More informationNumerical simulations of heat transfer in plane channel
Numerical simulations of heat transfer in plane channel flow Najla El Gharbi, Rafik Absi, Ahmed Benzaoui To cite this version: Najla El Gharbi, Rafik Absi, Ahmed Benzaoui. Numerical simulations of heat
More informationPASSIVE CONTROL OF SHOCK WAVE APPLIED TO HELICOPTER ROTOR HIGH-SPEED IMPULSIVE NOISE REDUCTION
TASK QUARTERLY 14 No 3, 297 305 PASSIVE CONTROL OF SHOCK WAVE APPLIED TO HELICOPTER ROTOR HIGH-SPEED IMPULSIVE NOISE REDUCTION PIOTR DOERFFER AND OSKAR SZULC Institute of Fluid-Flow Machinery, Polish Academy
More informationLaminar Flow in a Baffled Stirred Mixer
Laminar Flow in a Baffled Stirred Mixer Introduction This exercise exemplifies the use of the rotating machinery feature in the CFD Module. The Rotating Machinery interface allows you to model moving rotating
More informationJet Propulsion. Lecture-2. Ujjwal K Saha, Ph.D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1
Lecture-2 Prepared under QIP-CD Cell Project Jet Propulsion Ujjwal K Saha, Ph.D. Department of Mechanical Engineering Indian Institute of Technology Guwahati 1 Simple Gas Turbine Cycle A gas turbine that
More informationSimulation at Aeronautics Test Facilities A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640
Simulation at Aeronautics Test A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640 Questions How has the ability to do increasingly accurate modeling and
More informationPerspective on R&D Needs for Gas Turbine Power Generation
Perspective on R&D Needs for Gas Turbine Power Generation Eli Razinsky Solar Turbine Incorporated 2010 UTSR Workshop October 26, 2011 1 Research Requirements Overview Specific Requirements 2 Society Requirements
More informationTesting methods applicable to refrigeration components and systems
Testing methods applicable to refrigeration components and systems Sylvain Quoilin (1)*, Cristian Cuevas (2), Vladut Teodorese (1), Vincent Lemort (1), Jules Hannay (1) and Jean Lebrun (1) (1) University
More informationOperating conditions. Engine 3 1,756 3,986 2.27 797 1,808 2.27 7,757 6,757 4,000 1,125 980 5.8 3,572 3,215 1,566
JOURNAL 658 OEFELEIN OEFELEIN AND YANG: INSTABILITIES IN F-l ENGINES 659 Table 2 F-l engine operating conditions and performance specifications Mass flow rate, kg/s, Ibm/s Fuel Oxidizer Mixture ratio Pressure,
More informationThe ADREA-HF CFD code An overview
The ADREA-HF CFD code An overview Dr. A.G. Venetsanos Environmental Research Laboratory (EREL) National Centre for Scientific Research Demokritos, Greece venets@ipta.demokritos.gr Slide 2 Computational
More informationACETYLENE AIR DIFFUSION FLAME COMPUTATIONS; COMPARISON OF STATE RELATIONS VERSUS FINITE RATE KINETICS
ACETYLENE AIR DIFFUSION FLAME COMPUTATIONS; COMPARISON OF STATE RELATIONS VERSUS FINITE RATE KINETICS by Z Zhang and OA Ezekoye Department of Mechanical Engineering The University of Texas at Austin Austin,
More informationWEEKLY SCHEDULE. GROUPS (mark X) SPECIAL ROOM FOR SESSION (Computer class room, audio-visual class room)
SESSION WEEK COURSE: THERMAL ENGINEERING DEGREE: Aerospace Engineering YEAR: 2nd TERM: 2nd The course has 29 sessions distributed in 14 weeks. The laboratory sessions are included in these sessions. The
More informationCustomer Training Material. Lecture 2. Introduction to. Methodology ANSYS FLUENT. ANSYS, Inc. Proprietary 2010 ANSYS, Inc. All rights reserved.
