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公开(公告)号：US20160319686A1
公开(公告)日：2016-11-03
申请号：US15076127
申请日：2016-03-21
Inventor： Jun Shi , Ted J. Freeman , David J. Thomas
Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a pressure-activated seal. The pressure-activated seal is arranged in a channel formed between a first component and a second component that opens toward the high pressure zone.
Abstract translation: 适于将高压区域与低压区分离的燃气涡轮发动机组件包括压力激活的密封件。 压力激活密封件布置在形成在朝向高压区域打开的第一部件和第二部件之间的通道中。
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公开(公告)号：US20160258304A1
公开(公告)日：2016-09-08
申请号：US15055004
申请日：2016-02-26
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Richard C. Uskert , Peter J. Loftus , Andrew J. Lazur
CPC classification number: F01D25/246 , F05D2300/6033 , Y02T50/672
Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.
Abstract translation: 用于燃气涡轮发动机的涡轮罩包括载体和叶片轨道段。 载体形成为包括向内开口的叶片轨道通道，并且叶片轨道段定位在叶片轨道通道中以将叶片轨道段与载体相耦合。
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43.发明申请公开(公告)号：US20160245108A1
公开(公告)日：2016-08-25
申请号：US15049747
申请日：2016-02-22
Inventor： Aaron D. Sippel , Ted J. Freeman
CPC classification number: F16J15/44 , F01D11/005 , F05D2230/60 , F05D2240/55 , Y02T50/672
Abstract: An apparatus adapted for use in a gas turbine engine includes a first circumferential member and a second circumferential member. The first circumferential member includes an end portion that defines a recess and includes a first seal surface. The second circumferential member includes an end portion that includes a second seal surface. The end portion of the second circumferential member is configured to be at least partially disposed in the recess of the first circumferential member to collectively form at least a portion of a circumferential assembly of a gas turbine. The first seal surface of the first circumferential member is forms a first seal with a seal member and the second seal surface of the second circumferential member is forms a second seal with the seal member when the end portion of the second circumferential member is disposed in the recess of the first circumferential member.
Abstract translation: 适用于燃气涡轮发动机的装置包括第一周向构件和第二圆周构件。 第一周向构件包括限定凹部并包括第一密封表面的端部。 第二周向构件包括包括第二密封表面的端部。 第二圆周构件的端部构造成至少部分地设置在第一圆周构件的凹部中，以共同形成燃气轮机的圆周组件的至少一部分。 第一周向构件的第一密封面形成具有密封构件的第一密封件，并且第二周向构件的第二密封表面在第二周向构件的端部设置在第二密封构件中时与密封构件形成第二密封 第一周向构件的凹部。
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公开(公告)号：US20160201484A1
公开(公告)日：2016-07-14
申请号：US14974545
申请日：2015-12-18
Inventor： Todd Z. Engel , Ted J. Freeman , Robert J. Shinavski , Ian Thomson
CPC classification number: F01D5/3084 , F01D5/025 , F01D5/284 , F01D5/3007 , F01D5/3053 , F01D5/326 , F05D2220/32 , F05D2230/10 , F05D2230/236 , F05D2230/237 , F05D2230/60 , F05D2250/21 , F05D2260/30 , Y02T50/672 , Y02T50/673
Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机叶轮，其具有附接到转子盘的多个叶片。 每个叶片由包含陶瓷基质材料的复合材料形成。 叶片各自包括适合在转子盘的燕尾槽内的根部，并与叶片保持组件配合以将叶片耦合到转子盘。
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公开(公告)号：US20160177748A1
公开(公告)日：2016-06-23
申请号：US14971539
申请日：2015-12-16
Inventor： Jeffrey A. Walston , Daniel K. Vetters , Ted J. Freeman
CPC classification number: F01D5/303 , B23P15/006 , F01D5/28 , F01D5/282 , F01D5/284 , F01D5/3007 , F01D5/3061 , F01D5/34 , F05D2220/31 , F05D2230/12 , F05D2230/232 , Y02T50/672 , Y02T50/673
Abstract: A turbine wheel for use in a gas turbine engine having a bladed ring attached to a rotor disk. The bladed ring includes features to fit within slots of the rotor disk to couple the bladed ring to the rotor disk.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机叶轮，其具有附接到转子盘的叶片环。 叶片环包括装配在转子盘的槽中的特征，以将叶片环连接到转子盘。
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Patent Agency Ranking
46.发明申请ABRASIVE TIPS FOR CERAMIC MATRIX COMPOSITE BLADES AND METHODS FOR MAKING THE SAME 审中-公开用于陶瓷基复合材料刀片的磨料及其制造方法公开(公告)号：US20160177745A1
公开(公告)日：2016-06-23
申请号：US14957149
申请日：2015-12-02
Inventor： Richard C. Uskert , Kang N. Lee , Ted J. Freeman
CPC classification number: F01D5/284 , C23C16/045 , F01D5/14 , F01D5/147 , F01D5/18 , F01D5/282 , F01D5/288 , F01D11/12 , F05D2220/32 , F05D2230/314 , F05D2240/307 , F05D2260/20 , F05D2300/2261 , F05D2300/2282 , F05D2300/2283 , F05D2300/43 , F05D2300/6033
Abstract: A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil. The airfoil may comprise a ceramic material, and a distal end. A tip may extend from the distal end of the airfoil. The tip of the airfoil may comprise a substantially porous structure and may comprise infiltrated material extending from an airfoil preform to a tip preform to join the airfoil preform and the tip preform.
