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公开(公告)号：US20170260864A1
公开(公告)日：2017-09-14
申请号：US15069738
申请日：2016-03-14
发明人： Jeffrey Leon , Daniel C. Nadeau , Jeffrey R. Levine , Eleanor D. Kaufman , Richard N. Allen , Evan P. Molony , Gregory Anselmi
CPC分类号： F01D5/187 , B22C9/10 , F02C7/18 , F05D2220/32 , F05D2260/20 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.
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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：US10480333B2
公开(公告)日：2019-11-19
申请号：US15607998
申请日：2017-05-30
发明人： Evan P. Molony , Carey Clum , Wolfgang Balzer
摘要： A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.
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公开(公告)号：US20180347376A1
公开(公告)日：2018-12-06
申请号：US15613255
申请日：2017-06-04
CPC分类号： F01D5/187 , B22C9/103 , B22C9/24 , F01D5/081 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2250/185 , F05D2260/202
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：US10132168B2
公开(公告)日：2018-11-20
申请号：US15069738
申请日：2016-03-14
发明人： Jeffrey Leon , Daniel C. Nadeau , Jeffrey R. Levine , Eleanor D. Kaufman , Richard N. Allen , Evan P. Molony , Gregory Anselmi
摘要： An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.
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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：US20190024514A1
公开(公告)日：2019-01-24
申请号：US15656020
申请日：2017-07-21
发明人： Charles Thistle , Evan P. Molony , Carey Clum
摘要： Airfoils and airfoil cores for airfoils of gas turbine engines are provided. The airfoils include an airfoil body having a leading edge and a trailing edge, at least two serpentine flow cavities formed within the airfoil body, a resupply cavity fluidly connected to one serpentine flow cavity of the at least two serpentine flow cavities and arranged to supply a resupply air to the one serpentine flow cavity through a resupply bypass hole, a junction defined at a location where the resupply cavity fluidly connect to the one serpentine flow cavity, a separator rib within the airfoil body and fluidly separating part of the at least two serpentine flow cavities, at least one crossover rib located between the resupply bypass hole and the separator rib, and at least one crossover aperture located between the at least one crossover rib and the separator rib.
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公开(公告)号：US20180347381A1
公开(公告)日：2018-12-06
申请号：US15607998
申请日：2017-05-30
发明人： Evan P. Molony , Carey Clum , Wolfgang Balzer
CPC分类号： F01D5/3015 , F01D5/141 , F01D5/143 , F01D5/145 , F01D5/147 , F01D9/041 , F01D9/042 , F01D11/006 , F05B2240/301 , F05B2240/80 , F05D2240/11 , F05D2240/80
摘要： A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.
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