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91. 发明授权

US09784186B2 Device for mounting a spark plug in a combustion engine of a gas turbine engine 有权
公开(公告)号：US09784186B2
公开(公告)日：2017-10-10
申请号：US14116807
申请日：2012-05-03
申请人： Jacques Marcel Arthur Bunel , Mario César De Sousa , Gilles Ulryck
发明人： Jacques Marcel Arthur Bunel , Mario César De Sousa , Gilles Ulryck
IPC分类号： F02C7/20 , F23R3/06 , F23R3/60
CPC分类号： F02C7/20 , F02C7/266 , F05D2220/32 , F05D2240/35 , F05D2260/99 , F23R3/06 , F23R3/60 , F23R2900/00005 , F23R2900/00012
摘要： A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards. The bushing is floatingly mounted inside the chimney with its collars axially positioned between the collar of the chimney and the washer. The inner collar comes in operation to bear against the collar of the chimney. The outer collar presents an outside diameter (d1) greater than the inside diameter (d2) of the washer.

92. 发明授权

US09783315B2 Nacelle with longitudinal translating cowling and rotatable sleeves 有权
公开(公告)号：US09783315B2
公开(公告)日：2017-10-10
申请号：US13404982
申请日：2012-02-24
申请人： Norman John James
发明人： Norman John James
IPC分类号： B64D29/00 , B64D29/06 , B64D29/08 , F02K1/30 , F02K1/32 , B64D27/12 , B64D27/26 , F23R3/60
CPC分类号： B64D29/08 , B64D27/12 , B64D27/26 , B64D29/00 , B64D29/06 , B64D2027/262 , F02K1/30 , F02K1/32 , F23R3/60 , Y10T137/0536
摘要： A nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The nacelle also includes a second cowling that at least partially defines the inlet and which translates relative to the first cowling. The nacelle can include a third cowling that at least partially defines the outlet and translates relative to the first cowling.

93. 发明授权

US09683743B2 Combustion chamber tile of a gas turbine 有权
公开(公告)号：US09683743B2
公开(公告)日：2017-06-20
申请号：US14072452
申请日：2013-11-05
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Carsten Clemen
IPC分类号： F23R3/00 , F23M5/02 , F23M5/04 , F23R3/60 , F02C7/20
CPC分类号： F23R3/00 , F02C7/20 , F23M5/02 , F23M5/04 , F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042
摘要： A combustion chamber tile of a gas turbine includes a bolt for mounting the combustion chamber tile on a combustion chamber wall, with the combustion chamber tile being designed substantially plate-like and having on one side at least one mounting element, on which the bolt, which is provided as a separate component, is positively anchored.

94. 发明授权

US09657949B2 Combustor skin assembly for gas turbine engine 有权
公开(公告)号：US09657949B2
公开(公告)日：2017-05-23
申请号：US13651527
申请日：2012-10-15
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Honza Stastny , Robert Sze
IPC分类号： F23R3/06 , F23R3/00 , F23R3/60
CPC分类号： F23R3/06 , F23R3/002 , F23R3/60 , F23R2900/00017 , F23R2900/03041 , F23R2900/03044 , Y02T50/675 , Y10T29/49316
摘要： A combustor assembly includes a hot skin of a combustion chamber wall having an inner face exposed to the combustion chamber and an opposite outer face, a receiving skin having a securing portion affixed to the hot skin outer face in an air-tight manner and a receiving flange, extending from the securing portion, that is offset from the hot skin outer face to form a female recess, a cold skin having a cold wall portion spaced from the hot skin and forming a cooling cavity therebetween, a securing portion extending from a first end of the cold wall portion affixed to the hot skin outer face in an air-tight manner and a male flange extending from a second end of the cold wall portion opposite the first end, the male flange snugly received in the female recess and forming a sliding engagement therebetween.