Abstract translation: 这里描述了一种用于生产用于燃气涡轮发动机的叶片的叶片和方法。 叶片可以包括复合翼型件。 翼型件可以包括陶瓷材料和远端。 尖端可以从翼型的远端延伸。 翼型件的尖端可以包括基本上多孔的结构，并且可以包括从翼型件预制件延伸到尖端预制件以将翼型件预制件和尖端预制件连接的渗透材料。
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公开(公告)号：US20160169025A1
公开(公告)日：2016-06-16
申请号：US14968157
申请日：2015-12-14
Applicant: Rolls-Royce Corporation , Rolls-Royce plc , Rolls-Royce North American Technologies, Inc.
Inventor： Joseph P. Lamusga , Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Simon L. Jones
CPC classification number: F01D11/08 , F01D9/04 , F01D25/12 , F01D25/246 , F01D25/28 , F05D2220/30 , F05D2230/60 , F05D2240/11 , F05D2260/201 , F05D2260/30 , F05D2300/6033 , Y02T50/672 , Y02T50/676
Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.
Abstract translation: 公开了一种涡轮机的部件。 该部件包括具有轨道的载体段，框架段，其包括具有支撑在载体段的轨道上的凸缘的悬挂器，以及内表面，其具有限定在其中的涡轮机叶片的轨道部分。 该部件还包括固定在载体部分上的保持器部分，使得悬挂件固定在保持架部分和承载部分之间。
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公开(公告)号：US20160123163A1
公开(公告)日：2016-05-05
申请号：US14869427
申请日：2015-09-29
Inventor： Ted J. Freeman , Bruce E. Varney , David J. Thomas , Jeffrey A. Walston
CPC classification number: F01D25/005 , F01D5/282 , F01D5/284 , F01D9/042 , F01D9/065 , F05D2230/642 , F05D2300/6033 , Y02T50/672 , Y02T50/673
Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.
Abstract translation: 本文介绍了一种用于燃气涡轮发动机的叶片组件。 叶片组件包括内平台，外平台和含陶瓷的翼型件。 含陶瓷的翼型件从内平台延伸到外平台。 夹紧机构将内平台和外平台联接到含陶瓷的翼型件上。
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公开(公告)号：US09249684B2
公开(公告)日：2016-02-02
申请号：US14095604
申请日：2013-12-03
Inventor： Andrew J. Lazur , Ted J. Freeman , Aaron D. Sippel , David J. Thomas , Adam L. Chamberlain , Joseph P. Lamusga
CPC classification number: F01D25/005 , B29C70/205 , F01D5/282 , F01D5/284 , F01D5/286 , Y02T50/672 , Y10T428/24025
Abstract: A composite component includes a bonded portion and a component mount. The component mount is coupled to the bonded portion to move relative to the bonded portion. The bonded portion includes a fiber portion and a ceramic portion.
Abstract translation: 复合部件包括接合部分和部件安装件。 部件安装件联接到接合部分以相对于接合部分移动。 接合部分包括纤维部分和陶瓷部分。
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50.发明申请COMPOSITE BLADE WITH AN INTEGRAL BLADE TIP SHROUD AND METHOD OF FORMING THE SAME 有权具有整体叶片尖端的复合叶片及其形成方法公开(公告)号：US20150044050A1
公开(公告)日：2015-02-12
申请号：US14138627
申请日：2013-12-23
Inventor： David J. Thomas , Ted J. Freeman , Richard C. Uskert , Larry A. Junod , Joseph Lamusga
CPC classification number: F01D5/225 , F01D5/147 , F01D5/282 , F01D5/284 , F05D2300/6033 , Y02T50/672 , Y10T29/49321
Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.
Abstract translation: 一种燃气涡轮发动机气流元件，其包括叶片芯部，从所述叶片芯部延伸的护罩前端部，以及形成在所述叶片芯部外侧的翼型部，所述叶片芯部和所述护罩前端部构成为第一 整体结构和翼型部分构造为第二结构。 还公开了一种形成燃气涡轮发动机部件的方法。
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