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公开(公告)号：US11542845B2
公开(公告)日：2023-01-03
申请号：US16674647
申请日：2019-11-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Dana Tomescu , Daniel Alecu
IPC: F01M11/04 , F01D25/20 , F01M11/02 , F01M1/02 , B64D33/00 , F02C7/06 , F01M1/20 , F01M11/00 , B64D27/10
Abstract: A lubrication system for an aircraft engine includes an engine lubricant tank including at least a supply port hydraulically connectable to the aircraft engine, a lubricant makeup port, and an overfill port, an auxiliary lubricant tank, a lubricant makeup conduit hydraulically connecting the auxiliary lubricant tank to the lubricant makeup port. The lubricant makeup conduit includes a pump operable to move lubricant from the auxiliary lubricant tank to the lubricant makeup port, and an overfill conduit hydraulically connecting the overfill port to the auxiliary lubricant tank. A method of operating a lubrication system of an aircraft engine of an aircraft is also disclosed.
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公开(公告)号：US11274602B2
公开(公告)日：2022-03-15
申请号：US16421760
申请日：2019-05-24
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Bryan William Olver , Daniel Alecu , Jason Fish , Zoran Markovic
Abstract: A turbofan engine comprising an outer bypass duct, an annular bypass flow path between the outer bypass duct and a core engine, an engine component forming an airflow obstruction adjacent the outer bypass duct, an air cooler having a tube, the tube having at least a sinuous portion extending in the annular bypass flow path, the sinuous portion extending along the outer bypass duct, downstream of the airflow obstruction, the sinuous portion configured for exchanging heat between a fluid circulating in the tube and air circulating in the bypass flow path during operation of the turbofan engine.
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公开(公告)号：US11162494B2
公开(公告)日：2021-11-02
申请号：US16254800
申请日：2019-01-23
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Alecu , Sam Cutrara
Abstract: The pump can have a pump body, a main cavity having an inlet and an outlet, a rotor rotatably mounted in the main cavity and configured to pump fluid from the inlet to the outlet as it rotates, a separator cavity disposed adjacent the main cavity and configured to sustain a vortex, a fluid passage fluidly connecting the main cavity to the separator cavity, the fluid passage preserving momentum of fluid from the main cavity to the separator cavity to contribute to the vortex.
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公开(公告)号：US11060457B2
公开(公告)日：2021-07-13
申请号：US15367450
申请日：2016-12-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Daniel Alecu
Abstract: A cooling system for a gas turbine engine comprising a closed circuit containing a change-phase fluid, the closed circuit having at least one cooling exchanger configured to be exposed to a flow of cooling air for the change-phase fluid to release heat to the cooling air. A plurality of heat exchangers in are heat exchange relation with the change-phase fluid in the closed circuit, the plurality including at least a first heat exchanger configured to receive a first coolant from a first engine system for the change-phase fluid to absorb heat from the first coolant, and a second heat exchanger configured to receive a second coolant from a second engine system for the change-phase fluid to absorb heat from the second coolant. The system is configured so that the fluid at least partially vaporizes when absorbing heat from at least one of the first coolant and the second coolant and at least partially condenses when releasing heat to the cooling air. A method for cooling engine systems of a gas turbine engine is also provided.
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公开(公告)号：US11008116B2
公开(公告)日：2021-05-18
申请号：US16384270
申请日：2019-04-15
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andreas Eleftheriou , Daniel Alecu , Enzo Macchia
Abstract: A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.
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Patent Agency Ranking
公开(公告)号：US10760484B2
公开(公告)日：2020-09-01
申请号：US15267736
申请日：2016-09-16
Applicant: Pratt & Whitney Canada Corp.
Inventor： Daniel Alecu
Abstract: Multi-engine aircraft power plants and associated operating methods are disclosed. An exemplary multi-engine power plant comprises a first turboshaft engine and a second turboshaft engine configured to drive a common load such as a rotary wing of an aircraft; and a heat exchanger in thermal communication with an exhaust gas of the first turboshaft engine and in thermal communication with pre-combustion air of the second turboshaft engine. The heat exchanger is configured to permit heat transfer from the exhaust gas of the first turboshaft engine to the pre-combustion air of the second turboshaft engine.
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公开(公告)号：US10690000B1
公开(公告)日：2020-06-23
申请号：US16387773
申请日：2019-04-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Alecu , Enzo Macchia
Abstract: The gas turbine engine can have a rotor rotatably mounted to an engine casing, the rotor having compressor blades, and an alternator, the alternator having an armature with a winding forming part of the rotor and a magnetic field generator forming part of the engine casing, with an air gap between the magnetic field generator and the armature, the winding being electrically connected to a resistor embedded in at least one of the compressor blades.
