公开(公告)号：US20210276724A1

公开(公告)日：2021-09-09

申请号：US16784591

申请日：2020-02-07

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: B64D31/00 ,  B64D27/10 ,  B64C29/00

Abstract: The gas turbine engine for an aircraft includes at least a low pressure spool with a low pressure turbine shaft operatively connected to at least one turbine, the low pressure turbine shaft rotatable about an engine axis, and a low pressure compressor operatively connected to a low pressure compressor shaft that is independently rotatable relative to the low pressure turbine shaft. A differential gearbox has an input operatively connected to the low pressure turbine shaft, a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft and the second output of the differential gearbox operatively connected to an output shaft of the gas turbine engine. The differential gearbox permits the output shaft, the low pressure compressor shaft and the low pressure turbine shaft to rotate at different speeds.

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：US20210062727A1

公开(公告)日：2021-03-04

申请号：US16552131

申请日：2019-08-27

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: F02C9/18 ,  F02C7/18

Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. The system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid propeller configured to drive the bleed air through the heat exchanger. The fluid propeller is disposed downstream of the heat exchanger.

公开(公告)号：US20210061476A1

公开(公告)日：2021-03-04

申请号：US16552136

申请日：2019-08-27

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: B64D13/08

Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. In one embodiment, such system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid-driven fluid propeller configured to drive the bleed air through the heat exchanger.

公开(公告)号：US20220136448A1

公开(公告)日：2022-05-05

申请号：US17088128

申请日：2020-11-03

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: F02C9/18 ,  B64D27/18

Abstract: The aircraft can have a first engine secured to a first wing on a first side of a fuselage, and a second engine secured to a second wing on a second side of the fuselage, the second wing having a proximal end secured to the fuselage, and a distal end extending away from the fuselage. While operating the first engine, compressed gas can be conveyed from the first engine to a thrust generating device located at the distal end of the second wing.

公开(公告)号：US20210262391A1

公开(公告)日：2021-08-26

申请号：US16798592

申请日：2020-02-24

Applicant: PRATT & WHITNEY CANADA CORP.

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

IPC: F02C7/16 ,  F02C7/22 ,  F02C3/08 ,  F23R3/28

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.