摘要
为提高现代航空发动机的性能和可靠性 ,国内外许多研究机构都先后开展了叶尖间隙控制技术方面的研究 ,而进行叶尖间隙的数值分析是其中的重要内容之一。本文采用有限元数值分析法 ,结合某型发动机高压涡轮 ,分析了叶片、轮盘和机匣的热 -结构耦合变形及涡轮叶尖间隙的变化规律 ,得到了较为合理的计算结果。计算分析表明 :在发动机快速加、减速的情况下 ,叶尖间隙的变化较大 ;涡轮叶片的热响应最快 ,涡轮盘的热响应最慢 ;发动机在采用了控制机匣温度的方法后 ,叶尖间隙得到了有效的控制。
In order to improve the performance and the probability of the aero-engine, many researches on the technique of clearance control system are developed in many research departments. The numerical analysis method for the turbine or compressor tip clearance is important in this research fields. By using finite element method, the thermal-structure coupled displacement of the case, disc & blade and the transient response of tip clearance are analyzed in temperature and rotor speed. Results show that the numerical method used for calculating tip clearance is successful. By calculation and analysis, during an rapid acceleration or deceleration, the tip clearance of HPT changes remarkably. The thermal response speed of HPT blade is quicker than HPT disc. The control temperature of HPT case is efficient and the tip clearance is effectively controlled.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第1期63-67,共5页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
叶尖间隙
高压涡轮
数值分析
tip clearance
high pressure turbine
numerical analysis
