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11.发明授权公开(公告)号：US09546603B2
公开(公告)日：2017-01-17
申请号：US14244219
申请日：2014-04-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： John Meier , Daniel C. Crites , Yogendra Yogi Sheoran , Mark C. Morris , Jeff Howe , Ardeshir Riahi
CPC classification number: F02C7/30 , F01D5/081 , F01D9/065 , F01D25/32 , F02C3/04 , F02C7/052 , F02C7/18 , F04D29/441 , F05D2220/32 , F05D2260/232 , F05D2260/95 , Y02T50/673 , Y02T50/676
Abstract: A cooling arrangement is provided for a gas turbine engine with a turbine section. The cooling arrangement includes a first conduit to receive cooling air that includes particles; a separator system coupled to the first conduit to receive the cooling air and configured to remove at least a portion of the particles to result in relatively clean cooling air and scavenge air including the portion of the particles; and a second conduit coupled to the separator system and configured to direct the relatively clean cooling air to the turbine section.
Abstract translation: 为具有涡轮部分的燃气涡轮发动机提供冷却装置。 该冷却装置包括用于接收包括颗粒的冷却空气的第一管道; 分离器系统，其耦合到所述第一管道以接收所述冷却空气并且被配置为移除所述颗粒的至少一部分以导致相对干净的冷却空气并且清除包括所述颗粒的所述部分的空气; 以及耦合到分离器系统并被配置为将相对干净的冷却空气引导到涡轮机部分的第二导管。
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12.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
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Steve Halfmann , Mark C. Morris , Jason Smoke , Brandan Wakefield , Bob Mitlin
IPC: F01D5/14
CPC classification number: F01D5/14 , F01D5/141 , F01D5/22 , F01D5/3007 , F05D2240/80 , F05D2250/184 , F05D2250/75 , Y02T50/673 , Y10T29/49336
Abstract: 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.
Abstract translation: 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：US20140083116A1
公开(公告)日：2014-03-27
申请号：US13629284
申请日：2012-09-27
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Daniel Cregg Crites , Steve Halfmann , Mark C. Morris , Ardeshir Riahi
CPC classification number: F01D5/187 , F05D2260/201 , F05D2260/202 , F05D2260/221 , Y02T50/673 , Y02T50/676
Abstract: A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. 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, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.
Abstract translation: 提供了一种用于发动机的涡轮机部分的涡轮机转子叶片。 转子叶片包括平台和从平台延伸到涡轮部分的主流气体路径中的翼型件。 翼型件包括压力侧壁，在前缘和后缘处连接到压力侧壁的吸力侧壁和在吸力侧壁和压力侧壁之间延伸的尖端盖。 转子叶片还包括内部冷却回路，其具有构造成将冷却空气输送到顶盖的顶端通道和位于内部冷却回路的顶端通道内的流动加速器。
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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：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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18.发明申请公开(公告)号：US20190255608A1
公开(公告)日：2019-08-22
申请号：US15901097
申请日：2018-02-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Donald G. Godfrey , Brian G. Baughman , Morgan A. Mader , Mark C. Morris
IPC: B22F3/00 , B22F3/24 , B22F5/04 , B33Y10/00 , B33Y80/00 , C22C14/00 , B33Y70/00 , F01D5/14 , F01D5/28
Abstract: Methods for manufacturing an article include providing a three-dimensional computer model of the article and providing a metal alloy in powdered form. The metal alloy is a titanium aluminide alloy. The powdered form includes a grain size range of about 5 to about 20 microns and a d50 grain size average of about 10 to about 14 microns. The methods further include, at a binder jet printing apparatus, supplying the metal alloy and loading the three-dimensional model, and, using the binder jet printing apparatus, manufacturing the article in accordance with the loaded three-dimensional model in a layer-by-layer manner with the supplied metal alloy. A liquid binder is applied at each layer, and each layer has a thickness of about 10 to about 150 microns. The methods avoid remelting of the metal alloy and avoid metal alloy cooling rates of greater than about 100 ° F. per minute.
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19.发明申请公开(公告)号：US20190247921A1
公开(公告)日：2019-08-15
申请号：US15893903
申请日：2018-02-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Donald G. Godfrey , Brian G. Baughman , Morgan Mader , Mark C. Morris
IPC: B22F3/00 , B22F3/15 , B22F3/24 , B22F5/00 , B22F5/04 , B33Y10/00 , B33Y40/00 , B33Y50/02 , B33Y70/00 , C22C19/05
CPC classification number: C22C1/0433 , B22F1/0014 , B22F3/24 , B22F5/009 , B22F5/04 , B22F2998/10 , B33Y10/00 , B33Y70/00 , C22C19/055 , C22C19/056 , B22F3/008 , B22F3/15 , B22F2003/247 , B22F2003/248
Abstract: Methods for manufacturing an article include providing a three-dimensional computer model of the article and providing a metal alloy in powdered form. The metal alloy is a nickel-chromium-tungsten-molybdenum alloy. The powdered form includes a grain size range of about 5 to about 22 microns and a d50 grain size average of about 10 to about 13 microns. The methods further include, at a binder jet printing apparatus, supplying the metal alloy and loading the three-dimensional model, and, using the binder jet printing apparatus, manufacturing the article in accordance with the loaded three-dimensional model in a layer-by-layer manner with the supplied metal alloy. A liquid binder is applied at each layer, and each layer has a thickness of about 10 to about 150 microns. The methods avoid remelting of the metal alloy and avoid metal alloy cooling rates of greater than about 100° F. per minute.
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公开(公告)号：US10011892B2
公开(公告)日：2018-07-03
申请号：US14465078
申请日：2014-08-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Andy Szuromi , Brian Hann , Mark C. Morris , Donald G. Godfrey
IPC: C22C1/02 , C22C1/03 , B22D25/00 , B22F5/00 , B22F5/04 , B22F9/08 , C22C1/04 , C22C1/06 , C22C19/00 , C22C19/03 , C22C19/07 , B22F1/02 , B22F3/02 , B22F1/00 , B22F3/105 , B22F3/15 , B22F3/22 , C22C33/02
CPC classification number: C22C1/02 , B22D25/00 , B22F1/0007 , B22F1/0014 , B22F1/0048 , B22F1/02 , B22F3/02 , B22F3/1055 , B22F3/15 , B22F3/225 , B22F5/009 , B22F5/04 , B22F9/08 , B22F2999/00 , C22C1/023 , C22C1/03 , C22C1/04 , C22C1/0416 , C22C1/0433 , C22C1/0458 , C22C1/06 , C22C19/007 , C22C19/03 , C22C19/07 , C22C21/00 , C22C33/02 , C22C2202/02 , Y02P10/295 , B22F2201/01 , B22F2201/20 , B22F2201/013 , B22F2201/11 , B22F2201/12
Abstract: Methods are provided for producing alloy forms from alloys containing one or more extremely reactive elements and for fabricating a component therefrom. The fabricating method comprises substantially removing a reactive gas from the fabrication environment. An alloy form of the alloy is formed. The alloy form is formed by melting the alloy or by melting one or more base elements of the alloy to produce a molten liquid and introducing the one or more extremely reactive elements into the molten liquid. The molten alloy is shaped into the alloy form. The component is formed from the alloy form. If the one or more extremely reactive elements are introduced into the molten liquid, such introduction occurs just prior to the shaping step.
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