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：US10605174B2

公开(公告)日：2020-03-31

申请号：US15403025

申请日：2017-01-10

Applicant: ROLLS-ROYCE plc

Inventor： Arthur L Rowe ,  Alexander MacDonald

IPC: F02C9/28 ,  F02C9/46

Abstract: A method (30) of controlling fuel flow in a gas turbine engine. First, detect a surge condition. Set fuel flow demand (Wf_D) proportional to compressor discharge pressure (P30). Detect actual fuel flow (Wf_A). Then apply an enhanced schedule (50) for fuel flow demand (Wf_D) while fuel flow demand (Wf_D) is less than a predefined proportion (k) of actual fuel flow (Wf_A). Also a gas turbine engine (10), fuel flow system (68) and fuel flow control system (76) each implementing the method (30).

公开(公告)号：US10859003B2

公开(公告)日：2020-12-08

申请号：US16666928

申请日：2019-10-29

Applicant: ROLLS-ROYCE PLC

Inventor： Luis F Llano ,  Arthur L Rowe

IPC: F02C9/18 ,  F02C9/20 ,  F01D17/16 ,  F02C7/36 ,  F02K3/06

Abstract: A control system for a gas turbine engine includes an engine core, the engine core including combustion equipment, a turbine, a compressor, and a core shaft connecting the turbine to the compressor. The control system includes at least one variable stator vane for controlling the angle at which gas enters the engine core, and there is a bypass passage within the engine core for directing gas flow to bypass the combustion equipment.

公开(公告)号：US10392962B2

公开(公告)日：2019-08-27

申请号：US15620163

申请日：2017-06-12

Applicant: ROLLS-ROYCE plc

Inventor： Arthur L Rowe ,  Mark N Binnington ,  Colin J Woodward ,  Paul R Thornton

IPC: F01D21/00 ,  F02C9/00 ,  F04D27/00 ,  G01P3/46 ,  G01H1/00 ,  F01D21/04

Abstract: A rotor assembly (30) comprising a rotor (32) having an annular array of rotor blades (34), the rotor mounted to a shaft (38). A phonic wheel (40) coupled to the shaft. A speed sensor (44) axially aligned with the phonic wheel and configured to measure voltage (V), amplitude of the voltage being proportional to clearance (46) between the sensor and phonic wheel. A processor (48) configured to: receive the voltage measurement; derive shaft speed (ω) from the voltage measurement; identify modulation of the voltage amplitude at a frequency which is an integer multiple of the shaft speed; compare voltage amplitude to a threshold; and output a rotor damage signal based on the comparison.

公开(公告)号：US11187161B2

公开(公告)日：2021-11-30

申请号：US16798607

申请日：2020-02-24

Applicant: ROLLS-ROYCE plc

Inventor： Arthur L Rowe ,  Alexander MacDonald

IPC: F02C9/28 ,  F02C9/46

Abstract: A fuel flow control system is configured to perform a method including: setting a fuel flow demand proportional to compressor discharge pressure; detecting an actual fuel flow; and applying an enhanced schedule for fuel flow demand while fuel flow demand is less than a predefined proportion of actual fuel flow.

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.