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公开(公告)号：US12079735B2
公开(公告)日：2024-09-03
申请号：US17323667
申请日：2021-05-18
Applicant: General Electric Company
Inventor： Kudum Shinde , Mahesh Khandeparker
CPC classification number: G06N5/00 , F01D5/12 , F01D11/14 , F01D11/22 , F01D11/24 , F02C7/20 , G06N20/00 , F05D2270/54 , F05D2270/70 , F05D2270/709
Abstract: Systems and methods for optimizing clearances within an engine include an adjustable coupling configured to couple a thrust link to the aircraft engine, an actuator coupled to the adjustable coupling, where motion produced by the actuator adjusts a hinge point of the adjustable coupling, sensors configured to capture real time flight data, and an electronic control unit. The electronic control unit receives flight data from the sensors, implements a machine learning model trained to predict clearance values within the engine based on the received flight data, predicts, with the machine learning model, the clearance values within the engine based on the received flight data, determines an actuator position based on the clearance values, and causes the actuator to adjust to the determined actuator position.
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公开(公告)号：US11879356B2
公开(公告)日：2024-01-23
申请号：US17852875
申请日：2022-06-29
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann
CPC classification number: F01D5/186 , F01D1/12 , F01D5/147 , F01D5/284 , F01D11/122 , F01D11/14 , F05D2220/32 , F05D2230/31 , F05D2230/311 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2300/514
Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.
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公开(公告)号：US20190017607A1
公开(公告)日：2019-01-17
申请号：US15651081
申请日：2017-07-17
Applicant: United Technologies Corporation
Inventor： Conway Chuong , Ross Wilson
CPC classification number: F16J15/442 , F01D5/03 , F01D11/025 , F01D11/14 , F02C3/14 , F05D2220/323 , F05D2240/55 , F16J15/441 , F16J15/445
Abstract: An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes.
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4.发明授权公开(公告)号：US10060294B2
公开(公告)日：2018-08-28
申请号：US15130253
申请日：2016-04-15
Inventor： Joseph P. Lamusga
CPC classification number: F01D25/28 , F01D9/02 , F01D11/08 , F01D11/14 , F01D25/005 , F05D2220/32 , F05D2240/11 , F05D2250/184 , F05D2300/6033 , Y02T50/672
Abstract: An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position.
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公开(公告)号：US20180142567A1
公开(公告)日：2018-05-24
申请号：US15815494
申请日：2017-11-16
Applicant: MTU Aero Engines AG
Inventor： Hermann Klingels
CPC classification number: F01D11/20 , F01D5/225 , F01D5/288 , F01D11/08 , F01D11/12 , F01D11/127 , F01D11/14 , F05D2230/90 , F05D2240/55 , F05D2260/941
Abstract: The present invention relates to a sealing system for an axial turbomachine for a gas turbine, including a rotor with a radially outward arranged shroud and a housing that surrounds the rotor, wherein a gap is arranged between the shroud and the housing, and wherein the gap is bounded by a seal, which is joined to the housing, and at least one sealing tip arranged at the shroud opposite to the seal, for reducing the flow losses through the gap. At the downstream end region of the seal, another static sealing tip, which is joined to the housing, is arranged for influencing the flow through the gap and/or for influencing the flow downstream of the static sealing tip. The present invention further relates to an axial turbomachine with at least one low-pressure turbine stage, wherein the low-pressure turbine stage comprises a sealing system according to the invention.
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Patent Agency Ranking
公开(公告)号：US20170342849A1
公开(公告)日：2017-11-30
申请号：US15163079
申请日：2016-05-24
Inventor： Edward C. Rice , Daniel K. Vetters
CPC classification number: F01D11/005 , F01D9/04 , F01D11/14 , F01D17/105 , F01D25/12 , F01D25/24 , F05D2220/32 , F05D2240/11 , F05D2300/10 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine includes a blade track, a support assembly, and a seal system. The blade track is arranged around a central axis of the gas turbine engine to direct gasses through the gas turbine engine. The support assembly is arranged around the blade track to support the blade track relative to the central axis. The seal system is configured to block fluid communication between pressurized cavities formed in the support assembly.
