-
公开(公告)号：EP3597895A1
公开(公告)日：2020-01-22
申请号：EP19181975.4
申请日：2019-06-24
申请人： Rolls-Royce plc
发明人： Corin, Robert , Whurr, John
摘要： A turbofan engine for providing propulsive thrust to a supersonic aircraft is provided. The engine has an engine core comprising in flow series a compressor, a combustor and a turbine. The engine further has a fan located upstream of the engine core. The engine further has a supersonic intake for slowing down incoming air to subsonic velocities at an inlet to the fan formed by the intake. The engine further has a bypass duct surrounding the engine core, wherein the fan generates a core airflow to the engine core and a bypass airflow through the bypass duct. The engine further has a mixer for mixing an exhaust gas flow exiting the engine core and the bypass airflow exiting the bypass duct. The engine further has a thrust nozzle rearwards of the mixer for discharging the mixed flows. The engine further has a controller configured to control the thrust produced by the engine over a range of flight operations including relatively high thrust transonic push operation during which the aircraft transitions from subsonic to supersonic flight and relatively low thrust supersonic cruise operation. To change the level of engine thrust between the transonic push operation and the supersonic cruise operation, the controller varies an area of a variable area throat of the thrust nozzle and/or adjusts one or more components which vary the relative areas available for the hot exhaust gas flow and the cold bypass airflow at the mixer while holding the fan inlet non-dimensional mass flow w T / P substantially constant, where w is the mass flow of the incoming air at the fan inlet, T is stagnation temperature of the incoming air at the fan inlet and P is stagnation pressure of the incoming air at the fan inlet.
-
公开(公告)号：EP3597894A1
公开(公告)日：2020-01-22
申请号：EP19182551.2
申请日：2019-06-26
申请人： Rolls-Royce plc
发明人： Whurr, John , Hickey, Conor
摘要： The present disclosure relates to a turbofan engine having: an engine core having a centre axis and comprising in flow series a compressor, a combustor and a turbine; and a bypass duct surrounding the engine core, the bypass duct having a bypass duct exit area (A COLD ) at its downstream end. The engine further comprises an exhaust nozzle assembly comprising: coaxially arranged inner mixer and outer exhaust nozzles, the exhaust nozzle being axially downstream of said mixer nozzle; a core flow duct defined by the mixer nozzle, the core flow duct having a core exit area (A HOT ); and an exhaust duct defined at least in part by the exhaust nozzle downstream of the mixer nozzle, the exhaust duct having an exhaust throat area (A 8 ). The bypass duct exit area (A COLD ) and core exit area (A HOT ) are axially aligned at a mixing plane to form a mixing plane area (A MIX ). The turbofan engine has a transonic thrust condition, a supersonic cruise condition and a take-off condition. In the supersonic cruise condition, the exhaust throat area (A 8 ) is increased relative to the exhaust throat area (A 8 ). In the take-off condition, the core exit area (A HOT ) is increased relative to the core exit area (A HOT ) in the transonic condition, and the bypass duct exit area (A COLD ) is decreased relative to the bypass duct exit area (A COLD ) in the transonic condition.
-
公开(公告)号：EP3636906A1
公开(公告)日：2020-04-15
申请号：EP19197014.4
申请日：2019-09-12
申请人： Rolls-Royce plc
摘要： A turbofan engine, an afterburner system, and a method of operating a turbofan engine are provided. The turbofan engine has: an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor, and producing a core exhaust flow; a fan upstream of the engine core; a bypass duct surrounding the engine core and carrying a bypass air flow produced by the fan; an exhaust assembly comprising a first exhaust nozzle defining a downstream end of a first core flow duct which receives the core exhaust flow produced by the engine core. The turbofan engine further has an afterburner system comprising: a core plug defining a radially inner surface of the first core flow duct; a second core flow duct located in the core plug, and having one or more entrances from the first core flow duct for diversion into the second core flow duct of a portion of the core exhaust flow, and further having an exit therefrom for re-joining the diverted portion of the core exhaust flow to the undiverted portion of the core exhaust flow; one or more respective doors for the entrances to the second core flow duct, the doors being open during normal operation of the engine but being closable, during a reheat operation, to at least partially block the entrances to the second core flow duct; and one or more fuel injectors and one or more respective igniters operable, during the reheat operation, to respectively inject and ignite fuel within the second core flow duct, thereby providing a reheat flow into the core exhaust flow from the exit of the second core flow duct.
