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现代军用航空发动机的推重比已达到了10,甚至更高。为了提高推重比,需重新设计发动机的循环参数、提高总增压比和涡轮进口温度。发动机循环参数优化结果表明,总增压比增加不大,涡轮进口温度将比以前提高不少,即燃烧室的工作压力变化不大,但温升将比目前增加。先进燃烧室的特点先进燃烧室的主要特点是温升高。发动机制造商将高推重比发动机的结构可靠性、耐久性、可维护性和性能列入了同等重要的地位,并要求热端部件的使用寿命大大提高,这就使燃烧室的设计面临严峻的挑战。
The thrust-weight ratio of modern military aircraft engines has reached 10 or even higher. In order to improve the thrust-to-weight ratio, it is necessary to redesign the engine cycle parameters to increase the overall pressure ratio and turbine inlet temperature. The results of optimization of engine cycle parameters show that the increase of total pressure increase ratio is not large, and the inlet temperature of the turbine will increase a lot compared with the previous ones. That is to say, the working pressure of the combustion chamber has little change, but the temperature rise will increase than that of the present. Advanced Combustion Chamber Features The main features of an advanced combustion chamber are high temperature rise. Engine manufacturers have placed equal emphasis on the structural reliability, durability, maintainability and performance of high-thrust-heavy engines and have significantly increased the service life of hot-end components, which puts the design of the combustion chamber under severe challenge.