-
公开(公告)号：EP4148238A1
公开(公告)日：2023-03-15
申请号：EP22204820.9
申请日：2017-08-10
摘要： A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.
-
公开(公告)号：EP3199839B1
公开(公告)日：2020-02-26
申请号：EP17152870.6
申请日：2017-01-24
-
公开(公告)号：EP3199768B1
公开(公告)日：2020-02-26
申请号：EP17153200.5
申请日：2017-01-26
发明人： NIERGARTH, Daniel Alan , MILLER, Brandon Wayne , ERTAS, Bugra Han , BRADLEY, Donald Albert , DICKMAN, Joseph Robert
IPC分类号： F01D25/16 , F02K3/06 , F02C7/36 , F16H1/28 , F16H57/028
-
公开(公告)号：EP3176379B1
公开(公告)日：2019-09-04
申请号：EP16200477.4
申请日：2016-11-24
-
公开(公告)号：EP3124770B1
公开(公告)日：2019-05-22
申请号：EP16171821.8
申请日：2016-05-27
-
公开(公告)号：EP3428424A1
公开(公告)日：2019-01-16
申请号：EP18182064.8
申请日：2018-07-05
发明人： CLEMENTS, Jeffrey Donald , ZATORSKI, Darek Tomasz , MILLER, Brandon Wayne , DICKMAN, Joseph Robert
摘要： The present disclosure is directed to a gas turbine engine 10 defining a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine 10 includes a power turbine 100 including a first turbine rotor assembly 110 interdigitated with a second turbine rotor assembly 120 along the longitudinal direction; a gear assembly 300 coupled to the first turbine rotor assembly 110 and the second turbine rotor assembly 120, wherein the gear assembly 300 includes a first input interface 310 coupled to the first turbine rotor assembly 110, a second input interface 320 coupled to the second turbine rotor assembly 120, and one or more third gears 330 coupled to the first input interface 310 and the second input interface 320 therebetween; and a first output shaft 121 and a second output shaft 122, wherein each of the first output shaft 121 and the second output shaft 122 are configured to couple to an electrical load device.
-
公开(公告)号：EP3144226B1
公开(公告)日：2018-11-21
申请号：EP16188786.4
申请日：2016-09-14
IPC分类号： B64D27/08 , B64D27/14 , B64D29/04 , B64D27/20 , B64C21/06 , B64D29/00 , B64D27/26 , B64D33/02
CPC分类号： B64D27/14 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/00 , B64D29/04 , B64D2027/264 , B64D2033/0226
摘要： A propulsion system for an aircraft (10) is provided having an aft engine configured to be mounted to the aircraft (10) at an aft end of the aircraft (10). The aft engine includes a fan (304) rotatable about a central axis of the aft engine having a plurality of fan blades (310). The aft engine also includes a nacelle (306) encircling the plurality of fan blades (310) with one or more structural members (308) extending between the nacelle (306) and the mean line (15) of the aircraft (10) at a location forward of the plurality of fan blades (310) when the aft engine is mounted to the aircraft (10). The aft engine may increase a net thrust of the aircraft (10) when mounted to the aircraft (10).
-
公开(公告)号：EP3381797A1
公开(公告)日：2018-10-03
申请号：EP18163637.4
申请日：2018-03-23
发明人： MILLER, Brandon Wayne , VONDRELL, Randy M. , MARRINAN, Patrick Michael , GEMIN, Paul Robert , MOORE, Nicholas Taylor
摘要： An aeronautical propulsion system (50) defining a central axis and comprising:a fan (104) having a plurality of fan blades (128) rotatable about the central axis and defining a fan pressure ratio, FPR; andan electric motor (136) mechanically coupled to the fan (104) for driving the fan (104), the electric motor (136) comprising a number of poles (154), and defining a maximum power;wherein the relationship between the fan pressure ratio (104), the number of poles (154) of the electric motor (136), and the maximum power of the electric motor (136) is defined by an equation.
-
公开(公告)号：EP3354889A1
公开(公告)日：2018-08-01
申请号：EP18153271.4
申请日：2018-01-24
发明人： MILLER, Brandon Wayne , POLAKOWSKI, Matthew Ryan , MARRINAN, Patrick Michael , KIRK, Joel Francis , VONDRELL, Randy M. , CLEMENTS, Jeffrey Donald
CPC分类号： F02K3/06 , F01D25/26 , F02C3/04 , F02C7/18 , F02C7/36 , F05D2220/36 , F05D2300/20 , Y02T50/672
摘要： A turbofan engine 10 is provided including a fan 38 having a plurality of rotatable fan blades 40 and defining a fan pressure ratio during operation of the turbofan engine 10. The turbofan engine 10 also includes a turbomachine 16 operably coupled to the fan 38 for driving the fan 38, the turbomachine 16 including a compressor section, a combustion section 26, and a turbine section in serial flow order and together defining a core air flowpath 37. The turbofan 38 also includes an outer nacelle 50 at least partially surrounding the fan 38 and the turbomachine 16, the outer nacelle 50 defining a bypass passage 56 with the turbomachine 16. A bypass ratio of an amount of airflow through the bypass passage 56 to an amount of airflow through the core air flowpath 37 during operation of the turbofan 38 is less than or equal to about 11 and wherein the fan pressure ratio is less than or equal to about 1.5.
-
公开(公告)号：EP3179075A1
公开(公告)日：2017-06-14
申请号：EP16201914.5
申请日：2016-12-02
发明人： MILLER, Brandon Wayne , ANSTEAD, Duane Howard , SENNOUN, Mohammed El Hacin , FANG, Ning , SNOW, Kyle Robert
CPC分类号： F02C7/224 , B64D27/12 , B64D37/02 , B64D37/34 , F02C7/06 , F02C7/14 , F02C7/236 , F05D2220/32 , F05D2220/764 , F05D2240/35 , F05D2260/20 , F05D2260/205 , F05D2260/213 , F05D2260/98 , Y02T50/675
摘要： A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system 202 utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500°F. The system additionally includes a fuel system 206 having a deoxygenation unit 212 for deoxygenating fuel in the fuel system 206, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit 212. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system 202 and the fuel in the fuel system 206 for transferring heat from the oil in the first engine system 202 to the fuel in the fuel system 206.
摘要翻译： 用于管理飞行器或燃气涡轮发动机中的至少一个中的热传递的系统包括利用油传热的第一发动机系统202。 第一个系统的油的温度极限至少约为500°F。 该系统还包括燃料系统206，其具有用于使燃料系统206中的燃料脱氧的脱氧单元212以及位于脱氧单元212下游的燃料 - 油热交换器。燃料 - 油热交换器与 第一发动机系统202中的油和燃料系统206中的燃料，用于将热量从第一发动机系统202中的油传递到燃料系统206中的燃料。
-
-
-
-
-
-
-
-
-
搜索结果
86 条记录 (耗时 0.022 秒)
