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1. 发明申请

WO2015112226A2 BLADE FEATURE TO SUPPORT SEGMENTED COVERPLATE 审中-公开
标题翻译：刀片特征支持SEGMENTED COVERPLATE
公开(公告)号：WO2015112226A2
公开(公告)日：2015-07-30
申请号：PCT/US2014/064041
申请日：2014-11-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： HOUGH, Matthew Andrew , CORCORAN, Christopher , BEATTIE, Jeffrey S.
IPC分类号： F01D5/14 , F01D5/30
CPC分类号： F01D5/3015 , F01D25/005 , F05D2220/32 , Y02T50/671
摘要： A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.
摘要翻译：燃气涡轮发动机部件包括具有前缘和后缘的叶片。刀片安装到盘上并且被配置为围绕轴线旋转。平台支撑刀片，并且在前缘具有前缘部分和在后缘处的后缘部分。前边缘部分和后边缘部分中的至少一个包括由内翼片和与内翼片径向向外间隔开的外翼部限定的口部。至少一个盖板被内翼片保持抵靠盘片。还公开了一种燃气涡轮发动机。

2. 发明申请

WO2014025440A2 TURBINE BLADE ROOT WITH MICROCIRCUIT COOLING PASSAGES 审中-公开
标题翻译：涡轮叶片带微型冷却通道
公开(公告)号：WO2014025440A2
公开(公告)日：2014-02-13
申请号：PCT/US2013/041776
申请日：2013-05-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： BEATTIE, Jeffrey S. , JACQUES, Jeffrey Michael , PIGGUSH, Justin D.
CPC分类号： F01D5/187 , B22C9/04 , B22C9/103 , F05D2230/211 , F05D2260/204 , Y02T50/676 , Y10T29/49316
摘要： A method of fabricating an airfoil includes the steps of fabricating a first core including a first plurality of ribs defining a first plurality of passages of a completed airfoil, and fabricating as second core including a second plurality of ribs defining a second plurality of passages of the completed airfoil. The second plurality of ribs includes a plurality of standoffs. The plurality of standoffs set a spacing between the first plurality of ribs and the second plurality of ribs to define a spacing between the first plurality of channels and the second plurality of channels of the completed airfoil. The airfoil is then molded about the core assembly. Once completed, the core assembly is removed to provide a completed airfoil incorporating multiple microcircuits with a desired stability and structural integrity.
摘要翻译：一种制造翼型的方法包括以下步骤：制造第一芯，其包括限定完成的翼型件的第一多个通道的第一多个肋，并且制造为第二芯，该第二芯包括限定第二多个通路的第二多个肋完成机翼。第二多个肋包括多个支座。所述多个支座在所述第一多个肋与所述第二多个肋之间设置间隔，以限定所述第一多个通道与所述完整翼型的所述第二多个通道之间的间隔。然后将翼型件围绕芯组件成型。一旦完成，移除芯组件以提供具有期望的稳定性和结构完整性的并入多个微电路的完整翼型件。

3. 发明申请

WO2014150342A1 CAST COMPONENT HAVING CORNER RADIUS TO REDUCE RECRYSTALLIZATION 审中-公开
标题翻译：具有角度半径的CAST组件可以减少重构
公开(公告)号：WO2014150342A1
公开(公告)日：2014-09-25
申请号：PCT/US2014/022990
申请日：2014-03-11
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ASTERLIN, Max , BEATTIE, Jeffrey S. , GUNN, John R.
IPC分类号： B22D19/08 , B22D17/20 , B22D17/00 , B22D15/00
CPC分类号： B22D15/00 , B22C9/10 , B22D25/02 , B22D27/04 , B22D27/045 , C30B11/00 , C30B29/52 , F01D5/18 , F01D5/187 , F01D5/282 , F01D9/041 , F02C3/04 , F05D2220/30 , F05D2230/21 , F05D2230/211 , F05D2260/20 , F05D2260/204 , F05D2300/607 , F05D2300/608 , Y02T50/676
摘要： A cast component includes a cast body that has a single crystal microstructure and an internal corner bounding an internal cavity. The single crystal microstructure defines a critical internal residual stress with respect to investment casting of the cast body using a refractory metal core beyond which the single crystal microstructure recrystallizes under a predetermined condition. The internal corner has a corner radius that is greater than a critical corner radius below which an amount of internal residual stress in the single crystal microstructure exceeds the critical internal residual stress. The internal cavity includes a cross section less than about 20 mils near the corner radius.
摘要翻译：铸造组件包括具有单晶微结构的铸造体和包围内腔的内角。单晶微结构定义了使用难熔金属芯相对于铸造体的熔模铸造的关键内部残余应力，超临界内的单晶微结构在预定条件下重结晶。内角具有大于临界角半径的角半径，低于该半径时，单晶微结构中的内部残余应力的量超过临界内部残余应力。内腔包括在拐角半径附近小于约20密耳的横截面。

