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公开(公告)号：EP2824308B1
公开(公告)日：2018-12-26
申请号：EP14173655.3
申请日：2014-06-24
Applicant: Pratt & Whitney Canada Corp.
Inventor： Cunningham, Mark , Marini, Remo , Girgis, Sami , Kameshki, Mohammad Reza , Ramamurhty, Raja
CPC classification number: F01D25/30 , F02K1/386 , F02K1/48 , F05D2250/314 , F05D2250/37 , F05D2250/71 , Y02T50/672
Abstract: An exhaust mixer (32) for a gas turbine engine where each outer lobe (44) has at the downstream end a circumferential offset in a direction corresponding to that of the swirl component of the flow entering the mixer (32). The mixer (32) has a crest line (45) having at least a downstream portion curved with respect with respect to a circumferential direction of the mixer (32) and/or a center line at the downstream end tilted with respect to a radial line extending to the tip of the outer lobe (44) to define the circumferential offset.
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2.发明公开
公开(公告)号：EP3076077A4
公开(公告)日：2017-07-12
申请号：EP14865587
申请日：2014-11-26
Applicant: MITSUBISHI HITACHI POWER SYS
Inventor： TAMURA ISSEI , AKAMATSU SHINJI , SAITO KEIJIRO , MIYAUCHI KOTARO , KAWAKAMI TOMO
CPC classification number: F02C3/30 , F05D2220/32 , F05D2250/37 , F05D2250/73 , F23L7/002 , F23R3/28 , F23R3/343 , F23R2900/00013
Abstract: This combustion apparatus has a nozzle (35) in which a fuel injection port (41) for spraying fuel is formed on the center of the tip (35s) of said nozzle (35). Multiple water injecttion ports (42) are formed, at an interval in the circumferential direction, on the periphery of the fuel injection port (41) at the tip (35s) of the nozzle (25), and the water injection ports (42) are unevenly formed in the circumferential direction.
Abstract translation: 该燃烧装置具有在所述喷嘴（35）的前端（35s）的中央形成喷射燃料的燃料喷射口（41）的喷嘴（35）。 在喷嘴25的前端35s的燃料喷射口41的周围，沿圆周方向隔开间隔地形成有多个注水口42和注水口42， 在圆周方向上不均匀地形成。
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公开(公告)号：EP2971659A4
公开(公告)日：2016-11-23
申请号：EP14807350
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GILSON JONATHAN , BALTAS CONSTANTINE
CPC classification number: F02C7/045 , F01D25/24 , F02C3/107 , F02C7/24 , F02K1/827 , F05D2240/40 , F05D2250/00 , F05D2250/283 , F05D2250/37 , F05D2260/963
Abstract: A geared turbofan engine includes a first rotor, a fan, a second rotor, a gear train, a fan casing, a nacelle and a plurality of discrete acoustic liner segments. The fan is connected to the first rotor and is capable of rotation at frequencies between 200 and 6000 Hz and has a fan pressure ratio of between 1.25 and 1.60. The gear train connects the first rotor to the second rotor. The fan casing and nacelle are arranged circumferentially about a centerline and define a bypass flow duct in which the fan is disposed. The plurality of discrete acoustic liner segments with varied geometric properties are disposed along the bypass flow duct.
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4.发明公开
公开(公告)号：EP3032032A1
公开(公告)日：2016-06-15
申请号：EP14197574.8
申请日：2014-12-12
Applicant: MTU Aero Engines AG
Inventor： Ramm, Günter
CPC classification number: F01D25/30 , F01D5/143 , F01D5/145 , F01D9/041 , F02K1/78 , F02K3/06 , F05D2250/323 , F05D2250/37
Abstract: Die Erfindung betrifft ein Austrittsleitgitter mit einer äußeren Wandung (34'), einer inneren Wandung (36') zur Bildung eines Ringkanals (22) und zur Führung des Heißgasstroms und mit mindestens einer Leitschaufel (32), die zwischen der äußeren Wandung (34') und der inneren Wandung (36') angeordnet ist, wobei zwischen der Vorderkante (E) der Leitschaufel (32) und dem stromabwärtigen Ende (35') der äußeren Wandung (34') mindestens eine querschnittsverringernde Engstelle (38') angeordnet ist. Dabei ist mindestens eine absolute Engstelle (38') in dem Bereich zwischen der Vorderkante (E) und dem stromabwärtigen Ende (35') näher zur Hinterkante (H) der Leitschaufel (32) angeordnet als zum stromabwärtigen Ende (35').
