关键词: 隐身军机进气道, 航空发动机, 旋流/总压组合畸变, 畸变测试, 畸变模拟, 畸变指数

Abstract: Complex swirl/total pressure combined distortion occurs at the inlet exit of new-generation advanced stealth military aircraft. However, there is still no international consensus on the test and evaluation methods for swirl/total pressure combined distortion in aero-engines. Developing such test and evaluation methods for aero-engines to support the definition of safe operating boundaries of aero-engines is a critical technical issue that needs to be urgently addressed for the aerodynamic compatibility evaluation between the inlet and engine of new-generation advanced stealth military aircraft. Domestic and international entities have accumulated a certain technical foundation in areas such as swirl/total pressure combined distortion flow field testing, distortion generator design, and distortion index definition. Nevertheless, continuous technical research and development efforts are still required focusing on the following aspects: accurate steady/dynamic flow field testing under large flow deflection angles, 测点 distribution design for complex distortion profiles, efficient design and continuous adjustability of distortion generators, and the definition of distortion indices that can reflect changes in engine stability.

Key words: inlet duct of stealth military aircraft, aeroengine, combined distortion of swirl and total pressure, distortion measurement, distortion generator, distortion descriptor