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公开(公告)号：US09771814B2
公开(公告)日：2017-09-26
申请号：US14641470
申请日：2015-03-09
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC classification number: F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
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公开(公告)号：US20140093361A1
公开(公告)日：2014-04-03
申请号：US13630107
申请日：2012-09-28
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sarah Riley , Mark A. Boeke , Jeffrey J. DeGray , Shawn J. Gregg
CPC classification number: F01D25/12 , F01D5/187 , F01D9/02 , F05D2240/12 , F05D2240/126 , F05D2240/127 , F05D2240/81 , F05D2250/183 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
Abstract: 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.
Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 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平台和外平台。 在内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彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。
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公开(公告)号：US10443401B2
公开(公告)日：2019-10-15
申请号：US15255187
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Richard M. Salzillo, Jr. , Jeffrey J. DeGray
Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows 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 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 is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.
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Patent Agency Ranking
公开(公告)号：US10329937B2
公开(公告)日：2019-06-25
申请号：US15267632
申请日：2016-09-16
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Jeffrey J. DeGray , Richard M. Salzillo, Jr.
Abstract: A flow path component includes a platform having at least one radially aligned face. A chordal seal extends axially from the radially aligned face. The chordal seal includes a first curved face configured to prevent edge line contact under deflection conditions while the flow path component is installed in an engine.
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公开(公告)号：US20180106156A1
公开(公告)日：2018-04-19
申请号：US15295268
申请日：2016-10-17
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Jeffrey J. DeGray , Richard M. Salzillo , Dominic J. Mongillo
CPC classification number: F01D9/065 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US20180066524A1
公开(公告)日：2018-03-08
申请号：US15255187
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Richard M. Salzillo, JR. , Jeffrey J. DeGray
CPC classification number: F01D5/187 , F01D5/186 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2260/202 , F05D2260/221 , Y02T50/676
Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows 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 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 is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.
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公开(公告)号：US20160251969A1
公开(公告)日：2016-09-01
申请号：US14634006
申请日：2015-02-27
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Richard M. Salzillo , Jeffrey J. DeGray , Shawn J. Gregg
CPC classification number: F01D5/189 , F01D5/141 , F01D5/147 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/20 , F05D2230/60 , F05D2240/126 , F05D2240/301 , F05D2240/81 , F05D2260/221 , Y02T50/676
Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.
Abstract translation: 翼型件包括包括外部翼型件表面的翼型件壁，并且至少部分地限定翼型腔。 一个圆角在外部翼面上。 凹槽位于靠近圆角的翼型壁的内表面。 挡板管位于与凹槽间隔开的翼型腔中。
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公开(公告)号：US20140219778A1
公开(公告)日：2014-08-07
申请号：US13630419
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Mark A. Boeke , Shawn J. Gregg , Sarah Riley , Jeffrey J. DeGray , Richard M. Salzillo
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D25/12 , F01D25/246 , F05D2240/12 , F05D2240/81 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: 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.
Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。
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