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公开(公告)号：US10774657B2
公开(公告)日：2020-09-15
申请号：US16198906
申请日：2018-11-23
IPC分类号： F01D5/18
摘要： An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a first platform section. The airfoil section defines an internal core cavity for conveying a fluid flow, and a baffle assembly that has a first baffle and a second baffle. The first baffle includes a first baffle body extending in the internal core cavity. The first baffle body defines an internal baffle cavity. The second baffle includes a second baffle body dimensioned to extend from the platform section into the internal baffle cavity such that an outer periphery surface of the second baffle body and an external wall of the airfoil section cooperate to define a first cooling passage that directs cooling flow into the internal baffle cavity.
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公开(公告)号：US20200088038A1
公开(公告)日：2020-03-19
申请号：US16159149
申请日：2018-10-12
发明人： Ky H. Vu , Dominic J. Mongillo
摘要： A stator vane assembly including an inner diameter platform. The assembly also includes an outer diameter platform defining an air inlet orifice extending radially therethrough. Further included is an airfoil extending between the inner diameter platform and the outer diameter platform, the airfoil having a hollow portion therein defining a serpentine cooling airflow path fluidly coupled to the air inlet orifice. Yet further included is a collar extending radially outwardly from the outer diameter platform and positioned adjacent the air inlet orifice, the collar extending to a non-uniform radial distance. The assembly also includes a turn cover operatively coupled to the collar.
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公开(公告)号：US20200025027A1
公开(公告)日：2020-01-23
申请号：US16253038
申请日：2019-01-21
发明人： Susan M. Tholen , Dominic J. Mongillo , Paul M. Lutjen , James N. Knapp , Virginia L. Ross , Jonathan J. Earl , Eric A. Hudson
摘要： A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal.
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公开(公告)号：US10519782B2
公开(公告)日：2019-12-31
申请号：US15613255
申请日：2017-06-04
摘要： Airfoils having a body with leading and trailing edges and a first serpentine cavity within the body enabling a cooling flow in a first direction within the airfoil body, a second serpentine cavity fluidly connected to the first serpentine cavity enabling a cooling flow in a second direction, and a third serpentine cavity fluidly connected to the second serpentine cavity enabling a cooling flow in at least one of the first direction or a third direction. A resupply cavity is fluidly connected to the third serpentine cavity to supply a resupply air to the third serpentine cavity, a junction at the location of the second serpentine cavity, the resupply cavity and the third serpentine cavity, and a flow control feature arranged to turn the serpentine cooling air from the second direction and/or prevent resupply air backflow.
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公开(公告)号：US10480329B2
公开(公告)日：2019-11-19
申请号：US15496093
申请日：2017-04-25
摘要： Turn caps for airfoils of gas turbine engines having exterior side walls, an exterior top wall extending between the exterior side walls, a first turn cap divider extending from the exterior top wall and positioned between the exterior side walls and defining a first turning feature between the first turn cap divider and the exterior side walls, the first turning feature comprising a first suction-side turn passage and a first pressure-side turn passage wherein the first turn cap divider fluidly separates the first pressure-side turn passage from the first suction-side turn passage within the turn cap, and a merging chamber is formed in the turn cap wherein fluid flows passing through the first suction side turn passage and the first pressure side turn passage are merged at the merging chamber.
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公开(公告)号：US10428659B2
公开(公告)日：2019-10-01
申请号：US14976041
申请日：2015-12-21
摘要： A flowpath component for a gas turbine engine includes a leading edge, a trailing edge connected to the leading edge via a first surface and a second surface, an impingement cavity internal to the flowpath component, the impingement cavity being aligned with one of the leading edge and the trailing edge, a cooling passage extending at least partially through the flowpath component, and a plurality of crossover holes connecting the cooling passage to the impingement cavity. At least one of the crossover holes is aligned normal to an expected direction of fluid flow through the cooling passage and is unaligned with an axial line drawn perpendicular to a stacking line of the flowpath component.
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公开(公告)号：US10422230B2
公开(公告)日：2019-09-24
申请号：US15008148
申请日：2016-01-27
IPC分类号： F01D5/18 , F23R3/00 , F01D9/02 , F01D5/22 , F01D11/08 , F01D25/24 , F01D25/12 , F02C7/18 , F01D9/06
摘要： A gas turbine engine component having a cooling hole includes a first wall having a cooling hole inlet, a second wall generally opposite the first wall and having a cooling hole outlet, a metering section extending downstream from the inlet and having a hydraulic diameter (dh), and a diffusing section extending from the metering section to the outlet. The metering section includes a substantially convex first surface extending from a first end to a second end, a substantially concave second surface extending from a third end to a fourth end, and first and second curved portions connecting the ends of the first and second surfaces.
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公开(公告)号：US10358978B2
公开(公告)日：2019-07-23
申请号：US14772398
申请日：2014-03-12
IPC分类号： F01D5/18 , F01D9/04 , F01D9/06 , F02C7/18 , F02C7/25 , F02K1/82 , F23R3/16 , F01D11/08 , F01D25/12 , F01D25/30
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall, a second wall and at least one row of shaped pedestals extending between the first wall and the second wall. The at least one row of shaped pedestals includes a first set of C-shaped pedestals and a second set of C-shaped pedestals adjacent to the first set of C-shaped pedestals.
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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：US10273808B2
公开(公告)日：2019-04-30
申请号：US14938310
申请日：2015-11-11
摘要： An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.
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