-
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。
-
公开(公告)号：US20240208664A1
公开(公告)日：2024-06-27
申请号：US18088214
申请日：2022-12-23
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere
CPC classification number: B64D35/08 , B64D27/10 , B64D27/24 , B64D33/04 , F02C3/04 , F02C6/00 , H02K7/116 , H02K7/1823 , B64D2027/026
Abstract: An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.
-
公开(公告)号：US20230203962A1
公开(公告)日：2023-06-29
申请号：US17562306
申请日：2021-12-27
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere , Timothy Redford
CPC classification number: F01D11/22 , F01D11/001 , F05D2220/32 , F05D2240/11
Abstract: An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.
-
公开(公告)号：US11542836B2
公开(公告)日：2023-01-03
申请号：US17337621
申请日：2021-06-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere
Abstract: An engine bi-material joint includes a first flange composed of a first material and defining a first coefficient of thermal expansion, and a second flange composed of a second material and defining a second coefficient of thermal expansion. The second flange is different from the first material. An interface flange is engaged with the first flange and with the second flange. The interface flange defines a third coefficient of thermal expansion being equal to or less than the first coefficient of thermal expansion of the first flange. The third coefficient of thermal expansion is less than the second coefficient of thermal expansion of the second flange. The first coefficient of thermal expansion of the first flange is less than the second coefficient of thermal expansion of the second flange.
-
公开(公告)号：US11459953B2
公开(公告)日：2022-10-04
申请号：US16798592
申请日：2020-02-24
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Van Den Ende , David Menheere , Timothy Redford
Abstract: The gas turbine engine includes a combustion section including an annular swirl combustor having a combustor inlet, and a compressor section including a centrifugal compressor with an impeller, the impeller compressing and swirling an airflow and discharging the compressed and swirled airflow from the impeller outlet into the combustor inlet. The turbine section includes a radial turbine having a turbine fuel inlet and a turbine fuel outlet, the radial turbine receiving a flow of fuel at the turbine fuel inlet and discharging the flow of fuel from the turbine fuel outlet of the radial turbine into the combustor inlet.
-
Patent Agency Ranking
公开(公告)号：US11085319B2
公开(公告)日：2021-08-10
申请号：US16448508
申请日：2019-06-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Timothy Redford , David Menheere , Richard Kostka
Abstract: A system for controlling gas turbine engine rotor blades tip clearance is described. A rotor is mounted to an engine shaft, supported by a thrust bearing, for rotation within a gas path shroud circumscribing blades of the rotor, the gas path shroud having a non-cylindrical shape in the vicinity of the rotor blades. A rotary actuator is associated with the thrust bearing and configured for axial translation of the thrust bearing, to thereby axially translate the engine shaft and the rotor blades relative to the gas path shroud. This translation is configured to vary the blade tip clearance of the rotor.
-
公开(公告)号：US10422281B2
公开(公告)日：2019-09-24
申请号：US15373049
申请日：2016-12-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Daniel Alecu
Abstract: A cooling system for a gas turbine engine comprises a closed circuit containing a change-phase fluid, at least one heat exchanger configured to receive a first coolant from a first engine system for the change-phase fluid in the closed circuit to absorb heat from the first coolant, whereby the cooling system is configured so that the change-phase fluid at least partially vaporizes when absorbing heat from the at least one heat exchanger. The closed circuit has a cooling exchanger adjacent to an annular wall of a bypass duct, the cooling exchanger configured to be exposed to a flow of cooling air in the bypass duct for the change-phase fluid to release heat to the cooling air and condense at least partially, the cooling exchanger having conduits configured to feed the vaporized change-phase fluid from a heat exchange with the at least one heat exchanger to the cooling exchanger, and to direct condensed change-phase fluid by gravity from the cooling exchanger to the at least one heat exchanger.
-
公开(公告)号：US10371162B2
公开(公告)日：2019-08-06
申请号：US15286078
申请日：2016-10-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andreas Eleftheriou , Richard Ivakitch , David Menheere
Abstract: An integrally bladed fan (IBF) rotor of a gas turbine engine. The IBF rotor includes a hub and a plurality of fan blades extending radially outwardly from the hub and integral therewith. The hub has a fan attachment flange disposed at an end of the hub on a trailing edge side thereof for mounting a booster rotor to a trailing edge side of the fan. The fan attachment flange is disposed at a radial distance from a longitudinal center axis of the integrally bladed fan rotor. The hub has an outer hub surface disposed radially inward from the radial distance of the fan attachment flange.
-
公开(公告)号：US10329955B2
公开(公告)日：2019-06-25
申请号：US15007527
申请日：2016-01-27
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere , Andrew Marshall
Abstract: An oil system of a turbine engine and a method for driving an oil pump of such oil system are disclosed. In various embodiments, the oil system comprises an oil pump for fluid communication with one or more lubrication loads of the turbine engine, a first source of motive power and a coupling device. The first source of motive power is drivingly engaged to the oil pump for driving the oil pump during a first mode of operation. The coupling device is configured to drivingly disengage a second source of motive power from the oil pump during the first mode of operation and drivingly engage the second source of motive power with the oil pump to drive the oil pump during a second mode of operation.
-
公开(公告)号：US10253687B2
公开(公告)日：2019-04-09
申请号：US15227318
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony Jones , Andre Julien , David Menheere , Jean Thomassin , Richard Ullyott , Daniel Van Den Ende
Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.
-
-
-
-
-
-
-
-
-
Search Results
60
records
(took 0.024 seconds)
