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1. 发明授权

US09938930B2 Composite wear pad for exhaust nozzle 有权
公开(公告)号：US09938930B2
公开(公告)日：2018-04-10
申请号：US14709072
申请日：2015-05-11
申请人： United Technologies Corporation
发明人： Donald W. Peters , Emma J. Place
IPC分类号： F02K1/80 , F02K1/12 , F01D25/16 , F16C29/00 , F16C29/02 , F16C33/20
CPC分类号： F02K1/80 , F01D25/168 , F02K1/1223 , F05D2220/32 , F05D2240/128 , F05D2260/231 , F05D2300/434 , F05D2300/44 , F05D2300/603 , F05D2300/614 , F16C29/001 , F16C29/02 , F16C33/201 , Y02T50/672
摘要： A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.

2. 发明申请

US20160265370A1 CHOCKING AND RETAINING DEVICE 审中-公开
标题翻译：锁定和保持装置
公开(公告)号：US20160265370A1
公开(公告)日：2016-09-15
申请号：US15057407
申请日：2016-03-01
申请人： ROLLS-ROYCE plc
发明人： Christopher BENSON
IPC分类号： F01D5/32 , F01D25/06 , F01D5/30
CPC分类号： F01D5/326 , F01D5/282 , F01D5/3007 , F01D5/3053 , F01D5/323 , F01D25/06 , F05D2220/32 , F05D2220/36 , F05D2240/30 , F05D2260/30 , F05D2260/96 , F05D2300/432 , F05D2300/434 , F05D2300/603 , F05D2300/611
摘要： A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc includes a retention body having a key portion receivable in a keyway formed in the base of the slot, and a mating portion for mating with a complementary mating portion of the root to prevent relative axial movement between the retention body and the root. The retention body has a lowered position in which the key portion is received sufficiently deeply in the keyway to allow the root to be positioned in the slot without interference from the retention body and also has a raised position in which, after the root is positioned in the slot, a part of the key portion is still received in the keyway while the mating portion mates with the complementary mating portion of the root.
摘要翻译：用于将一个燃气涡轮发动机的叶片的燕尾根夹持在盘的边缘中的相应的轴向延伸的狭槽中的装置包括一个保持体，该保持体具有可接收在形成在槽的基部中的键槽中的键部分，以及配合部分，用于与根部的互补配合部分配合，以防止保持体和根部之间的相对轴向移动。保持体具有下降位置，其中键部在键槽中被足够深地接收，以允许根部定位在槽中而不受到保持体的干扰，并且还具有升高位置，在根部位于狭槽，键部分的一部分仍然被接收在键槽中，而配合部分与根部的互补配合部分配合。

3. 发明申请

US20150202707A1 Attachment of Structures Having Different Physical Characteristics 审中-公开
标题翻译：具有不同物理特性的结构附件
公开(公告)号：US20150202707A1
公开(公告)日：2015-07-23
申请号：US14510553
申请日：2014-10-09
申请人： United Technologies Corporation
发明人： Grant O. Cook, III , James T. Roach
IPC分类号： B23K1/00 , F04D19/00 , F04D29/38 , B23K1/19
CPC分类号： B23K1/0018 , B23K1/19 , B23K2101/001 , F01D5/282 , F01D5/3061 , F01D5/3092 , F02K3/06 , F04D29/322 , F05D2220/36 , F05D2230/236 , F05D2230/237 , F05D2300/433 , F05D2300/434 , F05D2300/436 , F05D2300/437 , F05D2300/44 , F05D2300/48 , F05D2300/50212
摘要： Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines. The method includes providing the first and second structures and plating or otherwise coating a portion of the first structure with a metal to provide a metal-coated portion. The method includes applying at least one intermediate material onto the metal-coated portion of the first structure. The method further includes bonding the metal-coated portion of the first structure and the intermediate material to the second structure. The bonding is carried out using a relatively low-temperature process, such as liquid phase bonding, including TLP and PTLP bonding. Brazing is also a suitable technique, depending on the materials chosen for the first and second structures.
摘要翻译：公开了将第一结构粘合到第二结构的方法，其中第一和第二结构是具有不同物理特性的制造材料。例如，第一结构可以是复合风扇叶片，并且第二结构可以是用于燃气涡轮发动机的复合或金属转子。该方法包括提供第一和第二结构，并用金属电镀或以其他方式涂覆第一结构的一部分以提供金属涂覆部分。该方法包括将至少一种中间材料施加到第一结构的金属涂覆部分上。该方法还包括将第一结构的金属涂覆部分和中间材料结合到第二结构。使用包括TLP和PTLP结合在内的相对低温的方法，例如液相结合来进行结合。取决于为第一和第二结构选择的材料，钎焊也是合适的技术。