4. 发明申请

WO2014134057A1 INSPECTING ONE OR MORE APERTURES OF A COMPONENT USING MOLDABLE MATERIAL 审中-公开
标题翻译：使用可塑材料检查组件的一个或多个孔
公开(公告)号：WO2014134057A1
公开(公告)日：2014-09-04
申请号：PCT/US2014/018370
申请日：2014-02-25
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： REED, Gordon M. , ROMANELLI, James , KOONANKEIL, James M. , KLINEFELTER, Kevin J. , FRITCH, Markus W. , HOLLMAN, Kenneth J. , BEATTIE, Jeffrey S.
IPC分类号： G01B11/00 , G01M13/00
CPC分类号： G01B11/00 , G01B11/24 , G01B21/20 , G01M13/00
摘要： A method is provided for inspecting at least one aperture of a component with curable material and an inspection system. At least a portion of the curable material is injected into the aperture. The curable material conforms to at least a portion the aperture and subsequently cures and forms a mold of at least a portion of the aperture. The mold is removed from the aperture. At least a portion of a geometry of the mold is compared to at least a portion of a geometry of a reference model for the aperture using the inspection system.
摘要翻译：提供了一种用于使用可固化材料和检查系统检查部件的至少一个孔的方法。至少一部分可固化材料被注入孔中。可固化材料符合孔的至少一部分并随后固化并形成孔的至少一部分的模具。将模具从孔中取出。将模具的几何形状的至少一部分与使用检查系统的孔的参考模型的几何形状的至少一部分进行比较。

5. 发明申请

WO2015053846A2 ENGINE COMPONENT HAVING PLATFORM WITH PASSAGEWAY 审中-公开
标题翻译：具有PASSAGEWAY平台的发动机组件
公开(公告)号：WO2015053846A2
公开(公告)日：2015-04-16
申请号：PCT/US2014/049749
申请日：2014-08-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： HOUGH, Matthew Andrew , BEATTIE, Jeffrey S. , PROPHETER-HINCKLEY, Tracy A. , QUACH, San
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D25/12 , F01D5/12 , F01D5/187 , F01D9/041 , F01D11/006 , F01D11/08 , F04D29/324 , F04D29/38 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2230/21 , F05D2230/211 , F05D2230/30 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/2212 , F05D2300/13 , F05D2300/20 , Y02T50/676
摘要： One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof. The platform including a core passageway configured to communicate fluid to the mateface.
摘要翻译：本公开的一个示例性实施例涉及包括部件的燃气涡轮发动机。该部件包括在其圆周侧上具有接合面的平台。该平台包括配置成将流体传送到配合面的芯通道。

6. 发明申请

WO2014186005A2 GAS TURBINE ENGINE COMPONENT WITH COMBINED MATE FACE AND PLATFORM COOLING 审中-公开
标题翻译：气体涡轮发动机组件与组合的油面和平台冷却
公开(公告)号：WO2014186005A2
公开(公告)日：2014-11-20
申请号：PCT/US2014/015194
申请日：2014-02-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： LEWIS, Scott D. , RAPP, Brandon M. , BEATTIE, Jeffrey S. , HOUGH, Matthew Andrew , TELLER, Bret M. , JACQUES, Jeffrey Michael , ASTERLIN, Max
CPC分类号： F01D5/186 , F01D5/18 , F01D9/023 , F01D9/065 , F01D11/08 , F01D25/12 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/02 , F23R3/04 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括在前缘和后缘之间轴向延伸的平台，其周向地在第一配合面和第二配合面之间延伸，以及包括气体路径表面和非气体通道表面。该部件限定至少一个至少部分地在部件内部延伸的空腔。第一多个冷却孔从所述至少一个空腔延伸到所述第一配合面和所述第二配合面中的至少一个，并且第二多个冷却孔从所述至少一个空腔或非气体通道表面延伸到气路面。