-
公开(公告)号：EP3179085A1
公开(公告)日：2017-06-14
申请号：EP16197708.7
申请日：2016-11-08
申请人： Rolls-Royce plc
发明人： Whurr, John , Richards, Martyn
CPC分类号： F01D7/00 , B64C11/32 , F01D5/146 , F02K3/06 , F04D29/323 , F04D29/388 , F05D2220/36 , F05D2240/30 , F05D2260/70 , Y02T50/673
摘要： A gas turbine engine fan blade apparatus is disclosed comprising a reverse pitch rotatable mounting and an aerofoil part. The aerofoil part comprises radially inner and radially outer portions that are separated by an interface extending from a leading edge of the aerofoil part to a trailing edge of the aerofoil part. The reverse pitch rotatable mounting locates the radially inner and radially outer portions with respect to one another. The reverse pitch rotatable mounting and separation at the interface permit relative pitch change rotation between the radially inner and radially outer portions such that one of the radially inner and radially outer portions is rotatable to a reverse pitch configuration by comparison with the other portion.
摘要翻译： 公开了一种燃气涡轮发动机风扇叶片装置，其包括反向变桨可旋转支架和翼型部分。 机翼部分包括由从机翼部分的前缘延伸到机翼部分的后缘的界面分隔的径向内部和径向外部。 反向间距可旋转安装将径向内部和径向外部相对于彼此定位。 在接口处的反向节距可旋转安装和分离允许径向内部和径向外部之间的相对节距改变旋转，使得径向内部和径向外部中的一个通过与另一部分相比可旋转到反向节距构造。
-
公开(公告)号：EP4350138A3
公开(公告)日：2024-07-03
申请号：EP24159731.9
申请日：2021-09-13
申请人： Rolls-Royce plc
发明人： Palmer, Chloe , Whurr, John
CPC分类号： F23R2900/0000220130101 , F23R3/50 , F23R3/283 , Y02T50/678 , F02C3/22 , F02C3/20 , F02C7/143 , F02C7/224 , F02C9/40 , F05D2260/21320130101 , F02C9/26
摘要： A complex cycle gas turbine engine (103) for an aircraft with hydrogen fuel supply. The gas turbine engine comprises, in fluid flow series, a core gas turbine (105) and a recuperator (701) for heating hydrogen fuel prior to combustion by turbine exhaust products.
-
公开(公告)号：EP4350138A2
公开(公告)日：2024-04-10
申请号：EP24159731.9
申请日：2021-09-13
申请人： Rolls-Royce plc
发明人： Palmer, Chloe , Whurr, John
IPC分类号： F02C9/26
摘要： A complex cycle gas turbine engine (103) for an aircraft with hydrogen fuel supply. The gas turbine engine comprises, in fluid flow series, a core gas turbine (105) and a recuperator (701) for heating hydrogen fuel prior to combustion by turbine exhaust products.
-
公开(公告)号：EP3978737A1
公开(公告)日：2022-04-06
申请号：EP21196323.6
申请日：2021-09-13
申请人： Rolls-Royce plc
发明人： Palmer, Chloe , Whurr, John
摘要： A complex cycle gas turbine engine (103) for an aircraft with hydrogen fuel supply comprises, in fluid flow series, a core gas turbine (105) and a recuperator (701) for heating hydrogen fuel prior to combustion by turbine exhaust products.
-
公开(公告)号：EP3179085B1
公开(公告)日：2018-07-11
申请号：EP16197708.7
申请日：2016-11-08
申请人： Rolls-Royce plc
发明人： Whurr, John , Richards, Martyn
CPC分类号： F01D7/00 , B64C11/32 , F01D5/146 , F02K3/06 , F04D29/323 , F04D29/388 , F05D2220/36 , F05D2240/30 , F05D2260/70 , Y02T50/673
摘要： A gas turbine engine fan blade apparatus is disclosed comprising a reverse pitch rotatable mounting and an aerofoil part. The aerofoil part comprises radially inner and radially outer portions that are separated by an interface extending from a leading edge of the aerofoil part to a trailing edge of the aerofoil part. The reverse pitch rotatable mounting locates the radially inner and radially outer portions with respect to one another. The reverse pitch rotatable mounting and separation at the interface permit relative pitch change rotation between the radially inner and radially outer portions such that one of the radially inner and radially outer portions is rotatable to a reverse pitch configuration by comparison with the other portion.
-
-
-
-
-
-
-
搜索结果
8 条记录 (耗时 0.011 秒)
