公开(公告)号：EP4193051B1

公开(公告)日：2024-08-07

申请号：EP22757312.8

申请日：2022-07-21

IPC分类号： F02D31/00 ,  B64C29/00 ,  B64C39/02 ,  B64D27/02 ,  B64D33/04 ,  B64C17/00 ,  B64D27/20 ,  B64D31/06 ,  B64D31/10 ,  F02K1/11 ,  F02K1/15 ,  F02K1/40 ,  B64C17/02 ,  B64D27/24

CPC分类号： F02D31/002 ,  F02D2250/2420130101 ,  B64C39/026 ,  B64D27/02 ,  F02K1/11 ,  F02K1/15 ,  F02K1/40 ,  F05D2270/05120130101 ,  F05D2270/0220130101 ,  F05D2270/1220130101 ,  B64D33/04 ,  B64C17/00 ,  B64D27/20 ,  B64D31/06 ,  B64D31/10 ,  B64C29/0058 ,  B64C29/0025 ,  B64C17/02 ,  B64D27/24

公开(公告)号：EP4421294A1

公开(公告)日：2024-08-28

申请号：EP23216566.2

申请日：2023-12-14

申请人： General Electric Company

发明人： SCHELFAUT, Timothy ,  KASBERG, Timothy ,  HOOPER, Tyler ,  RUFO, Massimo ,  GRAZIANO, Kevin ,  LEEKER, Brendon

IPC分类号： F01D15/10 ,  F02C7/36 ,  F02C9/00 ,  F02C6/00

CPC分类号： F02C6/00 ,  F02C7/36 ,  F02C9/56 ,  F02C9/00 ,  F02C9/54 ,  F05D2220/7620130101 ,  F01D15/10 ,  F01D11/20 ,  F05D2270/05120130101

摘要： A hybrid-electric gas turbine engine and method of operating includes independently controlling a first electric machine providing torque to a first shaft to maintain a desired clearance between a first set of blades rotatably coupled to the first shaft, and a casing.

公开(公告)号：EP4421301A1

公开(公告)日：2024-08-28

申请号：EP24153047.6

申请日：2024-01-22

申请人： Rolls-Royce plc

发明人： Horobin, Marcus S

IPC分类号： F02C9/28 ,  F02K3/10

CPC分类号： F02C9/28 ,  F02K3/10 ,  F05D2270/30120130101 ,  F05D2270/05120130101 ,  F05D2220/1020130101 ,  F05D2270/70820130101 ,  F05D2270/301520130101

摘要： A method (600) of thrust control for an airbreathing jet engine (50). The method comprises obtaining a demanded thrust setting, obtaining a value of static pressure at a first axial location (35) of a combustion chamber (30) of the airbreathing jet engine (50) and obtaining a value of static pressure at a second axial location (36) of the combustion chamber (30) of the airbreathing jet engine (50). The second axial location (36) is downstream of the first axial location (35). The method also comprises obtaining a ratio of the value of static pressure at the first axial location (35) of the combustion chamber to the value of static pressure at the second axial location (36) of the combustion chamber; and controlling a fuel flow rate of the airbreathing engine (50) based at least in part on the demanded thrust setting and the ratio of the value of the static pressure at the first axial location (35) to the value of the static pressure at the second axial location (36).

公开(公告)号：EP4368824A1

公开(公告)日：2024-05-15

申请号：EP23192829.2

申请日：2018-06-18

申请人： General Electric Company

发明人： HON, Robert Charles ,  GANSLER, Michael Thomas

IPC分类号： F02C6/14 ,  B60K6/24 ,  F02K5/00 ,  F02C7/32

CPC分类号： F02K5/00 ,  F02C6/14 ,  F02C7/32 ,  F05D2270/10120130101 ,  F05D2260/4220130101 ,  F05D2270/05120130101 ,  F05D2220/7620130101 ,  F05D2270/30320130101 ,  Y10S903/903 ,  Y02T50/60 ,  B64D27/026

摘要： A hybrid-electric propulsion system 50 includes a turbomachine 102 and an electric machine 56 coupled to the turbomachine 102. A method for operating the hybrid-electric propulsion system 50 includes receiving information indicative of an operability parameter of the turbomachine 102; determining the turbomachine 102 is operating within a predetermined operability range based at least in part of the received information indicative of the operability parameter of the turbomachine 102; and operating the hybrid electric propulsion system 50 in an electric generation mode to generate electric power with the electric machine 56 in response to determining the turbomachine 102 is operating within the predetermined operability range.

公开(公告)号：EP4361426A1

公开(公告)日：2024-05-01

申请号：EP23206774.4

申请日：2023-10-30

申请人： PRATT & WHITNEY CANADA CORP.

发明人： POISSANT, Jeffrey ,  PONTARELLI, Robert ,  CRAINIC, Cristina

IPC分类号： F02C9/28

CPC分类号： F02C9/28 ,  F05D2260/8120130101 ,  F05D2260/8020130101 ,  F05D2270/05120130101 ,  F05D2270/30420130101 ,  F05D2270/7120130101

摘要： A method and system for correlating engine thrust and engine thrust lever angle (TLA) during operation of a gas turbine engine powered aircraft is provided. The method includes: a) providing current flight conditions including a Mach number of the aircraft, altitude of the aircraft, and a TLA; b) determining a corrected fan speed value based on a sensed fan speed and flight conditions; c) determining a first corrected net thrust value based on the corrected fan speed value and the Mach number; d) determining a compensation factor using the corrected fan speed value, the Mach number, and the corrected net thrust value; e) determining a second corrected net thrust value as a function of the TLA; and f) correlating an engine fan speed to the TLA using the second corrected net thrust value as a function of the TLA and the compensation factor.