Numerical Investigation of a Model Scramjet Combustor Using DDES
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Junsu Shin
Abstract
Non-reactive flows moving through a model scramjet were investigated using a delayed detached eddy simulation (DDES), which is a hybrid scheme combining Reynolds averaged Navier-Stokes scheme and a large eddy simulation. The three dimensional Navier-Stokes equations were solved numerically on a structural grid using finite volume methods. An in-house was developed. This code used a monotonic upstream-centered scheme for conservation laws (MUSCL) with an advection upstream splitting method by pressure weight function (AUSMPW+) for space. In addition, a 4th order Runge-Kutta scheme was used with preconditioning for time integration. The geometries and boundary conditions of a scramjet combustor operated by DLR, a German aerospace center, were considered. The profiles of the lower wall pressure and axial velocity obtained from a time-averaged solution were compared with experimental results. Also, the mixing efficiency and total pressure recovery factor were provided in order to inspect the performance of the combustor.
Acknowledgements
This study was written based on a presentation paper given at APCATS 2015.
Nomenclature
- Dk
turbulent kinetic energy destruction term
- E
specific total energy
- h
specific enthalpy
- k
turbulent kinetic energy
- l
length scale
- Mt
turbulent Mach number
- p
static pressure
- pt
total pressure
- qj
specific heat flux
- t
time
- T
temperature
- u
velocity
- x
spatial coordinate
- Y
species mass fraction
- δij
kronecker delta
- μ
molecular viscosity
- μt
turbulent viscosity
- ρ
density
- τij
viscous stress tensor
- φ
equivalence ratio
- ω
turbulent frequency
References
1. Gieseking DA, Choi JI, Edwards JR, Hassan HA. Compressible-flow simulation using a new large-eddy simulation/reynolds-averaged Navier-Stokes model. AIAA J 2011;49:2194–209.10.2514/1.J051001Search in Google Scholar
2. Spalart PR, Jou WH, Strelets MK, Allmaras SR. “Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach”, 1st AFOSR International Conference on DNS/LES, 4–8 August 1997, Ruston, LA.Search in Google Scholar
3. Spalart PR, Deck S, Shur ML, Squires KD, Strelets MK, Travin AK. A new version of detached-eddy simulation, resistant to ambiguous grid densities. Theor Comput Fluid Dyn 2006;20:181–95.10.1007/s00162-006-0015-0Search in Google Scholar
4. Shur ML, Spalart PR, Strelets MK, Travin AK. A hybrid RANS-LES approach with delayed-DES and wall-modeled LES capabilities. Int J Heat Fluid Flow 2008;29:1638–49.10.1016/j.ijheatfluidflow.2008.07.001Search in Google Scholar
5. Guerra R, Waidmann W, Laible C. “An Experimental Investigation of the Combustion of a Hydrogen Jet Injected Parallel in a Supersonic Air Stream”, AIAA–91–5102.Search in Google Scholar
6. Oevermann M. Numerical investigation of turbulent hydrogen combustion in a SCRAMJET using flamelet modeling. Aerosp Sci Technol 2000;5:463–80.10.1016/S1270-9638(00)01070-1Search in Google Scholar
7. Gao Z, Wang J, Jiang C, Lee C. Application and theoretical analysis of the flamelet model for supersonic turbulent combustion flows in the scramjet engine. Combust Theor Model 2014;18:652–91.10.1080/13647830.2014.962617Search in Google Scholar
8. Niu D, Hou L. Comparison study on different compressibility modifications of turbulence model in supersonic combustion simulation. Adv Mech Eng 2014;6, Article ID:238250:9 pages.10.1155/2014/238250Search in Google Scholar
9. Fureby C, Fedina E, TegnerJ. A computational study of supersonic combustion behind a wedge-shaped flameholder. Shock Waves 2014;24:41–50.10.1007/s00193-013-0459-2Search in Google Scholar
10. Genin F, Menon S. Simulation of turbulent mixing behind a strut injector in supersonic flow. AIAA J 2010;48:526–39.10.2514/6.2009-132Search in Google Scholar
11. Potturi AS, Edwards JR. Hybrid large-Eddy/Reynolds-averaged Navier–Stokes simulations of flow through a model Scramjet. AIAA J 2014;52:1417–29.10.2514/1.J052595Search in Google Scholar
12. Yeom HW, Seo BG, Sung HG. Numerical analysis of a Scramjet engine with intake sidewalls and cavity flameholder. AIAA J 2013;51:1566–75.10.2514/1.J051677Search in Google Scholar
13. Yeom HW, Sung HG, Yang V. A numerical analysis of supersonic intake buzz in an axisymmetric ramjet engine. Int J Aeronaut Space Sci 2015;16:165–76.10.5139/IJASS.2015.16.2.165Search in Google Scholar
14. Menter FR. Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J 1994;32:1598–605.10.2514/3.12149Search in Google Scholar
15. Sarkar S, Erlebacher G, Hussaini MY, Kreiss HO. Analysis and Modeling of Dilatational Terms in Compressible Turbulence. J Fluid Mech 1991;227:473–93.10.1017/S0022112091000204Search in Google Scholar
16. Sung HG, Kim SJ, Yeom HW, Heo JY. On the assessment of compressibility effects of wo-Equation turbulence models for supersonic transition flow with flow separation. Int J Aeronaut Space Sci 2013;14:387–97.10.5139/IJASS.2013.14.4.387Search in Google Scholar
17. Kim KH, Kim CA, Rho OH. Methods for the accurate computations of hypersonic flows I. AUSMPW+ Scheme. J Comput Phys 2001;174:38–80.10.1006/jcph.2001.6873Search in Google Scholar
18. Peterson DM, Tylczaky EB, Candler GV. “Hybrid Reynolds-Averaged and Large-Eddy Simulation of Scramjet Fuel Injection”, AIAA–2011–2344.10.2514/6.2011-2344Search in Google Scholar
© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
Articles in the same Issue
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
