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1. 发明公开

EP3864297A1 MODULE DE SOUFFLANTE A PALES A CALAGE VARIABLE 有权
公开(公告)号：EP3864297A1
公开(公告)日：2021-08-18
申请号：EP19813617.8
申请日：2019-10-10
申请人： SAFRAN AIRCRAFT ENGINES
发明人： CHARIER, Giles Alain, Marie , FORMICA, Olivier , FRANTZ, Caroline, Marie , TANTOT, Nicolas, Jerôme, Jean
IPC分类号： F04D25/02 , B64C11/38 , F01D7/00 , F04D29/32 , F01D5/12 , F01D15/12 , F01D25/16 , F01D25/18 , F02K3/068 , F02C7/36 , F04D29/054 , F04D29/056 , F04D29/063

2. 发明公开

EP3670891A1 GEARED GAS TURBINE ENGINE 无效
公开(公告)号：EP3670891A1
公开(公告)日：2020-06-24
申请号：EP19210655.7
申请日：2019-11-21
申请人： Rolls-Royce plc
发明人： Stretton, Richard , Willmot, Michael
IPC分类号： F02K3/068
摘要： A gas turbine engine (10) for an aircraft comprises an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor; a fan (23) located upstream of the engine core (11), the fan comprising a plurality of fan blades (64) extending from a hub (66); and a gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan (23) so as to drive the fan at a lower rotational speed than the core shaft. The gas turbine engine (10) has an engine length (110) and a gearbox location (112) relative to a forward region of the fan (23), and a gearbox location ratio of:
gearbox location /engine length
is in a range from 0.19 to 0.45.

3. 发明公开

EP3587749A1 GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3587749A1
公开(公告)日：2020-01-01
申请号：EP19178849.6
申请日：2019-06-06
申请人： Rolls-Royce plc
发明人： Wilshaw, Johnathan
IPC分类号： F01D25/16 , F01D25/28 , F02C7/20 , B64D29/06 , F02K3/068
摘要： A gas turbine engine (10) for an aircraft comprising: a fan (23) located adjacent an air intake (12) of the engine (10), the fan (23) comprising a plurality of fan blades (25); downstream of the fan (23), an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine (19) to the compressor (14); an engine core housing (52) at least partly encasing the engine core (11); a fan case (72) surrounding the fan (23) and defining at least part of a bypass duct (22) radially outside the engine core (11); a plurality of outlet guide vanes (66) extending between the engine core housing (52) and an outlet guide vane support region (74) of the fan case (72), adjacent an upstream end of the bypass duct (22); one or more supports (50) extending from the fan case (72) to the engine core housing (52), wherein: a first end (76) of the one or more supports (50) is fixed to the fan case (72) at the outlet guide vane support region; a second end (78) of the one or more supports (50) is fixed to the engine core housing (52) adjacent an exhaust (20) of the engine core (11).

4. 发明授权

EP2223856B1 Turboproantrieb mit Druckpropeller 有权
标题翻译：涡轮推进与压力螺旋桨
公开(公告)号：EP2223856B1
公开(公告)日：2018-04-18
申请号：EP10001141.0
申请日：2010-02-04
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Negulescu, Dimitrie, Dr.
IPC分类号： B64D27/10 , B64D27/14 , B64D33/02 , B64D33/04 , F02C3/14 , F02K3/068 , F02K3/072
CPC分类号： B64D27/10 , B64D27/14 , B64D33/02 , B64D33/04 , B64D2027/005 , F02C3/145 , F02K3/025 , F02K3/072 , Y02T50/44 , Y02T50/66

5. 发明公开

EP3052789A4 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
标题翻译：与小的压力比的风扇马达和之间的入口和风扇尺寸的尺寸关系
公开(公告)号：EP3052789A4
公开(公告)日：2016-11-09
申请号：EP14850031
申请日：2014-09-18
申请人： UNITED TECHNOLOGIES CORP
发明人： LORD WESLEY K , MALECKI ROBERT E , QIU YUAN , ROSE BECKY E , GILSON JONATHAN
IPC分类号： F02C7/36 , F02C7/04 , F02K3/068
CPC分类号： F02K3/068 , F01D25/24 , F02C7/04 , F05D2220/36 , F05D2240/303 , F05D2260/40311 , F05D2260/96 , Y02T50/671
摘要： According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.
摘要翻译：。根据实施例的示例，一种燃气涡轮发动机组件包括，除其他事项外，风扇确实具有风扇叶片的复数。风扇的直径具有尺寸D做是基于所述风扇叶片的尺寸。每个风扇叶片具有领先优势。的入口部分向前风扇位于。入口部分的长度具有至少一些风扇叶片的和在入口部分的前边缘的前缘的位置之间的尺寸L。 L的尺寸关系/ D是约0.2至约12:45之间。

6. 发明公开

EP2954188A4 ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO 审中-公开
标题翻译： LÄNGLICHERGETRIEBETURBOLÜFTERMIT HOHEMNEBENSTROMVERHÄLTNIS
公开(公告)号：EP2954188A4
公开(公告)日：2016-10-05
申请号：EP14749309
申请日：2014-02-03
申请人： UNITED TECHNOLOGIES CORP
发明人： SCHWARZ FREDERICK M , MALECKI ROBERT E
IPC分类号： F02K3/068
CPC分类号： F02C7/36 , B64D33/02 , B64D2033/0286 , F02C3/10 , F02C3/107 , F02K3/06 , F02K3/068 , F05D2220/36 , Y02T50/672

