Design and validation of a two-dimensional variable geometry inlet
-
Huacheng Yuan
,
Yunfei Wang
,
Jun Liu
Abstract
The design of a two-dimensional variable geometry inlet which applied to a tandem type turbine-based combined cycle (TBCC) propulsion system was investigated in the present paper through three-dimensional simulations and wind tunnel tests. The operation Mach number range was between 0 and 3. A multi-ramp geometry scheme was adopted to achieve acceptable performance at different inflow Mach number. The first ramp angle was fixed whilst the angles of the second and the third ramps were variable at different inflow Mach numbers. The Mach numbers at throat region were maintained between 1.3 and 1.5 at different inflow Mach numbers according to this variable geometry scheme. A fixed geometry rectangular-to-circular shape diffuser was adopted to improve aerodynamic performance of the inlet. Three-dimensional numerical simulations were carried out between Ma1.5 and Ma3.0. The results indicated that good aerodynamic performance can be achieved at different inflow speed. At the design point, total pressure recovery of the inlet was 0.66 at critical condition. Wind tunnel validation experiment tests were conducted at Ma2.0, showing the movement of terminal shock wave from downstream to upstream as the back pressure increased. The inlet operated at supercritical, critical and subsonic conditions at different back pressure.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: NO.11772155
Acknowledgements
The authors gratefully acknowledge the financial support received from the National Natural Science Foundation of China (NO.11772155).
-
Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: None declared.
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Cockrell, CE, Auslender, AH, Guy, RW, McClinton, CR, Welch, SS. Technology roadmap for dual-mode scramjet propulsion to support space-access vision vehicle development. AIAA; 2002: 2002–5188 pp.10.2514/6.2002-5188Search in Google Scholar
2. Colville, JR, Starkey, RP, Lewis, MJ. Extending the flight Mach number of the SR-71 inlet. AIAA; 2005: 2005–3284 pp.10.2514/6.2005-3284Search in Google Scholar
3. David, WW, Lawrence, DH, Carl, AT, Karen, FC, Earl, HA. Propulsion airframe integration test techniques for hypersonic air-breathing configurations at NASA langley research center. AIAA; 2003: 2003–4406 pp.Search in Google Scholar
4. Zhang, HJ, Guo, RW, Li, B. Research status of TBCC inlet and its key technologies. Acta Aerodyn Sin 2010;28:613–21.Search in Google Scholar
5. Russell, D, Corin, S. Combined rocket and airbreathing propulsion systems for space-launch applications. J Propul Power 1998;14:605–12. https://doi.org/10.2514/2.5317.Search in Google Scholar
6. Colville, JR, Lewis, MJ. An aerodynamic redesign of the SR-71 inlet with applications to turbine based combined cycle engines. AIAA; 2004: 2004–3481 pp.10.2514/6.2004-3481Search in Google Scholar
7. Paul, AB, Nancy, BM, Douglas, GS. High speed turbines: development of a turbine accelerator (RTA) for space access. AIAA; 2003: 2003–6943 pp.Search in Google Scholar
8. Miyagi, H, Kimura, H, Kishi, K, Cabe, JL, Powell, TH, Yanagi, R. Combined cycle engine research in Japanese HYPR program. AIAA; 1998: 1998–3278 pp.10.2514/6.1998-3278Search in Google Scholar
9. Snyder, LE, Escher, DW, De Francesco, RL, Gutierrez, JL, Buckwalter, DL. Turbine based combination cycle (TBCC) propulsion subsystem integration. AIAA; 2004: 2004–3649 pp.10.2514/6.2004-3649Search in Google Scholar
10. Albertson, CW, Saied, E, Trexler, CA. Mach 4 test results of a dual-flow path, turbine based combined cycle inlet. AIAA; 2006: 2006–8138 pp.10.2514/6.2006-8138Search in Google Scholar
11. Colville, JR, Starkey, RP, Lewis, MJ. Axisymmetric inlet design for combined-cycle engines. J Propul Power 2006;22:1049–58. https://doi.org/10.2514/1.18063.Search in Google Scholar
12. Taguch, I, Yanagi, R. A study on pre-cooled turbojet-scramjet-rocket combined engines. AIAA; 1998: 98–35528 pp.10.2514/6.1998-3777Search in Google Scholar
13. Taguchi, H, Maita, M, Yatsuyanagi, N, Yamanakas, T. Airbreather/Rocket combined propulsion system research for Japanese SSTO space plane. AIAA; 1999: 99–45406 pp.10.2514/6.1999-4811Search in Google Scholar
14. Taguchi, H, Futamura, H, Shimodaira, K, Morimoto, T, Kojima, T, Okai, K. Design study on hypersonic engine components for TBCC space planes. AIAA; 2003: 2003–7006 pp.10.2514/6.2003-7006Search in Google Scholar
15. Okai, K, Taguchi, H, Kojima, T, Enomoto, S, Futamura, H. Numerical analysis of variable intake and nozzle for hypersonic engines. AIAA; 2003: 2003–7069 pp.10.2514/6.2003-7069Search in Google Scholar
16. Oswatisch, K. Pressure recovery in missiles with reaction propulsion at high supersonic speeds (the efficiency of shock diffusers). NACA TM1140; 1947.Search in Google Scholar
17. Lee, CC, Boedicker, C. Subsonic diffuser design and performance for advanced fighter aircraft. AIAA; 1985: 1985–3073 pp.10.2514/6.1985-3073Search in Google Scholar
18. Liu, J, Yuan, HC, Ge, N. The flow field and performance analyses of turbine-based combined cycle inlet mode transition at critical/subcritical conditions. Aero Sci Technol 2017;69:485–94. https://doi.org/10.1016/j.ast.2017.07.020.Search in Google Scholar
19. Liu, J, Yuan, HC, Hua, ZX, Chen, WF, Ge, N. Experimental and numerical investigation of smooth turbine-based combined cycle inlet mode transition. Aero Sci Technol 2017;60:124–30. https://doi.org/10.1016/j.ast.2016.11.005.Search in Google Scholar
20. Liu, J, Yuan, HC, Wang, YF, Ge, N. Unsteady supercritical/critical dual flow path inlet and its control method. Chin J Aeronaut 2017;30:1877–84. https://doi.org/10.1016/j.cja.2017.10.007.Search in Google Scholar
21. FLUENT 6.3 User’s Guide, FLUENT Inc., 2006.Search in Google Scholar
22. Teng, J, Yuan, HC. Variable geometry cowl sidewall for improving rectangular hypersonic inlet performanc. Aero Sci Technol 2015;4:128–35. https://doi.org/10.1016/j.ast.2015.01.011.Search in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
Articles in the same Issue
- Frontmatter
- Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
- Effect of multi-hole arrangement on the effusion cooling with backward injection
- Research on a component characteristic adaptive correction method for variable cycle engines
- Optimization of a circumferential groove in a centrifugal compressor
- Comparative study of numerical approaches to adaptive gas turbine cycle analysis
- Numerical simulation of shock wave/tip leakage vortex interaction for a transonic axial fan rotor
- Experimental research on suppressing unbalanced vibration of rotor by integral squeeze film damper
- The influence of the geometry of V-gutter bluff body on transient vortex shedding
- Design and validation of a two-dimensional variable geometry inlet
- Computational assessment of performance parameters of an aero gas turbine combustor for full flight envelope operation
- Investigation of effect of atomization performance on lean blowout limit for gas turbine combustors by comparison of utilizing aviation kerosene and methane as fuel
- Design optimization of a supersonic through-flow fan rotor based on the blade profiles
