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1. 发明申请

US20180112531A1 ROTOR DISC WITH PASSAGES 审中-公开
公开(公告)号：US20180112531A1
公开(公告)日：2018-04-26
申请号：US15333916
申请日：2016-10-25
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Farid ABRARI
IPC分类号： F01D5/02 , F01D5/34 , B22F3/15 , B22F5/00 , B33Y10/00 , B33Y80/00
CPC分类号： F01D5/02 , B22F3/15 , B22F5/009 , B22F2998/10 , B33Y10/00 , B33Y80/00 , F01D5/046 , F01D5/081 , F01D5/082 , F01D5/087 , F01D5/34 , F05D2220/32 , F05D2230/42 , F05D2230/50 , F05D2240/30 , F05D2250/14 , F05D2250/25 , Y02P10/295 , B22F3/1055 , B22F3/008
摘要： A rotor disc for a gas turbine engine includes an annular disc body configured to support a circumferential array of blades and having a plurality of passages defined therethrough. The passages form coils within the disc body and/or have a packing density of at least 0.1 in cross-sectional plane containing the central axis, the packing density being defined by a ratio between an open area of the passages and a solid area of the disc in the cross-sectional plane. A method of manufacturing a rotor disc is also discussed.

2. 发明授权

US09631635B2 Blades for axial flow compressor and method for manufacturing same 有权
公开(公告)号：US09631635B2
公开(公告)日：2017-04-25
申请号：US14373796
申请日：2013-01-21
申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA
发明人： Tomoaki Ikegaya , Daisuke Hayashi , Makoto Gouda , Yuji Matsuzaki , Kei Shimada , Katsumi Ikeda
IPC分类号： F04D29/38 , F04D29/32 , F04D29/54 , F04D29/02 , F01D9/04 , F01D5/14 , B22F7/06 , B22F3/12 , B22F5/04
CPC分类号： F04D29/388 , B22F3/12 , B22F5/04 , B22F7/06 , F01D5/14 , F01D9/041 , F04D29/023 , F04D29/324 , F04D29/542 , F05D2230/22 , F05D2230/42 , F05D2240/80 , F05D2300/605 , Y02T50/671 , Y02T50/673
摘要： An axial flow compressor blade unit including a platform section and an airfoil section, which are used as arranged on a circumference about an axis of the compressor. The platform section includes an inner diametric surface segment inwardly of the circumference, an outer diametric surface segment outwardly of the circumference, two annular side surface segments extending in a circumferential direction, two axially side surface segments extending in the axial direction, and a coupling portion formed in each of the annular side surface segments so as to extend in the circumferential direction and being of a shape projecting or recessed in the axial direction. The airfoil section is formed to erect from the platform section so as to extend in a radial direction. The platform section and the airfoil section are formed integrally with each other while having a powdered metal sintered structure.

3. 发明授权

US09574573B2 Wear resistant slurry pump parts produced using hot isostatic pressing 有权
标题翻译：耐磨浆料泵部件采用热等静压
公开(公告)号：US09574573B2
公开(公告)日：2017-02-21
申请号：US14072591
申请日：2013-11-05
申请人： SYNCRUDE CANADA LTD. in trust for the owners of the Syncrude Project
发明人： Hugh Roth , Khaled Obaia , Damien Reid , John Tieu , Daniel MacNeil
IPC分类号： F01D5/14 , F04D29/02 , F04D29/22
CPC分类号： F04D29/026 , F04D29/2294 , F05D2230/42 , F05D2300/171 , F05D2300/2263 , F05D2300/6032 , Y10T29/49243
摘要： In one aspect, a method for manufacturing a part for a centrifugal slurry pump is provided, comprising: forming a skeleton of the part having an outer dimension smaller than the part; placing the skeleton of the part in a metal enclosure having an interior dimension larger than the outer dimension of the skeleton of the part and thereby forming a space; adding a metal matrix composite powder into the metal enclosure to fill the space; and subjecting the metal enclosure to hot isostatic pressing, thereby allowing bonding of the metal matrix composite to the skeleton of the part to form the part.
摘要翻译：一方面，提供了一种制造离心式泥浆泵部件的方法，其特征在于，具备：形成所述部件的骨架，其外径尺寸比所述部件小; 将所述部件的骨架放置在具有大于所述部件的骨架的外部尺寸的内部尺寸的金属外壳中，从而形成空间; 在金属外壳中加入金属基质复合粉末填充空间; 并对金属外壳进行热等静压，从而使金属基质复合体与部件的骨架结合形成部分。

