摘要
本文介绍的设计计算方法 ,直接计入质量和能量掺混 ,但间接计入动量掺混影响。计算程序可以计及涡轮进口沿径总温、总压不均匀的影响、叶片冷却型式不同的影响以及各计算节点的比热和气体常数不同的影响。叶列损失按给出的损失模型迭代求解。在轴向间隙站对混气采用流线曲率法求解径向平衡方程。
This paper persents a method for aerodynamic design calculation of axial gas turbine stage with the mixing of cooling air.The mass flow mixing and the energy mixing of the cooling air with the main gas flow are considered directly in the continuity and the energy equations,while the momentum loss resulting from the mixing is considered indirectly.The losses of blade rows and their distributions in the radial direction are determined by means of the loss models provided in the paper.The influences of different cooling types of blades and the non uniformity of the inlet total temperature and total pressure in the radial direction have been considered in the calculation program.The method could be applied to multi stage air cooled gas turbine.The basic calculation method adopted is the streamline curvature method.As an example,a design calculation of an axial turbine stage are presented.The calculation results show that the effect of the cooling air mixing on the turbine efficiency is significant.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1989年第4期301-304,共4页
Journal of Aerospace Power
