一种涡轮基组合动力的整机低速风洞试验研究

doi:10.13675/j.cnki. tjjs. 180667

推进技术 ›› 2019, Vol. 40 ›› Issue (11): 2436-2443.DOI: 10.13675/j.cnki. tjjs. 180667

一种涡轮基组合动力的整机低速风洞试验研究

郭峰¹,桂丰²,尤延铖¹,朱剑锋¹,朱呈祥¹

1.厦门大学航空航天学院;2.中国航发四川燃气涡轮研究院，四川成都;610500

发布日期:2021-08-15
作者简介:郭峰，博士生，研究领域为高超声速气体动力学、内流气体动力学。E-mail：g234872714f@126.com
基金资助:
装发预研领域基金 61402060301;航空动力基金 6141B090308;兵发预研基金 6141B010266;福建省自然科学基金 2016J06011装发预研领域基金（61402060301）；航空动力基金（6141B090308）；兵发预研基金（6141B010266）；福建省自然科学基金（2016J06011）。

Experimental Study of TBCC Engine Performance inLow Speed Wind Tunnel

1.School of Aerospace Engineering,Xiamen University,Xiamen 361005,China;2.AECC Sichuan Gas Turbine Establishment，Chengdu 610500，China

Published:2021-08-15

摘要/Abstract

摘要： 针对一种多通道三动力涡轮基组合动力开展了整机低速风洞试验，着重从总体性能、流量分配、压力分布等方面，对三维内转组合进气道与涡轮发动机的耦合特性进行了分析。主要结论如下：低速状态下，三维内转进气道将给涡轮发动机带来最大10%的总压损失，组合动力推力最大损失24%、耗油率增加26%；内转进气道涡轮通道呈现出口总压分布不均、沿程静压先减小再增大的现象，随着涡轮发动机转速增大，通道出口高总压区逐渐向一侧移动；为减小低速状态三维内转进气道涡轮通道的流道损失，建议引入辅助进气门等引流装置、动态调整冲压通道流道面积，以匹配涡轮发动机工作状态。

关键词: 涡轮基组合动力;三维内转组合进气道;耦合特性;总体性能;流量分配;压力分布

Abstract: A three-power turbine-based combined cycle engine with multi-ducts was tested in a low speed wind tunnel. The coupling characteristics of turbine engines and inlet are analyzed from the aspects of engine’s performance, mass flow allocation and total pressure distribution at turbine entrance. The coupling characteristics of three-dimensional inward turning combined inlet and turbine engine are analyzed: the three-dimensional internal turning inlet will bring the maximum total pressure loss of 10% to the turbine engine in low-speed freestream, resulting in a maximum loss of 24% in thrust and a 26% increase in specific fuel consumption. The total pressure distribution at turbine entrance is uneven, and the static pressure decreases first and then increases along the turbojet flow path of inlet. As the turbine rotating speed increase, the high-pressure zone at the turbine entrance gradually moves to one side. In order to reduce the flow loss of the turbojet flow path, the three-dimensional inward turning inlet need to match the working state of the turbine engine. It is suggested to install auxiliary inlet valve or other drainage system and adjust the ramjet flow path dynamically.

Key words: TBCC (Turbine-based combined cycle);Three dimensional inward turning combined inlet;Coupling characteristics;Engine performance;Flow allocation;Pressure distribution

郭峰,桂丰,尤延铖,朱剑锋,朱呈祥. 一种涡轮基组合动力的整机低速风洞试验研究[J]. 推进技术, 2019, 40(11): 2436-2443.

GUO Feng¹,GUI Feng²,YOU Yan-cheng¹,ZHU Jian-feng¹,ZHU Cheng-xiang¹. Experimental Study of TBCC Engine Performance inLow Speed Wind Tunnel[J]. Journal of Propulsion Technology, 2019, 40(11): 2436-2443.

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一种涡轮基组合动力的整机低速风洞试验研究

Experimental Study of TBCC Engine Performance inLow Speed Wind Tunnel

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