4. 发明申请

US20160348216A1 NICKEL-BASED SUPERALLOYS AND ADDITIVE MANUFACTURING PROCESSES USING NICKEL-BASED SUPERALLOYS 审中-公开
标题翻译：基于镍的超级合金和使用镍基超级合金的添加剂制造工艺
公开(公告)号：US20160348216A1
公开(公告)日：2016-12-01
申请号：US14571332
申请日：2014-12-16
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Andy Szuromi , Hallee Zox Deutchman , Brian G. Baughman , Donald G. Godfrey , Harry Lester Kington , Mark C. Morris
IPC分类号： C22C19/05 , B22F3/105 , F01D9/02 , B33Y70/00 , F01D5/28 , C22F1/10 , B33Y10/00
CPC分类号： C22C19/057 , B22F3/1055 , B33Y10/00 , B33Y70/00 , C22C19/05 , C22F1/10 , F01D5/28 , F01D9/02 , F05D2220/32 , F05D2230/22 , F05D2230/30 , F05D2230/41 , F05D2230/42 , F05D2300/175 , F05D2300/177
摘要： Nickel-based superalloys and additive manufacturing processes using nickel-based superalloys are disclosed herein. For example, a nickel-based superalloy includes, on a weight basis of the overall superalloy: about 9.5% to about 10.5% tungsten, about 9.0% to about 11.0% cobalt, about 8.0% to about 8.8% chromium, about 5.3% to about 5.7% aluminum, about 2.8% to about 3.3% tantalum, about 0.3% to about 1.6% hafnium, about 0.5% to about 0.8% molybdenum, about 0.005% to about 0.04% carbon, and a majority of nickel. Exemplary additive manufacturing processes include subjecting such a nickel-based superalloy in powdered build material form to a high energy density beam in an additive manufacturing process to selectively fuse portions of the build material to form a built component and subjecting the built component to a finishing process to precipitate a gamma-prime phase of the nickel-based superalloy.
摘要翻译：本文公开了使用镍基超级合金的基于镍的超级合金和添加剂制造方法。例如，镍基超级合金的重量基于总超合金：约9.5％至约10.5％的钨，约9.0％至约11.0％的钴，约8.0％至约8.8％的铬，约5.3％至约5.3％约5.7％的铝，约2.8％至约3.3％的钽，约0.3％至约1.6％的铪，约0.5％至约0.8％的钼，约0.005％至约0.04％的碳，以及大部分镍。示例性的添加剂制造方法包括在添加剂制造过程中将这种粉末状构造材料形式的镍基超级合金经受高能量密度束，以选择性地熔化构建材料的部分以形成构建的部件并使内置部件经受精加工过程以沉淀镍基超级合金的γ'相。

5. 发明申请

US20160333694A1 MANUFACTURE OF METAL CORE BY USING RAPID PROTOTYPING METHOD AND METHOD FOR MANUFACTURING PRECISION PARTS THROUGH HOT ISOSTATIC PRESSING USING SAME, AND TURBINE BLISK FOR DRIVING LIQUID ROCKET TURBO PUMP USING SAME 审中-公开
标题翻译：通过使用快速原型制造方法和通过使用相同的热等静压制造精密部件的方法制造金属芯的制造和使用其驱动液压涡轮泵的涡轮机
公开(公告)号：US20160333694A1
公开(公告)日：2016-11-17
申请号：US15106378
申请日：2014-11-25
申请人： KOREA AEROSPACE RESEARCH INSTITUTE
发明人： Suk-Hwan YOON , Jin Han KIM
IPC分类号： F01D5/02 , F02K9/42 , B33Y10/00 , B22F3/105 , B22F5/00 , F01D5/12 , B22F3/15
CPC分类号： F01D5/02 , B22F3/1055 , B22F3/15 , B22F3/24 , B22F5/009 , B22F2003/244 , B22F2003/247 , B33Y10/00 , F01D5/12 , F01D5/34 , F02K9/42 , F05D2220/80 , F05D2230/10 , F05D2230/22 , F05D2230/42 , Y02P10/295
摘要： Disclosed is a method for manufacturing precision parts through hot isostatic pressing using a metal core manufactured through metal rapid prototyping to manufacture a turbine blisk for driving a turbo pump of a liquid rocket. The method includes: manufacturing a metal core that has an internal vacant space having the same shape as the precision parts, using rapid prototyping; putting the metal core in a housing; filling an inside of the housing with heat resistant steel powder and creating a vacuum state in the housing; treating the housing under high temperature and pressure to produce heat resistant steel; removing the housing and a portion of the heat resistant steel to expose a portion of the metal core; performing etching to remove the exposed metal core; and removing only a portion of the heat resistant steel through mechanical machining, wherein the remaining portion corresponds to the shape of the precision part.
摘要翻译：公开了一种通过使用金属芯通过金属快速成型制造的热等静压来制造精密零件的方法，以制造用于驱动液体火箭的涡轮泵的涡轮叶片。该方法包括：使用快速原型制造具有与精密部件相同形状的内部空间空间的金属芯; 将金属芯放在外壳中; 用耐热钢粉填充壳体内部并在壳体中产生真空状态; 在高温高压下对外壳进行处理，制作耐热钢; 移除所述壳体和所述耐热钢的一部分以暴露所述金属芯的一部分; 进行蚀刻以去除暴露的金属芯; 并且通过机械加工仅去除一部分耐热钢，其中剩余部分对应于精密部件的形状。

