公开(公告)号：US20250012200A1

公开(公告)日：2025-01-09

申请号：US18219288

申请日：2023-07-07

Applicant: Pratt & Whitney Canada Corp.

Inventor： Guy Lefebvre ,  Remy Synnott

IPC: F01D11/14 ,  F01D25/24 ,  F01D25/28

Abstract: An outer structural case of a turbine casing assembly, including: a plurality of threaded adjustment openings located about a periphery of the outer structural case, the plurality of threaded adjustment openings extending completely through the periphery of the outer structural case; and a plurality of threaded securement openings arranged orthogonally with respect to the plurality of adjustment openings.

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

IPC: F01D11/14 ,  F01D5/12 ,  F01D11/22 ,  F01D11/24 ,  F02C7/20 ,  G06N5/00 ,  G06N20/00

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.

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

IPC: F01D5/18 ,  F01D5/14 ,  F01D11/12 ,  F01D5/28 ,  F01D1/12 ,  F01D11/14

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.

公开(公告)号：US11674407B2

公开(公告)日：2023-06-13

申请号：US17688094

申请日：2022-03-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Matthew R. Feulner

IPC: F01D21/00 ,  F01D5/12 ,  F01D9/04 ,  B64D27/10 ,  F01D11/20 ,  F01D11/14 ,  F02C9/00 ,  F02K3/06

CPC classification number: F01D11/20 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/307 ,  F05D2240/55 ,  F05D2260/80 ,  F05D2270/20 ,  F05D2270/42

Abstract: A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.

公开(公告)号：US20220074355A1

公开(公告)日：2022-03-10

申请号：US17528670

申请日：2021-11-17

Applicant: General Electric Company

Inventor： Robert William Lambert

IPC: F02C9/28 ,  F02C9/30 ,  F02C9/34 ,  F02C9/36 ,  F02C9/16 ,  F02C9/38 ,  F01D11/14

Abstract: A method for reducing an engine core speed is disclosed, which includes determining a condition of an engine during operation of the engine, and controlling an engine turbine clearance based on the condition of the engine so as to influence the engine core speed. An engine system comprising an engine core speed reducing system is also disclosed.

公开(公告)号：US11145960B2

公开(公告)日：2021-10-12

申请号：US16285896

申请日：2019-02-26

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： John Joseph Costello ,  Richard Joseph Skertic ,  Glen Steven Bishop ,  Geoffrey L. Gatton

IPC: H01Q1/28 ,  F01D17/02 ,  F01D11/14 ,  F01D25/00 ,  H01Q9/04 ,  H01Q21/06 ,  G01B7/14

Abstract: A patch antenna array sensor is provided. The patch antenna array sensor includes a ceramic matrix composite body in which a patch antenna array is embedded, wherein the patch antenna array sensor is configured to detect blade tip clearance or some other aspect of one or more blades in a gas turbine engine.

公开(公告)号：US11136922B2

公开(公告)日：2021-10-05

申请号：US16545003

申请日：2019-08-20

Applicant: ROLLS-ROYCE plc

Inventor： Craig W Bemment ,  Pascal Dunning

IPC: F02C9/28 ,  F01D11/14 ,  F01D13/00 ,  F01D25/24

Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A low pressure turbine temperature change is defined as: the ⁢ ⁢ first ⁢ ⁢ turbine ⁢ ⁢ entrance ⁢ ⁢ temperature the ⁢ ⁢ first ⁢ ⁢ turbine ⁢ ⁢ exit ⁢ ⁢ temperature . A fan tip temperature rise is defined as: the ⁢ ⁢ fan ⁢ ⁢ tip ⁢ ⁢ rotor ⁢ ⁢ exit ⁢ ⁢ temperature the ⁢ ⁢ fan ⁢ ⁢ rotor ⁢ ⁢ entry ⁢ ⁢ temperature . A turbine to fan tip temperature change ratio of: the ⁢ ⁢ low ⁢ ⁢ pressure ⁢ ⁢ turbine ⁢ ⁢ temperature ⁢ ⁢ change the ⁢ ⁢ fan ⁢ ⁢ tip ⁢ ⁢ temperature ⁢ ⁢ rise is in the range from 1.46 to 2.0.

公开(公告)号：US20210108533A1

公开(公告)日：2021-04-15

申请号：US17113235

申请日：2020-12-07

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Jun Shi ,  Li Li ,  Ted J. Freeman

IPC: F01D11/12 ,  F01D5/28 ,  F01D11/14

Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.

公开(公告)号：US10753222B2

公开(公告)日：2020-08-25

申请号：US15700264

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Christopher Carter Venable ,  Michael G. McCaffrey

IPC: F01D11/14 ,  F01D25/24 ,  F16J15/08 ,  F01D11/08 ,  F16J15/16 ,  F01D11/12

Abstract: A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.

公开(公告)号：US10711640B2

公开(公告)日：2020-07-14

申请号：US15484168

申请日：2017-04-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jonathan Ortiz ,  Lane Mikal Thornton ,  Matthew A. Devore

IPC: F01D17/16 ,  F01D25/12 ,  F02C3/04 ,  F01D17/10 ,  F01D9/04 ,  F01D11/14 ,  F02C6/08 ,  F01D5/08 ,  F01D9/06

Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor, the tapped air being passed through a heat exchanger. A vane section has vanes downstream of the combustor, but upstream of the first stage blade, and the air downstream of the heat exchanger passes radially inwardly of the combustor, along an axial length of the combustor, and then radially outwardly through a hollow chamber in the vanes, and then across the blade outer air seal, to cool the blade outer air seal.