公开(公告)号：US20230167784A1

公开(公告)日：2023-06-01

申请号：US17940034

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J SELLERS ,  Stephen J BRADBROOK ,  Robert J CORIN ,  Richard J HUNSLEY

IPC: F02K3/06 ,  F01D15/10

CPC classification number: F02K3/06 ,  F01D15/10 ,  F05D2220/323 ,  F05D2220/36

Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine is positioned downstream of the fan assembly and is connected to the turbine module. The fan assembly includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The turbine module includes a lowest pressure turbine stage having a row of rotor blades. The gas turbine engine has a fan tip axis that joins a radially outer tip of the leading edge of one of the plurality of fan blades of the highest pressure fan stage, and the radially outer tip of the trailing edge of one of the rotor blades of the lowest pressure turbine stage. The fan tip axis lies in a longitudinal plane which contains a centreline of the gas turbine engine. The fan axis angle is between 11 and 20 degrees.

公开(公告)号：US20230219694A1

公开(公告)日：2023-07-13

申请号：US17940030

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J SELLERS ,  Andrew J NEWMAN ,  Gordon MARGARY ,  Paul R DAVIES ,  Stephen J BRADBROOK

IPC: B64D33/08

CPC classification number: B64D33/08 ,  B64D2027/026

Abstract: A cooling system for an aircraft comprises a gas turbine engine, an ancillary apparatus, and a heat exchanger. The gas turbine engine comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate an electrical power PEM1 (W). The heat exchanger is configured to transfer a total waste heat energy Q (W) generated by the gas turbine engine and the ancillary apparatus, to an airflow passing through the heat exchanger, and a ratio S of:




S
=


(


Total
⁢

Electrical
⁢

Power
⁢

Generated

=

P

EM
⁢
1



)


(


Total
⁢

Heat
⁢

Energy
⁢

Rejected
⁢

to
⁢

Airflow

=
Q

)






is in a range of between 0.50 and 5.00.

公开(公告)号：US20230167767A1

公开(公告)日：2023-06-01

申请号：US17940035

申请日：2022-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J SELLERS ,  Jonathan A CHERRY ,  Craig TOWN

IPC: F02C7/12 ,  F02C3/06

CPC classification number: F02C7/12 ,  F02C3/06 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/40

Abstract: An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine positioned downstream of the fan assembly is rotationally connected to the turbine module. The fan assembly is in fluid communication with the compressor module by an intermediate duct and includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The compressor module includes a lowest pressure compressor stage having a row of rotor blades. An intermediate flow axis is defined joining a radially outer tip of a trailing edge of one of the fan blades of the highest pressure fan stage, and a radially outer tip of a leading edge of one of the rotor blades of a leading edge of a lowest-pressure compressor blade. An intermediate flow axis angle and the intermediate flow axis angle is from −20 to −30 degrees.