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1. 发明授权

EP2246528B1 Load distribution system for gas turbine engine 有权
公开(公告)号：EP2246528B1
公开(公告)日：2018-09-12
申请号：EP10250676.3
申请日：2010-03-31
申请人： Pratt & Whitney Canada Corp.
发明人： Alecu, Daniel T. , Watson, John
IPC分类号： F01D25/16 , F01D3/04 , F16C41/02
CPC分类号： F01D25/168 , F01D3/04 , F05D2260/57 , F05D2270/65 , F16C41/02 , F16C2360/23
摘要： There is provided an axial bearing load distribution system (20) for a gas turbine engine of the type having a low pressure rotor (21) supported by axial bearings (22,24). The system comprises a line (30) having an inlet end positioned in a highpressure compressor gas path downstream of any compressor stage provided with a variable geometry. The line (30) is adapted to sense static pressure in the highpressure compressor gas path. The line (30) has an outlet end producing the static pressure. An air-tight pressure actuator (26) is operatively connected to the outlet end and to one of the axial bearings (24) to exert a force on the axial bearing (24) proportionally to a pressure of the outlet end.

2. 发明公开

EP3358150A1 STARTER AIR VALVE SYSTEM WITH DUAL ELECTROMECHANICAL CONTROLS 有权转让
公开(公告)号：EP3358150A1
公开(公告)日：2018-08-08
申请号：EP18155178.9
申请日：2018-02-05
申请人： United Technologies Corporation
发明人： GREENBERG, Michael D. , GELWAN, David , CLAUSON, Jesse W. , GOODMAN, Robert , DEHAIS, John M. , KELLY, Myles R.
IPC分类号： F01D19/00 , F02C7/26
CPC分类号： F02C7/277 , F01D5/02 , F01D15/12 , F01D19/00 , F02C7/26 , F05D2220/32 , F05D2260/4031 , F05D2260/57 , F05D2260/96 , F05D2270/02
摘要： According to an aspect, a system includes a starter air valve (116) in fluid communication with an air turbine starter (120) to drive motoring of a gas turbine engine responsive to a compressed air flow (108) from a compressed air source (114). The system also includes a variable-position electromechanical device (104) operable to adjust positioning of the starter air valve (116) and a discrete-position electromechanical device (106) operable to adjust positioning of the starter air valve (116) and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device (104).

3. 发明公开

EP2672079A3 Method and apparatus for roll-in and alignment of a casing shell of a gas turbine 审中-公开
标题翻译：一种用于燃气轮机的壳体的滚入和对准的方法和设备
公开(公告)号：EP2672079A3
公开(公告)日：2017-08-23
申请号：EP13170710.1
申请日：2013-06-05
申请人： General Electric Company
发明人： Black, Kenneth Damon , Klingler, Brett Darrick , Casavant, Matthew Stephen
IPC分类号： F01D25/28 , B66F9/04 , F01D9/04 , F01D25/26 , F04D29/62
CPC分类号： F01D25/285 , F01D9/04 , F01D25/26 , F04D29/644 , F05D2230/60 , F05D2230/644 , F05D2230/70 , F05D2260/53 , F05D2260/57 , Y10T29/49231 , Y10T29/53687
摘要： A method and apparatus for rolling and aligning a casing 201 of a gas turbine is disclosed. At least one jack 210, 212 having a roller at one end is positioned at a location to couple the roller to the casing 201. The casing 201 is rolled within the turbine by rolling over the roller of the at least one jack. The roller is moved relative to the at least one jack 210, 212 to align the casing within the turbine.
摘要翻译：公开了一种用于滚动和对准燃气轮机的壳体201的方法和设备。在一端具有辊子的至少一个千斤顶210,212定位在将辊子联接到壳体201的位置。壳体201通过在至少一个千斤顶的辊子上滚动而在涡轮内滚动。辊相对于至少一个千斤顶210,212移动以将壳体对准在涡轮机内。

4. 发明授权

EP2990611B1 VAPOR VALVE AND VAPOR TURBINE 有权
标题翻译：蒸气阀和蒸气涡轮机
公开(公告)号：EP2990611B1
公开(公告)日：2017-08-16
申请号：EP14882909.6
申请日：2014-02-19
申请人： Mitsubishi Heavy Industries Compressor Corporation
发明人： TAKEMURA, Daisuke
IPC分类号： F01D17/14 , F16K31/44
CPC分类号： F01D17/145 , F05D2220/31 , F05D2230/31 , F05D2260/30 , F05D2260/57 , F05D2260/60 , F05D2270/56 , F05D2270/58 , F05D2270/64 , F16K31/163 , F16K31/44

