涡轮基组合循环发动机进气道设计

采用等激波强度的方法,考虑进气道的气动性能和进气道前体斜板的调节规律。对高超声速涡轮基组合循环发动机的二维混压式几何可调进气道的设计进行了探索。控制进气道喉部出口马赫数的大小,给出了三斜板内外混合压缩进气道设计点的几何尺寸和非设计点的斜板调节规律。运用二维CFD数值计算手段,通过求解欧拉方程,对所设计进气道在不同飞行条件下的流场进行了计算。计算表明,设计的进气道结构简单,附加阻力小,总压恢复系数高,低速起动性能好,调节规律容易实现。

Turbine Based Combined Cycle Engine Inlet Design

TBCC jet has come to attract more and more attention in the past decades.As an important part of TBCC jet,inlet is critical.Constant shock intensity method is used,and considering the inlet dynamic performance,as well as its justification,the design of variable geometry mixed compression 2D-inlet is explored.Controlling the throat outlet Mach number,they give out the on-design point inlet dimension with three ramps,as well as off-design justify regulation.Using the 2D Computational Fluid Dynamic method,they modified the inlet geometry,and the fluid fields in different fly conditions are calculated.The computation result prove their expectation.