7. 发明公开

EP2809890A4 GAS TURBINE ENGINE BEARING ARRANGEMENT 有权转让
标题翻译：轴承安排燃气涡轮发动机
公开(公告)号：EP2809890A4
公开(公告)日：2015-11-04
申请号：EP13744407
申请日：2013-01-22
申请人： UNITED TECHNOLOGIES CORP
发明人： MULDOON MARC J , SHERIDAN WILLIAM G , REINHARDT GREGORY E , SAVELA GREGORY M
IPC分类号： F01D25/16 , F02C7/06 , F02K3/068
CPC分类号： F02C7/06 , F01D25/162 , F02K3/068 , Y02T50/671 , Y10T29/49229
摘要： An example gas turbine engine includes a housing and first and second spools coaxial with one another and arranged within the housing. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool. First and second bearings support the aft end of the first spool relative to the housing. An example method of assembling the gas turbine engine includes arranging a first spool within a second spool. First and second bearings are mounted between an aft end of the first spool and a fixed housing.

8. 发明授权

EP1825111B1 COUNTER-ROTATING COMPRESSOR CASE FOR A TIP TURBINE ENGINE 有权
标题翻译：反向旋转的压缩机壳体小费涡轮机
公开(公告)号：EP1825111B1
公开(公告)日：2011-08-31
申请号：EP04822094.1
申请日：2004-12-01
申请人： United Technologies Corporation
发明人： MERRY, Brian , SUCIU, Gabriel L. , NORRIS, James W. , NORDEEN, Craig A.
IPC分类号： F02C3/067 , F02K3/068 , F02C3/073 , F01D25/24
CPC分类号： F01D5/022 , F01D25/24 , F02C3/067 , F02C3/073 , F02K3/068 , F05D2230/60
摘要： A tip turbine engine (10) provides an axial compressor (22) having a compressor case (50) from which extend radially inwardly a plurality of outer compressor airfoils (54). The compressor case (50) is directly driven by the rotation of the turbine (32) and fan (28), while at least one gear (77) couples the rotation of the turbine (32) and fan (28) to an axial compressor rotor (46) having a plurality of inner compressor airfoils (52). In this manner, the axial compressor rotor (46) is driven in a direction opposite the direction of the outer compressor airfoils (54), thereby increasing the compression provided by the compressor without increasing the number of airfoils. The outer compressor airfoils (54) are formed on a plurality of outer airfoil assemblies (56) each having an arcuate substratem (58) from which the outer compressor airfoils (54) extend. Each of the outer compressor airfoil assemblies (56) includes more than one axially-spaced stage of outer compressor airfoils (54). For assembly, the outer compressor airfoil assemblies (56) are moved toward the axial compressor rotor (46) and then inserted into the compressor case (50).

9. 发明公开

EP2333287A1 Vectoring transition duct for turbine engine 审中-公开
标题翻译： ÜberleitkanalfürSchubvektorsteuerung eines Turbinentriebwerks
公开(公告)号：EP2333287A1
公开(公告)日：2011-06-15
申请号：EP11001239.0
申请日：2004-12-01
申请人： United Technologies Corporation
发明人： The designation of the inventor has not yet been filed
IPC分类号： F02K1/00 , F02K3/068
CPC分类号： F02K1/006 , F02K3/068
摘要： A transition duct (112) is provided at the outlet of a turbine engine (10). The transition duct transitions the outlet of the tip turbine engine from round to rectangular. The transition duct also provides a plurality of variable vanes (120) at the outlet of the transition duct. The transition duct incorporates a perimeter slot providing cooling to the duct outer wall and attached components. The variable vanes are installed to vector the exhaust gases. This allows the aircraft to decelerate, hover or accelerate in the forward direction by commanding the position of the variable vanes. One potential application of the tip turbine engine is for vertical installations in aircraft.
摘要翻译：在涡轮发动机（10）的出口处设置过渡管道（112）。过渡管道将尖端涡轮发动机的出口从圆形过渡到矩形。过渡管道还在过渡管道的出口处提供多个可变叶片（120）。过渡管道包括一个周边槽，为管道外壁和连接部件提供冷却。安装可变叶片来对废气进行传播。这允许飞机通过指示可变叶片的位置来向前方向减速，悬停或加速。尖端涡轮发动机的一个潜在应用是飞机中的垂直安装。

10. 发明授权

EP1825126B1 VECTORING TRANSITION DUCT FOR TURBINE ENGINE 有权
标题翻译：过渡通道有用于在燃气轮机中流矢影响
公开(公告)号：EP1825126B1
公开(公告)日：2011-02-16
申请号：EP04822617.9
申请日：2004-12-01
申请人： United Technologies Corporation
发明人： ROBERGE, Gary D.
IPC分类号： F02K1/00 , F02K3/068
CPC分类号： F02K1/006 , F02K3/068
摘要： A transition duct (112) is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine (10) from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of the transition duct. The transition duct incorporates a perimeter slot (124) providing cooling to the duct outer wall and attached components. The variable vanes (120) are installed to vector the exhaust gases. This allows the aircraft to decelerate, hover or accelerate in the forward direction by commanding the position of the variable vanes . One potential application of the tip turbine engine is for vertical installations in aircraft.

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