-
公开(公告)号：EP3882449B1
公开(公告)日：2024-09-11
申请号：EP21162962.1
申请日：2021-03-16
-
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
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：EP4417801A1
公开(公告)日：2024-08-21
申请号：EP24157898.8
申请日：2024-02-15
申请人： RTX Corporation
发明人： AVIDANE, Orin G. , AJAMI, Andre M. , WOOD, Coy Bruce , LINCOLN, David L. , KRAMER, Stephen K. , RAJAGOPALAN, Ramesh , MANTESE, Joseph V.
摘要： A combustion assembly (68) for a gas turbine engine (20) includes a combustor (40), a monochromator (128), and a photodetector assembly (122). The combustor (40) forms a combustion chamber (98). The monochromator (128) is disposed outside the combustion chamber (98). The monochromator (128) is configured to receive an optical input (130) from the combustion chamber (98) and direct an optical output (132). The optical input (130) has a range of light wavelengths. The optical output (132) has a subset of the range of light wavelengths. The photodetector assembly (122) is disposed outside the combustion chamber (98). The photodetector assembly (122) is configured to receive the optical output (132) from the monochromator (128) and generate an output signal representative of one or more optical characteristics of the optical output (132).
-
公开(公告)号：EP4194675B1
公开(公告)日：2024-07-17
申请号：EP22211920.8
申请日：2022-12-07
CPC分类号： F05D2260/82120130101 , F05D2270/301120130101 , F02C9/00 , F02C9/28
-
-
公开(公告)号：EP4363706A1
公开(公告)日：2024-05-08
申请号：EP22740435.7
申请日：2022-06-20
申请人： SAFRAN
-
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
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.
-
公开(公告)号：EP3994349B1
公开(公告)日：2024-04-17
申请号：EP20737131.1
申请日：2020-07-03
CPC分类号： F02K5/00 , F05D2220/7620130101 , F02C9/28 , F05D2270/0220130101 , F05D2270/31220130101 , Y02T50/60
-
9.发明公开
公开(公告)号：EP3418753A1
公开(公告)日：2018-12-26
申请号：EP18177655.0
申请日：2018-06-14
发明人： DJELASSI, Cedrik
CPC分类号： G01P3/4802 , F02C9/28 , F05D2220/323 , F05D2270/80 , G01P3/488 , G01P3/489
摘要： L'invention concerne un procédé de traitement d'un signal alternatif produit par un capteur à reluctance variable, comprenant des étapes de :
à partir d'un signal créneau brut commutant vers un niveau bas de tension, respectivement vers un niveau haut de tension, calcul d'un signal créneau traité, à l'aide d'une valeur de durée de maintien de commutation calculée en fonction d'une valeur de vitesse de rotation de l'arbre, et à partir du signal créneau brut,
mesure de la vitesse de rotation de l'arbre,
chaque commutation du signal créneau traité déclenchant le figeage du signal créneau traité, pendant une durée exactement égale à la durée de maintien de commutation,
de sorte que les commutations du signal créneau brut ne se traduisent pas par des commutations du signal créneau traité pendant ledit figeage, le signal créneau traité n'étant plus figé une fois la durée de maintien de commutation écoulée.-
公开(公告)号：EP3103969B1
公开(公告)日：2018-12-12
申请号：EP16172895.1
申请日：2016-06-03
CPC分类号： F01D21/14 , F01D21/003 , F01D21/04 , F01D21/045 , F01D21/06 , F02C3/04 , F02C9/28 , F02C9/46 , F02C9/48 , F04D27/001 , F04D27/0292 , F05D2260/80 , F05D2270/09 , F05D2270/101 , F05D2270/301 , F05D2270/304 , F05D2270/807
摘要： A gas turbine engine is provided with a controller configured to detect a spool shaft failure and to initiate an engine shut-down in response to the shaft failure. The controller evaluates the compressor speed probe, the speed probe continuity, P30 pressure and compressor surge to determine whether a shaft failure has occurred.
-
-
-
-
-
-
-
-
-
搜索结果
1153 条记录 (耗时 0.017 秒)
