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公开(公告)号：US10233841B2
公开(公告)日：2019-03-19
申请号：US14933518
申请日：2015-11-05
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz , Charles P. Gendrich , John C. DiTomasso , Andrew J. Murphy
IPC: F02C7/14 , F02C7/16 , F01D25/16 , F02K3/06 , F02C7/047 , B64D15/06 , F02C7/12 , B64D15/02 , B64D15/00 , F01D25/02
Abstract: In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.
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公开(公告)号：US20160131036A1
公开(公告)日：2016-05-12
申请号：US14933518
申请日：2015-11-05
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz , Charles P. Gendrich , John C. DiTomasso , Andrew J. Murphy
CPC classification number: F02C7/16 , B64D15/00 , B64D15/02 , B64D15/06 , F01D25/02 , F01D25/162 , F02C7/047 , F02C7/12 , F02C7/14 , F02K3/06 , F05D2220/32 , F05D2260/213 , F05D2260/98 , Y02T50/675
Abstract: In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.
Abstract translation: 在一个示例性实施例中，用于冷却发动机部件的燃气涡轮发动机系统包括发动机芯，容纳发动机芯的铁芯壳体，芯壳体前方的发动机芯驱动风扇，围绕风扇和芯壳体的机舱，以及 旁通管道限定在芯壳体的外径和机舱的内径之间。 还包括一种具有冷却剂回路的热管理系统，该冷却剂回路包括设置在机舱内径上的第一热交换器和布置在跨过旁通管的BiFi前缘的第二热交换器中的至少一个。 第一热交换器与第二热交换器热连通。
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公开(公告)号：US10823079B2
公开(公告)日：2020-11-03
申请号：US15363434
申请日：2016-11-29
Applicant: United Technologies Corporation
Inventor： Fadi S. Maalouf , Matthew E. Bintz
Abstract: A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter operable to drive rotation of a starting spool of the gas turbine engine and a starter air valve operable to deliver compressed air to the air turbine starter in response to the starter air valve being open. The system also includes a metered orifice coupled in a bypass configuration around the starter air valve to deliver a reduced amount of the compressed air to the air turbine starter while the starter air valve is closed. The reduced amount of the compressed air delivered to the air turbine starter limits a motoring speed of the gas turbine engine below a resonance speed of the starting spool of the gas turbine engine.
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公开(公告)号：US10823069B2
公开(公告)日：2020-11-03
申请号：US16185565
申请日：2018-11-09
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Matthew E. Bintz
Abstract: A high pressure compressor section of a gas turbine engine including: an inner case separating a core flow path of the gas turbine engine and a plenum formed between the inner case and an outer case; a bleed port located on an inner surface of the inner case, the inner surface being proximate the core flow path; an outlet located on an outer surface of the inner case, the outer surface being proximate the plenum; and a bleed air passageway passing through the inner case to fluidly connect the bleed port to the outlet, wherein the bleed air passageway is fluidly connected to the core flow path through the bleed port and the bleed air passageway is fluidly connected to the plenum through the outlet.
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公开(公告)号：US20200325792A1
公开(公告)日：2020-10-15
申请号：US16379179
申请日：2019-04-09
Applicant: United Technologies Corporation
Inventor： William S. Pratt , Matthew E. Bintz
Abstract: A vane arm assembly for a gas turbine engine includes a vane stem having a circumferential groove axially spaced from an outer end of the vane stem. The assembly also includes a vane arm defining an arm aperture that the vane stem is disposed within. The assembly further includes a mechanical fastener retaining an axial position of the vane arm in the axial direction. The assembly yet further includes a retention clip having a base portion and at least one clip arm, the base portion defining a clip aperture that the vane stem is disposed within, the base portion disposed within the circumferential groove of the vane stem to couple the retention clip to the vane stem, the at least one clip arm including a retention member engaged with the vane arm to provide redundant axial retention of the vane arm.
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Patent Agency Ranking
公开(公告)号：US20200291861A1
公开(公告)日：2020-09-17
申请号：US16353165
申请日：2019-03-14
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz
IPC: F02C7/28
Abstract: A seal for a rotor stack includes a first portion that includes a shaft contact surface. A second portion includes a rotor disk contact surface. A transition portion connects the first portion and the second portion. The transition portion extends radially outward from the first portion.
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公开(公告)号：US20200149474A1
公开(公告)日：2020-05-14
申请号：US16185565
申请日：2018-11-09
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Matthew E. Bintz
Abstract: A high pressure compressor section of a gas turbine engine including: an inner case separating a core flow path of the gas turbine engine and a plenum formed between the inner case and an outer case; a bleed port located on an inner surface of the inner case, the inner surface being proximate the core flow path; an outlet located on an outer surface of the inner case, the outer surface being proximate the plenum; and a bleed air passageway passing through the inner case to fluidly connect the bleed port to the outlet, wherein the bleed air passageway is fluidly connected to the core flow path through the bleed port and the bleed air passageway is fluidly connected to the plenum through the outlet.
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公开(公告)号：US10584598B2
公开(公告)日：2020-03-10
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
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.
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公开(公告)号：US20200032655A1
公开(公告)日：2020-01-30
申请号：US16431403
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： TROY SHANNON PRINCE , Matthew E. Bintz , Charles P. Gendrich
IPC: F01D5/14 , B29C70/86 , B29C70/88 , B29D99/00 , B29C35/02 , B29C65/48 , B29C65/00 , F01D5/28 , F03G7/06
Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.
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公开(公告)号：US10435776B2
公开(公告)日：2019-10-08
申请号：US15802837
申请日：2017-11-03
Applicant: United Technologies Corporation
Inventor： Christopher W. Strock , Matthew E. Bintz
IPC: F01D11/12 , C23C4/02 , C22C27/02 , C22C27/04 , C22C27/06 , C23C28/00 , C23C4/11 , C23C4/134 , F04D29/02 , F04D29/16 , F04D29/32 , F04D29/52 , F01D5/28
Abstract: A blade outer air seal (BOAS) or segment thereof comprises: a metallic substrate having an inner diameter (ID) surface; and a coating system along the inner diameter surface comprises: a bondcoat atop the substrate; and a ceramic barrier coat atop the bondcoat. The bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight.
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