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21.发明授权Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade 有权包括膜冷却系统的涡轮叶片翼型以及用于形成涡轮叶片的改进的薄膜冷却翼型的方法公开(公告)号：US09562437B2
公开(公告)日：2017-02-07
申请号：US13871655
申请日：2013-04-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Vighneswara Rao Kollati , Balamurugan Srinivasan , Jong Liu , Daniel C. Crites , Luis Tapia , Malak Fouad Malak , Rajiv Rana
CPC classification number: F01D5/186 , B23P15/02 , F05D2230/10 , F05D2240/303 , F05D2240/305 , F05D2240/306 , Y02T50/676 , Y10T29/49341
Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
Abstract translation: 提供了涡轮叶片翼型件，其薄膜冷却系统以及用于形成改进的薄膜冷却部件的方法。 涡轮叶片翼型件具有外壁表面并且包括前缘和后缘，压力和吸力侧壁均在前缘和后缘之间延伸，内腔，外壁表面中的一个或多个隔离沟槽，多个膜冷却 布置在冷却排中的孔，以及将相同冷却排中的膜冷却孔的出口互连的多个跨距表面连接器，以形成多排相互连接的膜冷却孔。 每个薄膜冷却孔具有连接到内部空腔的入口和外壁表面上的出口。 在至少一个所选择的互连薄膜冷却孔排中的跨度表面连接器设置在所述一个或多个隔离沟槽中。
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22.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
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Michael Kahrs , Timothy Vander Hoek , Loris Bedrosyan , Jason Smoke , Ardeshir Riahi , Daniel C. Crites
CPC classification number: B23P15/04 , B23K20/02 , B23K20/233 , B23K2101/001 , B23K2103/18 , B23K2103/26 , B23P15/006 , F01D5/3061 , F01D5/34 , F05D2230/232
Abstract: 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.
Abstract translation: 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：US20150078916A1
公开(公告)日：2015-03-19
申请号：US14030647
申请日：2013-09-18
Applicant: Honeywell International Inc.
Inventor： Loris Bedrosyan , Ardeshir Riahi , Daniel C. Crites
CPC classification number: F01D5/20 , F01D5/186 , F01D5/187 , F01D11/10 , F05D2240/307 , F05D2260/20 , Y02T50/673 , Y02T50/676
Abstract: A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.
Abstract translation: 涡轮转子叶片设置有用于包括围绕转子叶片的护罩的发动机的涡轮机部分。 转子叶片包括平台和从平台延伸到主流气体路径中的翼型件。 翼型件包括压力侧壁，连接到前缘处的压力侧壁的抽吸侧壁和后缘，在吸力侧壁和压力侧壁之间延伸的末端盖，从第一推进器尖端延伸部 压力侧壁相对于压力侧壁成第一角度，第一尖叫尖端延伸部限定在入口和出口之间会聚的第一冷却孔; 内部冷却回路，其构造成经由第一冷却孔将冷却空气输送到压力侧鸣响器末端延伸部和护罩之间的间隙。
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公开(公告)号：US11333042B2
公开(公告)日：2022-05-17
申请号：US16998523
申请日：2020-08-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Daniel C. Crites , Mark C. Morris , Steven Whitaker , David Waldman
Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.
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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
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Benjamin Dosland Kamrath , Jason Smoke , Daniel C. Crites , Mark C. Morris
Abstract: 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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Patent Agency Ranking
公开(公告)号：US20210172337A1
公开(公告)日：2021-06-10
申请号：US17181113
申请日：2021-02-22
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Steven Whitaker , Daniel C. Crites , Mark C. Morris , Ardeshir Riahi
Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.
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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
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
Abstract: 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：US20200318488A1
公开(公告)日：2020-10-08
申请号：US16378030
申请日：2019-04-08
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Benjamin Dosland Kamrath , Jason Smoke , Daniel C. Crites , Mark C. Morris
Abstract: 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：US20200291792A1
公开(公告)日：2020-09-17
申请号：US16855591
申请日：2020-04-22
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Steve Halfmann , Daniel C. Crites , Michael Kahrs , Ardeshir Riahi , Jude Miller
Abstract: 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：US10563520B2
公开(公告)日：2020-02-18
申请号：US15475597
申请日：2017-03-31
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Benjamin Dosland Kamrath , Jason Smoke , Daniel C. Crites
IPC: F01D5/18
Abstract: 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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