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公开(公告)号：US20190249554A1
公开(公告)日：2019-08-15
申请号：US15895157
申请日：2018-02-13
发明人： Gregory Terrence Garay , Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Steven Robert Brassfield
CPC分类号： F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/323 , F05D2240/121 , F05D2240/303 , F05D2260/202
摘要： An apparatus and method for an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage, an outlet located proximate the leading edge, with a connecting passage fluidly coupling the inlet to the outlet.
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公开(公告)号：US20190249553A1
公开(公告)日：2019-08-15
申请号：US16239524
申请日：2019-01-03
发明人： Jae Bin Lee
CPC分类号： F01D5/186 , F01D5/20 , F05D2240/307 , F05D2260/202 , F05D2260/22141
摘要： A gas turbine includes a housing in which combustion gas flows; a rotor section rotatably installed in the housing; and a turbine blade configured to rotate the rotor section by receiving a rotational force from the combustion gas and to be cooled by a cooling fluid flowing in a cooling path, the turbine blade including a tip side provided with tip cooling holes through which a portion of the cooling fluid in the cooling path is discharged from the turbine blade. The tip cooling holes include a first tip cooling hole formed in a pressure surface of the turbine blade, and a second tip cooling hole formed in a suction surface of the turbine blade. The gas turbine can easily maintain a gap between the tip side of the turbine blade and an inner circumferential surface of the housing, preventing degradation of the turbine blade efficiency.
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公开(公告)号：US20190211691A1
公开(公告)日：2019-07-11
申请号：US16353563
申请日：2019-03-14
发明人： Lane Thornton , Thomas N. Slavens
CPC分类号： F01D5/186 , F01D5/187 , F01D5/28 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2300/175 , F05D2300/505 , Y02T50/676
摘要： In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.
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公开(公告)号：US20190211689A1
公开(公告)日：2019-07-11
申请号：US15866557
申请日：2018-01-10
CPC分类号： F01D5/186 , F01D5/187 , F04D29/324 , F04D29/582 , F05D2220/32 , F05D2240/303 , F05D2260/201 , F05D2260/202
摘要： An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge, a first feeding cavity separated from the first impingement cavity and from the second impingement cavity by the internal wall, and a first crossover passage within the internal wall that connects the first impingement cavity and the first feeding cavity. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall connects to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.
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5.发明申请公开(公告)号：US20190186739A1
公开(公告)日：2019-06-20
申请号：US16210434
申请日：2018-12-05
发明人： Dennis M. Moura , Carey Clum
CPC分类号： F23R3/002 , F01D5/189 , F01D9/065 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/607 , F23M5/08 , F23R3/005 , F23R2900/00004 , F23R2900/03042 , F23R2900/03044
摘要： A gas turbine engine component assembly comprising: a first component having a first surface, a second surface opposite the first surface, a first cooling hole located in a first section of the first component extending from the second surface to first surface, and a second cooling hole located in a second section of the first component extending from the second surface to first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; wherein the first cooling hole is configured to direct at least one of the airflow and the particulate to impinge upon the second surface of the second component at first directional flow angle.
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公开(公告)号：US20190186277A1
公开(公告)日：2019-06-20
申请号：US16283279
申请日：2019-02-22
CPC分类号： F01D9/023 , F01D5/186 , F01D5/288 , F01D9/065 , F01D11/20 , F05D2240/11 , F05D2240/81 , F05D2250/12 , F05D2260/202 , F23R3/002 , F23R2900/03042
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.
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公开(公告)号：US20190101011A1
公开(公告)日：2019-04-04
申请号：US16089598
申请日：2016-03-31
发明人： Jan H. Marsh , Paul A. Sanders , Evan C. Landrum
CPC分类号： F01D5/189 , F01D5/186 , F01D5/188 , F01D9/041 , F05D2220/32 , F05D2240/121 , F05D2240/122 , F05D2240/127 , F05D2240/24 , F05D2250/185 , F05D2260/202 , F05D2260/221 , F05D2260/2212
摘要： An airfoil (10) includes at least one internal cooling channel (A-F) extending in the radial direction and adjoined on opposite sides by an airfoil pressure sidewall (16) and an airfoil suction sidewall (18). An internal surface (16a) of the airfoil pressure sidewall (16) and an internal surface (18a) of the airfoil suction sidewall (18) define heat transfer surfaces in relation to a coolant flowing through the internal cooling channel (A-F). A flow splitter feature (90) is located in a flow path of the coolant in the internal cooling channel (A-F) between the pressure and suction sidewalls (16, 18). The flow splitter feature (90) is effective to create a flow separation region downstream of the flow splitter feature (90), whereby coolant flow velocity is locally increased along the internal surfaces (16a, 18a) of the pressure and suction sidewalls (16, 18).
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公开(公告)号：US20190032493A1
公开(公告)日：2019-01-31
申请号：US15664996
申请日：2017-07-31
发明人： Brett Barker , Bruce Varney , Brian Shoemaker , Charles Bulgrin
CPC分类号： F01D5/186 , F01D5/147 , F01D5/189 , F01D9/042 , F01D9/065 , F05D2240/121 , F05D2240/303 , F05D2250/183 , F05D2250/184 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/2212 , F05D2260/22141 , F05D2300/6033
摘要： An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.
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公开(公告)号：US20180363467A1
公开(公告)日：2018-12-20
申请号：US16059212
申请日：2018-08-09
发明人： Stephen Mark Molter , Mark Edward Stegmiller , Shawn Michael Pearson , Steven Robert Brassfield
CPC分类号： F01D5/186 , B23P15/02 , F01D5/187 , F01D5/20 , F01D5/225 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2240/81 , F05D2260/202 , Y10T29/49341
摘要： A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
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公开(公告)号：US20180328191A1
公开(公告)日：2018-11-15
申请号：US15591242
申请日：2017-05-10
CPC分类号： F01D5/187 , F01D5/20 , F01D5/3007 , F02C3/04 , F05D2220/32 , F05D2240/307 , F05D2240/35 , F05D2260/202
摘要： A rotor blade includes an airfoil. The airfoil includes a leading edge and a trailing edge downstream of the leading edge. The airfoil also includes a radially outer tip with a pressure side tip rail and a suction side tip rail. A slot is formed in an aft portion of the suction side tip rail and an opening is positioned between the suction side tip rail and the pressure side tip rail at the trailing edge. Gas flows from the tip via the slot and the opening to inhibit formation of a vortex flow proximate to the suction side of the airfoil.
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