公开(公告)号：US20200240327A1

公开(公告)日：2020-07-30

申请号：US16256123

申请日：2019-01-24

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David MENHEERE ,  Timothy REDFORD ,  Daniel VAN DEN ENDE ,  Santo CHIAPPETTA

IPC: F02C3/10 ,  F02C6/08

Abstract: A gas turbine engine has an output shaft, a power turbine drivingly engaged to the output shaft, a boost compressor drivingly engaged by the power turbine; and a boost compressor bleed air circuit having an inlet fluidly connected to the boost compressor and an outlet fluidly connected to the power turbine.

公开(公告)号：US20190186352A1

公开(公告)日：2019-06-20

申请号：US16282754

申请日：2019-02-22

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony JONES ,  Andre JULIEN ,  Jean THOMASSIN ,  Richard ULLYOTT ,  David MENHEERE

IPC: F02B63/04 ,  F01C21/18 ,  F02B53/14 ,  F02B37/00 ,  F01P5/06 ,  F01P5/04 ,  F01P1/06 ,  B64D33/08 ,  B64D41/00 ,  F02B63/06 ,  F02B67/04 ,  F02B53/02 ,  F02C7/18 ,  F02C7/14 ,  F02C5/00 ,  F02K5/00 ,  F01C1/22

CPC classification number: F02B63/04 ,  B64D33/08 ,  B64D41/00 ,  F01C1/22 ,  F01C21/18 ,  F01P1/06 ,  F01P5/04 ,  F01P5/06 ,  F02B37/00 ,  F02B53/02 ,  F02B53/14 ,  F02B63/06 ,  F02B67/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C7/14 ,  F02C7/18 ,  F02K5/00 ,  F05D2220/50 ,  F05D2260/213 ,  Y02T10/144 ,  Y02T10/17 ,  Y02T50/53 ,  Y02T50/672 ,  Y02T50/676

Abstract: An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.

公开(公告)号：US20190186351A1

公开(公告)日：2019-06-20

申请号：US16284381

申请日：2019-02-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony JONES ,  Andre JULIEN ,  David MENHEERE ,  Jean THOMASSIN ,  Richard ULLYOTT ,  Daniel VAN DEN ENDE

IPC: F02B53/14 ,  F02B61/06 ,  F02B39/12 ,  F02C7/36 ,  F02B37/24 ,  F02B37/10 ,  F02B33/40 ,  F02C6/12 ,  B64D41/00 ,  F02B63/04 ,  F02B39/10 ,  F02C7/32

CPC classification number: F02B53/14 ,  B64D41/00 ,  F02B33/40 ,  F02B37/10 ,  F02B37/24 ,  F02B39/10 ,  F02B39/12 ,  F02B61/06 ,  F02B63/04 ,  F02B2053/005 ,  F02C6/12 ,  F02C7/32 ,  F02C7/36 ,  F05D2220/50 ,  F05D2260/40 ,  Y02T10/144 ,  Y02T50/44 ,  Y02T50/671

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

公开(公告)号：US20190128178A1

公开(公告)日：2019-05-02

申请号：US16227141

申请日：2018-12-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony JONES ,  Andre JULIEN ,  David MENHEERE ,  Jean THOMASSIN ,  Richard ULLYOTT ,  Daniel VAN DEN ENDE

IPC: F02B53/14 ,  F02B53/04 ,  B64D41/00 ,  F02B63/04

CPC classification number: F02B53/14 ,  B64D41/00 ,  F02B53/04 ,  F02B63/04 ,  Y02T50/53

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.

公开(公告)号：US20180156120A1

公开(公告)日：2018-06-07

申请号：US15367450

申请日：2016-12-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David MENHEERE ,  Daniel ALECU

IPC: F02C7/18

CPC classification number: F02C7/185 ,  F02C7/14 ,  F05D2260/207 ,  F05D2260/213

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.

