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公开(公告)号：US12044408B2
公开(公告)日：2024-07-23
申请号：US18344954
申请日：2023-06-30
CPC分类号： F23R3/10 , F01D9/023 , F01D9/04 , F01D9/06 , F02C3/06 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/13
摘要： A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.
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公开(公告)号：US11994293B2
公开(公告)日：2024-05-28
申请号：US17007089
申请日：2020-08-31
CPC分类号： F23R3/06 , F01D9/023 , F02C3/14 , F23R3/002 , F23R3/10 , F05D2260/201 , F23R2900/03044
摘要： An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.
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3.发明公开公开(公告)号：US20240076991A1
公开(公告)日：2024-03-07
申请号：US18505595
申请日：2023-11-09
发明人： Ryan C. Humes
CPC分类号： F01D9/023 , F01D17/145 , F23R3/002 , F05D2240/35 , F05D2260/232 , F05D2260/60 , F23R2900/03043
摘要： A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.
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公开(公告)号：US11879359B2
公开(公告)日：2024-01-23
申请号：US17901962
申请日：2022-09-02
CPC分类号： F01D9/023 , F23R3/002 , F02C7/18 , F05D2240/35 , F05D2250/71 , F23R3/06 , F23R2900/03042 , F23R2900/03043
摘要： Provided is a transition piece including a first flow path group formed by arraying a plurality of in-wall flow paths that extend inside a plate material forming the transition piece and a second flow path group that is positioned on a side closer to a combustor liner than the first flow path group is. Each in-wall flow path in the first flow path group and the second flow path group has an inlet that is located at one end section in a flow direction of a combustion gas and that faces a compressed air main flow path, and an outlet that is located at the other end section in the flow direction of the combustion gas and that faces a combustion gas flow path. An installation area of the first flow path group and an installation area of the second flow path group partially overlap in the flow direction of the combustion gas by a predetermined overlap amount, and the overlap amount is set large for a portion where a shape change of the transition piece is relatively large, as compared with a portion where the shape change of the transition piece is relatively small.
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公开(公告)号：US11753952B2
公开(公告)日：2023-09-12
申请号：US16593638
申请日：2019-10-04
CPC分类号： F01D9/044 , B22F10/40 , B22F10/64 , F01D9/023 , F01D9/041 , F23R3/002 , F23R3/50 , B33Y10/00 , B33Y80/00 , F05D2230/30 , F05D2240/12 , F05D2240/35 , F05D2300/1723 , F23R2900/00018 , B22F2999/00 , B22F2003/247 , B22F10/64 , B22F10/40
摘要： A method of manufacturing a turbine vane within an engine case includes additively manufacturing a combustor liner within an engine case, additively manufacturing a support structure attached to the combustor liner at a radially distal position, and additively manufacturing the turbine vane attached to the support structure at an inwardly adjacent position to the radially distal position.
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公开(公告)号：US20230175404A1
公开(公告)日：2023-06-08
申请号：US17439273
申请日：2020-04-08
发明人： Satoshi HADA , Yoshifumi OKAJIMA , Kunihiko WAKI
CPC分类号： F01D5/187 , F01D9/023 , F01D9/041 , F02C7/18 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A turbine stator vane includes; an airfoil portion; a shroud disposed on at least one of the side of a tip end portion or the side of a root end portion of the airfoil portion; and a protruding portion protruding toward the opposite side to the airfoil portion across a gas path surface in a radial direction. The shroud includes: a circumferential-direction passage disposed at the side of a trailing edge and extending in a circumferential direction; and a plurality of trailing edge end portion passages arranged in the circumferential direction at the side of the trailing edge, each trailing edge end portion passage having a first end portion connected to the circumferential-direction passage and a second end portion having an opening on a trailing edge end surface of the shroud. The circumferential-direction passage includes, in a cross-sectional view as seen in the circumferential direction, an oblique passage having a third end portion to protrude closer to the gas path surface toward the side of a leading edge, and a fourth end portion formed at the side of the trailing edge with respect to the third end portion, the oblique passage having an opening portion disposed on a trailing-edge side end surface of the protruding portion and closed by a lid portion, and a position, in an axial direction, of the first end portion where each trailing edge end portion passage connects to the circumferential-direction passage is positioned at the side of the leading edge with respect to a position of the trailing-edge side end surface of the protruding portion at a position where the protruding portion connects to the shroud.
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公开(公告)号：US20190178103A1
公开(公告)日：2019-06-13
申请号：US15840498
申请日：2017-12-13
发明人： Remy SYNNOTT , Mohammed ENNACER , Chris PATER , Denis BLOUIN , Kapila JAIN , Farough MOHAMMADI
CPC分类号： F01D25/12 , F01D5/081 , F01D5/185 , F01D5/186 , F01D5/225 , F01D9/023 , F01D9/04 , F01D11/08 , F05D2230/211 , F05D2240/11 , F05D2240/127 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/22141
摘要： A turbine shroud segment comprises a body having an upstream end portion and a downstream end portion relative to a flow of gases through the gas path. A core cavity is defined in the body and extends axially from the upstream end portion to the downstream end portion. A plurality of cooling inlets is defined in the upstream end portion of the body for feeding coolant in the core cavity. A plurality of cooling outlets is defined in the downstream end portion of the body for discharging coolant from the core cavity. Pedestals are provided in the core cavity.
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公开(公告)号：US20190071976A1
公开(公告)日：2019-03-07
申请号：US15697886
申请日：2017-09-07
CPC分类号： F01D5/186 , F01D9/023 , F01D9/041 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2220/323 , F05D2230/50 , F05D2240/11 , F05D2240/124 , F05D2240/306 , F05D2240/81 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R2900/03042
摘要： An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.
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公开(公告)号：US20180347371A1
公开(公告)日：2018-12-06
申请号：US15609576
申请日：2017-05-31
CPC分类号： F01D9/065 , B22F5/04 , F01D9/023 , F02K1/822 , F05D2230/31 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F05D2270/3032 , F23R3/002 , F23R3/06 , F23R2900/00018
摘要： A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover may include a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface.
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10.发明申请公开(公告)号：US20180320898A1
公开(公告)日：2018-11-08
申请号：US15947707
申请日：2018-04-06
发明人： Jongho Uhm
CPC分类号： F23R3/002 , F01D9/023 , F02C7/18 , F02K1/822 , F05D2260/201 , F23R3/286 , F23R2900/03044
摘要： Disclosed herein is a combustor capable of improving impingement cooling performance by reducing the influence of a cross-flow on a jet flow. The combustor includes a combustion liner, in which fuel sprayed from fuel nozzles of a gas turbine is mixed with compressed air and the mixture is combusted, a sleeve surrounding the outer surface of the combustion liner while being spaced apart therefrom in order to form a flow passage for compressed air, a cooling hole formed in the sleeve to introduce compressed air discharged from a compressor into the flow passage, and a first auxiliary hole formed upstream of the cooling hole in the airflow direction. Compressed air discharged from the compressor is introduced into the flow passage through the first auxiliary hole, impinges with compressed air flowing through the flow passage, and forms an air column.
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