公开(公告)号：US20240333020A1

公开(公告)日：2024-10-03

申请号：US18435580

申请日：2024-02-07

Applicant: Pratt & Whitney Canada Corp.

Inventor： Raphael Gariepy ,  Simon Lam ,  Remi Robache ,  Antwan Shenouda ,  Richard Freer

IPC: H02J7/14 ,  H02J7/00

CPC classification number: H02J7/1423 ,  H02J7/005

Abstract: An assembly for an aircraft includes a battery, a charger, and a battery monitoring system. The battery includes a plurality of battery strings. The charger is configured to charge the plurality of battery strings. The battery monitoring system further includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to determine the battery string voltage for each battery string of the plurality of battery strings, identify a highest-voltage battery string of the plurality of battery strings and a lower-voltage subset of the plurality of battery strings, and sequentially charge each battery string of the lower-voltage subset of the plurality of battery strings with the charger to a first target string voltage.

公开(公告)号：US11990806B2

公开(公告)日：2024-05-21

申请号：US17514661

申请日：2021-10-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric Latulipe ,  Richard Freer

IPC: H02K29/03 ,  F16H1/22 ,  H02K7/116 ,  H02K16/02

CPC classification number: H02K29/03 ,  F16H1/22 ,  H02K7/116 ,  H02K16/02

Abstract: An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.

公开(公告)号：US20240133335A1

公开(公告)日：2024-04-25

申请号：US17971239

申请日：2022-10-20

Applicant: Pratt & Whitney Canada Corp.

Inventor： Richard Freer

IPC: F01P7/16 ,  F01P11/08

CPC classification number: F01P7/16 ,  F01P11/08 ,  F01P2007/146

Abstract: An aircraft propulsion system and method of cooling the same are provided. The system includes a hydraulic pump, an intermittent IC engine, a hydraulic motor, an engine oil pump, and a cooling system. The intermittent IC engine drives the hydraulic pump. The hydraulic motor is powered by the hydraulic pump and drives a propulsor fan. The cooling system includes a first heat exchanger (AIR-EO HEX) and a second heat exchanger (EO-HF HEX). The AIR-EO HEX transfers heat between flows of engine oil and ambient air. The EO-HF HEX transfers heat between flows of engine oil and hydraulic fluid. The hydraulic pump provides motive force to cause the hydraulic oil to pass through the EO-HF HEX and back to the at least one hydraulic pump. The engine oil pump provides motive force to pass the engine oil to and through the AIR-EO HEX, the EO-HF HEX, and the intermittent IC engine.

公开(公告)号：US20230045952A1

公开(公告)日：2023-02-16

申请号：US17402474

申请日：2021-08-13

Applicant: Pratt & Whitney Canada Corp.

Inventor： Richard Freer

IPC: B64D41/00 ,  H02J1/00 ,  B64D27/24

Abstract: In accordance with at least one aspect of this disclosure, there is provided a system for aircraft power. The system includes a DC/DC converter having a DC input and a DC output and a switching circuit connecting the DC input to the DC output operable to vary voltage at the DC output. A control module is operatively connected to the switching circuit for variable control of the DC output. The control module includes machine readable instructions to cause the control module to receive input indicative of altitude and control the switching circuit to vary voltage of the DC output as a function of environmental conditions such as altitude and humidity. In embodiments the altitude sensor is operatively connected to the controller.

公开(公告)号：US11190093B2

公开(公告)日：2021-11-30

申请号：US16212802

申请日：2018-12-07

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric Latulipe ,  Richard Freer

IPC: H02K29/03 ,  H02K7/116 ,  H02K16/02 ,  F16H1/22

Abstract: An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.

公开(公告)号：US11011966B2

公开(公告)日：2021-05-18

申请号：US16212797

申请日：2018-12-07

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric Latulipe ,  Richard Freer

IPC: H02K29/03 ,  H02K16/02 ,  H02K7/116 ,  F16H1/22

Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.

公开(公告)号：US10826415B2

公开(公告)日：2020-11-03

申请号：US16411275

申请日：2019-05-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric Latulipe ,  Richard Freer

IPC: H02P6/12 ,  H02P9/00 ,  B60L50/60 ,  B64D35/08 ,  H02K47/04 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  B64D31/06 ,  F01D15/10 ,  F02K3/06 ,  H02P5/74 ,  B64D27/26 ,  B64D31/00 ,  H02K51/00 ,  H02P17/00 ,  B60L50/13 ,  B60L53/24 ,  B60L50/51 ,  B64D27/12 ,  H02K19/34 ,  H02P6/00 ,  B64D35/02 ,  G08C19/38 ,  H02K41/03 ,  H02P101/25 ,  H02P101/30

Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.

公开(公告)号：US20200079515A1

公开(公告)日：2020-03-12

申请号：US16437456

申请日：2019-06-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric Latulipe ,  Richard Freer

IPC: B64D27/02 ,  B64D27/24 ,  B64D27/12 ,  B60L50/13 ,  B60L50/51 ,  B60L50/60 ,  B60L53/24

Abstract: An aircraft comprising a hybrid electric aircraft propulsion system. The system comprises a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attached to the aircraft at a first location and the first thermal propulsor assembly attached to the aircraft at a second location. The system also comprises a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attached to the aircraft at a third location and the second thermal propulsor assembly attached to the aircraft at a fourth location.

公开(公告)号：US20250101909A1

公开(公告)日：2025-03-27

申请号：US18373237

申请日：2023-09-26

Applicant: Pratt & Whitney Canada Corp.

Inventor： Richard Freer

IPC: F02C3/10 ,  B64D27/02 ,  B64D27/24 ,  F01D15/10

Abstract: A hybrid-electric propulsion (HEP) system is provided that includes a gas turbine engine, an electrical power motive system, a system controller, and a propulsor. The gas turbine engine has a free turbine configuration and a compressor. The electrical power motive system has first and second electric motors and first and second inverters. The gas turbine engine provides motive force to the propulsor. The first electric motor is configurable in a drive mode or in generator mode. The second electric motor is in communication with the compressor. The system controller is in communication with the gas turbine engine, the first and second inverters, and a non-transitory memory storing instructions, which instructions cause the system controller to control the second inverter to operate the second electric motor to provide a motive force to the compressor of the gas turbine engine during a low power setting of the gas turbine engine.

公开(公告)号：US20250042559A1

公开(公告)日：2025-02-06

申请号：US18228986

申请日：2023-08-01

Applicant: Pratt & Whitney Canada Corp.

Inventor： David Meisels ,  Richard Freer

IPC: B64D27/24 ,  B64D35/08

Abstract: A method of and system for operating a hybrid-electric propulsion system is provided. The system has a thermal engine and an electrical propulsion subsystem having a plurality of components. The method includes providing a set of original engine ratings for operating the hybrid-electric propulsion system, the original engine ratings are based on one or more first performance/capability parameters of an original electrical propulsion subsystem component; replacing the original component with an alternative component, the alternative component having one or more second performance/capability parameters, wherein the second performance/capability parameters are different from the first performance/capability parameters; producing a set of alternative engine ratings based on the second performance/capability parameters; and operating the hybrid-electric propulsion system using the set of alternative engine ratings.