95. 发明授权

US09625158B2 Gas turbine combustion acoustic damping system 有权
公开(公告)号：US09625158B2
公开(公告)日：2017-04-18
申请号：US14566963
申请日：2014-12-11
申请人： Andrew J. Olsen , Ivar Austrem , M. Serkan Yildirim , Zheji Liu
发明人： Andrew J. Olsen , Ivar Austrem , M. Serkan Yildirim , Zheji Liu
IPC分类号： F23R3/06 , F23R3/54 , F23R3/60 , F02C7/24 , F02C3/14
CPC分类号： F02C7/24 , F01D5/02 , F02C3/04 , F02C3/145 , F02C7/18 , F04D29/321 , F05D2220/32 , F05D2240/35 , F05D2240/60 , F05D2260/201 , F05D2260/96 , F05D2260/963 , F05D2270/14 , F23R3/002 , F23R3/06 , F23R3/14 , F23R3/286 , F23R3/54 , F23R3/60 , F23R2900/00014 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

96. 发明授权

US09605561B2 Modular turbomachine inlet assembly and related inlet transition section 有权
公开(公告)号：US09605561B2
公开(公告)日：2017-03-28
申请号：US13801425
申请日：2013-03-13
申请人： General Electric Company
发明人： Sean Allen Smith , Michael Christopher Jones , Erik Eduardo Lopez Partida , Daniel Ross Predmore
IPC分类号： F01D9/02 , F23R3/00 , F23R3/60 , F01D25/24 , F01D25/26 , F01D9/06 , F01D9/04
CPC分类号： F01D25/24 , F01D9/023 , F01D9/048 , F01D9/06 , F01D9/065 , F01D25/246 , F01D25/26 , F05D2220/31 , F05D2230/51 , F05D2230/61 , F05D2240/14 , F23R3/002 , F23R3/60
摘要： An inlet transition section and an inlet bowl entry can be designed to reduce a number of turbomachine casing designs. Using relationships between flow properties, distances between elements, crossover/supply pipe diameter, ideal cross sectional area, aspect ratio, and inlet bowl entry size, a transition from circular cross section to substantially polygonal cross section can be made while enabling adoption of a single size of substantially polygonal inlet bowl entry for a plurality of turbine sizes and/or crossover/supply pipe sizes with minimal losses.

97. 发明申请

US20170067642A1 ASSEMBLY GROUP WITH A COMBUSTION CHAMBER SHINGLE FOR A GAS TURBINE 审中-公开
标题翻译：组装燃气轮机组
公开(公告)号：US20170067642A1
公开(公告)日：2017-03-09
申请号：US15255536
申请日：2016-09-02
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Ivo SZARVASY , Carsten CLEMEN , Tobias MELLENTIEN , Igor SIKORSKI
IPC分类号： F23R3/60 , F23R3/00
CPC分类号： F23R3/60 , F23R3/002 , F23R2900/00018
摘要： An assembly group for a combustion chamber of a gas turbine includes a combustion chamber shingle with a mounting element and a bolt formed as a separate structural component for supporting the combustion chamber shingle at a wall of the combustion chamber. The mounting element has a reception area into which a bolt head of the bolt is inserted transversely with respect to a longitudinal axis of the bolt and anchored therein in a form-fit manner. At the reception area, the mounting element forms an edge area that protrudes substantially radially with respect to the longitudinal axis of the bolt and that at least partially surrounds an edge of the bolt head. The edge of the bolt head does not extend exclusively in a plane that is perpendicular to the longitudinal axis of the bolt.
摘要翻译：用于燃气轮机的燃烧室的组件组包括与安装元件相结合的燃烧室，以及形成为用于在燃烧室的壁处支撑燃烧室木瓦的单独结构部件的螺栓。安装元件具有接收区域，螺栓的螺栓头相对于螺栓的纵向轴线横向插入到该接收区域中，并且以形状配合的方式锚固在该接收区域中。在接收区域，安装元件形成相对于螺栓的纵向轴线大致径向地突出并且至少部分地围绕螺栓头部的边缘的边缘区域。螺栓头的边缘不仅在垂直于螺栓的纵向轴线的平面内延伸。

