公开(公告)号：US11149647B2

公开(公告)日：2021-10-19

申请号：US16679568

申请日：2019-11-11

Applicant: ROLLS-ROYCE plc

Inventor： Stephen M. Husband ,  Ahmed M Y Razak ,  Paul R. Miller

IPC: F02C7/26 ,  F02C3/06 ,  F02C9/22 ,  F04D27/00

Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: increasing an angular velocity of a low pressure compressor; determining if an exit pressure of the low pressure compressor is equal to or greater than a first threshold pressure; in response to determining that the exit pressure of the low pressure compressor is equal to or greater than the first threshold pressure, controlling rotation of the low pressure compressor using a first electrical machine and controlling rotation of a high pressure compressor using a second electrical machine, to increase angular velocity of the high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a second threshold pressure.

公开(公告)号：US11518530B2

公开(公告)日：2022-12-06

申请号：US15984557

申请日：2018-05-21

Applicant: ROLLS-ROYCE plc

Inventor： Ahmed M Y Razak

IPC: B64D27/24 ,  F04D25/06 ,  B64D33/00 ,  B64D27/10 ,  B64D27/02 ,  F04C2/344 ,  F01D15/10 ,  H02K5/124

Abstract: A propulsor (101) for an aircraft is shown. The propulsor comprises a propulsive fan (106), and an electric machine (108) configured to drive the propulsive fan. The electric machine has a casing containing electrical and electromechanical components, a shaft which extends outside of the casing and which is connected to the propulsive fan, and a seal to seal the casing around the shaft. A depressurisation system depressurises the casing below an external pressure to prevent electrical breakdown within gas in the casing of the electric machine.

公开(公告)号：US11187150B2

公开(公告)日：2021-11-30

申请号：US16694134

申请日：2019-11-25

Applicant: ROLLS-ROYCE plc

Inventor： Ahmed M Y Razak ,  Arthur L Rowe

IPC: F02C7/10 ,  F01D13/02 ,  F02C3/06 ,  F02C6/18 ,  F01D25/10

Abstract: A combined cycle heat engine (10). The engine (10) comprises a first gas turbine engine (11) comprising a first air compressor system (14), a first combustion system (16) and a first turbine system (18) and a second gas turbine engine (32) comprising a second air compression system (36), a second turbine system (40), and a heat exchanger (38) configured to transfer heat from an exhaust (24) of the first turbine system (18) to compressed air from the second air compressor (36). The second gas turbine engine (32) comprises a second combustion system (20) downstream of the heat exchanger (38) and upstream of the second turbine system (40).

公开(公告)号：US10794330B2

公开(公告)日：2020-10-06

申请号：US15810263

申请日：2017-11-13

Applicant: ROLLS-ROYCE plc

Inventor： Ahmed M Y Razak ,  Paul Fletcher

IPC: F02C6/00 ,  F02C7/36 ,  F02K3/11 ,  F02K3/08 ,  F02C3/14 ,  F02C3/113 ,  F02K1/06 ,  F02K1/38 ,  F02K3/077 ,  F02K3/10 ,  F02K3/06

Abstract: A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow. A low pressure turbine may be provided downstream of the re-heat combustor and coupled to the low pressure compressor (14) by a low pressure shaft, the low pressure and high pressure shafts being independently rotatable. A shaft power transfer arrangement may be provided, which is configured to selectively transfer power between the low pressure and high pressure shafts.

公开(公告)号：US11365684B2

公开(公告)日：2022-06-21

申请号：US16679562

申请日：2019-11-11

Applicant: ROLLS-ROYCE plc

Inventor： Stephen M. Husband ,  Ahmed M Y Razak ,  Paul R. Miller

IPC: F02C7/26 ,  F02C7/262 ,  F02C7/275

Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: determining when a flame in a combustion chamber of a gas turbine engine is extinguished, during a start-up process or re-light process or during operation; purging the combustion chamber by controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; and controlling rotation of the low pressure compressor using the first electrical machine, and controlling rotation of the high pressure compressor using the second electrical machine to restart the start-up process or perform the re-light process.

公开(公告)号：US11175195B2

公开(公告)日：2021-11-16

申请号：US16540173

申请日：2019-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Ahmed M Y Razak ,  Arthur L Rowe

IPC: G01M15/14 ,  G01L5/13 ,  G01L5/00 ,  F02C7/36 ,  B64F5/60

Abstract: An apparatus measuring thrust of an aircraft gas turbine engine includes a core shaft connecting a turbine and compressor, a fan and gearbox with a sun gear driven by the core shaft, a plurality of planet gears, an annulus gear mounted in a static structure, and a planet carrier driven by the fan via fan shaft. The apparatus includes a sensor to measure force applied by the annulus gear on the static structure and first and second sensors to measure rotational speed of the core and fan shafts. A processor determines restoring torque on the annulus gear from measurement of force applied by the gear on the static structure, torque applied to the fan by the planet carrier using rotational speeds of core and fan shafts and restoring torque on the annulus gear, and thrust of the fan from torque applied to the fan and the fan's rotational speed.

公开(公告)号：US11149648B2

公开(公告)日：2021-10-19

申请号：US16679576

申请日：2019-11-11

Applicant: ROLLS-ROYCE plc

Inventor： Stephen M. Husband ,  Ahmed M Y Razak ,  Paul R. Miller

IPC: F02C7/262 ,  F02C7/266

Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling ignition within a combustion chamber of the gas turbine engine; controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a self-sustaining threshold pressure; and in response to determining that the exit pressure of the high pressure compressor is equal to or greater than the self-sustaining threshold pressure, ceasing controlling rotation of the low pressure compressor using the first electrical machine, and/or the high pressure compressor using a second electrical machine.