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1. 发明公开

US20240360772A1 RADIALLY RETRACTABLE OUTER AIR SEAL 审中-公开
公开(公告)号：US20240360772A1
公开(公告)日：2024-10-31
申请号：US18308960
申请日：2023-04-28
申请人： Raytheon Technologies Corporation
发明人： Michael G. McCaffrey
IPC分类号： F01D11/22
CPC分类号： F01D11/22 , F05D2220/323 , F05D2240/11
摘要： A blade outer airseal assembly of a gas turbine engine includes a blade outer airseal (BOAS) segment, and a BOAS carrier positioned radially outboard of the BOAS segment relative to an engine central longitudinal axis. The BOAS segment is secured to the BOAS carrier, and an adjustment lever is operably connected to the BOAS carrier. Rotation of the adjustment lever about a pivot axis at a pivot urges movement of the BOAS segment in a radial direction.

2. 发明授权

US12110800B2 Clearance control of fan blades in a gas turbine engine 有权
公开(公告)号：US12110800B2
公开(公告)日：2024-10-08
申请号：US18321491
申请日：2023-05-22
申请人： General Electric Company
发明人： Venkata Jayateja Nedunuri , Abhijeet Yadav , Shawn P. Riley , Richa Awasthi , Nilesh Vilas Varote , Ravindra Shankar Ganiger , Anusrita Raychaudhuri
IPC分类号： F01D11/22
CPC分类号： F01D11/22 , F05D2220/323 , F05D2240/515
摘要： Clearance control systems with electromagnetic actuators are disclosed. An example electromagnetically-actuated clearance control system for a gas turbine engine comprises an electromagnetic coil coupled to a first end of a facesheet, the electromagnetic coil to generate a magnetic field in response to a connection of a power supply, a ferromagnetic sheet coupled to a second end of the facesheet, the ferromagnetic sheet drawn radially-inward toward the electromagnetic coil when the magnetic field is generated, a first end of the ferromagnetic sheet coupled to a first compression spring and a second end of the ferromagnetic sheet coupled to a second compression spring, the first and second compression springs to compress in response to the ferromagnetic sheet being drawn radially-inward.

3. 发明授权

US11821372B2 Hybrid electric engine with electric tip clearance mechanism 有权
公开(公告)号：US11821372B2
公开(公告)日：2023-11-21
申请号：US17837829
申请日：2022-06-10
申请人： RTX Corporation
发明人： Marc J. Muldoon , Arnab Roy , John R. Farris
IPC分类号： F02C7/32 , B64D27/16 , B64D27/24 , F02C6/14 , F01D11/22 , B64D27/02
CPC分类号： F02C7/32 , B64D27/16 , B64D27/24 , F01D11/22 , F02C6/14 , B64D2027/026 , F05D2220/323 , F05D2220/76
摘要： A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; at least one blade outer air seal positioned between an outer case of the high pressure turbine and a plurality of blades of the high pressure turbine; a clearance control system operably coupled to the at least one blade outer air seal, the clearance control system configured to vary a position of the at least one blade outer air seal with respect to the plurality of blades of the high pressure turbine; and a controller operably coupled to the electric motor and the clearance control system, wherein the controller is configured to operate the clearance control system based upon an operational state of the electric motor.

4. 发明公开

US20230340887A1 CLEARANCE CONTROL OF FAN BLADES IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20230340887A1
公开(公告)日：2023-10-26
申请号：US18321491
申请日：2023-05-22
申请人： General Electric Company
发明人： Venkata Jayateja Nedunuri , Abhijeet Yadav , Shawn P. Riley , Richa Awasthi , Nilesh Vilas Varote , Ravindra Shankar Ganiger , Anusrita Raychaudhuri
IPC分类号： F01D11/22
CPC分类号： F01D11/22 , F05D2240/515 , F05D2220/323
摘要： Clearance control systems with electromagnetic actuators are disclosed. An example electromagnetically-actuated clearance control system for a gas turbine engine comprises an electromagnetic coil coupled to a first end of a facesheet, the electromagnetic coil to generate a magnetic field in response to a connection of a power supply, a ferromagnetic sheet coupled to a second end of the facesheet, the ferromagnetic sheet drawn radially-inward toward the electromagnetic coil when the magnetic field is generated, a first end of the ferromagnetic sheet coupled to a first compression spring and a second end of the ferromagnetic sheet coupled to a second compression spring, the first and second compression springs to compress in response to the ferromagnetic sheet being drawn radially-inward.

5. 发明授权

US11746670B2 Impeller shroud assembly and method for operating same 有权
公开(公告)号：US11746670B2
公开(公告)日：2023-09-05
申请号：US17562306
申请日：2021-12-27
申请人： Pratt & Whitney Canada Corp.
发明人： David Menheere , Timothy Redford
IPC分类号： F01D11/00 , F01D11/22
CPC分类号： F01D11/22 , F01D11/001 , F05D2220/32 , F05D2240/11
摘要： An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.