98. 发明申请

US20170044916A1 GAS TURBINE MEMBRANE SEAL 审中-公开
标题翻译：气体涡轮密封
公开(公告)号：US20170044916A1
公开(公告)日：2017-02-16
申请号：US15237145
申请日：2016-08-15
申请人： ANSALDO ENERGIA SWITZERLAND AG
发明人： Milad MALEKI , Robert PRZYBYL , Thomas HUBER
IPC分类号： F01D11/00 , F01D25/24 , F23R3/60
CPC分类号： F01D11/003 , F01D11/005 , F01D25/246 , F05D2220/32 , F05D2230/80 , F05D2240/35 , F05D2250/711 , F16J3/02 , F23R3/60
摘要： A gas turbine membrane seal is disclosed. The gas turbine membrane seal includes a membrane, the membrane configured and arranged to extend from a first gas turbine component to a second gas turbine component and to separate two volumes, and an anti-fretting part configured and arranged to be attached to the first gas turbine component. A face of the anti-fretting part is adjacent to the membrane, and the face of the anti-fretting part is convex. Further embodiments of the gas turbine membrane seal are also described, along with a gas turbine having the gas turbine membrane seal and a retrofitting method.
摘要翻译：公开了一种燃气轮机膜密封件。燃气涡轮机膜密封件包括膜，膜被构造和布置成从第一燃气轮机部件延伸到第二燃气轮机部件并且分离两个体积;以及抗微动部件，其构造和布置成附接到第一气体涡轮机组件。抗微动部件的表面与膜相邻，并且抗微动部件的表面是凸形的。还描述了燃气轮机膜密封件的另外的实施例，以及具有燃气轮机膜密封件和改装方法的燃气轮机。

99. 发明申请

US20170023250A1 COWLING PART AND COMBUSTOR ASSEMBLY FOR A GAS TURBINE 审中-公开
标题翻译：燃气涡轮机的组装部件和组装机组件
公开(公告)号：US20170023250A1
公开(公告)日：2017-01-26
申请号：US15208315
申请日：2016-07-12
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Carsten CLEMEN
IPC分类号： F23R3/00 , F23R3/10 , F23R3/60
CPC分类号： F23R3/002 , F23R3/06 , F23R3/10 , F23R3/60 , F23R2900/03043
摘要： A covering part for a combustion chamber of a gas turbine is configured and provided to guide a fluid flow downstream of a diffuser of the gas turbine at least partially into a flow area outside of a combustion space of the combustion chamber so as to cool a combustion chamber wall that delimits the combustion space and has at least one mounting edge at which at least one attachment site is provided for fixating the covering part at the combustion chamber wall by means of a separate attachment element. At least one guiding element is provided at the covering part in the area of the mounting edge, which during operation of the gas turbine guides the partial flow of the fluid flow to be guided in the direction of the flow area over and above a part of the attachment element that protrudes from the mounting edge.
摘要翻译：燃气轮机的燃烧室的覆盖部分被构造和设置成将燃气轮机的扩散器的下游的流体流至少部分地引导到燃烧室的燃烧空间外的流动区域，以便冷却燃烧限定燃烧空间并具有至少一个安装边缘，在该安装边缘处设有至少一个附接位置，用于通过单独的附接元件将覆盖部分固定在燃烧室壁处。至少一个引导元件设置在安装边缘的区域中的覆盖部分处，其在燃气轮机的操作期间引导沿着流动区域的方向被引导的流体流的部分流动超过和所述附接元件从所述安装边缘突出。

100. 发明申请

US20160319686A1 SEALS FOR A GAS TURBINE ENGINE ASSEMBLY 审中-公开
标题翻译：燃气涡轮发动机总成的密封
公开(公告)号：US20160319686A1
公开(公告)日：2016-11-03
申请号：US15076127
申请日：2016-03-21
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
发明人： Jun Shi , Ted J. Freeman , David J. Thomas
IPC分类号： F01D11/00 , F23R3/00 , F01D25/14 , F23R3/60 , F01D9/02 , F01D25/28
摘要： A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a pressure-activated seal. The pressure-activated seal is arranged in a channel formed between a first component and a second component that opens toward the high pressure zone.
摘要翻译：适于将高压区域与低压区分离的燃气涡轮发动机组件包括压力激活的密封件。压力激活密封件布置在形成在朝向高压区域打开的第一部件和第二部件之间的通道中。

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