Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC
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Yunfei Wang
,
Huacheng Yuan
,
Jinsheng Zhang
Abstract
Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet was carried out for tandem scheme turbine-based combined cycle (TBCC) propulsion system. The operation Mach number of the inlet was between 0 and 4. The design point was chosen as Mach number 4.0 in this paper. The determination of external and internal compression and the design method of annular to circle diffuser were illustrated. The inlet was unstart under Ma 3.0 without adjustment. Then, a variable scheme was designed to ensure self-start of the inlet and match the requirement of mass flow rate during the whole flight envelope. And four supports were used to fix the spike. According to the 3D numerical simulations, the total pressure recovery was 0.52 at Ma 4.0 at critical condition and the mass flow rate was consistent with the requirement at different flight Mach number.
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 11772155
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Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This research was supported by the National Natural Science Foundation of China (No. 11772155).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Bilardo, VJ, Curran, FM, Hunt, JL, Lovell, NT, Maggio, G, Wilhite, AW, et al. The benefits of hypersonic air breathing launch systems for access to space; 2003. AIAA 2003-5265.10.2514/6.2003-5265Search in Google Scholar
2. Chen, M, Tang, HL, Zhu, ZL. Goal programming for stable modetransition in tandem turbo-ramjet engines. Chin J Aeronaut 2009;22:486–92. https://doi.org/10.1016/S1000-9361(08)60130-2.Search in Google Scholar
3. Chen, M, Zhu, ZL, Zhu, DM, Zhang, J, Tang, HL. Performance analysis tool for turbine based combined cycle engine concept. J Astronaut 2006;27:854–9.Search in Google Scholar
4. Hank, JM, Franke, ME, Eklund, DR. TSTO reusable launch vehicles using air-breathing propulsion; 2006. AIAA 2006-4962.10.2514/6.2006-4962Search in Google Scholar
5. Steelant, J. Sustained hypersonic flight in Europe: first technology achievements with in LAPCATII; 2011. AIAA 2011-2243.10.2514/6.2011-2243Search in Google Scholar
6. Bradley, M, Bowcutt, K, McComb, J. Revolutionary turbine accelerator (RTA) two-stage-to-orbit (TSTO) vehicle study; 2002. AIAA 2002-3902.10.2514/6.2002-3902Search in Google Scholar
7. Okazaki, M, Miyazawa, K, Ishizawa, K. Engineering research for super/hypersonic transport propulsion system (HYPR); 1999. ISABE 99-7004.Search in Google Scholar
8. Chen, M, Tang, HL, Zhu, DM, Zhu, ZL. Hypersonic combined cycle engine concept with tandem layout. J Beijing Univ Aeronaut Astronaut 2007;33:265–8. https://doi.org/10.13700/j.bh.1001-5965.2007.03.004.Search in Google Scholar
9. Cai, YH, Zhang, JD, Wang, ZX. Exploring TBCC engine inlet design for Ma = 5. J Northwest Polytech Univ 2007;25:615–19.Search in Google Scholar
10. 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
11. Watanabe, Y, Miyagi, H, Sekido, T. Conceptual design study on combined-cycle engine for hypersonic transport; 1993. ISABE 1993-7018.Search in Google Scholar
12. Pearson, LW. Hypersonic research engine project. Phase 2A: inlet program; 1976. NASA-CR-66797.Search in Google Scholar
13. Earl, HA, Ernest, AM. Review of NASA’s hypersonic research engine project; 1993. AIAA 93-2323.Search in Google Scholar
14. Waltrup, PJ, White, ME, Zarlingo, F, Gravlin, ES. History of ramjet and scramjet propulsion development for U.S. Navy missiles. Johns Hopkins APL Tech Dig 1997;18:234–43.Search in Google Scholar
15. Voland, RT, Auslender, AH, Smart, MK, Roudakov, AS, Semenov, VL, Kopchennov, V. CIAM/NASA Mach 6.5 scramjet flight and around test; 1999. AIAA 99-4848.10.2514/6.1999-4848Search in Google Scholar
16. Norman, ES, Eldon, AL, Domald, BS. Variable geometry for supersonic mixed-comperssion inets; 1974. AIAA 74-1172.Search in Google Scholar
17. Jesse, RC, Ryan, PS, Mark, JL. Extending the flight Mach number of the SR-71 inlet; 2005. AIAA 2005-3284.Search in Google Scholar
18. Jesse, RC. Axisymmetric inlet design for combined cycle engines. Maryland, USA: University of Maryland; 2005.Search in Google Scholar
19. Takayuki, K, Nobuhiro, T, Tetsuya, S, Masao, M, Yoshinari, E. Development study on axisymmetric air inlet for ATREX engine; 2001. AIAA 2001-1895.Search in Google Scholar
20. Mizobata, K, Arai, T, Sugiyama, H. Conceptual feasibility of reusable launch vehicles based on the ATREX engine; 1999. AIAA 99-4829.10.2514/6.1999-4829Search in Google Scholar
21. Tetsuya, S, Nobuhiro, T, Hiroshi, H, Ken, G, Hiroaki, K, Junsuke, O, et al. Development study of the ATREX engine for TSTO spaceplane; 2001. AIAA 2001-1839.Search in Google Scholar
22. Yusuke, M, Nobuhiro, T, Tetsuya, S, Hiroaki, K, Keiichi, O. Multi-row disk arrangement concept for spike of axisymmetric air inlet; 2004. AIAA 2004-3407.Search in Google Scholar
23. Lois, JW, Bobby, WS, Jake, V. A new design concept for supersonic axisymmetric inlets; 2002. AIAA 2002-3775.Search in Google Scholar
24. Li, J. Research on variable hypersonic axisymmetric inlet. Nanjing, China: Nanjing University of Aeronautics and Astronautics; 2012.Search in Google Scholar
25. Guo, CW. Research on the design and regulation of variable axisymmetric inlet working under wide Mach number. Nanjing, China: Nanjing University of Aeronautics and Astronautics; 2014.Search in Google Scholar
26. Xie, LR, Guo, RW. Numerical simulation and experimental validation of flow in mixed-compression axisymmetric supersonic inlet with fixed-geometry. Acta Aeronaut Astronaut Sinica 2007;28:78–83.Search in Google Scholar
27. Zhang, HJ, Liu, XG, Guo, RW, Xie, LR. Design of turbo diffuser for TBCC inlet based on characteristics of turbo mode. J Aero Power 2014;29:181–91. https://doi.org/10.13224/j.cnki.jasp.2014.01.024.Search in Google Scholar
28. Davic, J, Midea, A. Propulsion and aerodynamic analysis of the Beta II two -stage-to-orbit vechile; 1992. AIAA 92-4245.10.2514/6.1992-4245Search in Google Scholar
29. Liu, J, Yuan, HC, Hua, ZX, Chen, WF, Ge, N. Preliminary research of terminal shock motion in tandem configuration turbine-based combined cycle inlet. Aeronaut J 2017;121:416–32. https://doi.org/10.1017/aer.2016.121.Search in Google Scholar
30. Kantrowitz, A, Donaldson, C. Preliminary investigation of supersonic diffusers; 1945. NACA WRL-713.Search in Google Scholar
31. Van Wie, DM, Kwok, FT, Walsh, RF. Starting characteristics of supersonic inlets; 1996. AIAA 1996-2914.10.2514/6.1996-2914Search in Google Scholar
© 2020 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