Abstract translation: 本发明涉及一种Austrittsleitgitter具有外部壁（34“），内壁（36”），以形成一个环形通道（22）和用于引导热气体流和至少一个导叶（32）（外壁34'之间 ）和“叶片（32）和下游端（35）被布置，其中（领先边e之间）”的内壁（36）“是至少一种querschnittsverringernde缩颈（38）”）布置在所述外壁（第34次 在前缘（E）和下游端（35'）之间的区域中的至少一个绝对收缩部（38'）位于比叶片（32）的后缘（H）更靠近下游端（35'）的位置。
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公开(公告)号：EP2946088A1
公开(公告)日：2015-11-25
申请号：EP13871803.6
申请日：2013-01-15
Applicant: United Technologies Corporation
Inventor： WONG, Chung , VITALE, Jack V. , OSORIO, Omar I. , CHEN, Daih-yeou
IPC: F02C1/00
CPC classification number: F02C7/25 , F01D25/145 , F02C7/22 , F05D2220/50 , F05D2230/54 , F05D2240/15 , F05D2250/231 , F05D2250/37 , F05D2300/603 , Y02T50/672 , Y02T50/675 , Y10T29/49828
Abstract: A gas turbine engine according to one disclosed non-limiting embodiment of the present disclosure includes an engine case, a multiple of fuel injectors mounted to the engine case, and a fire shield mounted to the engine case to surround at least one, but less than all, of the multiple of fuel injectors. In a further embodiment of the foregoing embodiment, the fire shield includes a sheet metal alloy layer. In the alternative or additionally thereto, in the foregoing embodiment the fire shield includes a composite cloth on an interior of the sheet metal alloy layer with respect to the engine case.
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Patent Agency Ranking
公开(公告)号：EP2522809A3
公开(公告)日：2018-04-04
申请号：EP12167116.8
申请日：2012-05-08
Applicant: Rolls-Royce plc
Inventor： Bagnall, Adam
CPC classification number: F01D5/141 , F01D5/142 , F01D5/145 , F01D9/041 , F01D9/065 , F04D29/544 , F05D2230/10 , F05D2240/122 , F05D2240/301 , F05D2250/314 , F05D2250/37 , Y02T50/671 , Y02T50/673 , Y10T29/49238
Abstract: A method of reducing the fluid flow effects of one or more flow modifiers (19) in a passage (16), the method comprising: providing a plurality of aerofoil structures (15) in the passage (16), wherein the geometry of each aerofoil structure (15) is initially substantially the same; and shortening the trailing edge (18) of one or more selected aerofoil structures (17) in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow (20a, 20e) in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or more flow modifiers (19) in the passage are reduced.
Abstract translation: 一种减少通道（16）中的一个或多个流量调节器（19）的流体流动影响的方法，该方法包括：在通道（16）中提供多个机翼结构（15），其中每个机翼 结构（15）最初基本相同; 和缩短在弦向方向上的一个或多个选定的机翼结构（17）的后缘（18）和至少在一个或多个选定机翼结构的翼展方向部分，使得在使用时，流体流动的方向 （20a，20e）在一个或多个所选翼型结构附近被改变并且所述通道中的所述一个或多个流量调节器（19）的流体流动效果被降低。
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公开(公告)号：EP3228854A1
公开(公告)日：2017-10-11
申请号：EP17161031.4
申请日：2017-03-15
Applicant: Rolls-Royce plc
Inventor： Stretton, Richard
CPC classification number: F02K1/72 , F02K1/563 , F02K1/64 , F02K1/763 , F02K1/766 , F02K3/06 , F04D29/522 , F04D29/542 , F04D29/563 , F05D2220/323 , F05D2250/37 , F05D2260/30
Abstract: An aircraft gas turbine engine nacelle (21) comprises a thrust reversal arrangement. The thrust reversal arrangement comprises at least first and second circumferentially spaced fixed thrust reverser cascade boxes (28a, 28b) each comprising a plurality of thrust reverser vanes (29) configured to direct air forwardly and circumferentially and at least one inter-leaved translating circumferential turning vane (37) configured to direct air in a direction having a circumferential component. The circumferential turning vane (37) is moveable from a stowed position provided between the first and second circumferentially spaced thrust reverser cascade boxes (28a, 28b), and a deployed position axially rearwardly of the thrust reverser cascade boxes (28a, 28b).
Abstract translation: 飞机燃气涡轮发动机舱（21）包括推力反向装置。 推力反向装置包括至少第一和第二周向间隔的固定推力反向器级联箱（28a，28b），每个固定推力反向器级联箱包括多个推力反向叶片（29）和至少一个叶片间平移的周向旋转 叶片（37），其构造成将空气导向具有周向分量的方向。 圆周转向叶片37可从设置在第一和第二周向间隔的推力反向器级联箱28a，28b之间的收起位置和反推力器级联箱28a，28b的轴向向后的展开位置移动。
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8.发明公开
公开(公告)号：EP3023592A1
公开(公告)日：2016-05-25
申请号：EP14194073.4
申请日：2014-11-20
Applicant: Siemens Aktiengesellschaft
Inventor： Fuchs, Florian , Hecklau, Martin , Herzog, Nils , Mavrommatis, Philippos Theodoros , Mutke, Stefan , Mühl, Julia , Pruss, Matthias , Reckert, Rafael , Speiser, Julian , Wohltat, Rene
CPC classification number: F04D29/542 , F01D9/02 , F02C3/14 , F04D19/02 , F04D29/4246 , F04D29/444 , F05D2220/32 , F05D2240/12 , F05D2240/128 , F05D2240/35 , F05D2250/37 , F23R3/04 , F23R3/42
Abstract: Die Erfindung betrifft einen Diffusor (1) einer thermischen Energiemaschine (3), insbesondere einer Gasturbine (5), mit einem Diffusoreintritt (20), mit einem Diffusoraustritt (22) und mit einer Vielzahl an Luftleitelementen (23), bei welchem ein Luftmassenstrom durch den Diffusoreintritt (20) hindurch in den Diffusor (1) hinein gelangt, und bei welchem der in den Diffusor (1) gelangte Luftmassenstrom durch den Diffusoraustritt (22) wieder aus dem Diffusor (1) hinaus gelangt und hierbei mittels der Luftleitelemente (23) als eine Vielzahl an Luftmassenpartialströmen (24) abströmt, wobei wenigstens zwei unmittelbar benachbarte Luftleitelemente (23) der Vielzahl an Luftleitelementen (23) derart ausgestaltet sind, dass deren Abströmwinkel α n bezogen auf die durch die in Umfangsrichtung (25) umlaufende Austrittsöffnung (31) des Diffusoraustritts (22) ausgestaltete Umfangsfläche (32) voneinander verschieden sind.
