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公开(公告)号：US11149556B2
公开(公告)日：2021-10-19
申请号：US16667949
申请日：2019-10-30
摘要： A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.
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公开(公告)号：US20190383147A1
公开(公告)日：2019-12-19
申请号：US16373008
申请日：2019-04-02
IPC分类号： F01D5/18
摘要： A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.
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公开(公告)号：US20190195074A1
公开(公告)日：2019-06-27
申请号：US15852400
申请日：2017-12-22
摘要： Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component, a hybrid resupply hole formed in the cold wall and fluidly connecting a cold cavity and the hybrid skin core cooling cavity, and a resupply cover located on the cold wall and within the hybrid skin core cooling cavity and positioned relative to the hybrid resupply hole to shield resupply air injected from the cold cavity into the hybrid skin core cooling cavity to minimize losses as the resupply air mixes with air flowing within the hybrid skin core cooling cavity.
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公开(公告)号：US11512597B2
公开(公告)日：2022-11-29
申请号：US16594379
申请日：2019-10-07
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. An arced rib extends from the first side to the second side and divides the internal core cavity into a forward cavity and an aft cavity. A cooling passage network is embedded in the airfoil wall aft of the rib and between inner and outer portions of the airfoil wall. The network includes a cooling passage leading edge and a cooling passage trailing edge. The aft core cavity has a central cavity section and a cavity lobe. The cavity lobe projects between the rib and the cooling passage leading edge.
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公开(公告)号：US11293347B2
公开(公告)日：2022-04-05
申请号：US16667941
申请日：2019-10-30
摘要： An airfoil has a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib extends from the first side to the second side and partitions an internal core cavity into a forward cavity and an aft cavity. A baffle is disposed in the forward cavity and has a showerhead array of impingement orifices adjacent the leading end of the airfoil wall. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall, an array of pedestals, and at least one outlet orifice through the outer portion. The inlet orifice opens to the forward cavity at a location aft of the showerhead array of impingement orifices.
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公开(公告)号：US11180998B2
公开(公告)日：2021-11-23
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：US11092017B2
公开(公告)日：2021-08-17
申请号：US16594156
申请日：2019-10-07
摘要： An airfoil includes an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The airfoil wall circumscribes an internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an inlet orifice through the inner portion of the airfoil wall to receive cooling air from the internal core cavity, a sub-passage region that includes an array of pedestals, and at least one outlet orifice through the outer portion. The outer portion of the airfoil wall has a protrusion in the cooling passage network that faces toward the inlet orifice.
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公开(公告)号：US10975710B2
公开(公告)日：2021-04-13
申请号：US16210393
申请日：2018-12-05
摘要： A component for a gas turbine engine includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit is defined by the wall portion and includes a plurality of pedestals that extend across the cooling circuit. A width of the cooling circuit increases or decreases in a downstream direction. At least one cooling fluid inlet extends through the interior surface and is in fluid communication with the cooling circuit. At least one cooling fluid outlet extends through the exterior surface and is in fluid communication with the cooling circuit.
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公开(公告)号：US20200332663A1
公开(公告)日：2020-10-22
申请号：US16594379
申请日：2019-10-07
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. An arced rib extends from the first side to the second side and divides the internal core cavity into a forward cavity and an aft cavity. A cooling passage network is embedded in the airfoil wall aft of the rib and between inner and outer portions of the airfoil wall. The network includes a cooling passage leading edge and a cooling passage trailing edge. The aft core cavity has a central cavity section and a cavity lobe. The cavity lobe projects between the rib and the cooling passage leading edge.
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公开(公告)号：US20200332662A1
公开(公告)日：2020-10-22
申请号：US16594353
申请日：2019-10-07
摘要： An airfoil section 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 airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.
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