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公开(公告)号：US11242764B2
公开(公告)日：2022-02-08
申请号：US15982062
申请日：2018-05-17
IPC分类号： F01D11/08
摘要： A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has an elongated seal body having a seal face that bounds a gas path and an opposed impingement face. The seal body defines an internal cavity extending in a circumferential direction between opposed mate faces and extending in a radial direction between walls of the seal body defining the seal and impingement faces. A baffle divides the internal cavity into at least a first region and a second region. The first region has a first section extending transversely from a second section. The first section has a component in the radial direction, and the second section has a component in an axial direction such that the second region is defined between the baffle and the walls of the seal body defining the seal face. A method of sealing is also disclosed.
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公开(公告)号：US10968746B2
公开(公告)日：2021-04-06
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：US10822959B2
公开(公告)日：2020-11-03
申请号：US15623787
申请日：2017-06-15
摘要： A casting core may include a core body and a tip comb extending from a tip region of the core body. The tip comb may be integrally formed with the core body. The tip comb may comprise a first casting pedestal and a second casting pedestal. The first casting pedestal and the second casting pedestal may define an aperture having a tapered geometry.
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公开(公告)号：US10731476B2
公开(公告)日：2020-08-04
申请号：US16005755
申请日：2018-06-12
摘要： An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section. A baffle includes an elongated body arranged in the second passage section to define a pair of cooling flow paths respectively established along a pair of opposed walls of the elongated body such that the pair of cooling flow paths extend from the turn section along a common length of the second passage section, and a first wedge region extending from the elongated body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the pair of cooling flow paths.
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公开(公告)号：US20200149416A1
公开(公告)日：2020-05-14
申请号：US16532594
申请日：2019-08-06
摘要： An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends, and the airfoil wall circumscribes an internal core cavity. First and second platforms are attached, respectively, with the first and second ends. A cooling passage circuit extends at least in the first platform and the airfoil section. The cooling passage circuit includes a first plenum in the first platform adjacent at least the first side of the airfoil wall, a hybrid skin core passage embedded in the first side of the airfoil wall and that extends longitudinally, and a resupply passage that connects the first plenum with the hybrid skin core passage.
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公开(公告)号：US10436113B2
公开(公告)日：2019-10-08
申请号：US14816125
申请日：2015-08-03
摘要： A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.
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公开(公告)号：US20190186278A1
公开(公告)日：2019-06-20
申请号：US16272646
申请日：2019-02-11
发明人： Carey Clum , Dominic J. Mongillo
CPC分类号： F01D11/001 , F01D11/122 , F01D25/12 , F05D2240/11 , F05D2240/55 , F05D2260/203 , F05D2260/2212 , F05D2260/22141
摘要： A blade outer air seal segment assembly includes a blade outer air seal segment configured to connect with an adjacent blade outer air seal segment to form part of a rotor shroud. A cooling channel is disposed in the first turbine blade outer air seal segment. The cooling channel extends at least partially between a first circumferential end portion and a second circumferential end portion. At least one inlet aperture provides a cooling airflow to the cooling channel. A series of trip strips in the cooling channel cause turbulence in the cooling airflow. The trip strips include at least one chevron shaped trip strip having a first and second leg joined at an apex arranged adjacent the inlet aperture. The trip strips also include at least one trip strip having a single skewed line.
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公开(公告)号：US10184353B2
公开(公告)日：2019-01-22
申请号：US15049775
申请日：2016-02-22
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：US20180340426A1
公开(公告)日：2018-11-29
申请号：US15605458
申请日：2017-05-25
发明人： Dominic J. Mongillo , Wolfgang Balzer , Atul Kohli
摘要： In one embodiment, a component for a gas turbine engine is provided. The component including: an airfoil having a tip portion; a tip shelf located in the tip portion; a first plurality of cooling openings located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of a pressure side of the tip portion.
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公开(公告)号：US20180334909A1
公开(公告)日：2018-11-22
申请号：US16048466
申请日：2018-07-30
发明人： Dominic J. Mongillo , Tracy A. Propheter-Hinckley , Mark F. Zelesky , Joel H. Wagner , Thomas N. Slavens
IPC分类号： F01D5/18 , F23R3/00 , B22F3/105 , B23P15/26 , F01D5/14 , F02C7/18 , F01D25/24 , F01D25/12 , F01D25/08 , F01D11/08 , F01D9/02 , B33Y80/00 , B33Y70/00 , B33Y10/00
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 defines a hollow vascular structure configured to communicate a fluid through the vascular engineered lattice structure. The vascular engineered lattice structure has at least one inlet hole and at least one outlet hole that communicates the fluid into and out of the hollow vascular structure. A method for producing a component is also disclosed.
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