-
公开(公告)号：US09879566B2
公开(公告)日：2018-01-30
申请号：US14793465
申请日：2015-07-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Mark C. Morris , David R. Waldman , Donald G. Godfrey , Brian G. Baughman , Mark McNair , Justin C. Mickelsen
IPC: F01D25/28 , F16L27/111 , F16L47/18 , F02K1/80 , F02C7/32
CPC classification number: F01D25/28 , B22F3/1055 , B33Y80/00 , F02C7/32 , F02K1/80 , F16L27/111 , F16L47/18 , Y02P10/295
Abstract: A coupling apparatus for use in sealingly connecting a first fluid flow path to a second fluid flow path. The coupling apparatus includes a rigid fluid flow channel having a first end and a second end, wherein the fluid flow channel is substantially rigid in an axial direction and a radial direction, a first sealing terminus that is rigidly connected to the first end and that is configured for sealing with the first fluid flow path, and a second sealing terminus that is slidingly disposed about the second end such that the second sealing terminus is configured for relative movement with respect to the second end, and wherein the second sealing terminus is further configured for sealing with the second fluid flow path. The coupling apparatus further includes a flexible coupler connected to both the first sealing terminus and the second sealing terminus and surrounding the fluid flow channel, wherein the coupler is relatively more flexible in the axial direction and the radial direction as compared to the fluid flow channel.
-
公开(公告)号：US09879544B2
公开(公告)日：2018-01-30
申请号：US14055521
申请日：2013-10-16
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David Waldman , Mark C. Morris , Malak Fouad Malak
CPC classification number: F01D5/18 , F01D5/147 , F01D5/20 , F05D2230/00 , F05D2260/20 , Y02T50/673 , Y10T29/49341
Abstract: A turbine rotor blade is provided for a turbine section of an engine. The turbine 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 first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; and a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air. The first cooling hole has a closed channel section and an open channel section. The open channel section forms a slot.
-
23.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
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Christopher David Gatto , Jude Miller , Benjamin Dosland Kamrath , Don Mittendorf , Jason Smoke , Mark C. Morris
CPC classification number: 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
Abstract: 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.
-
24.发明申请公开(公告)号：US20170129060A1
公开(公告)日：2017-05-11
申请号：US14933154
申请日：2015-11-05
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Andy Szuromi , Steve Starr , Donald G. Godfrey , Mark C. Morris
IPC: B23P6/04 , B22F3/105 , B23K15/00 , B22F3/26 , C23C18/38 , C23C18/32 , C23C18/16 , C25D5/48 , C23C10/60 , C23C18/42
CPC classification number: B23P6/045 , B22F3/105 , B22F3/1055 , B22F3/15 , B22F3/24 , B22F3/26 , B22F5/009 , B22F5/04 , B22F2003/247 , B22F2998/10 , B23K15/0086 , B33Y10/00 , B33Y99/00 , C22C1/0416 , C22C21/00 , C23C10/28 , C23C10/60 , C23C18/1637 , C23C18/1689 , C23C18/32 , C23C18/38 , C23C18/42 , C23C26/00 , C25D5/48 , F01D5/00 , F01D5/288 , F05D2230/22 , F05D2230/90 , Y02P10/295
Abstract: A method for improving the surface of an aluminum alloy article includes manufacturing the aluminum alloy article using an additive manufacturing technique, wherein the article as-manufactured includes one or more of cracks, roughness, or porosity at a surface of the article; coating the surface of the aluminum alloy article with a diffusion element, the diffusion element being capable of diffusing at least 0.2 mils into the article; heating the aluminum alloy article coated with the diffusion element to cause the diffusion element to diffuse the at least 0.2 mils into the article, thereby forming a diffusion layer of at least 0.2 mils in thickness comprising both aluminum alloy and diffusion element; and removing the diffusion layer from the aluminum alloy article, whereby upon the removing, a resulting improved surface of the article comprises fewer or smaller cracks, reduced roughness, or reduced porosity.
