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公开(公告)号：US20160138399A1
公开(公告)日：2016-05-19
申请号：US14929771
申请日：2015-11-02
Applicant: United Technologies Corporation
Inventor： Anthony R. Bifulco , Damon K. Brown , Nicholas Aiello
CPC classification number: F01D5/02 , F01D5/06 , F01D5/34 , F02C3/04 , F05D2220/32 , F05D2230/31 , F05D2230/60 , F05D2240/20 , F05D2240/35 , F05D2300/224 , F05D2300/48 , F05D2300/603 , F05D2300/6032 , F05D2300/614 , Y02T50/672
Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.
Abstract translation: 公开了一种用于燃气涡轮发动机的结构增强转子盘。 转子盘可以包括主体，其包括构造成支撑翼型件（其可以与翼型件分离或一体的）的边缘，设置在轮辋径向内侧的轴向延伸的孔以及连接轮辋和钻孔的径向延伸的腹板 。 孔可以包括轴向外边缘和在外边缘和腹板之间轴向形成的至少一个周向延伸的环形凹部。 转子盘还可以包括保持在环形凹部中的环形圈，并且环形圈可以由与转子盘的主体不同的材料形成，以便增加转子盘的自维持半径。
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公开(公告)号：US20150218955A1
公开(公告)日：2015-08-06
申请号：US14422368
申请日：2013-03-14
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E. Bintz , Peter T. Schutte , Brian J. Schuler , Anthony R. Bifulco
CPC classification number: F01D5/288 , F01D5/14 , F01D5/141 , F01D5/20 , F01D9/04 , F01D11/122 , F05D2240/125 , F05D2240/307 , Y02T50/673
Abstract: A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.
Abstract translation: 悬臂式翼型件尤其包括具有主体部分和尖端的翼型件，主体部分沿相对于径向成角度的第一方向延伸，翼型件的尖端相对于第二方向沿第二方向径向地成角度 身体部位。
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公开(公告)号：US20140144151A1
公开(公告)日：2014-05-29
申请号：US13689305
申请日：2012-11-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco
CPC classification number: F02C9/00 , B08B3/02 , B08B9/00 , F01D25/002 , F04D29/705 , Y10T29/49233
Abstract: A gas turbine engine includes: a compressor; a combustor downstream of the compressor along a gaspath; a turbine downstream of the combustor along the gaspath; a plurality of wash nozzles having outlets along the gaspath; and at least one inlet fitting coupled to the wash nozzles to bound a wash flowpath from an inlet port of the at least one inlet fitting to said outlets of said nozzles. The plurality of stages include: a stage upstream of blades of one compressor section; and another stage between said blades of one compressor section and blades of another compressor section.
Abstract translation: 燃气涡轮发动机包括：压缩机; 压缩机沿燃气路径下游的燃烧器; 沿燃气路径的燃烧器下游的涡轮; 多个具有沿气道的出口的洗涤喷嘴; 以及至少一个入口配件，其耦合到所述洗涤喷嘴以将洗涤流路从所述至少一个入口配件的入口端口连接到所述喷嘴的所述出口。 多个阶段包括：一个压缩机部分的叶片上游的阶段; 以及一个压缩机部分的所述叶片和另一个压缩机部分的叶片之间的另一个台阶。
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公开(公告)号：US10358934B2
公开(公告)日：2019-07-23
申请号：US15095640
申请日：2016-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco
Abstract: According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section comprising a plurality of stages of variable vanes, and also includes first and second synchronizing rings (sync-rings). Movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes. At least one sensor is configured to measure a condition of the gas turbine engine. A controller is configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor.
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公开(公告)号：US20190195082A1
公开(公告)日：2019-06-27
申请号：US15853486
申请日：2017-12-22
Applicant: United Technologies Corporation
Inventor： Anthony R. Bifulco , Jason B. Hickman , Alonso Meza , Andrew R. Carlson
IPC: F01D17/10
CPC classification number: F01D17/105 , F02C6/08 , F02C9/28 , F02K3/06 , F02K3/075 , F04D27/0207 , F05D2220/32 , F05D2250/41 , F05D2270/101 , F16K3/02
Abstract: A bleed valve system for a gas turbine engine that includes a retaining ring and a metering ring. The retaining ring abuts an end of a bleed air duct and defines a plurality of retaining ring apertures. The metering ring that is at least partially disposed within the bleed air duct and abuts the retaining ring, the metering ring defining a plurality of metering ring apertures, the metering ring being rotatable relative to the retaining ring to selectively facilitate a fluid flow through the bleed air duct.
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Patent Agency Ranking
公开(公告)号：US10330009B2
公开(公告)日：2019-06-25
申请号：US15406353
申请日：2017-01-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco
Abstract: A lock for securing a nosecone having first threading to an inlet case having second threading and for use with a gas turbine engine having an axis includes an annular ring designed to be positioned about the first threading. The lock also includes a tab extending radially from the annular ring, and having a ramped circumferential end and an angled circumferential end such that the ramped circumferential end passes over a detent of the inlet case in response to the nosecone being fastened to the inlet case and the angled circumferential end engages with the detent to resist unfastening of the nosecone from the inlet case.
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公开(公告)号：US10253694B2
公开(公告)日：2019-04-09
申请号：US14635366
申请日：2015-03-02
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Anthony R. Bifulco
Abstract: A gas turbine engine section includes a plurality of spaced rotor stages, with a static guide vane intermediate the spaced rotor stages. The static guide vane provides swirl into air passing toward a downstream one of the spaced rotor stages, and an outer housing surrounding the spaced rotor stages. A diverter diverts a portion of air radially outwardly through the outer housing, and across at least one heat exchanger. The diverted air passes back into a duct radially inwardly through the outer housing, and is exhausted toward the downstream one of the spaced rotor stages.
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公开(公告)号：US20180202359A1
公开(公告)日：2018-07-19
申请号：US15406353
申请日：2017-01-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco
CPC classification number: F02C7/04 , B64C11/14 , F01D5/066 , F01D25/24 , F05D2220/32 , F05D2220/36 , F05D2260/30 , F05D2260/33 , F05D2260/36
Abstract: A lock for securing a nosecone having first threading to an inlet case having second threading and for use with a gas turbine engine having an axis includes an annular ring designed to be positioned about the first threading. The lock also includes a tab extending radially from the annular ring, and having a ramped circumferential end and an angled circumferential end such that the ramped circumferential end passes over a detent of the inlet case in response to the nosecone being fastened to the inlet case and the angled circumferential end engages with the detent to resist unfastening of the nosecone from the inlet case.
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公开(公告)号：US10024238B2
公开(公告)日：2018-07-17
申请号：US14594663
申请日：2015-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Justin J. Phillips , James D. Hill , William K. Ackermann , Chris J. Niggemeier , Gabriel L. Suciu , Anthony R. Bifulco , Julian Partyka
Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.
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公开(公告)号：US20170276018A1
公开(公告)日：2017-09-28
申请号：US15079505
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco , Gabriel L. Suciu , Jesse M. Chandler
IPC: F01D17/16
CPC classification number: F01D17/162 , F01D9/04 , F01D17/12 , F01D25/34 , F05D2220/32 , F05D2240/12 , F05D2260/40 , F16H19/04 , F16H49/001 , Y02T50/671
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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