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

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

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

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。

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.