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公开(公告)号：US11015454B2
公开(公告)日：2021-05-25
申请号：US15967950
申请日：2018-05-01
发明人： Timothy J. Jennings , Carey Clum
IPC分类号： F01D5/18
摘要： An airfoil includes pressure and suction side walls that extend in a chord-wise direction between a leading edge and a trailing edge. The pressure and suction side walls extend in a radial direction between a platform and a tip to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction side walls and has a first passage along the pressure side wall and a second passage along the suction side wall. The first passage is configured to receive cooling air from a cooling air source radially inward of the platform. The second passage is configured to receive cooling air from the first passage near the tip. A root flag passage is configured to purge the cooling air from the second passage near the trailing edge.
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公开(公告)号：US10961854B2
公开(公告)日：2021-03-30
申请号：US16129457
申请日：2018-09-12
摘要： A component for use in a gas turbine engine includes a channel configured to port a gas from an inlet along a flow path. The component further includes a wall defining an outlet configured to receive the gas, the wall forming an angle with the flow path that is between 60 degrees and 120 degrees, the outlet having a first portion with a first diameter and a second portion with a second diameter, the first portion configured to receive the gas before the second portion, and the first diameter being greater than the second diameter.
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公开(公告)号：US20210079793A1
公开(公告)日：2021-03-18
申请号：US16552450
申请日：2019-08-27
摘要： Airfoils for a gas turbine engines and gas turbine engines are described. The airfoils include an airfoil body extending in a radial direction from a first end to a second end, and axially from a leading edge to a trailing edge. A radially extending leading edge channel is formed in the leading edge of the airfoil body, having first and second channel walls that join at a channel base. A first leading edge impingement cavity is located within the airfoil body proximate the leading edge and is defined, in part, by the first channel wall. A leading edge feed cavity is arranged aft of the first leading edge impingement cavity to supply air into the first leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled toward a portion of the second channel wall.
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公开(公告)号：US10584593B2
公开(公告)日：2020-03-10
申请号：US15791464
申请日：2017-10-24
摘要： Airfoils bodies having a first end, a second end, a leading edge, and a trailing edge with a leading edge channel having a first channel wall and a second channel wall that join at a channel base to define the leading edge channel. The leading edge channel extends in a radial direction along the leading edge. A first leading edge impingement cavity is located proximate the leading edge and the first channel wall defines a portion of the first leading edge impingement cavity and a second leading edge impingement cavity with the second channel wall forming a portion of the second leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled such that air flowing from the first leading edge impingement cavity and through the first leading edge impingement hole impinges upon a portion of the second channel wall.
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公开(公告)号：US10526898B2
公开(公告)日：2020-01-07
申请号：US15791784
申请日：2017-10-24
发明人： Timothy J. Jennings , Carey Clum
摘要： An airfoil may include an airfoil body that defines a central chamber, a skin chamber, and an impingement hole extending between the central chamber and the skin chamber. The central chamber may be in fluidic communication with the skin chamber via the impingement hole. In various embodiments, a first cross-sectional area of the impingement hole is greater than about 25% of a second cross-sectional area of the skin chamber. In various embodiments, the impingement hole is positioned and configured to deliver cooling circuit air to a predicted position of a hotspot on a surface of the airfoil. In various embodiments, the airfoil body further defines at least one structural hole formed from at least one structural core tie, wherein a first cross-sectional area of the impingement hole is at least twice a second cross-sectional area of the at least one structural hole.
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公开(公告)号：US20190101010A1
公开(公告)日：2019-04-04
申请号：US15723512
申请日：2017-10-03
摘要： Airfoil bodies having a first core cavity within the airfoil body and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall and at least one first cavity impingement hole is formed within the first surface. A funneling feature extends the second core cavity along the first exterior wall to funnel the first impingement flow along the first exterior wall.
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公开(公告)号：US20190101009A1
公开(公告)日：2019-04-04
申请号：US15723500
申请日：2017-10-03
摘要： Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the second core cavity and the first core cavity. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface and has an oblong shape with a long axis oriented between 0° and 180° relative to the first exterior side wall.
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公开(公告)号：US10077664B2
公开(公告)日：2018-09-18
申请号：US14961221
申请日：2015-12-07
发明人： Carey Clum , Timothy J. Jennings
IPC分类号： F01D5/14 , F01D9/02 , B22F3/105 , B22D25/02 , B22C9/10 , F01D25/12 , B23K15/00 , F23R3/00 , F02C7/18 , F01D11/08 , F01D25/30 , F01D5/18 , B33Y80/00 , B33Y10/00
CPC分类号： F01D5/147 , B22C9/108 , B22D25/02 , B22F3/1055 , B23K15/0086 , B33Y10/00 , B33Y80/00 , F01D5/186 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F01D25/30 , F02C7/18 , F05D2220/32 , F05D2230/21 , F05D2260/202 , F05D2260/204 , F23R3/002 , Y02T50/673 , Y02T50/676
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes a plurality of nodes, a plurality of branches that extend between the plurality of nodes, and a plurality of passages extending between the plurality of nodes and the plurality of passages. Further, at least one of the branches is non-circular in cross-section.
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公开(公告)号：US20170234447A1
公开(公告)日：2017-08-17
申请号：US15042985
申请日：2016-02-12
CPC分类号： F16K31/002 , F01D5/08 , F01D5/18 , F02C3/04 , F02C7/12 , F03G7/065 , F05D2300/505 , Y02T50/676
摘要： Methods and systems for modulating airflow may include a metering device comprising a face, an aperture through the face being defined by an aperture rim, and a metering appendage disposed adjacent to the aperture and coupled to the aperture rim and/or the face. The metering appendage may comprise a shape memory alloy and may be configured to transition from a first geometry to a second geometry.
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公开(公告)号：US11480057B2
公开(公告)日：2022-10-25
申请号：US15791745
申请日：2017-10-24
发明人： Timothy J. Jennings , Carey Clum
摘要： An airfoil may include an airfoil body that defines a skin chamber, a skin chamber outlet opening, and a tip flag chamber. In various embodiments, the skin chamber is in fluidic communication with the tip flag chamber via the skin chamber outlet opening. In various embodiments, the airfoil body further defines an outlet hole disposed on at least one of a trailing edge and a pressure side of the airfoil. The tip flag chamber may be in fluidic communication with the outlet hole (e.g., cooling circuit air in the tip flag chamber may exit the airfoil via the outlet hole). In various embodiments, the tip flag chamber extends parallel and directly adjacent to the outermost tip of the airfoil.
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