7. 发明申请

WO2013138331A1 A METHOD FOR INSPECTING A MANUFACTURING DEVICE 审中-公开
标题翻译：检查制造设备的方法
公开(公告)号：WO2013138331A1
公开(公告)日：2013-09-19
申请号：PCT/US2013/030508
申请日：2013-03-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROMANELLI, James , BEATTIE, Jeffrey S. , BOYER, Jesse R. , ERICKSON, Robert E. , JOYNER, Randall W. , SNYDER, Daniel A. , KRAUSE, David A. , TONG, Kun
IPC分类号： G01N21/84 , G01B11/00 , G01M13/00
CPC分类号： G05B19/4187 , G05B19/401 , G05B2219/37205 , G05B2219/37555 , G06F17/50 , Y02P90/265
摘要： A method is provided for inspecting a plurality of parts with an electronic measurement device and a processing system. The method includes a step of creating surface geometry maps of the parts utilizing the electronic measurement device, where each part was manufactured utilizing the manufacturing device. Geometric part models of the parts are generated from the surface geometry maps. The part models can subsequently be analyzed to determine whether a manufacturing device that manufactured the plurality of parts manufactures parts that comply with a part design specification.
摘要翻译：提供了一种利用电子测量装置和处理系统检查多个部件的方法。该方法包括使用电子测量装置创建部件的表面几何图形的步骤，其中每个部件利用制造装置制造。部件的几何零件模型从表面几何图生成。随后可以分析零件模型以确定制造多个零件的制造装置是否制造符合零件设计规范的零件。

8. 发明申请

WO2015057310A2 PLATFORM COOLING CORE FOR A GAS TURBINE ENGINE ROTOR BLADE 审中-公开
标题翻译：用于气体涡轮发动机转子叶片的平台冷却芯
公开(公告)号：WO2015057310A2
公开(公告)日：2015-04-23
申请号：PCT/US2014/053042
申请日：2014-08-28
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： HOUGH, Matthew Andrew , BEATTIE, Jeffrey S.
IPC分类号： F01D5/18 , F01D25/12 , F02C7/18
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/2212
摘要： A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.
摘要翻译：根据本公开的示例性方面的转子叶片包括平台，从平台延伸的翼型件，至少部分地在翼型内延伸的第一冷却芯，在平台内部的第二冷却芯以及在所述平台的配合面和所述第二冷却芯之间延伸的第一冷却孔。

9. 发明申请

WO2014160215A1 ROTOR BLADE WITH A CONIC SPLINE FILLET AT AN INTERSECTION BETWEEN A PLATFORM AND A NECK 审中-公开
标题翻译：在平台和NECK之间的交点处的转矩叶片
公开(公告)号：WO2014160215A1
公开(公告)日：2014-10-02
申请号：PCT/US2014/026062
申请日：2014-03-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： HOUGH, Matthew A. , BEATTIE, Jeffrey S.
IPC分类号： F01D5/22 , F01D5/30 , F02C7/20
CPC分类号： F01D5/141 , F01D5/147 , F01D5/22 , F01D5/3007 , F05D2220/30 , F05D2240/30 , F05D2240/80 , F05D2250/14 , F05D2250/711 , F05D2250/712 , F05D2260/941
摘要： A rotor blade for a turbine engine includes an airfoil that is connected to a base. The base includes a platform, a neck and a fillet. The fillet extends along at least a portion of an intersection between the platform and the neck. The fillet has a radius that substantially continuously changes as the fillet extends from the platform to the neck.
摘要翻译：用于涡轮发动机的转子叶片包括连接到基座的翼型件。底座包括平台，颈部和圆角。圆角沿平台和颈部之间的交叉点的至少一部分延伸。圆角的半径随着圆角从平台延伸到颈部而基本上连续变化。

10. 发明申请

WO2014099082A2 TURBINE BLADE ROOT PROFILE 审中-公开
标题翻译：涡轮叶片轮廓
公开(公告)号：WO2014099082A2
公开(公告)日：2014-06-26
申请号：PCT/US2013/061920
申请日：2013-09-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： BEATTIE, Jeffrey S. , JACQUES, Jeffrey Michael
CPC分类号： F01D5/30 , F01D5/18 , F01D5/3007
摘要： A turbine blade for a gas turbine engine includes an airfoil that extends in a first radial direction from a platform. A root extends from the platform in a second radial direction and has opposing lateral sides that provide a firtree-shaped contour. The contour includes first, second and third lobes on each of the lateral sides and that tapers relative to the radial direction away from the platform. The first, second and third lobes each provide contact surfaces arranged at about 45° relative to the radial direction. A contact plane on each lateral side at an angle of about 11° relative to the radial direction defining a contact point on each of the contact surfaces. The first, second and third lobes each include first, second and third grooves that are substantially aligned with one another along an offset plane spaced a uniform offset distance from the contact plane.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片包括从平台沿第一径向方向延伸的翼型件。根部在第二径向方向上从平台延伸并且具有相对的侧向侧面，该侧面侧面提供保持曲面的轮廓。轮廓包括在每个侧面上的第一，第二和第三凸角，并且相对于远离平台的径向方向逐渐变细。第一，第二和第三叶片各自提供相对于径向方向布置成大约45°的接触表面。在每个侧面上的接触平面相对于径向方向以约11°的角度限定每个接触表面上的接触点。第一，第二和第三凸耳各自包括第一，第二和第三凹槽，其沿着与接触平面间隔开均匀偏移距离的偏移平面彼此基本对准。

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