公开(公告)号：US20220119120A1

公开(公告)日：2022-04-21

申请号：US17562609

申请日：2021-12-27

Applicant: ROLLS-ROYCE PLC

Inventor： Gareth M ARMSTRONG ,  Nicholas HOWARTH

IPC: B64D27/10 ,  F02C3/06 ,  F02K3/06 ,  F02K3/068 ,  F02C3/04 ,  F01D5/28 ,  F02C7/04 ,  F02C3/107

Abstract: A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20200291865A1

公开(公告)日：2020-09-17

申请号：US16443938

申请日：2019-06-18

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas HOWARTH ,  Gareth M ARMSTRONG

IPC: F02C7/36 ,  F01D15/12 ,  F02C3/113

Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20200291785A1

公开(公告)日：2020-09-17

申请号：US16713666

申请日：2019-12-13

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas HOWARTH ,  Gareth M ARMSTRONG

IPC: F01D5/14 ,  F02C3/02 ,  F04D19/02 ,  F02C7/36 ,  F02K3/068 ,  F02C3/04 ,  F02C3/107 ,  F01D5/28 ,  F04D29/68 ,  F02K3/06 ,  F02C7/04

Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20230392554A1

公开(公告)日：2023-12-07

申请号：US18236666

申请日：2023-08-22

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas HOWARTH ,  Gareth M ARMSTRONG

IPC: F02C7/36 ,  F02C3/113 ,  F01D15/12

CPC classification number: F02C7/36 ,  F02C3/113 ,  F01D15/12

Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20210164401A1

公开(公告)日：2021-06-03

申请号：US17171439

申请日：2021-02-09

Applicant: ROLLS-ROYCE PLC

Inventor： Nicholas HOWARTH ,  Gareth M ARMSTRONG

IPC: F02C7/36 ,  F02C3/113 ,  F01D15/12

Abstract: A gas turbine engine has a compression system blade ratio defined as the ratio of the height of a fan blade to the height of the most downstream compressor blade in the range of from 45 to 95. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20220403743A1

公开(公告)日：2022-12-22

申请号：US17892696

申请日：2022-08-22

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas HOWARTH ,  Gareth M ARMSTRONG

IPC: F01D5/14 ,  F02C3/02 ,  F02C7/36 ,  F04D29/68 ,  F04D19/02 ,  F01D5/28 ,  F02C3/04 ,  F02C3/107 ,  F02C7/04 ,  F02K3/06 ,  F02K3/068

Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20210207483A1

公开(公告)日：2021-07-08

申请号：US17212554

申请日：2021-03-25

Applicant: ROLLS-ROYCE PLC

Inventor： Nicholas HOWARTH ,  Gareth M ARMSTRONG

IPC: F01D5/14 ,  F02C3/02 ,  F02C7/36 ,  F04D29/68 ,  F04D19/02 ,  F01D5/28 ,  F02C3/04 ,  F02C3/107 ,  F02C7/04 ,  F02K3/06 ,  F02K3/068

Abstract: A gas turbine engine that has improved fuel burn provides operability and/or maintenance requirements when installed on an aircraft. The gas turbine engine is provided with a core compressor that includes twelve, thirteen or fourteen rotor stages. The gas turbine engine has a ratio of a core compressor aspect ratio divided by a core compressor pressure ratio is in the range of from 0.03 to 0.09. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

公开(公告)号：US20200290743A1

公开(公告)日：2020-09-17

申请号：US16437284

申请日：2019-06-11

Applicant: ROLLS-ROYCE plc

Inventor： Gareth M ARMSTRONG ,  Nicholas HOWARTH

IPC: B64D27/10 ,  F02C3/06 ,  F02K3/06

Abstract: A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.