5. 发明公开

EP2584184A3 Variable area nozzle for gas turbine engine 无效转让
标题翻译：燃气涡轮发动机的可变面积喷嘴
公开(公告)号：EP2584184A3
公开(公告)日：2017-06-14
申请号：EP12185811.2
申请日：2012-09-25
申请人： Rolls-Royce plc
发明人： Kennea, Robin Charles , Howarth, Nicholas
IPC分类号： F02K1/09 , F02K1/80
CPC分类号： F02K1/09 , F02K1/805 , F05D2240/55 , F05D2260/38 , F05D2260/57
摘要： A variable area nozzle (200) for a gas turbine engine is provided that has a circumferential outer boundary (100), which may be formed at least in part by the nacelle of a turbofan engine, that has a fixed portion (110) and a movable portion (120). The movable portion is movable by an actuator (160) both upstream and downstream from a datum position. This allows the exit area (NA) of the variable area nozzle to be adjusted according to flight conditions. When the movable portion is at or upstream of the datum position, there is no flow path between the fixed and movable portions. This enables the nozzle exit area to be optimized throughout flight, for example during changing cruise conditions, without inducing unwanted and inefficient flow structures between the fixed and movable portions and without allowing flow to leak out of the outer boundary of the nozzle.
摘要翻译：提供用于燃气涡轮发动机的可变面积喷嘴（200），其具有可至少部分地由涡轮风扇发动机的机舱形成的周向外边界（100），所述周边外边界具有固定部分（110）和可动部分（120）。可移动部分可通过致动器（160）在基准位置的上游和下游移动。这可以根据飞行条件调整变面积喷嘴的出口面积（NA）。当可移动部分位于基准位置或基准位置的上游时，固定部分和可移动部分之间不存在流动路径。这使得喷嘴出口区域能够在整个飞行过程中例如在改变巡航条件期间被优化，而不会在固定部分和可移动部分之间引起不希望且低效的流动结构并且不允许流动从喷嘴的外边界泄漏。

6. 发明公开

EP3095708A1 MISTAKE PROOF RAM AIR TURBINE DOWNLOCK PROTECTION 有权
标题翻译： FEHLERSICHERER STAULUFTTINBINENSPERRSCHUTZ
公开(公告)号：EP3095708A1
公开(公告)日：2016-11-23
申请号：EP16170480.4
申请日：2016-05-19
申请人： Hamilton Sundstrand Corporation
发明人： BANNON, David G. , REINHARD, Paul Michael
IPC分类号： B64D41/00 , F15B15/20
CPC分类号： F15B15/149 , B64D41/007 , F01D5/02 , F01D25/28 , F05D2220/34 , F05D2240/24 , F05D2260/57 , F15B15/1476 , F15B15/204
摘要： An actuator assembly for stowing a ram air turbine includes a housing 32, an internal cavity within the housing configured to partially contain a pressurized fluid, a fluid inlet port 14 connecting a first opening on an outer surface of the housing to the internal cavity, a fluid outlet port 44 connecting a second opening on the outer surface of the housing to the internal cavity, and a pressure relief channel 48 having a relief inlet and a relief outlet. The relief outlet is in fluid communication with the internal cavity and a distance between the fluid inlet port and the relief outlet is less than half a distance between the fluid inlet port and fluid outlet port.
摘要翻译：用于收起压头空气涡轮机的致动器组件包括壳体32，壳体内的内部空腔，构造成部分地容纳加压流体;将壳体的外表面上的第一开口连接到内腔的流体入口端口14，液体出口44将外壳的外表面上的第二开口连接到内腔，以及具有释放入口和泄压出口的压力释放通道48。泄放出口与内腔流体连通，并且流体入口和泄放出口之间的距离小于流体入口和流体出口之间的一半距离。

