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公开(公告)号：US10072585B2
公开(公告)日：2018-09-11
申请号：US14769591
申请日：2014-03-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John H. Mosley , James P. Chrisikos , John J. O'Connor , Charles C. Wu , David Glasspoole , Roger Gates
CPC classification number: F02C9/18 , F01D5/082 , F02C7/18 , F05D2220/3215 , Y02T50/673 , Y02T50/676
Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
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公开(公告)号：US20180051583A1
公开(公告)日：2018-02-22
申请号：US15239899
申请日：2016-08-18
Applicant: United Technologies Corporation
Inventor： David R. Griffin , Joseph E. Barker , James P. Chrisikos , Graham R. Philbrick
CPC classification number: F01D11/24 , F01D11/005 , F01D25/24 , F05D2220/32 , F05D2260/20
Abstract: Aspects of the disclosure are directed to an active clearance control system for an engine of an aircraft, comprising: a collector that is configured to receive a cooling fluid, at least two manifolds coupled to the collector, where a first of the manifolds is configured to receive at least a first portion of the cooling fluid from the collector and a second of the manifolds is configured to receive at least a second portion of the cooling fluid from the collector, and an insert coupled to the collector and the manifolds, where the insert is configured to seal an interface between the collector and the at least two manifolds over an operating range of the engine.
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公开(公告)号：US20160003166A1
公开(公告)日：2016-01-07
申请号：US14769591
申请日：2014-03-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John H. Mosley , James P. Chrisikos , Roger Gates , John J. O'Connor , Charles C. Wu , David Glasspoole
CPC classification number: F02C9/18 , F01D5/082 , F02C7/18 , F05D2220/3215 , Y02T50/673 , Y02T50/676
Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
Abstract translation: 用于燃气涡轮发动机涡轮部分的冷却系统包括支撑具有冷却通道的叶片的转子。 盘相对于转子固定，并且在转子和盘之间形成空腔。 排气源与空腔流体连通。 在空腔内布置有叶轮。 叶轮被构造成增加空腔内的流体压力以驱使排放空气源的排出空气，从而向冷却通道提供加压的冷却流体。
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公开(公告)号：US20160230579A1
公开(公告)日：2016-08-11
申请号：US14616208
申请日：2015-02-06
Applicant: United Technologies Corporation
Inventor： Brian J. Schwartz , James P. Chrisikos
CPC classification number: F01D11/005 , F01D5/3007 , F01D5/303 , F01D5/326 , F01D11/001 , F01D25/04
Abstract: A rotor disk assembly comprises a circular body configured to rotate about an axis, a contoured slot formed partially through the circular body in an axial direction, and a protrusion extending radially from the circular body adjacent the contoured slot. A turbine or compressor assembly is also provided. The turbine or compressor assembly may include a first disk configured to rotate about an axis, a first contoured slot formed partially through the first disk, a first protrusion adjacent to the first contoured slot and extending radially outward from the first disk, and a first blade disposed in the first contoured slot and configured to engage the first protrusion.
Abstract translation: 转子盘组件包括被配置为围绕轴线旋转的圆形主体，在轴向方向上部分地穿过圆形主体形成的成形槽，以及从邻近轮廓槽的圆形体径向延伸的突起。 还提供涡轮或压缩机组件。 涡轮机或压缩机组件可以包括被配置为围绕轴线旋转的第一盘，部分地穿过第一盘形成的第一轮廓槽，与第一轮廓槽相邻并从第一盘径向向外延伸的第一突起，以及第一叶片 设置在第一轮廓槽中并且被配置为接合第一突起。
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