-
公开(公告)号:US10934888B2
公开(公告)日:2021-03-02
申请号:US16573242
申请日:2019-09-17
Applicant: United Technologies Corporation
Inventor: Thomas Bruce Avis , Francis Parnin , Michael Dreher , James S. Elder
Abstract: Disclosed is a lubricant supply system for a plurality of bearing dampers in a plurality of engine bearing compartments of a gas turbine engine, including a lubricant supply conduit, a first lubricant delivery conduit fluidly coupled to the supply conduit, the first delivery conduit including one or more lubricant delivery flow paths and delivering lubrication to engine components, a second lubricant delivery conduit fluidly coupled to the supply conduit, the second delivery conduit delivering lubricant to one or more of the plurality of bearing dampers, and an active oil flow management valve, selectively restricting lubricant flow in the first delivery conduit, increasing pressure in the second delivery conduit, based on an engine shaft rotational speed.
-
公开(公告)号:US20200011201A1
公开(公告)日:2020-01-09
申请号:US16573242
申请日:2019-09-17
Applicant: United Technologies Corporation
Inventor: Thomas Bruce Avis , Francis Parnin , Michael Dreher , James S. Elder
Abstract: Disclosed is a lubricant supply system for a plurality of bearing dampers in a plurality of engine bearing compartments of a gas turbine engine, including a lubricant supply conduit, a first lubricant delivery conduit fluidly coupled to the supply conduit, the first delivery conduit including one or more lubricant delivery flow paths and delivering lubrication to engine components, a second lubricant delivery conduit fluidly coupled to the supply conduit, the second delivery conduit delivering lubricant to one or more of the plurality of bearing dampers, and an active oil flow management valve, selectively restricting lubricant flow in the first delivery conduit, increasing pressure in the second delivery conduit, based on an engine shaft rotational speed.
-
公开(公告)号:US20180187629A1
公开(公告)日:2018-07-05
申请号:US15906201
申请日:2018-02-27
Applicant: United Technologies Corporation
Inventor: Lubomir A. Ribarov , James S. Elder
CPC classification number: F02K1/48 , B64D33/04 , B64D2027/005 , F02K1/386 , F02K3/062 , F05D2240/127 , F05D2260/2212 , Y02T50/672
Abstract: An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.
-
公开(公告)号:US10458278B2
公开(公告)日:2019-10-29
申请号:US15344195
申请日:2016-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Thomas Bruce Avis , Francis Parnin , Michael Dreher , James S. Elder
Abstract: Disclosed is a lubricant supply system for a plurality of bearing dampers in a plurality of engine bearing compartments of a gas turbine engine, including a lubricant supply conduit, a first lubricant delivery conduit fluidly coupled to the supply conduit, the first delivery conduit including one or more lubricant delivery flow paths and delivering lubrication to engine components, a second lubricant delivery conduit fluidly coupled to the supply conduit, the second delivery conduit delivering lubricant to one or more of the plurality of bearing dampers, and an active oil flow management valve, selectively restricting lubricant flow in the first delivery conduit, increasing pressure in the second delivery conduit, based on an engine shaft rotational speed.
-
公开(公告)号:US10364694B2
公开(公告)日:2019-07-30
申请号:US15105358
申请日:2014-12-01
Applicant: United Technologies Corporation
Inventor: Lubomir A. Ribarov , Leo J. Veilleux, Jr. , James S. Elder
Abstract: A turbomachine blade clearance system can include an actuator having an anchor portion for fixation to an interior surface of a turbomachine housing and an actuating portion for actuating movement relative to the anchor portion. A turbomachine blade seal can be operatively connected to the actuating portion of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade.
-
公开(公告)号:US09970386B2
公开(公告)日:2018-05-15
申请号:US14298331
申请日:2014-06-06
Applicant: United Technologies Corporation
Inventor: Lubomir A. Ribarov , James S. Elder
CPC classification number: F02K1/48 , B64D33/04 , B64D2027/005 , F02K1/386 , F02K3/062 , F05D2240/127 , F05D2260/2212 , Y02T50/672
Abstract: An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.
-
公开(公告)号:US20180128124A1
公开(公告)日:2018-05-10
申请号:US15344195
申请日:2016-11-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor: Thomas Bruce Avis , Francis Parnin , Michael Dreher , James S. Elder
CPC classification number: F01D25/18 , F01D5/02 , F01D19/00 , F01D25/16 , F01D25/164 , F01D25/166 , F01D25/20 , F05D2220/32 , F05D2260/96 , F05D2270/01 , F05D2270/304 , F16C27/045 , F16C2360/23
Abstract: Disclosed is a lubricant supply system for a plurality of bearing dampers in a plurality of engine bearing compartments of a gas turbine engine, including a lubricant supply conduit, a first lubricant delivery conduit fluidly coupled to the supply conduit, the first delivery conduit including one or more lubricant delivery flow paths and delivering lubrication to engine components, a second lubricant delivery conduit fluidly coupled to the supply conduit, the second delivery conduit delivering lubricant to one or more of the plurality of bearing dampers, and an active oil flow management valve, selectively restricting lubricant flow in the first delivery conduit, increasing pressure in the second delivery conduit, based on an engine shaft rotational speed.
-
公开(公告)号:US20150167549A1
公开(公告)日:2015-06-18
申请号:US14298331
申请日:2014-06-06
Applicant: United Technologies Corporation
Inventor: Lubomir A. Ribarov , James S. Elder
CPC classification number: F02K1/48 , B64D33/04 , B64D2027/005 , F02K1/386 , F02K3/062 , F05D2240/127 , F05D2260/2212 , Y02T50/672
Abstract: An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.
Abstract translation: 用于涡轮发动机的排气喷嘴包括围绕排气喷嘴周向布置的多个花式波纹。 每个雏形波纹具有径向内部基部和从基部径向向外突出的多个凸起。
-
-
-
-
-
-
-