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公开(公告)号：US10260371B2
公开(公告)日：2019-04-16
申请号：US15160366
申请日：2016-05-20
Applicant: Pratt & Whitney Canada Corp.
Inventor： Nashed Youssef , Andreas Eleftheriou , Daniel Alecu
Abstract: A method for providing an anti-icing airflow, including extracting a compressed airflow from a core flow path of an engine, heating the compressed airflow, mixing the heated compressed airflow with air extracted from a bypass flow path to create the anti-icing airflow having a higher temperature and pressure than that of the air extracted from the bypass flow path, and circulating the anti-icing airflow away from the bypass flow path. Also, an assembly located at least in part inside a turbofan engine and including a heat exchanger, a flow mixing device having a first inlet in the bypass flow path, a second inlet and an outlet, a first conduit providing fluid communication between the heat exchanger and a compressed air portion of the core flow path, a second conduit providing fluid communication between the heat exchanger and the second inlet, and a third conduit in fluid communication with the outlet.
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公开(公告)号：US09458764B2
公开(公告)日：2016-10-04
申请号：US13684863
申请日：2012-11-26
Applicant: Pratt & Whitney Canada Corp.
Inventor： Daniel Alecu , Richard Kostka
CPC classification number: F02C7/185 , F02C7/14 , F02C7/18 , F05D2220/32 , F05D2230/23 , F05D2260/213 , Y02T50/671 , Y02T50/675 , Y10T29/4935
Abstract: An air-to-air cooler has a heat exchanger integrated to a housing. A first passage extends through the housing for directing a flow of cooling air through the heat exchanger. A second passage extends through the housing for directing a flow of hot air to be cooled through the heat exchanger. The first passage has a cooling air outlet tube disposed downstream of the heat exchanger. The cooling air outlet tube extends across the second passage between the heat exchanger and a hot air inlet of the second passage. The hot air inlet is disposed to cause incoming hot air to flow over the cooling air outlet tube upstream of the heat exchanger. An ejector drives the flow of cooling air through the first passage of the air-to-air cooler. A portion of the hot air flow may be used to drive the ejector.
Abstract translation: 空气 - 空气冷却器具有与壳体集成的热交换器。 第一通道延伸穿过壳体，用于引导冷却空气流通过热交换器。 第二通道延伸穿过壳体，用于引导待冷却的热空气流通过热交换器。 第一通道具有设置在热交换器下游的冷却空气出口管。 冷却空气出口管延伸穿过热交换器和第二通道的热空气入口之间的第二通道。 热空气入口设置成使得热空气流入热交换器上游的冷却空气出口管。 喷射器通过空气 - 空气冷却器的第一通道驱动冷却空气的流动。 热空气流的一部分可以用于驱动喷射器。
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公开(公告)号：US20140260178A1
公开(公告)日：2014-09-18
申请号：US13804118
申请日：2013-03-14
Applicant: Pratt & Whitney Canada Corp.
Inventor： Andreas ELEFTHERIOU , Daniel Alecu , David Menheere
CPC classification number: B21D53/04 , B21D49/00 , F01D25/30 , F02C7/08 , F02K1/822 , F05D2210/34 , F05D2220/32 , F05D2250/711 , F05D2250/712 , F28D7/1684 , F28D9/0031 , F28D2021/0026 , F28F3/046 , F28F13/02 , F28F13/06 , Y02T50/672 , Y02T50/675 , Y10T29/49357
Abstract: A recuperator disposed in the exhaust duct of a gas turbine engine includes a plurality of recuperator plates arranged in a spaced-apart relationship to define therebetween a plurality of interstices and fluid channels, the plurality of interstices adapted to direct therethrough at least one first stream received at a leading plate edge of the recuperator plates and the plurality of fluid channels adapted to direct therethrough at least one second stream to effect heat exchange between the at least one first stream and the at least one second stream. Each recuperator plate includes, formed at the leading plate edge thereof, a first concavity extending along the leading edge in a direction substantially parallel to a longitudinal axis of the plate. The first concavity extends transversely to a direction of the at least one first stream flowing over each recuperator plate.
Abstract translation: 设置在燃气涡轮发动机的排气管道中的换热器包括以间隔开的关系布置的多个换热器板，以在其间限定多个间隙和流体通道，所述多个间隙适于引导至少一个接收的第一流 在所述换热器板的前板边缘处，并且所述多个流体通道适于引导至少一个第二流以在所述至少一个第一流和所述至少一个第二流之间进行热交换。 每个换热器板包括在其前板边缘处形成有沿着前缘沿基本上平行于板的纵向轴线的方向延伸的第一凹部。 第一凹部横向于流过每个换热器板的至少一个第一流的方向延伸。
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