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1. 发明授权

EP2900962B1 GAS TURBINE ENGINE AIRFOIL WITH VANE PLATFORM COOLING PASSAGE 有权转让
公开(公告)号：EP2900962B1
公开(公告)日：2018-12-05
申请号：EP13841073.3
申请日：2013-09-26
申请人： United Technologies Corporation , Boeke, Mark A. , Gregg, Shawn J. , Riley, Sarah , Degray, Jeffrey J. , Salzillo, Richard M.
发明人： BOEKE, Mark A. , GREGG, Shawn J. , RILEY, Sarah , DEGRAY, Jeffrey J. , SALZILLO, Richard M.
IPC分类号： F01D5/18 , F01D25/08 , F01D25/24 , F01D9/02 , F01D25/12
CPC分类号： F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
摘要： A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

2. 发明公开

EP2900962A1 GAS TURBINE ENGINE AIRFOIL WITH VANE PLATFORM COOLING PASSAGE 有权转让
标题翻译：随着对叶片的平台冷却通道燃气涡轮发动机叶片
公开(公告)号：EP2900962A1
公开(公告)日：2015-08-05
申请号：EP13841073.3
申请日：2013-09-26
申请人： United Technologies Corporation , Boeke, Mark A. , Gregg, Shawn J. , Riley, Sarah , Degray, Jeffrey J. , Salzillo, Richard M.
发明人： BOEKE, Mark A. , GREGG, Shawn J. , RILEY, Sarah , DEGRAY, Jeffrey J. , SALZILLO, Richard M.
IPC分类号： F02C7/12 , F01D5/18 , F02K3/00
CPC分类号： F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
摘要： A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

3. 发明公开

EP2900967A2 AIRFOIL WITH VARIABLE TRIP STRIP HEIGHT 有权转让
标题翻译：带可变行程杆高度的AIRFOIL
公开(公告)号：EP2900967A2
公开(公告)日：2015-08-05
申请号：EP13866792.8
申请日：2013-09-26
申请人： United Technologies Corporation , Riley, Sarah , Boeke, Mark A. , Degray, Jeffrey J. , Gregg, Shawn J.
发明人： RILEY, Sarah , BOEKE, Mark A. , DEGRAY, Jeffrey J. , GREGG, Shawn J.
IPC分类号： F02C7/12 , F01D5/18 , F01D25/12
CPC分类号： F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
摘要： An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.
摘要翻译：用于燃气涡轮发动机的翼型部件包括从平台延伸的翼型。翼型件和平台中的至少一个包括由表面限定的冷却通道。人字形跳闸条从表面延伸到沿着长度的跳闸条高度处的冷却通路。跳闸条高度沿长度变化。用于燃气涡轮发动机的涡轮叶片包括内部和外部平台。内部平台上设有冷却通道。冷却通道由第一和第二径向延伸的腿部提供，所述第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接。一对翼型从相同的内部平台径向延伸。跳闸条从表面沿着长度以跳闸条高度从表面延伸到圆周通道中。跳闸高度沿着长度变化。

4. 发明公开

EP3290638A1 COOLED TURBINE VANE WITH ALTERNATELY ORIENTATED FILM COOLING HOLE ROWS 有权转让
标题翻译：带有取向膜取向冷却孔排的冷却式涡轮叶片
公开(公告)号：EP3290638A1
公开(公告)日：2018-03-07
申请号：EP17189120.3
申请日：2017-09-01
申请人： United Technologies Corporation
发明人： LoRICCO, Nicholas M. , SALZILLO, Jr., Richard M. , DeGRAY, Jeffrey J. , BOEKE, Mark A.
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2260/202 , F05D2260/221 , Y02T50/676
摘要： A cooled component (62) for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis (A) of the gas turbine engine. The internal ribs are disposed within an internal cavity (110) defining cooling air passages within the cooled component (62). A plurality of cooling holes (84, 85) are arranged in rows (80) with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes (84, 85) includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes (84, 85) is disposed on a side opposite the internal rib relative to a corresponding internal opening.
摘要翻译：用于燃气涡轮发动机的冷却部件（62）包括基本平行于燃气涡轮发动机的纵向轴线（A）延伸的多个内部肋。内肋布置在限定冷却部件（62）内的冷却空气通道的内腔（110）内。多个冷却孔（84,85）排成行（80），其中轴向取向在径向向外偏压引导冷却空气径向向外和径向向内偏压引导冷却空气径向向内之间交替。每个冷却孔（84,85）包括与冷却空气通道之一连通的内部开口和通向冷却部件的外表面的外部开口。多个冷却孔（84,85）中的每个冷却孔的外部开口相对于相应的内部开口布置在与内部肋相对的一侧上。

5. 发明公开

EP3034805A1 FEATHERSEAL HAVING A TAPERED RADIAL PORTION AND GAS TURBINE ENGINE SECTION COMPRISING SUCH A FEATHER SEAL 有权转让
标题翻译：封带有一个圆锥形径向节和第燃气涡轮发动机带材这样的密封条
公开(公告)号：EP3034805A1
公开(公告)日：2016-06-22
申请号：EP15200752.2
申请日：2015-12-17
申请人： United Technologies Corporation
发明人： BOEKE, Mark A. , SALZILLO, Richard M. , RAJCHEL, Kevin , DeGRAY, Jeffrey J.
IPC分类号： F01D9/04 , F01D11/00
摘要： A section of a gas turbine engine (20) according to an exemplary aspect of this disclosure includes, among other things, a vane assembly (60) including a featherseal slot (82). The section further includes a featherseal (92, 94) at least partially received in the featherseal slot (82). The featherseal (92, 94) includes a radial portion (92R, 94R) having at least one tapered side. A corresponding featherseal is also provided.
摘要翻译：燃气涡轮发动机（20）根据本公开的示例性方面的部分包括，除了别的以外，一个叶片组件（60）包括一个featherseal槽（82）。该部分包括一个另外featherseal（92，94）在featherseal槽（82）至少部分地接收。所述featherseal（92，94）包括具有至少一个锥形侧面的径向部分（92R，94R）。因此相应的featherseal设置。

