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公开(公告)号：US11136995B2
公开(公告)日：2021-10-05
申请号：US16376445
申请日：2019-04-05
摘要： A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a hot fairing structure adjacent to the exit guide vane ring to define a multiple of diffusion passages around the engine longitudinal axis; an outer radial interface between a radial outer surface of the hot fairing structure and the exit guide vane ring, the outer radial interface being a full hoop structure; and an anti-rotation feature between the hot fairing structure and the exit guide vane ring, the anti-rotation features inboard of the multiple of diffusion passages.
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公开(公告)号：US10301958B2
公开(公告)日：2019-05-28
申请号：US15021945
申请日：2014-08-21
摘要： A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.
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公开(公告)号：US20160230666A1
公开(公告)日：2016-08-11
申请号：US14617109
申请日：2015-02-09
发明人： Kevin Zacchera , Matthew Andrew Hough , Jonathan Lemoine , Christopher Treat , Alberto A. Mateo
CPC分类号： F02C7/20 , F01D5/081 , F02C7/12 , F05D2230/64 , F05D2260/14 , F05D2260/30 , F05D2260/36 , Y02T50/676
摘要： A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.
摘要翻译： 用于燃气涡轮发动机的冷却结构包括限定冷却腔的燃气涡轮发动机结构。 冷却部件构造成将冷却流沿所需方向引导到冷却腔中。 支架支撑冷却部件并且具有附接接口以将支架固定到燃气涡轮发动机结构。 与支架相关联的第一个定向功能。 第二定向特征与燃气涡轮发动机结构相关联。 第一和第二取向特征彼此配合以确保冷却部件仅相对于燃气涡轮发动机结构安装在一个方位上。 还公开了一种燃气涡轮发动机和安装冷却结构的方法。
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公开(公告)号：US11384936B2
公开(公告)日：2022-07-12
申请号：US16376451
申请日：2019-04-05
摘要： A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts; and a multiple of diffusion passage ducts attached to the ring-strut-ring structure. A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a ring-strut-ring structure adjacent to the exit guide vane ring to form a multiple of diffusion passages defined around the engine longitudinal axis, an inlet to each of the multiple of diffusion passages smaller than an exit from each of the multiple diffusion passage through the ring-strut-ring structure; a diffusion passage duct attached to the ring-strut-ring structure at the exit from each of the multiple diffusion passage.
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公开(公告)号：US11022144B2
公开(公告)日：2021-06-01
申请号：US16361938
申请日：2019-03-22
发明人： Matthew Andrew Hough , John S. Tu , Stephen C. Harmon , Paul F. Croteau , Russell B. Hanson , Joshua C. Rathgeb
摘要： A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.
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公开(公告)号：US20200300103A1
公开(公告)日：2020-09-24
申请号：US16361938
申请日：2019-03-22
发明人： Matthew Andrew Hough , John S. Tu , Stephen C. Harmon , Paul F. Croteau , Russell B. Hanson , Joshua C. Rathgeb
IPC分类号： F01D9/02
摘要： A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.
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公开(公告)号：US10533453B2
公开(公告)日：2020-01-14
申请号：US14910551
申请日：2014-08-05
IPC分类号： F01D25/12 , F01D5/18 , F01D5/12 , F01D9/04 , F01D11/08 , F04D29/32 , F04D29/38 , F04D29/54 , F04D29/58 , F01D11/00
摘要： One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof. The platform including a core passageway configured to communicate fluid to the mateface.
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公开(公告)号：US10036260B2
公开(公告)日：2018-07-31
申请号：US14765852
申请日：2014-03-07
CPC分类号： F01D5/26 , F01D5/02 , F01D5/12 , F01D5/22 , F01D5/3007 , F01D5/326 , F01D11/006 , F05D2220/32 , F05D2240/55 , F05D2250/71 , F05D2250/73 , F05D2260/96
摘要： A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.
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公开(公告)号：US10012085B2
公开(公告)日：2018-07-03
申请号：US14765859
申请日：2014-03-10
CPC分类号： F01D5/10 , F01D5/26 , F01D5/3007 , F01D11/006 , F05D2260/96 , Y10T29/49323
摘要： A gas turbine engine rotor assembly has a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.
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公开(公告)号：US20160222787A1
公开(公告)日：2016-08-04
申请号：US15021060
申请日：2014-09-17
摘要： An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.
摘要翻译： 根据本公开的示例性方面的组件包括盘，在盘的第一轴向侧提供空腔的盖板，包括由至少一个中的至少一个中的凹口提供的入口的通道 盘和盖板与空腔流体连通，并且从入口延伸到设置在与第一轴向侧相对的盘的第二轴向侧处的出口的通道，与入口流体连通的出口和配置的通道 以提供从空腔到出口的流体流动。
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