4. 发明申请

US20150078893A1 SEAL ARRANGEMENT FOR A TURBOMACHINE AND PROCESS FOR THE PRODUCTION THEREOF 审中-公开
标题翻译：涡轮机的密封装置及其生产方法
公开(公告)号：US20150078893A1
公开(公告)日：2015-03-19
申请号：US14490931
申请日：2014-09-19
申请人： MTU Aero Engines AG
发明人： Siegfried SCHMID , Michael SCHOBER , Siegfried SIKORSKI , Axel MATTSCHAS , Robert BADER
IPC分类号： F01D11/02 , B29C65/02 , B29C65/70 , F16J15/447
CPC分类号： F01D11/02 , B29C65/02 , B29C65/70 , F01D11/122 , F05D2220/32 , F05D2230/21 , F05D2230/40 , F05D2230/41 , F05D2240/11 , F05D2240/58 , F05D2300/434 , F05D2300/437 , F05D2300/44 , F05D2300/603 , F16J15/447 , Y02T50/672
摘要： The present invention relates to a process for producing a seal arrangement (1) for a turbomachine which comprises a seal support (2) and a stripping lining (3) which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.
摘要翻译：本发明涉及一种用于制造用于涡轮机的密封装置（1）的方法，该密封装置包括密封支撑件（2）和布置在密封支撑件上的剥离衬里（3），其中密封件支撑件包括纤维增强塑料和剥离衬里包括聚硅氧烷，并且其中密封支撑件和剥离衬里被制备成非固化状态，并且根据密封装置的构造彼此直接接触地布置，并随后经受普通的固化过程使纤维增强塑料和聚硅氧烷彼此交联。本发明还涉及相应地生产的密封装置和具有这种密封装置的涡轮机。

5. 发明申请

US20140174092A1 Closure of Cooling Holes with a Filling Agent 有权
标题翻译：用填充剂封闭冷却孔
公开(公告)号：US20140174092A1
公开(公告)日：2014-06-26
申请号：US13722253
申请日：2012-12-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： William Bogue , Ron I. P. E. Prihar
IPC分类号： B05D7/22 , F23R3/00
CPC分类号： B05D7/22 , B23P6/007 , B23P2700/06 , B23P2700/13 , C23C4/02 , F01D5/005 , F01D5/288 , F05D2230/42 , F05D2230/80 , F05D2230/90 , F05D2300/434 , F23R3/002 , F23R2900/00016 , F23R2900/00019
摘要： A method for filling cooling holes in a component of a gas turbine engine is disclosed. The component may include a plurality of first cooling holes extending through the wall of the component. The method may comprise the steps of exposing the outer surface of the component, filling the plurality of first cooling holes with a polyimide, curing the polyimide to block the passage of cooling fluid through the plurality of first cooling holes, and applying a thermal bather coating over the outer surface of the component. The method may further include the step of installing a second plurality of cooling holes in the wall of the component wherein the plurality of second cooling holes penetrate the thermal barrier coating and the wall of the component and allow cooling fluid to pass therethrough.
摘要翻译：公开了一种用于在燃气涡轮发动机的部件中填充冷却孔的方法。部件可以包括延伸穿过部件的壁的多个第一冷却孔。该方法可以包括以下步骤：暴露组件的外表面，用聚酰亚胺填充多个第一冷却孔，固化聚酰亚胺以阻止冷却流体通过多个第一冷却孔，并且施加热泡沫涂层在组件的外表面上。该方法还可以包括在组件的壁中安装第二多个冷却孔的步骤，其中多个第二冷却孔穿过热障涂层和部件的壁并允许冷却流体通过。