-
公开(公告)号：US20160146024A1
公开(公告)日：2016-05-26
申请号：US14551293
申请日：2014-11-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Mark C. Morris , Daira Legzdina , Don Mittendorf , Milton Ortiz , Ardeshir Riahi , Michael Vinup
IPC: F01D5/30 , F01D5/28 , B23K20/12 , C22F1/18 , B23K31/02 , B23K20/00 , C22F1/10 , F01D5/18 , B23K31/12
CPC classification number: F01D5/3061 , B23K20/002 , B23K20/1205 , B23K31/02 , B23K31/12 , B23P15/006 , C22F1/10 , C22F1/183 , F01D5/187 , F01D5/28 , F01D5/288 , F05D2220/32 , F05D2230/10 , F05D2230/239 , F05D2230/411 , F05D2230/90 , F05D2240/30 , F05D2260/20 , F05D2260/941 , F05D2300/17 , F05D2300/174
Abstract: Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A hybrid bonded turbine rotor comprises a turbine disk and a plurality of turbine blades each metallurgically bonded to a corresponding raised blade attachment surface of a plurality of raised blade attachment surfaces of the turbine disk to define a bond plane located at a selected radial position. Turbine disk has a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with the plurality of raised blade attachment surfaces defining the outer periphery. The selected radial position is outboard of the live rim. Each pair of adjacent turbine blades defines a shank cavity therebetween. The shank cavity extends radially outwardly from the live rim and includes a live rim notch disposed below the bond plane and above the live rim.
Abstract translation: 提供混合式涡轮转子及其制造方法。 混合结合的涡轮机转子包括涡轮盘和多个涡轮机叶片，每个涡轮机叶片各自冶金地结合到涡轮盘的多个凸起的叶片附接表面的对应的凸起的叶片附接表面，以限定位于选定径向位置处的接合平面。 涡轮盘具有边缘部分，其包括周向连续材料的活边缘和在涡轮盘的外周中的多个带状轮缘切口，与限定外周的多个凸起刀片附接表面交替。 所选的径向位置是活动边缘的外侧。 每对相邻的涡轮叶片在它们之间限定一个柄腔。 柄腔从活边缘径向向外延伸，并且包括设置在接合平面下方和活边缘上方的活边缘凹口。
-
Patent Agency Ranking
公开(公告)号：US09267189B2
公开(公告)日：2016-02-23
申请号：US13801662
申请日：2013-03-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Donald G. Godfrey , Richard Bye , Mark C. Morris , Harry Kington
CPC classification number: C22C1/0416 , B22F3/1055 , B22F2202/11 , B22F2301/052 , Y02P10/295
Abstract: In accordance with an exemplary embodiment, a method of forming a dispersion-strengthened aluminum alloy metal includes the steps of providing a dispersion-strengthened aluminum alloy composition in a powdered form, directing a low energy density laser beam at a portion of the powdered alloy composition, and withdrawing the laser beam from the portion of the powdered alloy composition. Subsequent to withdrawal of the laser beam, the portion of the powdered alloy composition cools at a rate greater than or equal to about 106° C. per second, thereby forming the dispersion-strengthened aluminum alloy metal.
Abstract translation: 根据示例性实施例，形成分散强化铝合金金属的方法包括以下步骤：提供粉末形式的分散强化铝合金组合物，在粉末状合金组合物的一部分处引导低能量密度激光束 并且从该粉末状合金组合物的部分中取出激光束。 在激光束退出之后，粉末状合金组合物的部分以大于或等于约106℃/秒的速率冷却，从而形成分散强化的铝合金金属。
-
公开(公告)号：US20150082808A1
公开(公告)日：2015-03-26
申请号：US13855417
申请日：2013-04-02
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Daniel Cregg Crites , Mark C. Morris , Lorenzo Crosatti , Ardeshir Riahi
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
Abstract: An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
Abstract translation: 提供了一种用于燃气涡轮发动机的翼型件。 翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。 内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。
-
28.发明申请公开(公告)号：US20140360698A1
公开(公告)日：2014-12-11
申请号：US13911904
申请日：2013-06-06
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David Waldman , Mark C. Morris , Donald G. Godfrey
CPC classification number: F28F1/10 , B22F3/1055 , F16L27/11 , F28D1/05316 , F28D7/0058 , F28D7/16 , F28D2021/0021 , F28F1/006 , F28F1/08 , F28F1/26 , F28F5/00 , F28F2255/02 , F28F2255/18 , F28F2265/26 , Y02P10/295
Abstract: Unitary heat exchangers having integrally-formed compliant heat exchanger tubes and heat exchange systems including the same are provided. The unitary heat exchanger comprises an inlet plenum and an outlet plenum and a plurality of integrally-formed compliant heat exchanger tubes. The plurality of integrally-formed compliant heat exchanger tubes extend between and are integral with the inlet and outlet plenums to define a heat exchanger first flow passage. Each integrally-formed compliant heat exchanger tube comprises a tubular member and a plurality of integral heat transfer fins extend radially outwardly from at least one portion of the tubular member. The tubular member has a proximal tube end and a distal tube end and comprises a tubular wall having an outer wall surface and an inner wall surface.
