Shock vector controlling (SVC) nozzle, based on confined transverse injection and shock wave/boundary layer interaction, offers an alternative for future aircraft thrust vectoring (TV) exhausting system, due to its simple structure, low weight, and quick vector response. In the paper, the flow mechanism of SVC nozzle was studied by numerical simulation after the validation of computational fluid dynamics (CFD) models was confirmed. Then, the influence of substantial affecting factors, including injection configurations and injection angles, on the confined transverse injection flowfield characteristics and vector performance was investigated numerically. The results show that the “λ” shock wave induced by the jet injection causes unbalanced side force for the primary flow deflecting, and under larger secondary pressure ratio (SPR), the induced shock wave interacts with upper wall, weakening the thrust vector efficiency; with the increase of injection orifice numbers, the vector angle of SVC nozzle rises and is less than that of slot injection configuration; under smaller SPR, the thrust vector angle increases with the injection angle. For the case of SPR = 1.0 and 1.2, there exist optimal injection angles at which the maximum TV angle achieved.
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October 2016
Research-Article
Investigation on Flowfield Characteristics and Performance of Shock Vector Control Nozzle Based on Confined Transverse Injection
Shi Jingwei,
Shi Jingwei
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: shijingwei@mail.nwpu.edu.cn
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: shijingwei@mail.nwpu.edu.cn
Search for other works by this author on:
Zhou Li,
Zhou Li
Professor
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: zhouli@nwpu.edu.cn
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: zhouli@nwpu.edu.cn
Search for other works by this author on:
Wang Zhanxue,
Wang Zhanxue
Professor
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: wangzx@nwpu.edu.cn
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: wangzx@nwpu.edu.cn
Search for other works by this author on:
Sun Xiaolin
Sun Xiaolin
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: 2014100446@mail.nwpu.edu.cn
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: 2014100446@mail.nwpu.edu.cn
Search for other works by this author on:
Shi Jingwei
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: shijingwei@mail.nwpu.edu.cn
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: shijingwei@mail.nwpu.edu.cn
Zhou Li
Professor
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: zhouli@nwpu.edu.cn
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: zhouli@nwpu.edu.cn
Wang Zhanxue
Professor
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: wangzx@nwpu.edu.cn
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: wangzx@nwpu.edu.cn
Sun Xiaolin
Collaborative Innovation Center for
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: 2014100446@mail.nwpu.edu.cn
Advanced Aero-Engine,
School of Power and Energy,
Northwestern Polytechnical University,
Xi'an 710072, China
e-mail: 2014100446@mail.nwpu.edu.cn
Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received August 13, 2015; final manuscript received February 22, 2016; published online April 26, 2016. Assoc. Editor: Eric Petersen.
J. Eng. Gas Turbines Power. Oct 2016, 138(10): 101502 (11 pages)
Published Online: April 26, 2016
Article history
Received:
August 13, 2015
Revised:
February 22, 2016
Citation
Jingwei, S., Li, Z., Zhanxue, W., and Xiaolin, S. (April 26, 2016). "Investigation on Flowfield Characteristics and Performance of Shock Vector Control Nozzle Based on Confined Transverse Injection." ASME. J. Eng. Gas Turbines Power. October 2016; 138(10): 101502. https://doi.org/10.1115/1.4033140
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