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公开(公告)号：US09752450B2
公开(公告)日：2017-09-05
申请号：US14731155
申请日：2015-06-04
Applicant: United Technologies Corporation
Inventor： Brian Duguay , Timothy M. Davis
Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly may include a blade outer air seal segment, a linkage and an actuation device. The linkage may include a shaft and a head, where the shaft is connected to the blade outer air seal segment and extends radially outward to the head. The actuation device may include a sloped slide block located radially within and engaged with the head. The actuation device may be configured to laterally translate the sloped slide block and thereby radially move the blade outer air seal segment.
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8.发明申请公开(公告)号：US20170218787A1
公开(公告)日：2017-08-03
申请号：US15118510
申请日：2016-02-18
Applicant: Siemens Aktiengesellschaft
Inventor： Ching-Pang Lee , Kok-Mun Tham , Gm Salam Azad , Zhihong Gao , Erik Johnson , Eric Schroeder , Nicholas F. Martin, Jr.
CPC classification number: F01D11/122 , F01D5/02 , F01D5/12 , F01D11/14 , F01D25/24 , F01D25/246 , F05D2220/30 , F05D2230/10 , F05D2230/60 , F05D2240/24 , F05D2250/182 , F05D2250/183 , F05D2250/282 , F05D2250/294 , F05D2250/71 , Y10T29/49236
Abstract: Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with asymmetric forward and aft ridge surface area density. The forward ridges have greater surface area density than the aft ridges to compensate for greater ridge erosion in the forward zone during engine operation and reduce blade tip wear in the aft zone. Some abradable component embodiments increase forward zone ridge surface area density by incorporating wider ridges than those in the aft zone.
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公开(公告)号：US20160356170A1
公开(公告)日：2016-12-08
申请号：US14913785
申请日：2014-07-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy M. Davis , Brian Duguay
CPC classification number: F01D11/22 , F01D11/08 , F01D11/14 , F04D29/164 , F05D2220/32 , F05D2260/50 , F05D2270/60
Abstract: An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.
Abstract translation: 燃气涡轮发动机的主动间隙控制系统包括多个叶片外部空气密封组件和具有多个分级组的同步环。 每个分级组与多个叶片外部空气密封组件中的一个相关联。 燃气涡轮发动机的主动间隙控制系统包括具有多个分级组的同步环。 每个分级组包括多个刻度以确定相应的多个叶片外部空气密封组件中的每一个的相关的径向位置。
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10.发明申请TURBINE ENGINE TIP CLEARANCE CONTROL SYSTEM WITH LATER TRANSLATABLE SLIDE BLOCK 有权涡轮发动机提升间隙控制系统，具有可翻转的滑块公开(公告)号：US20160356168A1
公开(公告)日：2016-12-08
申请号：US14731155
申请日：2015-06-04
Applicant: United Technologies Corporation
Inventor： Brian Duguay , Timothy M. Davis
Abstract: An assembly is provided for a turbine engine with an axial centerline. This turbine engine assembly may include a blade outer air seal segment, a linkage and an actuation device. The linkage may include a shaft and a head, where the shaft is connected to the blade outer air seal segment and extends radially outward to the head. The actuation device may include a sloped slide block located radially within and engaged with the head. The actuation device may be configured to laterally translate the sloped slide block and thereby radially move the blade outer air seal segment.
Abstract translation: 为具有轴向中心线的涡轮发动机提供组件。 该涡轮发动机组件可以包括叶片外部空气密封段，连杆机构和致动装置。 连杆可以包括轴和头部，其中轴连接到叶片外部空气密封部分并且径向向外延伸到头部。 致动装置可以包括位于径向位于头部并与头部接合的倾斜滑块。 致动装置可以构造成横向平移倾斜的滑块，从而径向移动叶片外部空气密封段。
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