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：US20230323810A1

公开(公告)日：2023-10-12

申请号：US18184008

申请日：2023-03-15

Applicant: ROLLS-ROYCE plc

Inventor： Christopher A. MURRAY ,  Nicholas HOWARTH ,  Richard G. STRETTON

IPC: F02C6/08 ,  B64D13/06

CPC classification number: F02C6/08 ,  B64D13/06 ,  B64D2013/0618 ,  F05D2260/205 ,  F05D2220/323

Abstract: There is provided a gas turbine engine comprising a blower system for supplying pressurised air to an airframe via an airframe port. The blower system comprises a compressor configured to receive air from a bypass duct or a core of the gas turbine engine and to discharge compressed air into a delivery line extending from the compressor to the airframe port. The blower system also comprises a heat exchanger configured to transfer heat from the compressed air to a coolant and a valve arrangement configured to switch between operation of the blower system in a baseline mode and a cooling mode, the valve arrangement being configured to: selectively divert the compressed air within the delivery line to the heat exchanger for operation in the cooling mode; and/or selectively provide the coolant to the heat exchanger for operation in the cooling mode.

公开(公告)号：US20230130991A1

公开(公告)日：2023-04-27

申请号：US17818818

申请日：2022-08-10

Applicant: ROLLS-ROYCE plc

Inventor： Nicholas HOWARTH

IPC: F01D9/04 ,  G01B7/30 ,  F01D21/00

Abstract: A compressor variable angle measurement system for guiding the positioning variable vanes supported on a penny of a compressor of a gas turbine engine. The system comprising a gauge assembly that is connectable to a computing device. the gauge assembly comprises a base plate and a clamp arm. The gauge assembly is configured to removably grip a variable vane between three vane contact portions of the baseplate and the vane contact portion of the clamp arm and on the leading edge vane engaging portion and the trailing edge vane engaging portion of the base plate, the stagger angle of the variable vane with respect to the radial setting pin being determined by the computing device from measurements made by an inertial measurement unit.

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：US20150308353A1

公开(公告)日：2015-10-29

申请号：US14688423

申请日：2015-04-16

Applicant: ROLLS-ROYCE PLC

Inventor： Alasdair GARDNER ,  Arthur Laurence ROWE ,  Mark David TAYLOR ,  Nicholas HOWARTH

IPC: F02C9/22 ,  F02C7/36 ,  F02C6/00

CPC classification number: F02C9/22 ,  F01D17/162 ,  F02C6/00 ,  F02C7/36 ,  F02C9/20 ,  F02C9/54 ,  F05D2220/32 ,  F05D2220/76 ,  F05D2270/05 ,  F05D2270/06 ,  F05D2270/303 ,  F05D2270/304 ,  Y02T50/671

Abstract: An engine that has, in axial flow series, booster compressor, core compressor, combustion equipment, core turbine, and low-pressure turbine. Core turbine drives core compressor via an interconnecting high-pressure shaft. Low-pressure turbine drives booster compressor via an interconnecting low-pressure shaft. Low-pressure turbine also drives external load having a defined speed characteristic that dictates speed of the low-pressure turbine and booster compressor. Booster compressor has one or more rows of variable stator vanes. The method includes: scheduling variation in the angle of variable stator vanes as a function of speed of the booster compressor wherein the vanes open as booster compressor speed increases; measuring or setting one or more operational parameters which are determinative of temperature at entry to core turbine; and biasing scheduling of angle variation of variable stator vanes as a function of operational parameter(s) to reduce variation in temperature at entry to core turbine.

Abstract translation: 具有轴流式系列的增压压缩机，核心压缩机，燃烧设备，核心涡轮机和低压涡轮机的发动机。 核心涡轮机通过互连的高压轴驱动核心压缩机。 低压涡轮机通过互连低压轴驱动增压压缩机。 低压涡轮机还驱动具有限定低速涡轮机和增压压缩机的速度的限定速度特性的外部负载。 增压压缩机具有一排或多排可变定子叶片。 该方法包括：根据增压压缩机的速度调整可变定子叶片的角度变化，其中当增压压缩机转速增加时叶片打开; 测量或设定一个或多个确定进入核心涡轮机时的温度的操作参数; 并且可变定子叶片的角度变化的偏置调度作为操作参数的函数，以减少进入核心涡轮机时的温度变化。