6. 发明申请

US20150037163A1 BLADES FOR AXIAL FLOW COMPRESSOR AND METHOD FOR MANUFACTURING SAME 有权
标题翻译：轴流式压缩机用叶片及其制造方法
公开(公告)号：US20150037163A1
公开(公告)日：2015-02-05
申请号：US14373796
申请日：2013-01-21
申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA
发明人： Tomoaki Ikegaya , Daisuke Hayashi , Makoto Gouda , Yuji Matsuzaki , Kei Shimada , Katsumi Ikeda
IPC分类号： F04D29/38 , B22F5/04 , B22F3/12
CPC分类号： F04D29/388 , B22F3/12 , B22F5/04 , B22F7/06 , F01D5/14 , F01D9/041 , F04D29/023 , F04D29/324 , F04D29/542 , F05D2230/22 , F05D2230/42 , F05D2240/80 , F05D2300/605 , Y02T50/671 , Y02T50/673
摘要： An axial flow compressor blade unit including a platform section and an airfoil section, which are used as arranged on a circumference about an axis of the compressor. The platform section includes an inner diametric surface segment inwardly of the circumference, an outer diametric surface segment outwardly of the circumference, two annular side surface segments extending in a circumferential direction, two axially side surface segments extending in the axial direction, and a coupling portion formed in each of the annular side surface segments so as to extend in the circumferential direction and being of a shape projecting or recessed in the axial direction. The airfoil section is formed to erect from the platform section so as to extend in a radial direction. The platform section and the airfoil section are formed integrally with each other while having a powdered metal sintered structure.
摘要翻译：轴流式压缩机叶片单元，其包括平台部分和翼型部分，其被布置在围绕压缩机的轴线的圆周上。平台部分包括圆周内部的内径表面段，圆周向外的外直径表面段，沿圆周方向延伸的两个环形侧表面段，沿轴向方向延伸的两个轴向侧表面段，以及连接部分形成在每个所述环形侧表面段中，以便在所述圆周方向上延伸并且呈沿所述轴向突出或凹陷的形状。翼型部形成为从平台部直立而沿径向延伸。平台部分和翼型部分彼此一体地形成，同时具有粉末状的金属烧结结构。

