公开(公告)号：US20200173364A1

公开(公告)日：2020-06-04

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 ,  F02C6/18 ,  F02C3/06

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：US20180010527A1

公开(公告)日：2018-01-11

申请号：US15637400

申请日：2017-06-29

Applicant: ROLLS-ROYCE plc

Inventor： Arthur L. ROWE

IPC: F02C9/28 ,  B64D33/02 ,  F02C9/24 ,  F02C7/057 ,  B64D15/20 ,  F02C7/047 ,  F01D25/02

CPC classification number: F02C9/28 ,  B64D15/20 ,  B64D33/02 ,  B64D2033/0233 ,  F01D25/02 ,  F02C7/047 ,  F02C7/057 ,  F02C9/00 ,  F02C9/24 ,  F05D2220/32 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/44

Abstract: A system for operating a gas turbine engine to mitigate the risk of ice formation within the engine, the system including a controller arranged to control at least one operational parameter of the engine such that the engine operates in a safe zone; and, a processor configured to function as a determining module to make a comparison between values and determine whether the engine is operating within a safe zone based on at least a core pressure parameter relating to the pressure within the engine and a core temperature parameter relating to the temperature within the engine, wherein the safe zone is defined by the product (multiplied) of the core pressure parameter and core temperature parameter being above a safe threshold.

公开(公告)号：US20170211486A1

公开(公告)日：2017-07-27

申请号：US15403025

申请日：2017-01-10

Applicant: ROLLS-ROYCE plc

Inventor： Arthur L. ROWE ,  Alexander MACDONALD

IPC: F02C9/28

CPC classification number: F02C9/28 ,  F02C9/46 ,  F05B2270/3013 ,  F05D2270/101 ,  F05D2270/301

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：US20200141330A1

公开(公告)日：2020-05-07

申请号：US16666928

申请日：2019-10-29

Applicant: ROLLS-ROYCE PLC

Inventor： Luis F. LLANO ,  Arthur L. ROWE

IPC: F02C9/18 ,  F02C3/073

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：US20200088595A1

公开(公告)日：2020-03-19

申请号：US16540173

申请日：2019-08-14

Applicant: ROLLS-ROYCE plc

Inventor： Ahmed M. Y. RAZAK ,  Arthur L. ROWE

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

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：US20190264701A1

公开(公告)日：2019-08-29

申请号：US16272156

申请日：2019-02-11

Applicant: ROLLS-ROYCE plc

Inventor： Arthur L. ROWE

IPC: F04D27/02 ,  F02C3/04

Abstract: A gas turbine engine compressor operating system for a gas turbine engine is disclosed. The gas turbine engine comprises a low pressure compressor and a high pressure compressor. The low and high pressure compressors are driven by low and high pressure shafts respectively, with the high pressure compressor being provided downstream in core mass flow of the low pressure compressor. The compressor operating system comprises a controller configured to control a variable geometry actuator of the low pressure compressor. The controller is configured to control the variable geometry actuator on the basis of low pressure compressor rotational speed (N1) and a high pressure compressor operating parameter such as one or more of core mass flow rate ({dot over (m)}), high pressure compressor pressure ratio (P30:P26), high pressure compressor rotational speed (N2), and high pressure compressor variable guide vane angle (α).