Abstract translation: 提供具有整体形成的顺应性热交换器管和包括其的热交换系统的单一热交换器。 整体热交换器包括入口气室和出口增压室以及多个整体形成的顺应性热交换器管。 多个整体形成的顺应性热交换器管在入口和出口增压室之间延伸并且与入口和出口增压室成一体，以限定热交换器第一流动通道。 每个整体形成的柔性热交换器管包括管状构件和从管状构件的至少一部分径向向外延伸的多个整体传热翅片。 管状构件具有近端管端和远端管端，并且包括具有外壁表面和内壁表面的管状壁。
-
公开(公告)号：US08876471B2
公开(公告)日：2014-11-04
申请号：US13887801
申请日：2013-05-06
Applicant: Honeywell International Inc.
Inventor： Mark C. Morris , Harry Lester Kington , James Neumann
CPC classification number: F01D9/00 , F01D5/284 , F01D9/041 , F05D2300/606 , Y02T50/673
Abstract: In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.
Abstract translation: 根据示例性实施例，涡轮机定子部件包括第一端壁; 第二端壁 耦合在第一和第二端壁之间的第一定子翼型件; 以及与第一翼型件相邻并且连接在第一和第二端壁之间的第二定子翼型件。 第一定子翼型件具有第一晶体初级和次级取向。 第二定子翼型具有第二晶体初级和次级取向，第一晶体初级和次级取向不同于第二晶体初级和次级取向。
-
30.发明申请SPRING ASSEMBLIES FOR USE IN GAS TURBINE ENGINES AND METHODS FOR THEIR MANUFACTURE 有权用于气体涡轮发动机的弹簧组件及其制造方法公开(公告)号：US20140283922A1
公开(公告)日：2014-09-25
申请号：US13742210
申请日：2013-01-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Laurie Strom , Donald G. Godfrey , Harry Lester Kington , Douglas Hall , Mark C. Morris
CPC classification number: F16K17/048 , B22F3/1055 , B22F5/009 , B33Y80/00 , F01D17/00 , F02C7/232 , F02C9/38 , F05D2230/31 , F16F1/043 , F16F1/047 , F16F2226/04 , Y02P10/295 , Y10T29/49412 , Y10T137/2705
Abstract: In accordance with an exemplary embodiment, a method for manufacturing a bypass valve of a turbine engine control system is described. The bypass valve includes a proportional valve and an integrator valve and the integrator valve includes an integrator spring assembly. The method includes forming the integrator spring assembly using an additive manufacturing technique. The integrator spring assembly comprises first and second end portions with a spring portion disposed between the first and second end portions. The first and second end portions and the spring portion are formed as an integral unit without welding or brazing using the additive manufacturing technique. The method further includes assembling the integrator spring assembly, the integrator valve, and the proportional valve into a complete bypass valve assembly.
Abstract translation: 根据示例性实施例，描述了一种用于制造涡轮发动机控制系统的旁通阀的方法。 旁通阀包括比例阀和积分阀，积分器阀包括积分器弹簧组件。 该方法包括使用添加剂制造技术形成积分器弹簧组件。 积分器弹簧组件包括具有设置在第一和第二端部之间的弹簧部分的第一和第二端部。 使用添加剂制造技术，第一和第二端部和弹簧部分形成为不用焊接或钎焊的整体单元。 该方法还包括将积分器弹簧组件，积分器阀和比例阀组装成完整的旁通阀组件。
-
-
-
-
-
-
-
-
-
Search Results
91
records
(took 0.031 seconds)
