专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20210222589A1 MECHANICAL ARRANGEMENT FOR JOINING ENGINE COMPONENTS 有权
公开(公告)号：US20210222589A1
公开(公告)日：2021-07-22
申请号：US16744531
申请日：2020-01-16
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Guy LEFEBVRE , Francois DOYON , Remy SYNNOTT
IPC分类号： F01D25/24
摘要： A turbine exhaust case assembly has an exhaust case and a bearing housing mounted in the exhaust case. A plurality of fasteners secures the bearing housing to the exhaust case. A spacer is mounted between the fasteners and one of the bearing housing and the exhaust case. The fasteners are welded to the spacer, thereby locking the fasteners against rotation.

2. 发明申请

US20200308984A1 BEARING HOUSING 审中-公开
公开(公告)号：US20200308984A1
公开(公告)日：2020-10-01
申请号：US16369688
申请日：2019-03-29
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Guy LEFEBVRE , Remy SYNNOTT , François DOYON
IPC分类号： F01D25/16 , F01D21/04 , F16C33/40
摘要： There is disclosed a bearing assembly for a gas turbine engine including at least two bearings axially spaced from one another relative to a central axis, and a squirrel cage secured to a casing of the gas turbine engine. The squirrel cage supports respective bearing loads of the at least two bearings. The squirrel cage has a frangible section between the bearings configured to preferentially fail upon application of a load greater than a preselected threshold bearing load.

3. 发明申请

US20170096901A1 SHROUDED BLADE FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170096901A1
公开(公告)日：2017-04-06
申请号：US15380212
申请日：2016-12-15
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Ghislain PLANTE , Remy SYNNOTT , Jaideep GAHLAWAT
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05D2220/32 , F05D2240/307
摘要： A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face. Each of the fins has an end disposed toward the pressure side and another end disposed toward the suction side. The ribs extend from and connecting the upstream fin to the downstream fin at locations other than the ends of the upstream and downstream fins. The ribs converge toward the downstream fin at an angle of between about 10 and about 45 degrees. A shroud for a blade is also presented.

4. 发明申请

US20170044919A1 TURBINE SHROUD SEGMENT SEALING 有权
标题翻译：涡轮SHROUD部分密封
公开(公告)号：US20170044919A1
公开(公告)日：2017-02-16
申请号：US15338840
申请日：2016-10-31
申请人： Pratt & Whitney Canada Corp.
发明人： John PIETROBON , Remy SYNNOTT
IPC分类号： F01D11/08 , F01D25/12 , F01D9/04
CPC分类号： F01D11/08 , F01D9/041 , F01D11/24 , F01D25/12 , F05D2220/32 , F05D2240/30 , F05D2250/141 , F05D2250/191 , F05D2250/231 , F05D2260/201
摘要： An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments. The blade shroud segments integrally extend downstream from the vane shroud segments and each pair of circumferentially adjacent blade shroud segments defines an inter-segment gap. At least one slot extends axially from a location downstream of the vane shroud segments to an aft end of the blade shroud segment. The inter-segment gaps and slots are sealed by a sealing band mounted around the full circumference of the integrated shroud structure.
摘要翻译：集成的护罩结构围绕定子叶片的圆周阵列和燃气涡轮发动机的转子叶片的圆周阵列。护罩结构包括多个叶片护罩段和多个叶片护罩段。叶片护罩段从叶片护罩段一体地延伸到下游，并且每对周向相邻的叶片护罩段限定跨段间隙。至少一个狭槽从叶片护罩区段下游的位置轴向延伸到叶片护罩区段的后端。跨段间隙和槽由围绕整体护罩结构的整个圆周安装的密封带密封。

5. 发明申请

US20220112819A1 GAS TURBINE ENGINE BEARING HOUSING 有权
公开(公告)号：US20220112819A1
公开(公告)日：2022-04-14
申请号：US17065914
申请日：2020-10-08
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Guy LEFEBVRE , Remy SYNNOTT
IPC分类号： F01D25/16
摘要： A gas turbine engine has a bearing housing mounted to structure linked to the engine mounting pads. The bearing housing has bearing housing flanges with bearing housing flange openings aligned with attachment flange openings of the structure. Some of the bearing housing flange openings are slots. A first group of fasteners extends through one of the attachment flange openings and through one of the bearing housing flange openings. A second group of fasteners extends through one of the attachment flange openings and through one of the slots. The first group of fasteners are sacrificial fasteners configured to fracture in response to a load on the bearing housing exceeding a fracture load. The bearing housing is displaceable relative to the structure after fracture of the sacrificial fasteners via the second group of the fasteners moving within and relative to respective ones of the slots.

