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Annular combustor having ceramic liner

机译:具有陶瓷衬里的环形燃烧器

摘要

An annular combustor for a jet turbine engine of generally rectangular cr-section having an axially-projecting aft exhaust outlet is lined by a plurality of circumferentially-extending heat-insulating liner segments, preferably ceramic, spaced from the metal shell of the combustor by spring-like spacers. The liner segments have offset tabs at their edges to slidably mate with each other and with retaining clips adjacent to the exhaust outlet, thereby being slidably secured to accept expansion of the metal shell without placing appreciable stress on the liner segments. Arcuate, generally planer liner segments along the forward and aft walls of the combustor are keyed in place by a radially- inward flanged liner segment along the outer perimetrical wall of the shell.
机译:用于具有大致轴向cr形截面的喷气涡轮发动机的环形燃烧器,其具有轴向突出的后部排气出口,其内衬有多个周向延伸的绝热衬套段,所述绝热衬套段优选是陶瓷的,其通过弹簧与燃烧器的金属壳隔开状的垫片。衬管段在其边缘处具有偏置突片,以彼此可滑动地配合并且与邻近排气出口的保持夹配合,从而被可滑动地固定以接受金属壳的膨胀,而不会在衬管段上施加明显的应力。沿着燃烧器的前壁和后壁的弓形,大体上是平面的衬里部分通过沿着壳体的外圆周壁的径向向内的带凸缘衬里部分固定在适当的位置。

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