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公开(公告)号：US5605437A
公开(公告)日：1997-02-25
申请号：US253985
申请日：1994-06-03
Applicant: Pierre Meylan
Inventor： Pierre Meylan
CPC classification number: F04D29/584 , F01D11/24
Abstract: In a compressor (1), in particular for a gas turbine, which compressor includes a rotor (3), which is rotatably supported about a compressor center line and possesses at its periphery a plurality of rotor blades (5a-d), and a compressor casing (2), which concentrically surrounds the rotor (3), a radial clearance being provided between the outer ends of the rotor blades (5a-d) and the inner wall of the compressor casing (2), the possibility of a warm start without sacrificing efficiency is achieved by configuring the compressor casing (2) so that it can be heated in order to reduce the fluctuations in the radial clearance and by connecting it to a separate heating appliance (22, 25, 27), which is independent of the operation of the compressor and by means of which the compressor casing can be heated in the case of a warm start.
Abstract translation: 在压缩机（1）中，特别是一种用于燃气轮机的压缩机，该压缩机包括转子（3），转子（3）围绕压缩机中心线可旋转地支撑并且在其周围具有多个转子叶片（5a-d） 压缩机壳体（2）同心地围绕转子（3），在转子叶片（5a-d）的外端和压缩机壳体（2）的内壁之间设置有径向间隙，温度可能 开始而不牺牲效率是通过配置压缩机壳体（2）来实现的，使得其可以被加热，以便减小径向间隙的波动并且将其连接到独立的加热装置（22,25,27），其独立 压缩机的操作，并且在热启动的情况下，压缩机壳体可以被加热。
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公开(公告)号：US12209501B1
公开(公告)日：2025-01-28
申请号：US18235394
申请日：2023-08-18
Applicant: RTX Corporation
Inventor： Graham R. Philbrick , Gary Collopy , John P. Virtue, Jr.
Abstract: An operating method is provided during which a command is received to decrease thrust generated by a propulsor rotor from a first thrust level to a second thrust level. The propulsor rotor is operatively coupled to an engine core and an electric machine. The engine core includes a flowpath, a compressor section, a combustor section and a turbine section. The engine core is operated in a transient state to decrease total power of the engine core from a first power level to a second power level in response to the command. The electric machine is operated as a generator to reduce power output from the engine core to the propulsor rotor while the engine core is operating in the transient state. A clearance control system for the engine core is operated based on the operation of the electric machine.
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公开(公告)号：US20250027424A1
公开(公告)日：2025-01-23
申请号：US18235394
申请日：2023-08-18
Applicant: RTX Corporation
Inventor： Graham R. Philbrick , Gary Collopy , John P. Virtue, Jr.
Abstract: An operating method is provided during which a command is received to decrease thrust generated by a propulsor rotor from a first thrust level to a second thrust level. The propulsor rotor is operatively coupled to an engine core and an electric machine. The engine core includes a flowpath, a compressor section, a combustor section and a turbine section. The engine core is operated in a transient state to decrease total power of the engine core from a first power level to a second power level in response to the command. The electric machine is operated as a generator to reduce power output from the engine core to the propulsor rotor while the engine core is operating in the transient state. A clearance control system for the engine core is operated based on the operation of the electric machine.
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公开(公告)号：US12049828B2
公开(公告)日：2024-07-30
申请号：US17900513
申请日：2022-08-31
Applicant: General Electric Company
Inventor： Anusrita Raychaudhuri , Ravindra Shankar Ganiger , Bhanu Battu , Richa Awasthi , Nilesh Varote , Vidyashankar Buravalla
IPC: F01D11/20 , F01D11/02 , F01D11/08 , F01D11/14 , F01D11/22 , F01D11/24 , F02C7/042 , F02C7/057 , F04D29/52
CPC classification number: F01D11/20 , F01D11/025 , F01D11/22 , F01D11/24 , F02C7/042 , F04D29/526 , F01D11/08 , F01D11/14 , F02C7/057 , F05D2220/32 , F05D2240/11 , F05D2300/505
Abstract: Variable sleeve clearance control systems for gas turbine engines are disclosed. An example variable sleeve clearance control system for a gas turbine engine includes a sleeve comprising a first end and a second end, the first end of the sleeve coupled to a first spring that biases the sleeve inward, and the second end of the sleeve coupled to a second spring that biases the sleeve outward, a proximity sensor to measure a clearance width, and a controller for each of the first and second springs, the controller to obtain the measured clearance width from the proximity sensor and determine a response of the first and second springs.
