公开(公告)号：US20220205386A1

公开(公告)日：2022-06-30

申请号：US17697630

申请日：2022-03-17

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W BEMMENT ,  Pascal DUNNING

IPC: F02C3/04 ,  F02C7/36

Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor; and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.

公开(公告)号：US20240175391A1

公开(公告)日：2024-05-30

申请号：US18405485

申请日：2024-01-05

Applicant: ROLLS-ROYCE plc

Inventor： Craig W. BEMMENT ,  Pascal DUNNING

IPC: F02C3/04 ,  F02C7/36 ,  F02K3/06

CPC classification number: F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2200/14 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/307 ,  F05D2260/4031

Abstract: A gas turbine engine for an aircraft comprises an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor, wherein a compressor exit temperature is defined as an average temperature of airflow at the exit from the compressor;
and a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, wherein a fan rotor entry temperature is defined as an average temperature of airflow across the leading edge of each fan blade at cruise conditions and a fan tip rotor exit temperature is defined as an average temperature of airflow across a radially outer portion of each fan blade at the trailing edge at cruise conditions. A core to fan tip temperature rise ratio is in the range from 2.845 to 3.8.

公开(公告)号：US20200049104A1

公开(公告)日：2020-02-13

申请号：US16423277

申请日：2019-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M. TOWNES ,  Pascal DUNNING ,  Michael J. WHITTLE

IPC: F02K3/065 ,  F01D5/14 ,  F02C3/107 ,  F02K3/02 ,  F01D5/02 ,  F02C7/36

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20200049063A1

公开(公告)日：2020-02-13

申请号：US16398760

申请日：2019-04-30

Applicant: ROLLS-ROYCE PLC

Inventor： Michael J WHITTLE ,  Pascal DUNNING ,  Roderick M TOWNES

IPC: F02C3/06 ,  F01D5/28

Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20210207528A1

公开(公告)日：2021-07-08

申请号：US17209989

申请日：2021-03-23

Applicant: ROLLS-ROYCE PLC

Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J. WHITTLE

IPC: F02C3/073 ,  F02C7/36 ,  F01D5/28 ,  F01D5/30

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20200049072A1

公开(公告)日：2020-02-13

申请号：US16527771

申请日：2019-07-31

Applicant: ROLLS-ROYCE PLC

Inventor： Michael J. WHITTLE ,  Pascal DUNNING ,  Roderick M. TOWNES

IPC: F02C7/18 ,  F02C3/06 ,  F01D5/28 ,  F01D9/04 ,  F01D11/08

Abstract: A highly efficient gas turbine engine includes a fan which is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, which results in efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20200049070A1

公开(公告)日：2020-02-13

申请号：US16411862

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M. TOWNES ,  Michael J. WHITTLE ,  Pascal DUNNING

IPC: F02C7/08 ,  F02K3/06 ,  F02C9/16

Abstract: A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20200049065A1

公开(公告)日：2020-02-13

申请号：US16411253

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Michael J WHITTLE ,  Roderick M TOWNES ,  Pascal DUNNING

IPC: F02C3/073 ,  F02C7/36

Abstract: A gas turbine engine is highly efficient. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20200049064A1

公开(公告)日：2020-02-13

申请号：US16411224

申请日：2019-05-14

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Michael J. WHITTLE ,  Roderick M. TOWNES

IPC: F02C3/073 ,  F02C7/36

Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

公开(公告)号：US20230272752A1

公开(公告)日：2023-08-31

申请号：US18137123

申请日：2023-04-20

Applicant: ROLLS-ROYCE plc

Inventor： Pascal DUNNING ,  Roderick M. TOWNES ,  Michael J. WHITTLE

IPC: F02C7/36 ,  F02C3/073 ,  F01D5/28 ,  F01D5/30

CPC classification number: F02C7/36 ,  F02C3/073 ,  F01D5/284 ,  F01D5/3084 ,  F05D2240/30 ,  F05D2240/12

Abstract: A highly efficient gas turbine engine is provided. The fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.