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公开(公告)号：US20180320531A1
公开(公告)日：2018-11-08
申请号：US15584106
申请日：2017-05-02
CPC分类号： F01D5/187 , F01D5/147 , F01D9/041 , F05D2210/40 , F05D2220/32 , F05D2230/211 , F05D2240/125 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/22141
摘要： Turn caps for airfoils of gas turbine engines having a first pressure-side turn passage extending from a respective inlet to a respective outlet within the turn cap, a first suction-side turn passage extending from a respective inlet to a respective outlet within the turn cap, and a merging chamber fluidly connected to the outlets of the first pressure-side turn passage and the first suction-side turn passage, wherein each of the first suction-side turn passage and the first pressure-side turn passage turn a direction of fluid flow from a first direction to a second direction such that a fluid flow exiting the first suction-side turn passage and the first pressure-side turn passage are aligned when entering the merging chamber.
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公开(公告)号：US20180073369A1
公开(公告)日：2018-03-15
申请号：US15266855
申请日：2016-09-15
发明人： Scott D. Lewis , Dominic J. Mongillo , Atul Kohli
CPC分类号： F01D5/186 , F01D5/187 , F01D9/02 , F01D11/08 , F01D25/12 , F04D29/083 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/303 , F05D2250/38 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges to provide an exterior airfoil surface. The pressure and suction side walls are spaced apart from one another in a thickness direction. A stagnation line is located near the leading edge. A cooling passage is provided between the pressure and suction side walls. The showerhead cooling holes are arranged at least one of adjacent to or on the stagnation line. At least one of the showerhead cooling holes has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole is arranged on each of opposing sides of the stagnation line. Each showerhead cooling hole has the diffuser with a first diffuser angle that expands downstream in the thickness direction in opposing directions from one another when separated by the stagnation line.
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公开(公告)号：US20170175631A1
公开(公告)日：2017-06-22
申请号：US15450087
申请日：2017-03-06
发明人： Shawn J. Gregg , Dominic J. Mongillo , Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer
CPC分类号： F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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公开(公告)号：US20160084164A1
公开(公告)日：2016-03-24
申请号：US14816125
申请日：2015-08-03
CPC分类号： F02C7/18 , F01D5/081 , F01D5/145 , F01D5/18 , F01D5/181 , F01D5/182 , F01D5/183 , F01D5/184 , F01D5/185 , F01D5/186 , F01D5/187 , F01D5/188 , F01D5/189 , F01D5/30 , F01D9/06 , F01D9/065 , F02C3/04 , F02C9/16 , F05D2220/32 , F05D2250/51 , F05D2250/71 , F05D2250/72 , F05D2250/73 , F05D2260/232 , Y02T50/676
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.
摘要翻译： 用于燃气涡轮发动机部件的冷却装置包括具有限定冷却流路的上游通道和下游通道的燃气涡轮发动机部件。 仪表特征包括至少一个孔，用于测量从上游通道到下游通道的流量，并具有上游侧和下游侧。 出口扩散器从仪表特征的下游侧向外延伸以控制在所需方向上的流向下游通道。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US11939883B2
公开(公告)日：2024-03-26
申请号：US16532603
申请日：2019-08-06
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2260/22141
摘要： An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.
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公开(公告)号：US11015457B2
公开(公告)日：2021-05-25
申请号：US16202483
申请日：2018-11-28
发明人： Christopher J. Peters , Emma J. Place , Jeffrey J. DeGray , Dominic J. Mongillo , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
摘要： A method of forming an airfoil, includes forming a hybrid skin core, a tip flag core, and a trailing edge core. The hybrid skin core, tip flag core, and trailing edge core are connected to form a first core portion. A leading edge core and a serpentine core are formed. The first core portion, the leading edge core, and the serpentine core are assembled together to form an airfoil core. An airfoil is formed around the airfoil core.
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公开(公告)号：US10662781B2
公开(公告)日：2020-05-26
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 , F01D11/08 , F01D25/24 , F02C7/18 , F01D25/12 , B22F3/105 , B23P15/26 , F01D5/14 , F01D9/02 , F01D25/08 , B33Y10/00 , B33Y70/00 , B33Y80/00
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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公开(公告)号：US10273820B2
公开(公告)日：2019-04-30
申请号：US15295268
申请日：2016-10-17
发明人： Nicholas M. LoRicco , Mark A. Boeke , Jeffrey J. DeGray , Richard M. Salzillo , Dominic J. Mongillo
IPC分类号： F01D9/06
摘要： 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：US20170226885A1
公开(公告)日：2017-08-10
申请号：US15019197
申请日：2016-02-09
发明人： Carey Clum , Dominic J. Mongillo
CPC分类号： F01D11/08 , F01D5/02 , F01D9/02 , F01D25/12 , F04D19/002 , F05D2220/32 , F05D2240/11 , F05D2240/80 , F05D2260/201 , F05D2260/2212
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：US20170211396A1
公开(公告)日：2017-07-27
申请号：US15143717
申请日：2016-05-02
CPC分类号： F01D5/187 , F01D9/02 , F01D25/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2250/185 , F05D2260/202 , F05D2260/22141 , F05D2260/606 , Y02T50/676
摘要： An airfoil of a gas turbine engine is provided including a leading edge extending in a radial direction, a tip extending in an axial direction from the leading edge, a first rib extending radially within the airfoil, the leading edge and the first rib defining a leading edge cavity within the airfoil, a second rib, the second rib and the first rib defining a serpentine cavity therein, a third rib extending axially within the tip, a flag tip cavity defined by the third rib, the leading edge, and the tip, the leading edge cavity fluidly connected to the flag tip cavity, and a bypass aperture formed between the first rib and the third rib, the bypass aperture configured to fluidly connect the serpentine cavity with the flag tip cavity.
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