6. 发明授权

US10619743B2 Splined honeycomb seals 有权
公开(公告)号：US10619743B2
公开(公告)日：2020-04-14
申请号：US15022838
申请日：2014-07-30
申请人： United Technologies Corporation
发明人： Timothy M. Davis , Jeffrey Vincent Anastas
IPC分类号： F16J15/34 , F02C7/28 , F01D11/08 , F01D11/12 , F01D11/22 , F01D11/00 , F16J15/44 , F01D9/02
CPC分类号： F16J15/3496 , F01D9/02 , F01D11/001 , F01D11/003 , F01D11/08 , F01D11/12 , F01D11/122 , F01D11/125 , F01D11/127 , F01D11/22 , F02C7/28 , F16J15/3464 , F16J15/444 , F05D2220/32 , F05D2240/55 , F05D2250/283
摘要： A seal assembly includes an annular carrier defining a radially inward face, and an opposed radially outward face defining a plurality of spline slots. The spline slots are configured and adapted to receive corresponding spline tabs to center the carrier in a surrounding structure. A honeycomb seal is mounted to the radially inward face of the carrier. The honeycomb seal is configured for sealing engagement with a knife-edge seal rotating relative to the honeycomb seal. The seal assembly has a relatively low coefficient of thermal expansion in comparison to the static component or the knife-edge seal. For example, a gas turbine engine can include a seal assembly as described above, wherein the carrier is mounted to a static component and a rotor mounted for rotation relative to the carrier, and wherein the rotor includes the knife edge seal component sealingly engaged to the honeycomb seal.

7. 发明授权

US09951643B2 Rapid response clearance control system with spring assist for gas turbine engine 有权
公开(公告)号：US09951643B2
公开(公告)日：2018-04-24
申请号：US14781168
申请日：2014-02-06
申请人： United Technologies Corporation
发明人： Brian Duguay
IPC分类号： F01D11/22 , F01D11/14 , F01D11/16 , F01D11/20 , F01D25/24 , F02C7/28
CPC分类号： F01D11/22 , F01D11/14 , F01D11/16 , F01D11/20 , F01D25/24 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2270/01
摘要： An active clearance control system of a gas turbine engine includes an actuation cylinder, a puller engaged with an air seal segment and damped with respect to the actuation cylinder, and a full-hoop thermal control ring that at least partially supports the air seal segment. The puller may move the air seal segment between an extended radially contracted BOAS position and a retracted radially expanded BOAS position.

8. 发明申请

US20180030846A1 GAS TURBINE ENGINE ACTIVE CLEARANCE CONTROL SYSTEM 审中-公开
公开(公告)号：US20180030846A1
公开(公告)日：2018-02-01
申请号：US15221061
申请日：2016-07-27
申请人： United Technologies Corporation
发明人： Michael G. McCaffrey
IPC分类号： F01D11/22 , F01D25/24
CPC分类号： F01D11/22 , F01D11/20 , F01D25/24 , F05D2260/97
摘要： A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.

9. 发明申请

US20170342994A1 IMPELLER SHROUD WITH THERMAL ACTUATOR FOR CLEARANCE CONTROL IN A CENTRIFUGAL COMPRESSOR 审中-公开
公开(公告)号：US20170342994A1
公开(公告)日：2017-11-30
申请号：US15165404
申请日：2016-05-26
申请人： Rolls-Royce Corporation
发明人： Michael Nesteroff , Jonathan Acker , Nate Cooper , Nathan Ottow
IPC分类号： F04D27/00 , F04D29/42 , F04D29/16 , F04D29/28
CPC分类号： F04D29/162 , F01D11/08 , F01D11/18 , F01D11/22 , F01D11/24 , F04D27/0246 , F04D29/4206 , F04D29/622 , F04D29/624
摘要： A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

10. 发明申请

US20160102565A1 TIP-CONTROLLED INTEGRALLY BLADED ROTOR FOR GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的TIP控制的整体式叶片转子
公开(公告)号：US20160102565A1
公开(公告)日：2016-04-14
申请号：US14973943
申请日：2015-12-18
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Alexandre Ayers
IPC分类号： F01D7/02 , F01D5/30 , F01D5/22 , F01D5/02
CPC分类号： F01D7/02 , F01D5/02 , F01D5/225 , F01D5/3069 , F01D5/34 , F01D11/16 , F01D11/22 , F05D2220/32 , F05D2240/20 , F05D2300/501
摘要： An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim. Each of the split hub members has a radially outer flex arm portion extending form the hub and a radially inner moment flange portion. At least one moment inducing element separately formed from the hub is mounted axially between the opposed split hub members and acts on the moment flange portions of the opposed split hub members to generate an inward bending moment on the flex arm portions of the opposed split hub members during rotation of the rotor, thereby deflecting the rim and the blades of the rotor radially inwardly.
摘要翻译：用于燃气涡轮发动机的整体叶片转子包括轮毂，从轮毂径向延伸并与其一体形成的多个叶片。所述轮毂具有叶片从其突出的边缘，以及一对轴向相对的分开的轮毂构件，其至少从轮缘径向向内延伸。每个分离轮毂构件具有从轮毂延伸的径向外部柔性臂部分和径向内侧力矩凸缘部分。从轮毂分开形成的至少一个力矩引导元件被轴向地安装在相对的分开的轮毂件之间并且作用在相对的分开轮毂件的力矩凸缘部分上，以在相对的分开轮毂构件的挠性臂部分上产生向内的弯曲力矩在转子旋转期间，从而使转子的轮缘和叶片径向向内偏转。

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