涡轮基组合循环发动机并联式进气道的气动特性

Aerodynamic characteristics of over/under inlet for turbine based combined cycle engine

关键词:  涡轮基组合循环发动机+  可调进气道+  气动特性

Key words:  Turbine-based-combined-cycle engine+  Variable inlet+  Aerodynamic characteristic

摘要:

为了研究工作马赫数范围0~5的涡轮/冲压组合发动机进气道的工作特性,对一种内并联式涡轮基组合循环发动机(TBCC)变几何进气道进行了型面设计并对其二维流场进行了数值模拟。得到了进气道在各典型工作状态下的流场特征,在不采用附面层抽吸的条件下进气道在各典型飞行马赫数下均能正常起动。以设计巡航状态和过渡工作状态为例,分析了反压变化对进气道性能的影响,结果表明,进气道出口反压对进气道性能有重要影响,尤其是进气道在过渡工作状态时,两流道之间存在气动耦合效应。文中还给出了进气道气动参数随飞行条件变化的特性曲线,初步研究了影响进气道性能的主要因素,分析了该进气道在典型飞行工况下的气动性能。

Abstract:

To discuss the operating characteristics of the inlet which is used in Turbojet/Ramjet Combined Cycle engine at Mach 0 to 5,the profile of an "over/under" TBCC variable geometry inlet was given.Using CFD tools,the two-dimensional flow-field of the inlet was shown with properties of flow at different operating points.At every flight Mach number,the inlet can start without boundary layer suction.Based on the flow-field of cruise and transition states,the operating characteristics at different back pressure were analyzed.The result indicates that the back pressure at exit has effect on the performance of the inlet,especially at the transition state——change of back pressure between over and under exit can bring on aerodynamic coupling effects in the two ducts.The aerodynamic characteristic diagram varied with flight conditions of the inlet was presented.The factors affecting the performance of the inlet and the aerodynamic characteristics at typical flight conditions were analyzed.