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1.发明授权公开(公告)号：US11181006B2
公开(公告)日：2021-11-23
申请号：US16831045
申请日：2020-03-26
发明人： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
摘要： A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
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公开(公告)号：US11156116B2
公开(公告)日：2021-10-26
申请号：US16378030
申请日：2019-04-08
摘要： A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.
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公开(公告)号：US10900378B2
公开(公告)日：2021-01-26
申请号：US15899780
申请日：2018-02-20
发明人： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
摘要： A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.
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4.发明申请公开(公告)号：US20180363486A1
公开(公告)日：2018-12-20
申请号：US15899756
申请日：2018-02-20
发明人： Jason Smoke , Kent L. Kime , Blake Petersen , Luke Zurmehly
CPC分类号： F01D11/08 , F01D9/04 , F01D11/005 , F01D11/122 , F01D25/12 , F01D25/246 , F05D2240/11 , F05D2240/55 , F05D2240/56 , F05D2260/201 , F05D2260/204
摘要： A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
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公开(公告)号：US20180283182A1
公开(公告)日：2018-10-04
申请号：US15475597
申请日：2017-03-31
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/18 , F05D2220/323 , F05D2240/30 , F05D2250/18 , F05D2250/60 , F05D2260/20 , F05D2260/2212 , F05D2260/22141 , F05D2260/607 , Y02T50/676
摘要： A turbine component with shaped cooling pins is provided. The turbine component includes at least one cooling circuit defined within the turbine component, the at least one cooling circuit in fluid communication with a source of a cooling fluid. The turbine component includes at least one shaped cooling pin disposed in the at least one cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is upstream in the cooling fluid and the minor diameter is less than the major diameter.
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公开(公告)号：US20180195729A1
公开(公告)日：2018-07-12
申请号：US15403286
申请日：2017-01-11
发明人： Jason Smoke , David K. Jan , Mark Matwey
CPC分类号： F23R3/425 , F01D9/023 , F01D9/026 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2220/50 , F05D2240/35 , F05D2260/205 , F05D2260/22141 , F23R3/26 , Y02T50/675
摘要： A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
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公开(公告)号：US20170304929A1
公开(公告)日：2017-10-26
申请号：US15648577
申请日：2017-07-13
发明人： Amandine Miner , David K. Jan , Don Mittendorf , Jason Smoke
IPC分类号： B23K20/02 , B23K1/00 , F01D5/30 , B23K20/22 , B23K20/26 , B23P15/00 , F01D5/34 , B23K20/14 , B23K31/02 , B23K101/00 , B23K20/00
CPC分类号： B23K20/028 , B23K1/00 , B23K1/0018 , B23K20/002 , B23K20/021 , B23K20/023 , B23K20/14 , B23K20/22 , B23K20/26 , B23K31/02 , B23K2101/001 , B23P15/006 , F01D5/3061 , F01D5/34 , F05D2220/323 , F05D2230/236 , F05D2230/60 , F05D2300/17 , F05D2300/606 , F05D2300/607 , Y10T29/49323
摘要： Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.
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公开(公告)号：US20170254209A1
公开(公告)日：2017-09-07
申请号：US15062952
申请日：2016-03-07
发明人： Jason Smoke , David K. Jan , Amandine Miner , Deanna Pinar Chase , Michael Kahrs , Lorenzo Crosatti
CPC分类号： F01D5/187 , F01D1/08 , F01D5/045 , F01D5/046 , F01D5/3061 , F05D2220/32 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.
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9.发明申请GAS TURBINE ENGINES WITH TURBINE ROTOR BLADES HAVING IMPROVED PLATFORM EDGES 有权具有改进平台边缘的涡轮转子叶片的气体涡轮发动机公开(公告)号：US20150075178A1
公开(公告)日：2015-03-19
申请号：US14028734
申请日：2013-09-17
发明人： Steve Halfmann , Mark C. Morris , Jason Smoke , Brandan Wakefield , Bob Mitlin
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/141 , F01D5/22 , F01D5/3007 , F05D2240/80 , F05D2250/184 , F05D2250/75 , Y02T50/673 , Y10T29/49336
摘要： A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.
摘要翻译： 提供涡轮转子叶片。 涡轮转子叶片包括根部，连接到根部的平台以及从平台延伸的翼型件。 平台具有前缘，后缘，吸力侧边缘和压力侧边缘。 压力侧边缘包括第一凹部。
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公开(公告)号：US20230271150A1
公开(公告)日：2023-08-31
申请号：US17931441
申请日：2022-09-12
发明人： Stephen Yates , Amanda Childers , Mehrad Mehr , Jeffrey Spencer , Jason Smoke , Abigail Parsons
CPC分类号： B01J6/008 , C01B3/24 , C01B2203/0272 , C01B2203/1241
摘要： A thermal process system includes a retort assembly, a heating assembly, and a vessel housing. The retort assembly includes a retort chamber and is configured to substantially form a containment boundary to contain one or more gases in the retort chamber during a thermal process. The heating assembly includes one or more heating elements and is configured to heat the retort chamber. The vessel housing is positioned around the retort chamber and the one or more heating elements and configured to form a pressure boundary to maintain a pressure within the retort chamber and reduce a pressure across the retort chamber.
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