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1. 发明授权

US08684662B2 Ring segment with impingement and convective cooling 有权
标题翻译：环形区段具有冲击和对流冷却
公开(公告)号：US08684662B2
公开(公告)日：2014-04-01
申请号：US12875224
申请日：2010-09-03
申请人： Nan Jiang , Samuel R. Miller, Jr. , Friedrich Rogers , Hubert Paprotna
发明人： Nan Jiang , Samuel R. Miller, Jr. , Friedrich Rogers , Hubert Paprotna
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2240/11 , F05D2260/201
摘要： A ring segment for a gas turbine engine includes an outer panel defining a structural body for the ring segment. An outer side of an inner panel is attached to an inner side of the outer panel at an interface, and an inner side of the inner panel defines a portion of a hot gas path through the gas turbine engine. An outer side of the outer panel, opposite from the interface, is in communication with a source of cooling air. A plurality of impingement holes extend through the outer panel from the outer side to the inner side of the outer panel for directing impingement air to the outer side of the inner panel. The outer and inner panels define a plurality of flow channels at the interface for effecting convective cooling of the outer panel along the flow channels between the outer and inner panels.
摘要翻译：用于燃气涡轮发动机的环段包括限定用于环段的结构体的外板。内板的外侧在界面处附接到外板的内侧，并且内板的内侧限定通过燃气涡轮发动机的热气路径的一部分。外部面板的与界面相对的外侧与冷却空气源连通。多个冲击孔从外板的外侧到内侧延伸穿过外板，用于将冲击空气引导到内板的外侧。外板和内板在界面处限定多个流动通道，用于沿着外板和内板之间的流动通道进行外板的对流冷却。

2. 发明授权

US09388704B2 Vane array with one or more non-integral platforms 有权
标题翻译：具有一个或多个非积分平台的叶片阵列
公开(公告)号：US09388704B2
公开(公告)日：2016-07-12
申请号：US14078599
申请日：2013-11-13
申请人： Andrew S. Lohaus , Christian Xavier Campbell , Samuel R. Miller, Jr. , John J. Marra
发明人： Andrew S. Lohaus , Christian Xavier Campbell , Samuel R. Miller, Jr. , John J. Marra
IPC分类号： F01D9/04 , F01D25/24 , F01D5/14 , F01D5/30 , F01D11/00
CPC分类号： F01D9/042 , F01D5/143 , F01D5/3053 , F01D11/008 , F01D25/246 , F05D2240/80
摘要： A vane array adapted to be coupled to a vane carrier within a gas turbine engine is provided comprising: a plurality of elongated airfoils comprising at least a first airfoil and a second airfoil located adjacent to one another; a U-ring; first connector structure for coupling a radially inner end section of each of the first and second airfoils to the U-ring; second connector structure for coupling a radially outer end section of each of the first and second airfoils to the vane carrier; a platform extending between the first and second airfoils; and platform connector structure for coupling the platform to one of the U-ring and the vane carrier.
摘要翻译：提供一种适于联接到燃气涡轮发动机内的叶片载体的叶片阵列，包括：多个细长翼型件，其包括至少第一翼型件和彼此相邻布置的第二翼型件; U形圈; 第一连接器结构，用于将第一和第二翼型件的每个的径向内端部分联接到U形环; 第二连接器结构，用于将每个第一和第二翼型件的径向外端部分连接到叶片承载件; 在第一和第二翼型之间延伸的平台; 以及用于将平台联接到U形环和叶片载体之一的平台连接器结构。

3. 发明授权

US08926267B2 Ambient air cooling arrangement having a pre-swirler for gas turbine engine blade cooling 有权
标题翻译：环境空气冷却装置具有用于燃气涡轮发动机叶片冷却的预旋转器
公开(公告)号：US08926267B2
公开(公告)日：2015-01-06
申请号：US13766909
申请日：2013-02-14
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra
IPC分类号： F01D25/12 , F01D5/14 , F01D9/06 , F02C7/12 , F01D5/18 , F01D5/08 , F01D11/00
CPC分类号： F01D5/187 , F01D5/082 , F01D5/143 , F01D9/065 , F01D11/001 , F01D25/12 , F02C7/12 , F05D2240/127
摘要： A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.
摘要翻译：一种燃气涡轮发动机，包括：环境空气冷却回路（10），其具有设置在涡轮机叶片（22）中并与环境空气源（12）流体连通的冷却通道（26）;以及预旋流器 18），所述预旋转器具有：内罩（38）; 外护罩（56）; 以及多个导向叶片（42），每个导向叶片从内护罩跨越到外护罩。周向相邻的导向叶片（46,48）在其间限定相应的喷嘴（44）。通过涡轮叶片的旋转产生的力通过冷却回路激励环境空气。预旋流器被配置为对通过喷嘴抽吸的环境空气赋予涡流，并且将旋转的环境空气引导到涡轮叶片的基部。预旋转器的端壁（50,54）可以是轮廓。

4. 发明授权

US09017014B2 Aft outer rim seal arrangement 有权
标题翻译：后外缘密封布置
公开(公告)号：US09017014B2
公开(公告)日：2015-04-28
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/08 , F01D25/12 , F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

5. 发明申请

US20150003973A1 AFT OUTER RIM SEAL ARRANGEMENT 有权
标题翻译： AFT外部RIM密封安排
公开(公告)号：US20150003973A1
公开(公告)日：2015-01-01
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

6. 发明授权

US5271715A Cooled turbine blade 失效
标题翻译：冷却涡轮叶片
公开(公告)号：US5271715A
公开(公告)日：1993-12-21
申请号：US993584
申请日：1992-12-21
申请人： Mark F. Zelesky , Samuel R. Miller, Jr. , William L. Plank , Thomas A. Auxier
发明人： Mark F. Zelesky , Samuel R. Miller, Jr. , William L. Plank , Thomas A. Auxier
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/2212
摘要： An air cooled gas engine turbine blade that includes a plurality of longitudinally spaced cavities adjacent the leading edge of the blade is designed to include angularly disposed impingement passages flowing cooling air into each of the cavities in a direction extending from the root to the tip of the blade and including an annular projection upstream of the impingement passage but adjacent thereto for directing air into the respective cavities with total instead of static pressure. The impingement holes are oriented to align with the film cool holes in the blade surface at the leading edge. Ribs formed between cavities are also oriented to be parallel to the impingement holes.
摘要翻译：包括与叶片的前缘相邻的多个纵向隔开的空腔的空气冷却燃气发动机涡轮机叶片被设计成包括角度设置的冲击通道，其将冷却空气沿从根部延伸到每个空腔的方向叶片并且包括在冲击通道上游但邻近的环形突起，用于将空气全部导入相应的空腔中而不是静压力。冲击孔定位成与前缘处的叶片表面中的膜冷却孔对准。在空腔之间形成的肋还被定向成平行于冲击孔。

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