公开(公告)号：US20170226959A1

公开(公告)日：2017-08-10

申请号：US15227519

申请日：2016-08-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Andre JULIEN ,  Jean THOMASSIN ,  Maxime COURTOIS ,  Bruno VILLENEUVE ,  Serge DUSSAULT ,  Richard ULLYOTT ,  Serge LAFORTUNE ,  Luc DIONNE ,  Anthony JONES ,  Behzad HAGSHENAS ,  David MENHEERE

IPC: F02K1/38 ,  F01P5/02 ,  F02B63/04 ,  F02K1/82 ,  F02B53/02 ,  F01P11/10 ,  F01N3/05

CPC classification number: F02K1/386 ,  B64D41/00 ,  B64D2041/002 ,  F01C1/22 ,  F01C21/18 ,  F01N3/05 ,  F01P5/02 ,  F01P11/10 ,  F02B53/02 ,  F02B63/04 ,  F02B63/06 ,  F02B67/04 ,  F02B2053/005 ,  F02C5/00 ,  F02C7/14 ,  F02C7/18 ,  F02K1/82 ,  F02K5/00 ,  F05D2220/50 ,  F05D2260/213 ,  F05D2300/173 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T10/17 ,  Y02T50/53 ,  Y02T50/672 ,  Y02T50/676

Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

公开(公告)号：US20140252769A1

公开(公告)日：2014-09-11

申请号：US13792739

申请日：2013-03-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David MENHEERE ,  Andreas ELEFTHERIOU ,  Richard KOSTKA

IPC: F02C7/275 ,  H02K23/52 ,  H02K7/18 ,  F02C7/36 ,  H02K15/14

CPC classification number: F02C7/275 ,  F02C7/36 ,  F05D2220/766 ,  H02K7/1823 ,  H02K15/14 ,  H02K23/52 ,  Y10T29/49009

Abstract: A gas turbine engine including high and low pressure shafts, an electromechanical device having a rotor and a stator coupled such that the rotor is rotatable with respect to the stator, the rotor having a device gear secured thereto, the device being secured to a support structure in a bearing housing forming part of a bearing assembly supporting a portion of the low pressure shaft extending in proximity of the high pressure shaft and of the shaft gear, and a coupling idle gear secured for rotation about a stationary gear support mounted in the bearing housing, the idle gear being in toothed engagement with the shaft gear and with the device gear. An electromechanical device assembly for a gas turbine engine and a method of operating an electromechanical device are also provided.

Abstract translation: 一种包括高压和低压轴的燃气涡轮发动机，具有转子和定子的机电装置，所述定子联接成使得所述转子相对于所述定子可旋转，所述转子具有固定到其上的装置齿轮，所述装置固定到支撑结构 在形成轴承组件的一部分的轴承壳体中，所述轴承组件支撑在所述高压轴和所述轴齿轮附近延伸的所述低压轴的一部分，以及联接空转齿轮，所述联接空转齿轮被固定以围绕安装在所述轴承壳体 ，空转齿轮与轴齿轮和装置齿轮啮合。 还提供了一种用于燃气涡轮发动机的机电装置组件和操作机电装置的方法。

公开(公告)号：US20230304444A1

公开(公告)日：2023-09-28

申请号：US18092637

申请日：2023-01-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel ALECU ,  David MENHEERE

IPC: F02C7/28 ,  F01D9/06 ,  F01D25/12 ,  F01D25/18 ,  F02C6/08 ,  F02C7/18

CPC classification number: F02C7/28 ,  F01D9/065 ,  F01D25/125 ,  F01D25/183 ,  F02C6/08 ,  F02C7/18 ,  F02C3/04

Abstract: Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

公开(公告)号：US20230136870A1

公开(公告)日：2023-05-04

申请号：US17452917

申请日：2021-10-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David MENHEERE ,  Daniel ALECU

IPC: F01D25/24

Abstract: An aircraft engine comprises a casing extending circumferentially around a central axis. A support flange is secured to the casing and extends circumferentially around the axis. The support flange has an inner and an outer flange face. A component is drivingly engaged by a shaft of the engine. The component has a connecting section extending around the central axis. The connecting section has a connecting face. The inner flange face is in abutment against the connecting face. A retaining ring extends circumferentially around the central axis. The retaining ring is in abutment against the outer flange face of the support flange. The retaining ring has a coefficient of thermal expansion, which is less than that of the support flange.

公开(公告)号：US20210277826A1

公开(公告)日：2021-09-09

申请号：US17325278

申请日：2021-05-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard IVAKITCH ,  David MENHEERE ,  Paul STONE

IPC: F02C7/047

Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.