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直到工业激光器出现,汽体透平结构中的精密小孔的加工一直是个问题,而对更小孔的需求量又在不断增加。1976年10600马力(7904千瓦)的大型透平的采用与激光技术的发展恰相呼应,这种情况达到了一个关键时刻.技术要求对新透平规定了非常高的燃料效率和性能,这样,燃烧室的衬套上就需要有很多的小冷却孔。新型燃烧室衬套设计要求30个独立的条目,其中包括有15个冷却孔的要求.冷却孔的主要用途是让发动机上的压缩机部件中的空气在重要的冲击时刻进入燃烧室,在燃烧室衬套内壁和燃烧室里的猛烈的环形火球之间产生一个气体薄雾边界层,以避免发生过热现象。
Until industrial lasers appeared, the machining of precision holes in gas turbine structures was always a problem, and the demand for smaller holes was increasing. The introduction of 10,600 horsepower (7,904 kilowatts) of large turbines in 1976 coincides with the development of laser technology, which reached a critical moment in terms of technical requirements that set very high fuel efficiency and performance for the new turbine, The combustion chamber liner needs a lot of small cooling holes. The new combustion chamber liner design requires 30 separate entries including 15 cooling holes, the main purpose of which is to allow air in the compressor components on the engine to enter the combustion chamber at critical impact moments, A gas mist boundary layer is created between the inner wall of the chamber liner and the violent torus in the combustion chamber to prevent overheating.