7. 发明公开

EP2971592A4 ACTUATOR FOR GAS TURBINE ENGINE BLADE OUTER AIR SEAL 有权转让
标题翻译：燃气轮机叶片外部密封组件可调
公开(公告)号：EP2971592A4
公开(公告)日：2016-11-09
申请号：EP14797409
申请日：2014-02-18
申请人： UNITED TECHNOLOGIES CORP
发明人： DUGUAY BRIAN
IPC分类号： F01D11/20 , F01D11/08 , F01D11/22 , F02C7/28 , F04D29/08
CPC分类号： F01D11/20 , F01D11/08 , F01D11/22 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2240/55 , F05D2260/57
摘要： A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.
摘要翻译：根据本公开的示例性方面的叶片外部空气密封（BOAS）致动器组件包括致动器构件; 以及牵开器，其构造成与所述致动器构件一起移动以将BOAS段从第一位置移动到位于所述第一位置的径向外侧的第二位置，所述BOAS段在处于所述第一位置时与所述支撑结构抵靠并与所述支撑结构间隔开当处于第二位置时。

8. 发明授权

EP2873813B1 Gas turbine engine turbine blade tip active clearance control system and method 失效转让
标题翻译：系统和方法，用于燃气涡轮发动机的涡轮机的叶片尖端间隙的主动控制
公开(公告)号：EP2873813B1
公开(公告)日：2016-09-21
申请号：EP14189292.7
申请日：2014-10-16
申请人： Honeywell International Inc.
发明人： Tillman, Don , Gage, Raymond , Barrett, Rich
IPC分类号： F01D11/20 , F02C7/18 , F01D11/24
CPC分类号： B64D31/06 , F01D11/20 , F01D11/24 , F02C7/18 , F02C9/16 , F05D2260/20 , F05D2260/201 , F05D2260/57 , F05D2270/07 , F05D2270/44 , Y02T50/676

9. 发明公开

EP3018329A1 CASCADE TYPE THRUST REVERSER WITH REDUCED DRAG 有权
标题翻译： KASKADENARTIGER SCHUBUMKEHRER MIT VERRINGERTEM LUFTWIDERSTAND
公开(公告)号：EP3018329A1
公开(公告)日：2016-05-11
申请号：EP15193422.1
申请日：2015-11-06
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/76 , F02K1/72
CPC分类号： F02K1/763 , F02K1/70 , F02K1/72 , F02K1/766 , F05D2220/36 , F05D2260/50 , F05D2260/56 , F05D2260/57
摘要： A system for a thrust reverser of an aircraft includes a primary sleeve 202 and a secondary sleeve 226 having cascades 526. The secondary sleeve 226 is coupled to a set of blocker doors 208. The sliding motions of the primary sleeve 202 and the secondary sleeve 226 are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve 202 may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve 226.
摘要翻译：用于飞行器的推力反向器的系统包括主套筒202和具有级联526的次级套筒226.次级套筒226联接到一组阻挡门208.主套筒202和次级套筒226的滑动当它们在其收起位置和展开位置之间移动时不直接耦合。主套筒202的滑动可以在不同的时间开始，并且以与次级套筒226的滑动运动不同的速度继续。

10. 发明公开

EP3018328A1 SLEEVE LINKAGE FOR THRUST REVERSER 有权
标题翻译： HÜLSENVERBINDUNGFÜRSCHUBUMKEHRER
公开(公告)号：EP3018328A1
公开(公告)日：2016-05-11
申请号：EP15193426.2
申请日：2015-11-06
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/72 , F02K1/76 , F02K3/06
CPC分类号： F02K1/763 , F02K1/70 , F02K1/72 , F02K3/06 , F05D2220/323 , F05D2250/41 , F05D2260/57
摘要： Aspects of the disclosure are directed to a system for a thrust reverser of an aircraft comprising: a primary sleeve 202, and a secondary sleeve 232, wherein a first stroke 202' associated with the primary sleeve 202 is different from a second stroke 232' associated with the secondary sleeve 232, and wherein the primary sleeve 202 traverses a first distance associated with the first stroke 202' at the outset of a deployment of the thrust reverser and a second distance associated with the first stroke at a later stage of the deployment.
摘要翻译：本公开的方面涉及一种用于飞机的推力反向器的系统，包括：主套筒202和次级套筒232，其中与主套筒202相关联的第一冲程202'与第二冲程232'相关联与次级套筒232相连，并且其中主套筒202在推力反向器的展开开始时穿过与第一冲程202'相关联的第一距离，并且在部署的稍后阶段与第一冲程相关联的第二距离。

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