Abstract translation: 本发明涉及一种热动力发动机（3）的扩散器（1），特别是燃气涡轮机（5），具有扩散器入口（20），具有扩散器出口（22）和具有多个空气导向元件（23），其中的空气质量通过流 扩散器入口（20）进入所述扩散器（1）进入，并且其中所述进入扩散器（1）通过扩散器出口（22）的空气质量流出来的扩散器（1）也通过的，并且在这种情况下，由空气导向件的装置（23） 作为多个Luftmassenpartialströmen的（24）中流动，其中，所述多个空气导向元件（23）中的至少两个直接相邻的空气引导元件（23）被设计为使得在周向方向流出角±相对于圆周n至（25）的出口（31） 配置的外围表面（32）的扩散器出口（22）的距离彼此不同。
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公开(公告)号：EP2841717A2
公开(公告)日：2015-03-04
申请号：EP13785969.0
申请日：2013-04-22
Applicant: General Electric Company
CPC classification number: F01D25/16 , F01D25/164 , F02C7/06 , F05D2230/64 , F05D2250/312 , F05D2250/36 , F05D2250/37 , F16C19/54 , F16C27/04 , F16C35/042 , F16C2360/23
Abstract: A bearing support housing for a gas turbine engine includes: an annular mounting flange; a first bearing cage including: an annular first bearing support ring; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the mounting flange; and a second bearing cage including: an annular second bearing support ring; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the mounting flange, the second spring arms defining spaces therebetween. The first spring arms are received between the second spring arms, and the bearing cages are sized so as to permit independent flexing motion of the first and second spring arms.
Abstract translation: 用于燃气涡轮发动机的轴承支撑壳体包括：环形安装凸缘; 第一轴承保持架，包括：环形的第一轴承支承环; 以及将所述第一轴承支撑环和所述安装凸缘互连的轴向延伸的第一弹簧臂的环形阵列; 以及第二轴承保持架，包括：环形第二轴承支撑环; 以及将所述第二轴承支撑环和所述安装凸缘互连的轴向延伸的第二弹簧臂的环形阵列，所述第二弹簧臂在其间限定空间。 第一弹簧臂被容纳在第二弹簧臂之间，并且轴承保持架的尺寸设计成允许第一和第二弹簧臂的独立的弯曲运动。
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公开(公告)号：EP2522809A2
公开(公告)日：2012-11-14
申请号：EP12167116.8
申请日：2012-05-08
Applicant: Rolls-Royce plc
Inventor： Bagnall, Adam
CPC classification number: F01D5/141 , F01D5/142 , F01D5/145 , F01D9/041 , F01D9/065 , F04D29/544 , F05D2230/10 , F05D2240/122 , F05D2240/301 , F05D2250/314 , F05D2250/37 , Y02T50/671 , Y02T50/673 , Y10T29/49238
Abstract: A method of reducing the fluid flow effects of one or more flow modifiers (19) in a passage (16), the method comprising: providing a plurality of aerofoil structures (15) in the passage (16), wherein the geometry of each aerofoil structure (15) is initially substantially the same; and shortening the trailing edge (18) of one or more selected aerofoil structures (17) in a chordwise direction and over at least a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow (20a, 20e) in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or more flow modifiers (19) in the passage are reduced.
Abstract translation: 一种降低通道（16）中一种或多种流动改性剂（19）的流体流动效应的方法，所述方法包括：在通道（16）中提供多个机翼结构（15），其中每个翼型 结构（15）最初基本相同; 并且沿着弦方向缩短一个或多个选定的机翼结构（17）的后缘（18）并且在一个或多个选定的机翼结构的至少翼展方向部分上方缩短，使得当使用时，流体流动的方向 （20a，20e）在一个或多个选定的机翼结构附近被改变，并且通道中的一个或多个流动改进剂（19）的流体流动效应降低。
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