6. 发明申请

US20200217214A1 RIM SEAL 审中-公开
公开(公告)号：US20200217214A1
公开(公告)日：2020-07-09
申请号：US16825031
申请日：2020-03-20
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Remy SYNNOTT , John PIETROBON , Franco DI PAOLA , Lorenzo SANZARI
IPC分类号： F01D11/00 , F01D11/02
摘要： A rim seal between a stator and a rotor in a gas turbine engine is described. The seal includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

7. 发明申请

US20190178101A1 TURBINE SHROUD COOLING 审中-公开
公开(公告)号：US20190178101A1
公开(公告)日：2019-06-13
申请号：US15840088
申请日：2017-12-13
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Remy SYNNOTT , Mohammed ENNACER , Chris PATER , Denis BLOUIN , Kapila JAIN , Farough MOHAMMADI
IPC分类号： F01D25/12 , F01D9/02 , F01D17/10
摘要： A turbine shroud segment has a body having a radially outer surface and a radially inner surface extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. A first serpentine channel is disposed axially along the first lateral edge. A second serpentine channel is disposed axially along the second lateral edge. The first and second serpentine channels each define a tortuous path including axially extending passages between a front inlet proximate the leading edge and a rear outlet at the trailing edge of the body.

8. 发明申请

US20180347399A1 TURBINE SHROUD WITH INTEGRATED HEAT SHIELD 审中-公开
公开(公告)号：US20180347399A1
公开(公告)日：2018-12-06
申请号：US15611018
申请日：2017-06-01
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Remy SYNNOTT , John PIETROBON , Franco DI PAOLA
IPC分类号： F01D25/14 , F01D9/04 , F01D25/12 , F01D25/24 , F01D5/02 , F01D11/00
摘要： A turbine shroud segment forms part of a circumferentially segmented shroud assembly surrounding a circumferential array of turbine blades of a gas turbine engine. The turbine shroud segment has a platform extending axially from an upstream end portion to a downstream end portion relative to a flow of gas through the gas turbine engine. A heat shield extension projects radially inwardly and in an upstream direction from the upstream end portion of the platform.

9. 发明申请

US20160003102A1 AXIAL RETAINING RING FOR TURBINE VANES 有权
标题翻译：涡轮叶片轴向保持环
公开(公告)号：US20160003102A1
公开(公告)日：2016-01-07
申请号：US14324107
申请日：2014-07-04
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Remy SYNNOTT
IPC分类号： F01D25/24 , F01D9/04
CPC分类号： F01D25/246 , F01D9/041 , F01D11/005 , F05D2230/237 , F05D2230/64 , F05D2260/30
摘要： A gas turbine engine is described which has first and second turbine vane assemblies with multiple turbine vanes within respective first and second circumferential outer shrouds. The first outer shroud has a first radially extending flange and the second outer shroud has a second radially extending flange. The radially extending first and second flanges each defining an upstream mating surface and a downstream mating surface relative to a direction of air flow through the engine in use. The downstream mating surface of the first flange mates with the upstream mating surface of the second flange. An axial retaining ring axially retains together the first and second flanges, and has an annular body extending between an upstream portion of the body abutted against the upstream mating surface of the first flange and a downstream portion of the body abutted against the downstream mating surface of the second flange.
摘要翻译：描述了一种燃气涡轮发动机，其具有在相应的第一和第二周向外护罩内具有多个涡轮叶片的第一和第二涡轮叶片组件。第一外护罩具有第一径向延伸凸缘，第二外护罩具有第二径向延伸的凸缘。径向延伸的第一和第二凸缘各自限定相对于在使用中通过发动机的气流的方向的上游配合表面和下游配合表面。第一凸缘的下游配合表面与第二凸缘的上游配合表面配合。轴向保持环将第一和第二凸缘轴向地保持在一起，并且具有环形体，其在与第一凸缘的上游配合表面邻接的主体的上游部分与抵靠下游配合表面的下游配合表面之间延伸的主体第二个法兰。

10. 发明申请

US20220260001A1 INSTRUMENTED TURBINE EXHAUST DUCT 有权
公开(公告)号：US20220260001A1
公开(公告)日：2022-08-18
申请号：US17178708
申请日：2021-02-18
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Guy LEFEBVRE , Remy SYNNOTT , Michael PAOLUCCI
IPC分类号： F01N13/00 , F02C3/00
摘要： A gas turbine engine exhaust system comprises an instrumented exhaust duct including a set of exhaust temperature probes installed at the exhaust end of the duct in an air space between the engine outer case and a surrounding engine nacelle. A shield is removably installed at the end of the exhaust duct to protect the probes and associated wiring in the air space.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式