Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
-
Jun Liu
,
Meng Yao
Abstract
The physical characteristics of self-sustain shock oscillation and the key factors that affect the shock oscillation in turbine-based combined-cycle(TBCC) inlet were investigated through unsteady numerical simulation method in this paper. The terminal shock oscillation in the throat was caused by the separation bubble appeared in the lower wall of the turbojet flowpath. The angle of the splitter and the offset of the diffuser were the main factors which affect the characteristics of the shock oscillation. When the angle of the splitter increased from 0 deg to 12 deg, the frequency of terminal shock increased from 100Hz to 133Hz; while when it was greater than 18 deg the terminal shock oscillation phenomenon disappeared. Different offset of the turbojet diffuser affect the motion of terminal shock in the inlet. When the y-coordinate value of the control point (ym) in the turbojet diffuser was smaller than 1.5, the shock oscillated in the inlet; when ym was greater than 2.0, the shock oscillation disappeared. The bleed in the diffuser was able to control the oscillation of the terminal shock.
Funding statement: Funding for Outstanding Doctoral Dissertation in NUAA (No.BCXJ16-01) support by the Fundamental Research Funds for the Central Universities. Foundation of Graduate Innovation Center in NUAA (No.kfjj20160204) support by the Fundamental Research Funds for the Central Universities. the Fundamental Research Funds for the Central Universities (No. NS2015025)
Nomenclature
- f
frequency of pressure fluctuation (Hz)
- Ma
Mach number
- PSD
power spectral density ((Pa)2/Hz)
- t
time (ms)
- T
non-dimensional time
- u
shock oscillation velocity (m/s)
- x
x-coordinate (m)
- xm
x-coordinate value of control point
- y
y-coordinate (m)
- ym
y-coordinate value of control point
- θ
angle of splitter (deg)
- π
static pressure ratio
References
1. Bilardo VJ, Curran FM, Hunt JL, Lovell NT, Maggio G, Wilhite AW, et al. The benefits of hypersonic airbreathing launch systems for access to space. AIAA paper 2003-5265, July 2003.10.2514/6.2003-5265Suche in Google Scholar
2. Auslender AH, Kenneth LS, Thomas SR. An overview of the NASA FAP hypersonics project airbreathing propulsion research. AIAA paper 2009-7277, 2009.10.2514/6.2009-7277Suche in Google Scholar
3. Miyagi H, Miyagawa H, Monji T, Kishi K, Powell TH, Mortita M. Combined cycle engine research in Japanese HYPR project. AIAA paper 95-2751, Jul. 1995.10.2514/6.1995-2751Suche in Google Scholar
4. Davic JR, Midea AC. Propulsion and aerodynamic analysis of the beta II two-stage-to-orbit vehicle. AIAA paper 92-4245, Aug. 1992.10.2514/6.1992-4245Suche in Google Scholar
5. Oswatitsch K. Pressure recovery for missiles with reaction propulsion at high supersonic speeds. NACA Translation TM 1140, 1944.Suche in Google Scholar
6. Ferri A, Nucci LM. The origin of aerodynamic instability of supersonic inlets at subcritical conditions. NACA RM L50K30, 1951.Suche in Google Scholar
7. Dailey CL. Supersonic diffuser instability. Ph.D. Thesis, California Institute of Technology, Pasadena, CA, 1954.10.2514/8.3452Suche in Google Scholar
8. Tan HJ, Shu S, Yin ZL. Oscillatory flows of rectangular hypersonic inlet unstart caused by downstream mass-flow choking. J Propul Power. 2009;25:138–47.10.2514/1.37914Suche in Google Scholar
9. Tan HJ, Li LG, Wen YF, Zhang QF. Experimental investigation of the unstart process of a generic hypersonic inlet. AIAA J. 2011;49:279–88.10.2514/1.J050200Suche in Google Scholar
10. Hyoung JL, Bok JL, Sung DK, Jeung IS. Flow characteristics of small-sized supersonic inlets. J Propul Power. 2011;27:306–18.10.2514/1.46101Suche in Google Scholar
