-
公开(公告)号：EP4420986A3
公开(公告)日：2024-10-30
申请号：EP24188514.4
申请日：2022-02-10
发明人： WU, Eric , VERMEIREN, Sébastien , SHORTTE, Maurice , MIRANDA, Pedro , LAVEAU, Benoit , RÖSICK, Joel
IPC分类号： F01D25/02 , F02C7/047 , F01D25/04 , F01D25/06 , F01D25/36 , F01D15/10 , F01D5/08 , F01D5/10 , B64D27/24
摘要： The present invention provides an electric aircraft engine. It also provides an aircraft, comprising such an electric aircraft engine. According to both a first aspect and a second aspect of the present invention, the electric aircraft engine comprises an electric motor with a rotor configured to be driven in rotation about a central axis, a fan having a central yoke mechanically coupled to the rotor for driving the fan and a plurality of fan blades projecting radially outwardly from the yoke, and an anti-icing and/or de-icing system to remove and/or prevent built-up of ice on the fan, said anti-icing and/or de-icing system comprising an electrical power source and a wireless energy transfer system for wirelessly transferring energy for anti-icing and/or de-icing from the electrical power source to the fan. In the first aspect of the present invention, the electric motor comprises an electromagnetically excited resolver for determining an angular position of the rotor of the electric motor, and an anti-icing and/or de-icing control unit is configured to induce losses by adding a high-power, highfrequency component of current and flux to the normal excitation signals of the resolver, thereby heating up the resolver. In the second aspect of the present invention, the wireless energy transfer system consists of two coils, a transmitter coil electrically coupled to the electrical power source and a receiver coil thermally connected to the fan, the energy being transmitted wirelessly by induction via an air gap from the transmitter coil to the receiver coil.
-
公开(公告)号：EP4355656A1
公开(公告)日：2024-04-24
申请号：EP22741346.5
申请日：2022-06-15
申请人： Safran Nacelles
CPC分类号： B64D2033/023320130101 , B64D15/163 , F01D25/02
-
公开(公告)号：EP4123127A1
公开(公告)日：2023-01-25
申请号：EP22185814.5
申请日：2022-07-19
发明人： RIVERIN, Guy
IPC分类号： F01D25/02
摘要： A turbofan engine has a fan (12) drivingly engaged by a shaft for rotation about a rotation axis and having: fan blades (21, 121, 221) circumferentially distributed about the rotation axis and drivingly engaged by the shaft; an ice-accruing feature (F, F1, F2) located on a surface of the fan (12) exposed to an air flow flowing between the fan blades (21, 121, 221), the ice-accruing feature (F, F1, F2) having a shape providing a non-axisymmetric ice accumulation on the fan (12) to create a rotational imbalance; a balancing feature (B) secured to the fan (12) or to the shaft to counteract the ice-accruing feature (F, F1, F2) such that the fan (12) is rotationally balanced when the fan (12) is free of ice, the balancing feature (B) being located such as to be outside the air flow; an aircraft controller (40); and a sensor (30) operatively connected to the fan (12) and operable to send a signal to the aircraft controller (40), the signal indicative of the rotational imbalance caused by the ice-accruing feature (F, F1, F2).
-
-
公开(公告)号：EP4019756A1
公开(公告)日：2022-06-29
申请号：EP21214629.4
申请日：2021-12-15
摘要： An anti-icing system (38) for a gas turbine system (10) includes multiple nozzle assemblies (52). Each nozzle assembly (52) of the multiple nozzle assemblies (52) includes a nozzle (40) having one or more outlets (102) that are configured to inject a heated fluid in a radial outward direction and a cap (44) having an annular wall (112) that circumferentially surrounds at least a portion of the nozzle (40). The cap (44) is configured to direct the heated fluid to flow in an upstream direction into an airflow (34) to facilitate mixing of the heated fluid with the airflow (34).
-
公开(公告)号：EP3981970A1
公开(公告)日：2022-04-13
申请号：EP21200618.3
申请日：2021-10-04
申请人： Rolls-Royce plc
发明人： Bradbrook, Stephen , Goodhand, Martin , Hield, Paul , Parsley, Andrew , Wong, Natalie , Corin, Robert , Binnington, Thomas
摘要： A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module comprises a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes, and a set of channel airflows through each of the channels. Each vane airflow has a vane mass flow rate Flow Vane ,, and each channel air flow has a channel mass flow rate Flow Chan . Each of the hollow vanes accommodates at least one heat transfer element for the transfer of heat from a first fluid contained within the or each heat transfer element to the corresponding vane airflow passing over a surface of the or each heat transfer element.
Each hollow vane comprises, in axial flow sequence, an inlet portion, a heat transfer portion, and an exhaust portion, with the inlet portion comprising a diffuser element, and the heat transfer portion comprising at least one heat transfer element. The diffuser element is configured to cause the vane mass flow rate Flow Vane to be lower than the channel mass flow rate Flow Chan by a user-defined margin.-
公开(公告)号：EP3981968A1
公开(公告)日：2022-04-13
申请号：EP21198481.0
申请日：2021-09-23
申请人： Rolls-Royce plc
发明人： Bradbrook, Stephen J , Goodhand, Martin N , Hield, Paul M , Parsley, Andrew , Wong, Natalie C , Corin, Robert J , Binnington, Thomas S
摘要： A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module comprises a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels. Each vane airflow having a vane mass flow rate Flow Vane , and each channel air flow has a channel mass flow rate Flow Chan . At least one of the hollow vanes accommodates at least one heat transfer element for the transfer of heat from a first fluid contained within the or each heat transfer element to the or each corresponding vane airflow passing over a surface of the or each heat transfer element.
In use, a Vane Airflow Ratio parameter V AR is defined as: VAR = Flow VaneTot Flow ChanTot where:
Flow VaneTot = total mass flow rate of the vane mass flow rates, Flow Vane ; and
Flow ChanTot = total mass flow rate of the channel mass flow rates, Flow Chan ; and the V AR parameter is in the range of 0.05 to 3.0.-
-
公开(公告)号：EP3071814B1
公开(公告)日：2021-05-05
申请号：EP14863876.0
申请日：2014-10-21
-
公开(公告)号：EP3708850A1
公开(公告)日：2020-09-16
申请号：EP20157733.5
申请日：2020-02-17
申请人： Rolls-Royce plc
发明人： Bousfield, Ian , MacDougall, Duncan
摘要： The present invention relates to a core duct assembly (43) for a gas turbine engine (10), the assembly comprising: a core duct (44) with an outer wall (48) having an interior surface (52) and an inner wall (46), a vane (54) extending between said inner and outer walls and at least one rotor blade (56) located downstream of the vane, the rotor blade extending between a platform (56c) and a tip (56d). An upstream wall axis (102) is defined as an axis tangential to a point on a first portion (62) of the interior surface (52) of the outer wall (52) of the core duct (44) extending downstream from the vane (54) and wherein the upstream wall axis intersects the rotor blade (56) at a point spaced radially inward by a distance (c) from the rotor blade tip (56d). Thus, rotor damages due to shed ice are mitigated.
-
-
-
-
-
-
-
-
-
搜索结果
300 条记录 (耗时 0.023 秒)
