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公开(公告)号：US20180334962A1
公开(公告)日：2018-11-22
申请号：US15601499
申请日：2017-05-22
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , William K. Ackermann , Matthew P. Forcier
IPC: F02C7/18
CPC classification number: F02C7/18 , F01P2023/00 , F01P2025/04 , F01P2025/08 , F02C6/08 , F02C7/057 , F02C9/18 , F05D2270/301 , F05D2270/303 , F16K31/00
Abstract: A bleed air cooling system for a gas turbine engine includes a bleed port located at an axial location of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. A modulating valve is located at the bleed duct and is movable between a fully open position and a fully closed position to regulate the bleed airflow through the bleed duct based on one or more operating conditions of the gas turbine engine.
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公开(公告)号：US09938840B2
公开(公告)日：2018-04-10
申请号：US14618035
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
CPC classification number: F01D9/041 , F01D5/02 , F01D11/001 , F01D11/02 , F01D25/24 , F04D29/164 , F04D29/542 , F05D2220/32 , F05D2240/12 , F05D2240/80 , F05D2250/16 , F05D2250/712
Abstract: An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.
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公开(公告)号：US20160369816A1
公开(公告)日：2016-12-22
申请号：US15252331
申请日：2016-08-31
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Matthew P. Forcier , Brian J. Schuler
CPC classification number: F04D29/324 , F01D5/082 , F01D5/146 , F01D11/001 , F04D29/584 , F05D2240/126 , F05D2240/129 , Y02T50/673 , Y02T50/676
Abstract: A gas turbine engine has a compressor section with a downstream most blade stage and a downstream vane row positioned downstream of the downstream most blade stage. The downstream most blade stage includes a plurality of blade pairs with the majority of blade pairs being circumferentially spaced apart from others of the blade pairs, each the blade pair being operatively connected to a rotor disk disposed radially inward from the blade pairs with each blade pair including a forward blade and an aft blade. The aft blades are configured to further condition airflow with respect to the forward blade. A tangential onboard injector (TOBI) is positioned radially inwardly of the downstream vane row.
Abstract translation: 燃气涡轮发动机具有压缩机部分，其具有下游最多的叶片级和位于下游最大叶片级的下游叶片排。 下游的大多数叶片级包括多个叶片对，其中大多数叶片对与叶片对中的其它叶片对沿周向间隔开，每个叶片对可操作地连接到从每个叶片对的叶片对径向向内设置的转子盘 包括前刀片和后刀片。 后叶片构造成进一步调节相对于前叶片的气流。 切向机载喷油器（TOBI）位于下游叶片排的径向内侧。
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公开(公告)号：US20160076379A1
公开(公告)日：2016-03-17
申请号：US14851912
申请日：2015-09-11
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Paul J. Hiester
IPC: F01D5/08
CPC classification number: F01D5/081 , F02C6/08 , F02C9/18 , F04D29/321 , F04D29/584 , F05D2260/209
Abstract: A turbomachine includes an aft stage including a rotor disk having a rotor disk bore hole and a rotor disk rim, and a valve disposed within the turbomachine and in fluid communication with the rotor disk bore hole. The valve is in selective fluid communication with a first pressure source such that, in an first position, the valve allows fluid to flow from the first pressure source through the rotor disk bore hole and radially outward along the aft rotor disk toward the aft rotor disk rim.
Abstract translation: 涡轮机包括后台，其包括具有转子盘孔和转子盘轮缘的转子盘，以及设置在涡轮机内并与转子盘钻孔流体连通的阀。 阀与第一压力源选择性地流体连通，使得在第一位置，阀允许流体从第一压力源流过转子盘钻孔并且沿着后转子盘朝向后转子盘径向向外流动 轮缘。
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公开(公告)号：US11739697B2
公开(公告)日：2023-08-29
申请号：US15601524
申请日：2017-05-22
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Matthew P. Forcier , William K. Ackermann
CPC classification number: F02C9/18 , F01D9/065 , F01D17/02 , F02C7/18 , F05D2220/32 , F05D2260/20 , F05D2270/30
Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed ports located at one or more axial locations of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. One or more safety sensors are configured to sense operational characteristics of the gas turbine engine, and a controller is operably connected to the one or more safety sensors and configured to evaluate the sensed operational characteristics for anomalies in operation of the bleed air cooling system.
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Patent Agency Ranking
公开(公告)号：US10161250B2
公开(公告)日：2018-12-25
申请号：US14618041
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
Abstract: A rotor includes a rotor hub that is rotatable about an axis. The rotor hub includes a bore portion and a rim. An arm extends axially and radially inwardly from the rim. The arm has a radially inner side, a radially outer side, and a protruding ramp on the radially outer side.
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公开(公告)号：US10107206B2
公开(公告)日：2018-10-23
申请号：US14878018
申请日：2015-10-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew P. Forcier , Paul J. Hiester , Andrew J. Murphy
Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A high pressure air tap includes a lower temperature tapped path and a higher temperature tapped path and a valve for selectively delivering one of the lower temperature tapped path and the higher temperature tapped path into the bore of the disc. The valve is operable to selectively block flow of either of the lower pressure and higher pressure tapped paths to the bore of the disc, with the disc including holes to allow air from compressor chambers to communicate with the bore of the disc. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.
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公开(公告)号：US09995222B2
公开(公告)日：2018-06-12
申请号：US14754325
申请日：2015-06-29
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Matthew P. Forcier
CPC classification number: F02C9/18 , F01D5/08 , F01D5/082 , F01D9/065 , F01D11/24 , F01D25/10 , F02C3/34 , F02C7/125 , F05D2260/20 , F05D2260/941 , Y02T50/676
Abstract: A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.
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公开(公告)号：US20180087398A1
公开(公告)日：2018-03-29
申请号：US15278612
申请日：2016-09-28
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Joseph B. Staubach
CPC classification number: F01D25/12 , F01D5/08 , F02C7/08 , F05D2220/36 , F05D2260/208 , F28D15/02 , F28D15/046 , F28D2021/0026 , F28F21/02 , Y02T50/671 , Y02T50/676
Abstract: A graphene heat pipe for a gas turbine engine includes a body of graphene. The body has a hot side to accept heat from the gas turbine engine, a cold side to reject heat from the body, and an adiabatic portion to flow heat within the body between the hot side and the cold side.
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公开(公告)号：US20160230575A1
公开(公告)日：2016-08-11
申请号：US14618035
申请日：2015-02-10
Applicant: United Technologies Corporation
Inventor： Matthew P. Forcier , Brian J. Schuler , Jordan T. Wall
CPC classification number: F01D9/041 , F01D5/02 , F01D11/001 , F01D11/02 , F01D25/24 , F04D29/164 , F04D29/542 , F05D2220/32 , F05D2240/12 , F05D2240/80 , F05D2250/16 , F05D2250/712
Abstract: An airfoil includes a stator vane that has a platform with a first radial side and a second radial side, and a platform axial leading end and a platform axial trailing end. An airfoil portion extends radially outwardly from the first side. The platform axial trailing end includes a rear axial face that extends from the first radial side and a radially sloped face that extends from the rear axial face to the second radial side.
Abstract translation: 翼型件包括具有第一径向侧和第二径向侧的平台的定子叶片，以及平台轴向前端和平台轴向后端。 翼型部分从第一侧径向向外延伸。 平台轴向后端包括从第一径向侧延伸的后轴向面和从后轴向面延伸到第二径向侧的径向倾斜面。
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