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一、概述涡喷六发动机Ⅱ级涡轮叶片是用GH37高温合金模锻件制成的,材料毛坯经过1180±10℃保温2小时空冷;1050±10℃保温4小时缓冷;800±10℃保温16小时空冷热处理后,获得较好的耐高温综合性能.叶片随涡轮转子在高速旋转中,受到高温燃气流的巨大冲击力和热应力以及转动惯性离心力.如果发动机的转速超过设计值或者发动机连续工作时间过长,惯性离心力以及由它造成的叶片内部的拉伸应力,将破坏叶片的基体强度,最终导致叶片断裂.
First, an overview Turbocharged six engine Ⅱ turbine blades GH37 high temperature alloy forgings are made, the material blank after 1180 ± 10 ℃ heat 2 hours air cooling; 1050 ± 10 ℃ insulation 4 hours slow cooling; 800 ± 10 ℃ insulation 16 Small hour and cold heat treatment, to obtain a better performance of high temperature resistant blades with turbine rotor rotating at high speed, high temperature gas flow by the huge impact and thermal stress and rotational inertial centrifugal force if the engine speed exceeds the design value or the engine continuous work Over time, centrifugal force of inertia and the tensile stress inside the blade caused by it will damage the base strength of the blade and finally cause the blade to rupture.