公开(公告)号：US11649767B2

公开(公告)日：2023-05-16

申请号：US17484371

申请日：2021-09-24

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: F02C7/18 ,  F02C6/08 ,  F28D9/00 ,  B64D33/02 ,  F28D21/00

CPC classification number: F02C7/185 ,  F02C6/08 ,  F28D9/0018 ,  B64D2033/0286 ,  F05D2260/20 ,  F28D2021/0021

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 a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.

公开(公告)号：US11549438B2

公开(公告)日：2023-01-10

申请号：US17494523

申请日：2021-10-05

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: F02C7/12 ,  F25B11/00

Abstract: A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate FlowVane, and each channel air flow has a channel mass flow rate FlowChan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes FlowVane to be lower than FlowChan.

公开(公告)号：US11111793B2

公开(公告)日：2021-09-07

申请号：US16283287

申请日：2019-02-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin N Goodhand ,  Ian M Bunce

IPC: F04D29/28 ,  F01D5/14 ,  F02C1/10 ,  F01K25/10

Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of backswept blades (211,212) each of which have a blade exit angle (χ2) of from −50 to −70 degrees, and a fully vaneless diffuser (203).

公开(公告)号：US11111792B2

公开(公告)日：2021-09-07

申请号：US16282976

申请日：2019-02-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin N Goodhand ,  Ian M Bunce

IPC: F04D29/28 ,  F01D5/14 ,  F04D17/10

Abstract: A turbomachine (105) configured to compress supercritical carbon dioxide is shown. The turbomachine comprises, in fluid flow series, an inlet (201), an inducerless radial impeller (202) having a plurality of blades, and a fully vaneless diffuser (203). The radius of the inlet (r0) is from 25 to 50 percent of the radius of the impeller (r2).

公开(公告)号：US11649736B2

公开(公告)日：2023-05-16

申请号：US17495418

申请日：2021-10-06

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: B64D33/10 ,  F02C7/14 ,  F01D25/10 ,  F01D5/18 ,  F02C7/141 ,  F02K3/06

CPC classification number: F01D25/10 ,  B64D33/10 ,  F01D5/18 ,  F02C7/141 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/221 ,  F05D2270/303 ,  F05D2270/306

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 a plurality of fan blades defining a fan diameter. The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module including a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. Each heat transfer element may be individually and independently fluidly isolated from the remaining heat transfer elements.

公开(公告)号：US11649730B2

公开(公告)日：2023-05-16

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: F02C7/12 ,  F01D5/18 ,  F01D5/02 ,  F28D7/16 ,  F01D9/04 ,  F28D21/00

CPC classification number: F01D5/18 ,  F01D5/021 ,  F01D9/041 ,  F02C7/12 ,  F28D7/1615 ,  F05D2220/32 ,  F05D2220/36 ,  F28D2021/0026

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.