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115.发明授权公开(公告)号：US11885228B2
公开(公告)日：2024-01-30
申请号：US17667793
申请日：2022-02-09
Applicant: General Electric Company
Inventor： Subramanya Shankar , Marc Christopfel , Brian G. Quinn , Omar A. Ramirez , Sean M. O′Melia
CPC classification number: F01D21/003 , F01D11/14 , F05D2260/30 , F05D2260/80 , F05D2270/305 , F05D2270/804 , G01B11/14 , G01C9/02
Abstract: A system and method for inspecting fan blade clearances in a fan stator module are presented. The method includes rotating a fan rotor assembly that includes an attached bracket situated between adjacent fan blades connected to the fan rotor assembly. The bracket includes a laser module and an inclinometer configured to measure a circumferential position of the laser module. The method further includes projecting a laser beam from the laser module to the fan case to determine a distance measurement between the laser module and the fan case at multiple circumferential points around the fan case. The distance measurement and circumferential position data is processed by a computing device to determine a clearance distance between a fan blade and the fan case.
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Patent Agency Ranking
公开(公告)号：US11788424B2
公开(公告)日：2023-10-17
申请号：US17595755
申请日：2020-05-20
Applicant: SAFRAN HELICOPTER ENGINES
Inventor： Thomas Louis Guedot , Fabien Hourquet , Eloi Duflos , Patrice Postel
CPC classification number: F01D11/12 , F01D11/08 , F01D11/14 , F02C7/28 , F05D2220/323 , F05D2230/31 , F05D2240/55
Abstract: Sealing ring for a wheel of an aircraft turbomachine turbine, the ring having an annular body extending around an axis of revolution and including an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further including an annular wall extending around the annular body and at a radial distance from the body, the annular wall including openings through which cooling air flows by impact on the outer surface, wherein the body and the wall are integrally formed.
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公开(公告)号：US20230057881A1
公开(公告)日：2023-02-23
申请号：US17978315
申请日：2022-11-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： San Quach , Robert A. White, III , Tyler G. Vincent
Abstract: A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.
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公开(公告)号：US20230029124A1
公开(公告)日：2023-01-26
申请号：US17866512
申请日：2022-07-17
Applicant: MTU Aero Engines AG
Inventor： Kacper PALKUS , Roman SCHMIERER , Hermann KLINGELS
Abstract: A turbine module (2) for a turbomachine (1). The turbine module (2) includes a main channel (26) to guide a main flow (36) through the turbine module (2), a rotor blade (21) and a stator vane (22), the stator vane (22) including a stator airfoil (22) and a platform (23), with the stator airfoil (22) arranged downstream of the rotor blade (21) in the main channel (26), and a cavity (30) including an inlet (31) for injecting a part (36.2) of the main flow (36) into the cavity (30), an outlet (32) for a reinjection of the part (36.2) of the main flow (36) from the cavity (30) into the main channel (26), wherein the cavity (30) is arranged at an axial position of the stator vane (20) and is radially offset from the stator airfoil (22).
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公开(公告)号：US11530653B2
公开(公告)日：2022-12-20
申请号：US17528670
申请日：2021-11-17
Applicant: General Electric Company
Inventor： Robert William Lambert
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.
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120.发明申请公开(公告)号：US20220195882A1
公开(公告)日：2022-06-23
申请号：US17126301
申请日：2020-12-18
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
IPC: F01D11/14 , F16J15/3288
Abstract: Sealing arrangements and rotor assemblies are provided. A sealing arrangement includes a stationary component, a rotating component spaced apart from the stationary component. A clearance is defined between the stationary component and the rotating component. The sealing arrangement further includes a plurality of magnets embedded within the rotating component. The sealing arrangement further includes a brush seal having a frame and a plurality of magnetically responsive filaments. The plurality of magnetically responsive filaments each extending from the frame to a free end. The plurality of magnetically responsive filaments are attracted to the rotating component by the plurality of magnets. The plurality of magnetically responsive filaments at least partially covering the clearance, such that a flow of fluid across the clearance is restricted.
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