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公开(公告)号：US4222706A
公开(公告)日：1980-09-16
申请号：US929908
申请日：1978-08-01
IPC分类号： F01D11/08
CPC分类号： F01D11/08
摘要： A turbine housing for a jet engine is provided with a ring of an abradableorous material. A supporting and mounting device consisting of a cylindricoconical monoblock having a conical internal jacket provides for the convection cooling of the external surface and a cylindrical jacket for cooling air is held over the abradable ring by means of a perforated ferrule integral with the rest of the device. The abradable ring carries transverse partitions to prevent axial leakage.
摘要翻译： 用于喷气发动机的涡轮壳体设置有耐磨多孔材料的环。 由具有锥形内套的圆柱形整体构成的支撑和安装装置提供外表面的对流冷却，并且用于冷却空气的圆柱形护套通过与该装置的其余部分成一体的多孔套圈保持在可磨损环上 。 耐磨环承载横向隔板以防止轴向泄漏。
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公开(公告)号：US4329113A
公开(公告)日：1982-05-11
申请号：US82338
申请日：1979-10-05
CPC分类号： F01D11/18
摘要： A portion of the stator of a gas turbine known as turbine shroud, which isituated radially opposite the mobile vanes of a turbine stage includes an "abradable" member supported by a first shell braced by a second shell and connected with turbine casing 2 by a thin, i.e. flexible, annular wall member embedded in a casing. Cooling air inflates the second shell so as to brace the exterior shell and circulates between the two shells so as to cool them and also cools the "abradable" member by impingement. The present invention is applicable to aviation turbojets.
摘要翻译： 称为涡轮罩的定子的一部分被称为涡轮机护罩，其位于与涡轮机级的可动叶片径向相对的位置，包括由第二壳体支撑的第一壳体支撑并由涡轮机壳体2连接的“可磨损”构件 薄的，即柔性的环形壁构件嵌入壳体中。 冷却空气使第二壳体膨胀以支撑外壳并在两个壳体之间循环以便冷却它们，并且还通过冲击来冷却“可磨损”构件。 本发明适用于航空涡轮喷气发动机。
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公开(公告)号：US4320903A
公开(公告)日：1982-03-23
申请号：US79433
申请日：1979-09-27
CPC分类号： F01D25/12 , F01D11/02 , F02C7/12 , F02C7/18 , F02C7/28 , Y02T50/675 , Y10S277/931
摘要： A labyrinth seal mounted between a shaft and the casing of a gas turbine combustion chamber, wherein the support of an abradable sealing surface in the seal which operates in conjunction with rapidly rotating fins is cooled by an upstream airflow parallel to the envelope surface of the extremities of such fins and opening into an upstream space. The cooling air is taken in from the casing by means of a conduit which is connected with an overflow valve tied to the gas turbine load. The invention is applicable to aviation turbojets.
摘要翻译： 安装在轴和燃气轮机燃烧室的壳体之间的迷宫式密封件，其中密封件中可磨损的密封表面的支撑件与快速旋转的翅片结合起来，其通过平行于末端的包络面的上游气流来冷却 的这种翅片并打开到上游空间。 冷却空气通过与连接到燃气轮机负载的溢流阀连接的导管从壳体中吸入。 本发明适用于航空涡轮喷气发动机。
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公开(公告)号：US4231704A
公开(公告)日：1980-11-04
申请号：US929910
申请日：1978-08-01
CPC分类号： F02C7/18 , F01D5/08 , F04D29/321 , F04D29/582 , Y02T50/676
摘要： A device for moving air from the jet flow of an axial compressor of a gas rbine group, to be conducted along the axis of the group to the turbine to be cooled. The air is moved by a wheel having an outer rim serving as a brace between two adjacent compressor disks and centripetal blading which moves the air through openings formed in the rim, to accelerate it and discharge it into a space surrounding the axis of the compressor.
摘要翻译： 用于将空气从燃气轮机组的轴向压缩机的喷流流动的装置，沿组的轴线传导到要冷却的涡轮。 空气由具有作为两个相邻的压缩机盘之间的支架的外轮缘的轮子和向心叶片移动，所述向心叶片使空气通过形成在轮辋中的开口移动，以加速它并将其排出到围绕压缩机轴线的空间中。
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