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1.发明申请GAS TURBINE ENGINE COMPONENT HAVING TRANSVERSELY ANGLED IMPINGEMENT RIBS 审中-公开气动涡轮发动机组件具有横向旋转轴承RIBS公开(公告)号：US20160003053A1
公开(公告)日：2016-01-07
申请号：US14759271
申请日：2013-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. PROPHETER-HINCKLEY , San QUACH , Matthew A. DEVORE
CPC classification number: F01D5/186 , B22D30/00 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2230/21 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , F23R3/002
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion that includes a first wall spaced apart from a second wall and disposed about a centerline axis. At least one rib extends between the first wall and the second wall. The at least one rib extends along a rib axis that is transversely angled relative to the centerline axis. At least one impingement hole extends through the at least one rib.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括主体部分，其包括与第二壁间隔开并围绕中心线轴线设置的第一壁。 至少一个肋在第一壁和第二壁之间延伸。 至少一个肋沿着相对于中心线轴线横向成角度的肋轴线延伸。 至少一个冲击孔延伸穿过至少一个肋。
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公开(公告)号：US20160130950A1
公开(公告)日：2016-05-12
申请号：US14896730
申请日：2014-06-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： San QUACH , Tracy A. PROPHETER-HINCKLEY , Matthew A. DEVORE
CPC classification number: F01D5/186 , B22C9/103 , F01D5/187 , F01D9/041 , F01D25/12 , F02C3/04 , F04D29/324 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/125 , F05D2240/30 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a first sidewall and a second sidewall joined together at a leading edge and a trailing edge and extending from a base to a tip. A plenum is defined inside the airfoil. A first cooling cavity merges into the plenum and a second cooling cavity merges into the plenum. A rib extends from at least one of the first sidewall and the second sidewall at least partially into the plenum to separate the first cooling cavity from the second cooling cavity.
Abstract translation: 根据本公开的示例性方面的部件包括除了别的以外的翼型件，其包括在前缘和后缘处连接在一起并且从基部延伸到尖端的第一侧壁和第二侧壁。 在翼型内定义了一个通风室。 第一个冷却腔并入集气室，第二个冷却腔并入集气室。 肋条从第一侧壁和第二侧壁中的至少一个至少部分地延伸到气室中，以将第一冷却腔与第二冷却腔分开。
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公开(公告)号：US20170204742A1
公开(公告)日：2017-07-20
申请号：US14997315
申请日：2016-01-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Anthony B. SWIFT , Paul M. LUTJEN , Neil L. TATMAN , Dominic J. MONGILLO, JR. , Matthew A. DEVORE , Ken F. BLANEY
CPC classification number: F01D25/12 , F01D11/08 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.
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公开(公告)号：US20160376895A1
公开(公告)日：2016-12-29
申请号：US14713186
申请日：2015-05-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Eleanor D. KAUFMAN , Matthew A. DEVORE
Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform.
Abstract translation: 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具有外表面和在前缘部分和后缘部分之间轴向延伸的内表面的平台。 至少一个增强特征设置在平台的外表面的至少前缘部分或后缘部分上。
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