基于二次流喷射的并联式TBCC 排气系统性能提升技术研究

Zhan Xue Wang; Shao Bo Qi; Li Zhou; Jing Wei Shi

doi:10.13675/j.cnki.tjjs.2018.04.005

基于二次流喷射的并联式TBCC 排气系统性能提升技术研究

Translated title of the contribution: Performance Improvement Study of Over-Under TBCC Exhaust System by Secondary Flow Injection

Zhan Xue Wang, Shao Bo Qi, Li Zhou, Jing Wei Shi

School of Power and Energy

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

Base on CFD, the flow characteristics of over-under TBCC (Turbine Based Combined Cycle, TBCC) exhaust system was analyzed. A method to enhance the exhaust system performance by injecting high pressure secondary flow into the down wall of turbo-engine nozzle was proposed. And the effects of secondary injection on the performance, e.g, thrust coefficient and thrust vector angle were investigated in different flight Mach number. Results show that secondary injection produces bow shock, which can generate new flow separation region interaction with ramp of nozzle. Bow shock improve turbo-engine nozzle and ramjet nozzle pressure distributions, thus improve nozzle thrust and thrust vector performance, and obviously improve over-under TBCC nozzle performance at subsonic and transonic condition, which makes the axial thrust coefficient increase by 7.34% and thrust vector angle increase by 12.76°.

Translated title of the contribution	Performance Improvement Study of Over-Under TBCC Exhaust System by Secondary Flow Injection
Original language	Chinese (Traditional)
Pages (from-to)	760-767
Number of pages	8
Journal	Tuijin Jishu/Journal of Propulsion Technology
Volume	39
Issue number	4
DOIs	https://doi.org/10.13675/j.cnki.tjjs.2018.04.005
State	Published - 1 Apr 2018

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title = "基于二次流喷射的并联式TBCC 排气系统性能提升技术研究",

abstract = "Base on CFD, the flow characteristics of over-under TBCC (Turbine Based Combined Cycle, TBCC) exhaust system was analyzed. A method to enhance the exhaust system performance by injecting high pressure secondary flow into the down wall of turbo-engine nozzle was proposed. And the effects of secondary injection on the performance, e.g, thrust coefficient and thrust vector angle were investigated in different flight Mach number. Results show that secondary injection produces bow shock, which can generate new flow separation region interaction with ramp of nozzle. Bow shock improve turbo-engine nozzle and ramjet nozzle pressure distributions, thus improve nozzle thrust and thrust vector performance, and obviously improve over-under TBCC nozzle performance at subsonic and transonic condition, which makes the axial thrust coefficient increase by 7.34% and thrust vector angle increase by 12.76°.",

keywords = "Exhaust system, Secondary injection, TBCC, Thrust coefficient, Thrust vector angle",

author = "Wang, {Zhan Xue} and Qi, {Shao Bo} and Li Zhou and Shi, {Jing Wei}",

year = "2018",

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doi = "10.13675/j.cnki.tjjs.2018.04.005",

language = "繁体中文",

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T1 - 基于二次流喷射的并联式TBCC 排气系统性能提升技术研究

AU - Wang, Zhan Xue

AU - Qi, Shao Bo

AU - Zhou, Li

AU - Shi, Jing Wei

PY - 2018/4/1

Y1 - 2018/4/1

N2 - Base on CFD, the flow characteristics of over-under TBCC (Turbine Based Combined Cycle, TBCC) exhaust system was analyzed. A method to enhance the exhaust system performance by injecting high pressure secondary flow into the down wall of turbo-engine nozzle was proposed. And the effects of secondary injection on the performance, e.g, thrust coefficient and thrust vector angle were investigated in different flight Mach number. Results show that secondary injection produces bow shock, which can generate new flow separation region interaction with ramp of nozzle. Bow shock improve turbo-engine nozzle and ramjet nozzle pressure distributions, thus improve nozzle thrust and thrust vector performance, and obviously improve over-under TBCC nozzle performance at subsonic and transonic condition, which makes the axial thrust coefficient increase by 7.34% and thrust vector angle increase by 12.76°.

AB - Base on CFD, the flow characteristics of over-under TBCC (Turbine Based Combined Cycle, TBCC) exhaust system was analyzed. A method to enhance the exhaust system performance by injecting high pressure secondary flow into the down wall of turbo-engine nozzle was proposed. And the effects of secondary injection on the performance, e.g, thrust coefficient and thrust vector angle were investigated in different flight Mach number. Results show that secondary injection produces bow shock, which can generate new flow separation region interaction with ramp of nozzle. Bow shock improve turbo-engine nozzle and ramjet nozzle pressure distributions, thus improve nozzle thrust and thrust vector performance, and obviously improve over-under TBCC nozzle performance at subsonic and transonic condition, which makes the axial thrust coefficient increase by 7.34% and thrust vector angle increase by 12.76°.

KW - Exhaust system

KW - Secondary injection

KW - TBCC

KW - Thrust coefficient

KW - Thrust vector angle

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U2 - 10.13675/j.cnki.tjjs.2018.04.005

DO - 10.13675/j.cnki.tjjs.2018.04.005

M3 - 文章

AN - SCOPUS:85053722164

SN - 1001-4055

VL - 39

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JO - Tuijin Jishu/Journal of Propulsion Technology

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基于二次流喷射的并联式TBCC 排气系统性能提升技术研究

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