Lecture 2 Introduction to CFD Methodology Introduction to ANSYS FLUENT L2-1 What is CFD? Computational Fluid Dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions,
More informationAdaptation of General Purpose CFD Code for Fusion MHD Applications*
Adaptation of General Purpose CFD Code for Fusion MHD Applications* Andrei Khodak Princeton Plasma Physics Laboratory P.O. Box 451 Princeton, NJ, 08540 USA akhodak@pppl.gov Abstract Analysis of many fusion
More informationCFD Analysis of a Centrifugal Pump with Supercritical Carbon Dioxide as a Working Fluid
KNS 2013 Spring CFD Analysis of a Centrifugal Pump with Supercritical Carbon Dioxide as a Working Fluid Seong Gu Kim Jeong Ik Lee Yoonhan Ahn Jekyoung Lee Jae Eun Cha Yacine Addad Dept. Nuclear & Quantum
More informationA NODAL MODEL FOR DISPLACEMENT VENTILATION AND CHILLED CEILING SYSTEMS IN OFFICE SPACES
A NODAL MODEL FOR DISPLACEMENT VENTILATION AND CHILLED CEILING SYSTEMS IN OFFICE SPACES Simon J. Rees and Philip Haves School of Mechanical & Aerospace Engineering, Oklahoma State University, Stillwater,
More informationEco Pelmet Modelling and Assessment. CFD Based Study. Report Number 610.14351-R1D1. 13 January 2015
EcoPelmet Pty Ltd c/- Geoff Hesford Engineering 45 Market Street FREMANTLE WA 6160 Version: Page 2 PREPARED BY: ABN 29 001 584 612 2 Lincoln Street Lane Cove NSW 2066 Australia (PO Box 176 Lane Cove NSW
More informationCOMPUTATIONAL FLUID DYNAMICS (CFD) ANALYSIS OF INTERMEDIATE PRESSURE STEAM TURBINE
Research Paper ISSN 2278 0149 www.ijmerr.com Vol. 3, No. 4, October, 2014 2014 IJMERR. All Rights Reserved COMPUTATIONAL FLUID DYNAMICS (CFD) ANALYSIS OF INTERMEDIATE PRESSURE STEAM TURBINE Shivakumar
More informationFluid structure interaction of a vibrating circular plate in a bounded fluid volume: simulation and experiment
Fluid Structure Interaction VI 3 Fluid structure interaction of a vibrating circular plate in a bounded fluid volume: simulation and experiment J. Hengstler & J. Dual Department of Mechanical and Process
More informationAeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics
Aeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics David Corson Altair Engineering, Inc. Todd Griffith Sandia National Laboratories Tom Ashwill (Retired) Sandia National
More informationTurbulence, Heat and Mass Transfer (THMT 09) Poiseuille flow of liquid methane in nanoscopic graphite channels by molecular dynamics simulation
Turbulence, Heat and Mass Transfer (THMT 09) Poiseuille flow of liquid methane in nanoscopic graphite channels by molecular dynamics simulation Sapienza Università di Roma, September 14, 2009 M. T. HORSCH,
More informationSteady Flow: Laminar and Turbulent in an S-Bend
STAR-CCM+ User Guide 6663 Steady Flow: Laminar and Turbulent in an S-Bend This tutorial demonstrates the flow of an incompressible gas through an s-bend of constant diameter (2 cm), for both laminar and
More informationHeat Transfer Prof. Dr. Ale Kumar Ghosal Department of Chemical Engineering Indian Institute of Technology, Guwahati
Heat Transfer Prof. Dr. Ale Kumar Ghosal Department of Chemical Engineering Indian Institute of Technology, Guwahati Module No. # 04 Convective Heat Transfer Lecture No. # 03 Heat Transfer Correlation
More information1 Foundations of Pyrodynamics
1 1 Foundations of Pyrodynamics Pyrodynamics describes the process of energy conversion from chemical energy to mechanical energy through combustion phenomena, including thermodynamic and fluid dynamic
More informationCoupling Forced Convection in Air Gaps with Heat and Moisture Transfer inside Constructions
Coupling Forced Convection in Air Gaps with Heat and Moisture Transfer inside Constructions M. Bianchi Janetti 1, F. Ochs 1 and R. Pfluger 1 1 University of Innsbruck, Unit for Energy Efficient Buildings,
More informationTHE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA
THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA Adam Kosík Evektor s.r.o., Czech Republic KEYWORDS CFD simulation, mesh generation, OpenFOAM, ANSA ABSTRACT In this paper we describe
