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公开(公告)号：US20200378262A1
公开(公告)日：2020-12-03
申请号：US16826953
申请日：2020-03-23
IPC分类号： F01D5/18
摘要： An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.
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2.发明申请公开(公告)号：US20180156054A1
公开(公告)日：2018-06-07
申请号：US15367735
申请日：2016-12-02
发明人： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
摘要： Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.
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3.发明申请SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME 审中-公开SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUIFACTTING THE SAME公开(公告)号：US20160084103A1
公开(公告)日：2016-03-24
申请号：US14495319
申请日：2014-09-24
发明人： Michael Kahrs , Timothy Vander Hoek , Loris Bedrosyan , Jason Smoke , Ardeshir Riahi , Daniel C. Crites
CPC分类号： B23P15/04 , B23K20/02 , B23K20/233 , B23K2101/001 , B23K2103/18 , B23K2103/26 , B23P15/006 , F01D5/3061 , F01D5/34 , F05D2230/232
摘要： Methods are provided for manufacturing a shrouded bonded turbine rotor. A shrouded blade ring is formed. The shrouded blade ring is formed by bonding a unitary shroud ring to an assembled blade ring or assembling a plurality of shrouded turbine blade segments. The shrouded blade ring is bonded to a hub. The shrouded bonded turbine rotors are also provided. The shrouded bonded turbine rotor comprises a shrouded blade ring and a shroud. The shrouded blade ring comprises a plurality of turbine blade segments and a shroud. Each turbine blade segment comprises an airfoil portion including an airfoil having a root and a tip. The shroud covers the tip of each airfoil in the shrouded blade ring. A hub is bonded with the shrouded blade ring.
摘要翻译： 提供了用于制造被覆盖的粘结涡轮转子的方法。 形成有盖的叶片环。 被覆盖的叶片环通过将整体护罩环结合到组装的叶片环或组装多个带盖的涡轮叶片段而形成。 被覆盖的叶片环结合到轮毂。 还提供了带盖的粘合涡轮转子。 被覆盖的粘合涡轮转子包括被覆盖的叶片环和护罩。 被覆盖的叶片环包括多个涡轮叶片段和护罩。 每个涡轮机叶片段包括翼型部分，其包括具有根部和尖端的翼型件。 护罩覆盖被覆盖的叶片环中每个翼型的末端。 轮毂与被覆盖的叶片环结合。
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公开(公告)号：US10851660B2
公开(公告)日：2020-12-01
申请号：US16580951
申请日：2019-09-24
发明人： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
摘要： Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.
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公开(公告)号：US20200291792A1
公开(公告)日：2020-09-17
申请号：US16855591
申请日：2020-04-22
发明人： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
摘要： A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes a plurality of cooling passages each having a respective inlet in fluid communication with a source of cooling fluid to receive a cooling fluid. The turbine blade includes a plurality of flow meters, with at least a respective one of the plurality of flow meters associated with a respective one of the plurality of cooling passages at the respective inlet.
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公开(公告)号：US20190145266A1
公开(公告)日：2019-05-16
申请号：US15810809
申请日：2017-11-13
IPC分类号： F01D5/18
摘要： An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.
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公开(公告)号：US20210003023A1
公开(公告)日：2021-01-07
申请号：US17014547
申请日：2020-09-08
发明人： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
摘要： A turbine engine includes a turbine wheel including a rotor disk and turbine blades connected to the rotor disk through blade mounts. The blade mounts and the rotor disk have fore and aft surfaces. The blade mount includes a blade attachment surface connecting the fore and aft surfaces with the turbine blade extending from the blade attachment surface. A gap is defined between and separating adjacent blade mounts and extends into the rotor disk. The gap includes a pocket having a fore opening and a rotor relief hole. The turbine wheel further includes a plug disposed in a rotor relief opening and a pocket seal disposed in the pocket. The turbine engine further includes a fore seal plate having an edge abutting the blade mounts about a circumference of the turbine wheel and a finger extending toward and contacting the plug to maintain the plug in the rotor relief opening.
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公开(公告)号：US10683763B2
公开(公告)日：2020-06-16
申请号：US15285347
申请日：2016-10-04
发明人： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
摘要： A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.
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公开(公告)号：US20180094527A1
公开(公告)日：2018-04-05
申请号：US15285347
申请日：2016-10-04
发明人： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
IPC分类号： F01D5/18
摘要： A turbine blade with an integral flow meter is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade includes at least one cooling passage defined internally within the turbine blade, and the at least one cooling passage is in fluid communication with a source of cooling fluid via an inlet to receive a cooling fluid. The turbine blade also includes at least one flow meter formed within the turbine blade at the inlet that supplies the cooling fluid to the at least one cooling passage.
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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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