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公开(公告)号：US11293292B2
公开(公告)日：2022-04-05
申请号：US16736199
申请日：2020-01-07
发明人： Jason Smoke , David K. Jan , Mark Matwey
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：US20210372289A1
公开(公告)日：2021-12-02
申请号：US17444754
申请日：2021-08-10
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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33.发明申请公开(公告)号：US20210003025A1
公开(公告)日：2021-01-07
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：US20200318488A1
公开(公告)日：2020-10-08
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：US10669862B2
公开(公告)日：2020-06-02
申请号：US16035184
申请日：2018-07-13
发明人： Luis Tapia , Jason Smoke
IPC分类号： F01D5/18
摘要： An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.
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公开(公告)号：US10655859B2
公开(公告)日：2020-05-19
申请号：US15403286
申请日：2017-01-11
发明人： Jason Smoke , David K. Jan , Mark Matwey
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：US10563520B2
公开(公告)日：2020-02-18
申请号：US15475597
申请日：2017-03-31
IPC分类号： F01D5/18
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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38.发明申请公开(公告)号：US20180363499A1
公开(公告)日：2018-12-20
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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公开(公告)号：US09850760B2
公开(公告)日：2017-12-26
申请号：US14687464
申请日：2015-04-15
发明人： Lorenzo Crosatti , Jason Smoke
IPC分类号： F01D5/08 , F04D29/32 , F01D5/04 , F01D5/12 , F04D29/28 , F04D29/58 , F01D25/12 , F01D25/00 , F01D5/34
CPC分类号： F01D5/087 , F01D5/04 , F01D5/046 , F01D5/048 , F01D5/082 , F01D5/12 , F01D5/34 , F01D25/005 , F01D25/12 , F04D29/28 , F04D29/324 , F04D29/582 , F05D2230/23 , F05D2230/236 , F05D2240/24 , F05D2260/20
摘要： A rotating machine includes a hub portion, wherein the hub portion comprises a forward face and an aft face. The rotating machine further includes a cooling channel formed on either the forward face or the aft face and configured to direct cooling air to a location on the rotating machine, wherein the cooling channel extends from a radially inner location along the face to a radially outer location along the face, and wherein the cooling channel is configured as a recess formed into an outer surface of the face.
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40.发明申请公开(公告)号：US20170268089A1
公开(公告)日：2017-09-21
申请号：US15071630
申请日：2016-03-16
发明人： Christopher David Gatto , Jude Miller , Benjamin Dosland Kamrath , Don Mittendorf , Jason Smoke , Mark C. Morris
CPC分类号： C22F1/10 , B23P15/006 , C21D1/42 , C21D11/00 , F01D5/02 , F01D5/063 , F01D5/28 , F01D5/286 , F01D5/34 , F04D29/023 , F04D29/321 , F04D29/322 , F05D2220/32 , F05D2230/211 , F05D2230/40 , F05D2230/41 , F05D2230/42 , F05D2300/17 , F05D2300/175 , F05D2300/606
摘要： Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.
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