某燃气轮机低压压气机结构设计方案研究  

Research on the Design of a Gas Turbine Low Pressure Compressor

作　　者：孙远伟 Sun Yuanwei(AECC Gas Turbine Co. ,Ltd., Shenyang 110179,China)

机构地区：[1]中国航发燃气轮机有限公司,沈阳110179

出　　处：《燃气轮机技术》2021年第4期25-29,共5页Gas Turbine Technology

摘　　要：双涵道航空发动机(简称航机)改制成地面燃气轮机通常须新制低压压气机来提高燃气轮机做功能力和效率,但研制周期长且技术风险高;而采用低压压气机静子部件新设计、转子叶片直接切顶方式,压气机性能较原航机降低幅度较大。研究某航机低压压气机结构后,在航机低压压气机静子部件中增加隔环及挡片,减小流道,转子部件在转子轮盘及叶片榫头不变的前提下新设计叶片叶型,经气动和强度计算后总压比2.863,绝热效率88%,满足设计要求。进口空气流量偏大,可调节可调叶片,动叶片强度经校核满足要求。Dual culvert aviation engine(referred to as aircraft)such as the transformation into ground gas turbine usually requires the new production of low-pressure compressor to improve the power and efficiency of gas turbine,however,the development cycle is long and the technical risk is high.But if the new design of low-pressure compressor static parts are adopted,the rotor blades are cut the top directly,and the performance of the compressor is reduced by a large margin.After studying the structure of a low-pressure compressor of an aircraft,the spacers and baffles are added to the stator parts of the aircraft’s low-pressure compressor to reduce the flow path,the rotor parts are newly designed with the rotor disc and blade tenon unchanged.After pneumatic and strength calculation,the total pressure ratio of the new structural is 2.863,and the insulation efficiency is 88%,it meets the design requirements,the import air flow is too large,it can be adjusted through adjustable blades,and the rotor blades strength have been checked to meet the requirements.

关 键 词：燃气轮机 低压压气机机匣 静子叶片 动叶片 强度 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]