6. 发明公开

EP3091199A1 AIRFOIL AND CORRESPONDING VANE 审中-公开
标题翻译： SCHUUFELPROFIL UNDZUGEHÖRIGELEITSCHAUFEL
公开(公告)号：EP3091199A1
公开(公告)日：2016-11-09
申请号：EP16168598.7
申请日：2016-05-06
申请人： United Technologies Corporation
发明人： BOEKE, Mark A. , DeGRAY, Jeffrey J. , SALZILLO, Richard M.
IPC分类号： F01D25/12 , F01D9/04
CPC分类号： F01D9/041 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： An airfoil (90) for a gas turbine engine (20) includes a first platform (94) located at a first end of a first airfoil (92). A cooling passage (100) extends through the first platform (94) and includes a first portion (108) that has a first thickness (D1) and a second portion (110) that has a second thickness (D2) and surrounds opposing ends of the first portion (108).
摘要翻译：用于燃气涡轮发动机（20）的翼型件（90）包括位于第一翼型件（92）的第一端处的第一平台（94）。冷却通道（100）延伸穿过第一平台（94）并且包括具有第一厚度（D1）和第二部分（110）的第一部分（108），第二部分具有第二厚度（D2）并且包围第二部分第一部分（108）。

7. 发明公开

EP3020929A1 AIRFOIL PLATFORM RIM SEAL ASSEMBLY 审中-公开
标题翻译： SCHAUFELPLATTFORMKANTENDICHTUNGSANORDNUNG
公开(公告)号：EP3020929A1
公开(公告)日：2016-05-18
申请号：EP15194006.1
申请日：2015-11-11
申请人： United Technologies Corporation
发明人： AGGARWALA, Andrew S. , BERGMAN, Russell J. , BOEKE, Mark A. , LANA, Kyle C. , SNYDER, Daniel A.
IPC分类号： F01D11/00 , F01D11/02
CPC分类号： F01D11/006 , F01D5/22 , F01D11/001 , F01D11/02
摘要： An airfoil stage of a turbine engine (20) includes an upstream airfoil assembly (62), a downstream airfoil assembly (64) in rotational relationship to the upstream airfoil assembly (62) and a rim seal assembly (118) integrated therebetween. The rim seal assembly (118) may include a sloped downstream portion (94) of a platform (70) of the upstream airfoil assembly (62), an upstream segment (110) of a platform (76) of the downstream airfoil assembly (64) and a nub (120) that projects radially outward from the upstream segment (110). The downstream portion (94) and the upstream segment (110) are spaced from one-another defining a cooling cavity (114) therebetween for the flow of cooling air. The portion (94) and segment (110) overlap axially such that the nub (120) is axially aligned to the downstream portion (94) to reduce a core airflow (73) into the cooling cavity (114).
摘要翻译：涡轮发动机（20）的翼型段包括上游翼型组件（62），与上游翼型组件（62）成旋转关系的下游翼型组件（64）和与它们之间形成的边缘密封组件（118）。轮缘密封组件（118）可以包括上游翼型组件（62）的平台（70）的倾斜下游部分（94），下游翼型组件（64）的平台（76）的上游段（110））和从上游段（110）径向向外突出的突出部（120）。下游部分（94）和上游段（110）在其间限定冷却空腔（114）之间的间隔开，以使冷却空气流动。部分（94）和段（110）轴向重叠，使得凸块（120）与下游部分（94）轴向对齐，以将芯气流（73）减少到冷却腔（114）中。

8. 发明公开

EP2964934A1 GAS TURBINE ENGINE COMPONENT HAVING VARIABLE WIDTH FEATHER SEAL SLOT 有权转让
标题翻译：宽度可变的弹性密封槽燃气涡轮发动机部件
公开(公告)号：EP2964934A1
公开(公告)日：2016-01-13
申请号：EP14760315.3
申请日：2014-03-06
申请人： United Technologies Corporation
发明人： BOEKE, Mark A. , RAJCHEL, Kevin , SALZILLO,Richard M. , DEGRAY, Jeffrey J. , MAINELLI, Allison
IPC分类号： F02C7/28 , F02C9/16 , F01D5/22 , F01D11/00
CPC分类号： F01D11/005 , F01D9/041 , F05D2240/11 , F05D2240/57
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a mate face and a feather seal slot axially extending along the mate face, the feather seal slot having a variable width along a portion of its axial length.

9. 发明授权

EP3296519B1 FLOWPATH COMPONENT FOR A GAS TURBINE ENGINE INCLUDING A CHORDAL SEAL 有权转让
公开(公告)号：EP3296519B1
公开(公告)日：2019-08-14
申请号：EP17191286.8
申请日：2017-09-15
申请人： United Technologies Corporation
发明人： BOEKE, Mark A. , DeGRAY, Jeffrey J. , SALZILLO Jr., Richard M.
IPC分类号： F01D11/00

10. 发明授权

EP2900967B1 TURBINE VANE WITH TRIP STRIPS OF VARIABLE HEIGHT 有权转让
公开(公告)号：EP2900967B1
公开(公告)日：2019-07-17
申请号：EP13866792.8
申请日：2013-09-26
申请人： United Technologies Corporation
发明人： RILEY, Sarah , BOEKE, Mark A. , DEGRAY, Jeffrey J. , GREGG, Shawn J.
IPC分类号： F02C7/12 , F01D5/18 , F01D25/12

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