7. 发明授权

US4787821A Dual alloy rotor 失效
标题翻译：双合金转子
公开(公告)号：US4787821A
公开(公告)日：1988-11-29
申请号：US36616
申请日：1987-04-10
申请人： Louis D. Cruse , E. Scott Wright
发明人： Louis D. Cruse , E. Scott Wright
IPC分类号： B23K20/02 , B23P15/00 , F01D5/04 , F01D5/28 , F04D29/28 , B63H1/16
CPC分类号： B23P15/006 , B23K20/021 , F01D5/045 , F01D5/048 , F01D5/28 , F04D29/023 , F04D29/284 , F05D2230/42 , F05D2300/174 , Y02T50/671 , Y02T50/673
摘要： A rotor member for a turbomachine includes a first portion formed of comparatively higher creep rupture strength material, and a second portion integrally joined to the first portion and formed of comparatively higher tensile strength material. The rotor defines a bore and is configured such that the operative environment thereof inflicts higher temperatures upon the first portion, and higher centrifugally-induced stresses upon the second portion. In order to improve the operating speed, burst margin, or both, of the rotor a plurality of circumferentially spaced and annularly arrayed cavities are provided within the rotor at the union of the two portions. The portions are intimately united by hot isostatic pressing (HIP) so that the rotor is of a single piece (monolithic) having portions of selected physical properties appropriate to the thermal/physical stresses imposed thereon, and defining voids which reduce the weight and bore stresses thereof.
摘要翻译：用于涡轮机的转子构件包括由相对较高的蠕变断裂强度材料形成的第一部分和与第一部分一体地接合并由较高拉伸强度的材料形成的第二部分。转子限定孔，并且构造成使得其操作环境在第一部分上施加更高的温度，并且在第二部分上产生较高的离心引起的应力。为了提高转子的操作速度，爆裂边缘或两者，多个沿周向间隔开的和环形排列的空腔在转子内设置在两个部分的联合处。这些部分通过热等静压（HIP）紧密地结合在一起，使得转子是单片（整体），其具有适合于施加在其上的热/物理应力的选定物理性质的部分，并且限定了减小重量和孔应力的空隙其中。

8. 发明授权

US10837287B2 Mistuned bladed rotor and associated manufacturing method 有权
公开(公告)号：US10837287B2
公开(公告)日：2020-11-17
申请号：US15411236
申请日：2017-01-20
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Farid Abrari
IPC分类号： F01D5/16 , F01D5/04 , F04D29/30 , F01D5/14 , F04D29/28 , F04D29/66 , F04D29/38 , B33Y80/00 , F01D5/18 , F04D29/32
CPC分类号： F01D5/16 , B33Y80/00 , F01D5/046 , F01D5/048 , F01D5/147 , F01D5/18 , F04D29/284 , F04D29/30 , F04D29/324 , F04D29/666 , F04D29/384 , F05D2230/31 , F05D2230/42 , F05D2240/301 , F05D2250/291 , F05D2260/961 , Y02T50/673 , Y02T50/676
摘要： Mistuned bladed rotors and associated manufacturing methods are disclosed. An exemplary method includes forming two or more blades of the bladed rotor where the two or more blades have substantially identical external aerodynamic surfaces and have different internal configurations causing the two or more blades to have different natural frequencies.

9. 发明申请

US20180169972A1 METHOD AND TOOLING FOR SHAPING A FAN CASING 审中-公开
公开(公告)号：US20180169972A1
公开(公告)日：2018-06-21
申请号：US15841987
申请日：2017-12-14
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Richard MATHON , Dominique Michel Serge MAGNAUDEIX
IPC分类号： B29C70/44 , B29C70/54 , B29C33/50 , B29D99/00 , F01D25/24
CPC分类号： B29C70/446 , B29C33/505 , B29C49/44 , B29C53/20 , B29C53/82 , B29C53/84 , B29C70/545 , B29D99/006 , B29L2031/7504 , F01D25/24 , F05D2230/42 , F05D2240/14 , F05D2300/44 , F05D2300/603
摘要： A method of shaping the profile of a fan casing having an inside surface, the method including placing the casing around a surface of revolution of a drum of shaping tooling; interposing at least one bladder that is inflatable under the action of a fluid under pressure between a portion of the inside surface of the casing and the drum, the bladder extending over all or part of the surface of revolution of the drum; stoving the assembly including the casing, the tooling, and the at least one bladder at a predetermined temperature; and during the stoving, applying isostatic pressure via the at least one bladder so as to impart a cylindrical profile to the portion of the inside surface of the casing facing the at least one bladder.

10. 发明申请

US20170268089A1 METHODS FOR PROCESSING BONDED DUAL ALLOY ROTORS INCLUDING DIFFERENTIAL HEAT TREATMENT PROCESSES 审中-公开
公开(公告)号：US20170268089A1
公开(公告)日：2017-09-21
申请号：US15071630
申请日：2016-03-16
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Christopher David Gatto , Jude Miller , Benjamin Dosland Kamrath , Don Mittendorf , Jason Smoke , Mark C. Morris
IPC分类号： C22F1/10 , F01D5/02 , F04D29/32
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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