11. Chang JT, Wang L, Bao W, Qin J. Novel oscillatory patterns of hypersonic inlet buzz. J Propul Power. 2012;28:1214–21.10.2514/1.B34553Suche in Google Scholar
12. Trapier S, Deck S, Duveau P, Sagaut P. Time–frequency analysis and detectionof supersonic inlet buzz. AIAA J. 2007;45. DOI:10.2514/1.29196Suche in Google Scholar
13. Bogar TJ, Sajben M, Kroutil JC. Characteristic frequencies of transonic diffuser flow oscillations. AIAA J. 1982;21:1232–40.10.2514/3.8234Suche in Google Scholar
14. Liou MS, Coakleyt TJ. Numerical simulation of unsteady transonic flow in diffusers. AIAA J. 1984;22:1139–45.10.2514/6.1982-1000Suche in Google Scholar
15. Robinet JC, Casalis G. Shock oscillations in diffuser modeled by a selective noise amplification. AIAA J. 1999;37:453–59.10.2514/2.755Suche in Google Scholar
16. Handa T, Masuda M, Matsuo K. Mechanism of shock wave oscillation in transonic diffusers. AIAA J. 2003;41:64–70.10.2514/2.1914Suche in Google Scholar
17. Csank JT, Stueber TJ. Shock position control for mode transition in a turbine based combined cycle engine inlet model. NASA/TM-2013-217824, 2013.Suche in Google Scholar
18. Cheng DS, Tan HJ, Sun S, Tong Y. Computational study of a high-performance submerged inlet with bleeding vortex. J Aircr. 2012;49:853–60.10.2514/1.C031483Suche in Google Scholar
19. Bruce PJK, Babinsky H. Experimental and numerical study of oscillating transonic sonic waves in ducts. AIAA J. 2011;49:1710–20.10.2514/1.J050944Suche in Google Scholar
20. Liu J, Yuan HC, Guo RW. Analysis of over/under TBCC inlet mode transition flow characteristics. J Astronautics. 2016;37:461–69.Suche in Google Scholar
21. Lee CC, Boedicker C. Subsonic diffuser design and performance for advanced fighter aircraft. AIAA paper 85-3073, Oct., 1985.10.2514/6.1985-3073Suche in Google Scholar
22. Zhang HJ, Liu XG, Guo RW, Xie LR. Design of turbo diffuser for TBCC inlet and characteristics of turbo mode. J Aerosp Power. 2014;29:181–91.Suche in Google Scholar
23. Slater JW, Saunders JD. Modeling of fixed-exit porous bleed systems for supersonic inlets. J Propul Power. 2010;26:193–202.10.2514/1.37390Suche in Google Scholar
24. Ghosh S, Choi J, Edwards JR. Simulation of shock/boundary-layer interactions with bleed using immersed-boundary methods. J Propul Power. 2010;26:203–14.10.2514/6.2009-1330Suche in Google Scholar
25. Zhang XT. Research on design technique of an over/under type TBCC variable geometry inlet. Master Thesis, Nanjing University of Aeronautics and Astronautics, Nanjing, 2015.Suche in Google Scholar
© 2017 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
Artikel in diesem Heft
- Frontmatter
- Investigation of a High Pressure Ratio Centrifugal Compressor with Wedge Diffuser and Pipe Diffuser
- Qualification of a Small Gas Turbine Engine as a Starter Unit
- Creep Life Prediction of Aircraft Turbine Disc Alloy Using Continuum Damage Mechanics
- Obtaining Dynamic Responses of Rotor from a Synchronizing Derived System Driven by Responses of Some Elastic Supports
- Effect of Swirling Secondary Flow on the Under-expanded Non-circular Supersonic Jets
- Life enhancement of Nozzle Guide Vane of an Aero Gas Turbine Engine through Pack Aluminization
- Investigation on the Aerodynamic Performance of the Compressor Cascade Using Blended Blade and End Wall
- Numerical Simulation of Terminal Shock Oscillation in Over/Under Turbine-Based Combined-Cycle Inlet
- Model Simulation and Design Optimization of a Can Combustor with Methane/Syngas Fuels for a Micro Gas Turbine
- Matching Performance Prediction Between Core Driven Fan Stage and High Pressure Compressor
- Effect of Variable Geometry Guide-Vane with Cylindrical Endwalls on Turbine Stage Performance