More informationContents. Microfluidics - Jens Ducrée Physics: Fluid Dynamics 1
Contents 1. Introduction 2. Fluids 3. Physics of Microfluidic Systems 4. Microfabrication Technologies 5. Flow Control 6. Micropumps 7. Sensors 8. Ink-Jet Technology 9. Liquid Handling 10.Microarrays 11.Microreactors
More informationFlow distribution and turbulent heat transfer in a hexagonal rod bundle experiment
Flow distribution and turbulent heat transfer in a hexagonal rod bundle experiment K. Litfin, A. Batta, A. G. Class,T. Wetzel, R. Stieglitz Karlsruhe Institute of Technology Institute for Nuclear and Energy
More informationBasic Equations, Boundary Conditions and Dimensionless Parameters
Chapter 2 Basic Equations, Boundary Conditions and Dimensionless Parameters In the foregoing chapter, many basic concepts related to the present investigation and the associated literature survey were
More informationThermal Simulation of a Power Electronics Cold Plate with a Parametric Design Study
EVS28 KINTEX, Korea, May 3-6, 2015 Thermal Simulation of a Power Electronics Cold Plate with a Parametric Design Study Boris Marovic Mentor Graphics (Deutschland) GmbH, Germany, boris_marovic@mentor.com
More informationA DEVELOPMENT AND VERIFICATION OF DENSITY BASED SOLVER USING LU-SGS ALGORITHM IN OPENFOAM
A DEVELOPMENT AND VERIFICATION OF DENSITY BASED SOLVER USING LU-SGS ALGORITHM IN OPENFOAM Junghyun Kim*, Kyuhong Kim** *Korea Aerospace Research Institute(KARI), **Seoul National University Abstract A
More informationTHE PSEUDO SINGLE ROW RADIATOR DESIGN
International Journal of Mechanical Engineering and Technology (IJMET) Volume 7, Issue 1, Jan-Feb 2016, pp. 146-153, Article ID: IJMET_07_01_015 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=7&itype=1
More informationIterative calculation of the heat transfer coefficient
Iterative calculation of the heat transfer coefficient D.Roncati Progettazione Ottica Roncati, via Panfilio, 17 44121 Ferrara Aim The plate temperature of a cooling heat sink is an important parameter
More informationCalculate Available Heat for Natural Gas Fuel For Industrial Heating Equipment and Boilers
For Industrial Heating Equipment and Boilers Prepared for California Energy Commission (CEC) Prepared By: Southern California Gas Company (A Sempra Energy Utility) E3M Inc. May 2012 i Disclaimer The CEC
More informationFUNDAMENTALS OF ENGINEERING THERMODYNAMICS
FUNDAMENTALS OF ENGINEERING THERMODYNAMICS System: Quantity of matter (constant mass) or region in space (constant volume) chosen for study. Closed system: Can exchange energy but not mass; mass is constant
More informationEVALUATION OF PHOENICS CFD FIRE MODEL AGAINST ROOM CORNER FIRE EXPERIMENTS
EVALUATION OF PHOENICS CFD FIRE MODEL AGAINST ROOM CORNER FIRE EXPERIMENTS Yunlong Liu and Vivek Apte CSIRO Fire Science and Technology Laboratory PO Box 31 North Ryde, NSW 167, Australia TEL:+61 2 949
More informationAN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL
14 th European Conference on Mixing Warszawa, 10-13 September 2012 AN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL Joanna Karcz, Lukasz Kacperski
More informationCFD Simulation of HSDI Engine Combustion Using VECTIS
CFD Simulation of HSDI Engine Combustion Using VECTIS G. Li, S.M. Sapsford Ricardo Consulting Engineer s Ltd., Shoreham-by-Sea, UK ABSTRACT As part of the VECTIS code validation programme, CFD simulations
More informationModule 6 Case Studies
Module 6 Case Studies 1 Lecture 6.1 A CFD Code for Turbomachinery Flows 2 Development of a CFD Code The lecture material in the previous Modules help the student to understand the domain knowledge required
More informationTurbulence Modeling in CFD Simulation of Intake Manifold for a 4 Cylinder Engine
HEFAT2012 9 th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 16 18 July 2012 Malta Turbulence Modeling in CFD Simulation of Intake Manifold for a 4 Cylinder Engine Dr MK
More information