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1. 发明申请

US20070081890A1 Shroud with aero-effective cooling 有权
标题翻译：护罩与空气有效的冷却
公开(公告)号：US20070081890A1
公开(公告)日：2007-04-12
申请号：US11247812
申请日：2005-10-11
申请人： Paul Lutjen , Dmitriy Romanov , Jeremy Drake , Gary Grogg , Gregory Reinhardt
发明人： Paul Lutjen , Dmitriy Romanov , Jeremy Drake , Gary Grogg , Gregory Reinhardt
IPC分类号： F03B11/00
CPC分类号： F01D11/24
摘要： A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.
摘要翻译：涡轮机罩部分包括通过表面中的开口将冷却空气排出的冷却通道。冷却通道相对于预期的流体流动方向形成一个角度。该角度限定圆周方向上的角度分量，其与预期的流体流动方向对准，以减少通过发动机的流体流动的动量能量损失。

2. 发明申请

US20060216143A1 Split ring retainer for turbine outer air seal 有权
标题翻译：用于涡轮机外部空气密封的分离环保持器
公开(公告)号：US20060216143A1
公开(公告)日：2006-09-28
申请号：US11091204
申请日：2005-03-28
申请人： Steven Trinks , Steven Lemieux , Gregory Reinhardt
发明人： Steven Trinks , Steven Lemieux , Gregory Reinhardt
IPC分类号： F01D9/00
CPC分类号： F01D11/08 , F01D9/04 , F01D25/246 , Y02T50/671
摘要： A retainer for securing the outer air seal assembly of a turbine rotor stage in a locked position. The outer air seal is suspended from the turbine casing over the rotor stage and is locked to the casing by annular segmented locking keys. A series of circumferentially spaced seats are located upon the front face of the locking key segments with the outer surfaces of the seats describing a circle approximating a first diameter. A split ring retainer is slidably carried in a radially disposed groove and is arranged to secure the key segments in a locked position. A series of lugs extend inwardly from the inside wall of the ring. The lugs are circumferentially spaced about the ring with the inner surface of the lugs approximating a circle having a second diameter that is less that of the first diameter approximated by the seats. The lugs are spaced so that each lug can be seated upon a seat to flex the ring outwardly in a radial direction and thus secure the key segment in a locking position.
摘要翻译：用于将涡轮转子级的外部空气密封组件固定在锁定位置的保持器。外部空气密封件从涡轮机壳体悬挂在转子平台上并且通过环形分段锁定锁定到壳体。一系列周向间隔开的座椅位于锁定钥匙段的前表面上，座椅的外表面描述了接近第一直径的圆圈。开口环保持器可滑动地承载在径向设置的凹槽中并且被布置成将键段固定在锁定位置。一系列凸耳从环的内壁向内延伸。凸耳围绕环周向间隔开，凸耳的内表面近似于具有小于由座椅近似的第一直径的第二直径的圆。凸耳是间隔开的，使得每个凸耳可以坐在座上以使环向径向方向弹性，从而将键部分固定在锁定位置。

3. 发明申请

US20070098545A1 Integrated bladed fluid seal 有权
标题翻译：集成叶片流体密封
公开(公告)号：US20070098545A1
公开(公告)日：2007-05-03
申请号：US11260357
申请日：2005-10-27
申请人： Ioannis Alvanos , Rajendra Agrawal , Gregory Reinhardt
发明人： Ioannis Alvanos , Rajendra Agrawal , Gregory Reinhardt
IPC分类号： F04D29/08
CPC分类号： F01D11/02 , F01D5/081 , F01D11/001 , F02C7/28 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.
摘要翻译：公开了用于限制冷却空气泄漏并改善冷却空气对密封件的分配的燃气轮机叶片与叶片接口密封件的各种实施例。因此，涡轮转子包含径向延伸和周向分布的叶片的第一和第二阶段。阶段通过位于叶片的径向内侧的环形联接器彼此轴向分开，在它们之间形成室。在叶片级之间插入叶片级。叶片台包含一个面向径向内侧的平台。环从第一和第二叶片台阶中的每一个朝向叶片台轴向突出。环也可以从联接器径向伸向叶片台。环与陆部径向配合，并一起形成叶片与叶片接口密封。联接器包括用于将冷却的流体径向引入到腔室中以用于冷却密封件的孔。

4. 发明授权

US09228451B2 Gas turbine engine module adapter to a carrier 有权
标题翻译：燃气轮机发动机模块适配器到载体
公开(公告)号：US09228451B2
公开(公告)日：2016-01-05
申请号：US13099681
申请日：2011-05-03
申请人： Gregory Reinhardt , Joseph Swiderski , Douglas Pollock , Réal Barrette , Stéphane Mongeau
发明人： Gregory Reinhardt , Joseph Swiderski , Douglas Pollock , Réal Barrette , Stéphane Mongeau
IPC分类号： B25B1/24 , F01D25/28
CPC分类号： F01D25/285 , B66C11/04 , F01D25/24 , F01D25/28 , F05D2220/30 , F05D2220/32 , F05D2220/36 , F05D2230/60 , F05D2230/68 , F05D2230/72 , F05D2240/91 , Y02T50/671 , Y10T29/49229 , Y10T29/49826
摘要： An engine mounting arrangement is provided for supporting a gas turbine engine. The mounting arrangement comprises a module adaptor mounted to an overhead or a ground based carrier for rotation about a substantially horizontal axis. The module adaptor extends horizontally from a base to an axially-opposed distal end having a first mounting interface configured for attachment to a module of the engine. The module adaptor holds the engine by the module to which it is attached and with the other engine modules projecting in a cantilever fashion from the supported module.
摘要翻译：提供用于支撑燃气涡轮发动机的发动机安装装置。安装装置包括安装到顶部或基于地面的载体上的模块适配器，用于围绕基本上水平的轴线旋转。模块适配器从基座水平延伸到具有构造成附接到发动机的模块的第一安装接口的轴向相对的远端。模块适配器通过其所连接的模块将引擎保持在发动机上，而其它发动机模块以悬臂方式从支撑的模块突出。

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