进气导叶与吸波导流环气动/隐身一体化设计方法研究

Integrated Design Method of Aerodynamic and Stealth Performance for Inlet Guide Vane and Wave Absorbing Deflector Ring

关键词:  涡轮发动机  吸波导流环  一体化结构  气动  隐身  雷达散射面积

Key words:  Turbine engine  Wave absorbing deflector ring  Integrated structure  Aerodynamic  Stealth  Radar cross section

摘要:

针对涡轮发动机隐身需求提出了一种进气导叶与吸波导流环一体化设计方法，确定了吸波导流环主要设计参数。将涡轮发动机中的导流支板等结构替换为进气导叶与吸波导流环一体化结构，并对两种结构气动性能与隐身性能进行了计算分析。计算结果表明，相比于原型支板，进气导叶与吸波导流环一体化结构雷达散射面积（RCS）在P波段平均下降1.55dB，L波段平均下降2.70dB，X波段平均下降10.23dB，而从气动性能角度，同样压比条件下，换算流量下降约1.7%~1.8%，总压恢复系数下降约0.04%~0.1%，而进气道出口总压畸变指数下降约0.2%。进气导叶与吸波导流环一体化结构可以明显提高进气系统隐身性能，而对气动性能影响较小。

Abstract:

Integrated design method of inlet guide vane and wave absorbing deflector ring considering stealth performance of turbine engine was proposed. Fundamental design parameters of wave absorbing deflector ring were described. The deflector struts in turbine engine was replaced with integrated structure of inlet guide vane and wave absorbing deflector ring. Aerodynamic and stealth performance of both kinds of structure was computed and analyzed. Results show that the radar cross section（RCS） of the integrated structure of inlet guide vane and wave absorbing deflector ring was decreased by 1.55dB in P Band， 2.70dB in L Band and 10.23dB in X Band， compared to the prototype strut. As to the aerodynamic performance， the equivalent mass flow was decreased by 1.7%~1.8%， and the total pressure recovery coefficient was decreased by 0.04%~0.1%， at the same total pressure ratio， while the total pressure distortion was decreased by 0.2% at the outlet of the inlet. The stealth performance of the intake system could be improved significantly， while the aerodynamic performance might be influenced slightly， by adopting the integrated structure of inlet guide vane and wave absorbing deflector ring.