The invention belongs to the field of engine stability margin design, and relates to an aero-gas turbine engine whole machine stability margin evaluation method, which comprises the following steps: according to engine rotor blade tip clearance dynamic simulation results under different operation processes and simulation results of influence of rotor blade tip clearance on fan, gas compressor and turbine characteristics, evaluating the stability margin of an aero-gas turbine engine; the method comprises the following steps: respectively obtaining characteristic change values and compressor surge boundary down-shift after blade gaps of a fan, a compressor and a high-low pressure turbine are changed, calculating up-shift of a common working line of the compressor according to an engine overall performance simulation program, and calculating the stability margin decline of the engine in combination with the compressor surge boundary down-shift. The engine complete machine simulation calculation model is adopted to evaluate the engine complete machine stability margin variation under different operation processes, the efficiency of obtaining the complete machine stability margin variation under different processes is greatly improved, and the time cost, manpower, financial resources and material resources are saved.
本申请属于发动机稳定裕度设计领域,为一种航空燃气涡轮发动机整机稳定裕度评估方法,根据不同运转历程下发动机转子叶尖间隙动态仿真结果以及转子叶尖间隙对风扇、压气机和涡轮特性影响仿真结果,分别获得风扇、压气机和高低压涡轮叶片间隙变化后的特性变化值和压气机喘振边界下移量,再根据发动机总体性能仿真程序,计算出压气机共同工作线的上移量,并结合压气机喘振边界下移量计算得到发动机稳定裕度下降量。采用发动机整机仿真计算模型评估不同运转历程下发动机整机稳定裕度变化量,极大提高了获得不同历程下整机稳定裕度变化的效率,节约了时间成本和人力、财力、物力。
Complete machine stability margin assessment method for aviation gas turbine engine
一种航空燃气涡轮发动机整机稳定裕度评估方法
15.10.2024
Patent
Elektronische Ressource
Chinesisch
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |
General aviation turbine engine /GATE/ concepts
NTRS | 1979
|General aviation turbine engine /GATE/ concepts
AIAA | 1979
|General Aviation Turbine Engine (GATE) Study
NTIS | 1979
|