公开(公告)号：US20230242264A1

公开(公告)日：2023-08-03

申请号：US18098463

申请日：2023-01-18

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

CPC classification number: B64D27/10 ,  F01D5/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/04 ,  F02K3/06 ,  F02K3/068 ,  B64D2033/0286 ,  F05D2220/36

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：US20240317411A1

公开(公告)日：2024-09-26

申请号：US18675809

申请日：2024-05-28

Applicant: ROLLS-ROYCE plc

Inventor： Gareth M. ARMSTRONG ,  Nicholas HOWARTH

IPC: B64D27/10 ,  B64D33/02 ,  F01D5/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/04 ,  F02K3/06 ,  F02K3/068

CPC classification number: B64D27/10 ,  F01D5/28 ,  F02C3/04 ,  F02C3/06 ,  F02C3/107 ,  F02C7/04 ,  F02K3/06 ,  F02K3/068 ,  B64D2033/0286 ,  F05D2220/3215 ,  F05D2220/3219 ,  F05D2220/36 ,  F05D2260/40311

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：US20220412269A1

公开(公告)日：2022-12-29

申请号：US17731877

申请日：2022-04-28

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：US20230079630A1

公开(公告)日：2023-03-16

申请号：US17987516

申请日：2022-11-15

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：US20200248555A1

公开(公告)日：2020-08-06

申请号：US16743311

申请日：2020-01-15

Applicant: ROLLS-ROYCE plc

Inventor： Gareth M. ARMSTRONG ,  Michael P. KEENAN

IPC: F01D5/02

Abstract: The present disclosure relates to a metallic shaft for connecting components of a gas turbine engine. Example embodiments include a metallic shaft (400) for connecting components of a gas turbine engine, the shaft (400) having a longitudinal axis (410) and comprising: a first section (401) extending from a first end (403) of the shaft (400) to a joint (405), the first section (401) composed of a material having a first thermal expansion coefficient along the longitudinal axis (410); a second section (402) extending from a second opposing end (404) of the shaft to the joint (405), the second section (402) composed of a material having a second thermal expansion coefficient along the longitudinal axis (410) that is different to the first thermal expansion coefficient.