公开(公告)号：US20230193822A1

公开(公告)日：2023-06-22

申请号：US18110664

申请日：2023-02-16

Applicant: ROLLS-ROYCE PLC

Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

IPC: F02C7/04 ,  F02C7/18 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D27/20 ,  B64D33/10 ,  F02K3/06 ,  F02K3/075 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F01D9/06

CPC classification number: F02C7/04 ,  F02C7/18 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D27/20 ,  B64D33/10 ,  F02K3/06 ,  F02K3/075 ,  F02C7/08 ,  F02C7/12 ,  F02C7/14 ,  F01D9/065 ,  F05D2260/213 ,  B64D2033/0286 ,  F05D2220/323 ,  B64D2033/024 ,  F05D2220/36 ,  F02K3/115

Abstract: An aircraft includes a machine body that encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine includes, in axial flow sequence, a first heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The aircraft includes a second heat exchanger module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the first heat exchanger module. When a temperature of the fluid cooling flow is less than a temperature of a fluid to be cooled, the fluid to be cooled is directed to the first heat exchanger module, and when a temperature of the fluid cooling flow is greater than a temperature of the fluid to be cooled, the fluid to be cooled is directed to the second heat exchanger module and cooled using a fuel supply for the gas turbine engine.

公开(公告)号：US20220112813A1

公开(公告)日：2022-04-14

申请号：US17496193

申请日：2021-10-07

Applicant: ROLLS-ROYCE plc

Inventor： Stephen J BRADBROOK ,  Martin N GOODHAND ,  Paul M HIELD ,  Andrew PARSLEY ,  Natalie C WONG ,  Robert J CORIN ,  Thomas S BINNINGTON

IPC: F01D5/18 ,  F28D7/16 ,  F02C7/12 ,  F01D5/02

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes fan blades defining a fan diameter. The heat exchanger module is in communication with the fan assembly by an inlet duct, and the heat exchanger module further includes radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between hollow vanes. Each hollow vane accommodates at least one heat transfer element to transfer heat from a first fluid contained within the or each heat transfer element to a corresponding vane airflow passing through the hollow vane and over a surface of the or each heat transfer element. Each hollow vane further includes a flow modulator configured to regulate airflow in proportion to total airflow entering the heat exchanger module in response to a user requirement.

公开(公告)号：US20240369023A1

公开(公告)日：2024-11-07

申请号：US18625743

申请日：2024-04-03

Applicant: ROLLS-ROYCE plc

Inventor： Andrew PARSLEY ,  Natalie C WONG

IPC: F02C9/18

Abstract: An apparatus and method for reducing a pressure differential across a turbine 19 of a gas turbine engine 10 during a shaft break event, comprises a pressure equalization apparatus 200, 300, 400, 500, 600, 700 configured to introduce a pressurised fluid into a core airflow A at a region directly downstream of the turbine 19 in the event of a shaft break to directly increase a local pressure at the downstream region 29 of the turbine 19 and thereby reduce the pressure differential across the turbine 19. The reduction in the pressure differential may result in a reduction in the acceleration of the turbine 19.

公开(公告)号：US20220205388A1

公开(公告)日：2022-06-30

申请号：US17494537

申请日：2021-10-05

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

IPC: F02C7/08 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, a combustor module, and an exhaust module.
The machine body comprises either one or two fluid inlet apertures. The or each fluid inlet aperture is configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan module, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module.

公开(公告)号：US20220112838A1

公开(公告)日：2022-04-14

申请号：US17484771

申请日：2021-09-24

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C WONG ,  Thomas S BINNINGTON ,  David A JONES ,  Daniel BLACKER

IPC: F02C7/08 ,  F02K3/00

Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes fan blades defining a corresponding fan area (AFAN). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and includes radially-extending vanes arranged in a circumferential array with at least one vane including a heat transfer element for heat transfer from a first fluid contained within each element to an airflow passing over a surface of each heat transfer element before entering the fan assembly inlet. Each heat transfer element extends axially along the corresponding vane, with a swept heat transfer element area (AHTE) being the wetted surface area of all heat transfer elements in contact with the airflow. A Fan to Element Area parameter FEA of AHTE/AFAN lies in the range of 47 to 132.