6. 发明申请

US20070090726A1 Piezoelectric fan 审中-公开
标题翻译：压电风扇
公开(公告)号：US20070090726A1
公开(公告)日：2007-04-26
申请号：US11256759
申请日：2005-10-24
申请人： Grant Morris , Jared Brosch
发明人： Grant Morris , Jared Brosch
IPC分类号： H01L41/00
CPC分类号： F04D29/023 , F04D33/00 , F05D2230/31 , F05D2300/20 , F05D2300/222 , F05D2300/43 , F05D2300/434 , F05D2300/50 , F05D2300/603 , H01L41/094
摘要： A method of making a piezoelectric fan includes using a portion of the fan blade material as the substrate for the electronic circuit. By this method a single material may serve as both the substrate for the electronic circuitry and as the fanning end of the fan blade. Flex circuitry, including elements such as bleed resistors, inductors, capacitors, DC to AC conversion, shielding, or even drive circuitry, may be used. The piezoelectric material used to power the fan blade may have a Curie temperature high enough to survive reflow soldering, thus allowing the fan to be surface mountable on an electronic device. The fan may include an interconnect to facilitate connecting the piezoelectric material to the electronic circuit of the fan, and to facilitate connecting the electronic circuit of the fan to the electrical system of an electronic device. The interconnect may also facilitate mechanically mounting the fan.
摘要翻译：制造压电风扇的方法包括使用风扇叶片材料的一部分作为电子电路的基板。通过该方法，单个材料可以用作电子电路的基板和风扇叶片的扇形端。可以使用Flex电路，包括诸如泄放电阻器，电感器，电容器，DC到AC转换，屏蔽或甚至驱动电路的元件。用于为风扇叶片供电的压电材料可具有足够高的居里温度以回流焊接，从而允许风扇可表面安装在电子设备上。风扇可以包括互连以便于将压电材料连接到风扇的电子电路，并且便于将风扇的电子电路连接到电子设备的电气系统。互连还可以有助于机械地安装风扇。

7. 发明授权

US07147434B2 Nozzle ring with adhesive bonded blading for aircraft engine compressor 有权
标题翻译：用于飞机发动机压缩机的带有粘合剂叶片的喷嘴环
公开(公告)号：US07147434B2
公开(公告)日：2006-12-12
申请号：US10876610
申请日：2004-06-28
申请人： Claude Marcel Mons , Sandra Andrieu , Manuel Girard , Francois Pierre Georges Maurice Ribassin
发明人： Claude Marcel Mons , Sandra Andrieu , Manuel Girard , Francois Pierre Georges Maurice Ribassin
IPC分类号： F01D9/04
CPC分类号： F04D29/023 , F01D9/042 , F04D29/542 , F05D2230/23 , F05D2300/434 , F05D2300/603 , Y02T50/672 , Y10T29/49323 , Y10T29/49885
摘要： Blades (3) extending radially from the inner shroud (1) to the outer shroud (2) are attached to the inner shroud by means of a sealing cement containing an organic polyimide-based polymer adhesive.
摘要翻译：从内护罩（1）向外护罩（2）径向延伸的刀片（3）通过含有有机聚酰亚胺基聚合物粘合剂的密封胶水附接到内护罩。

8. 发明申请

US20020192074A1 Spring-backed abradable seal for turbomachinery 有权
标题翻译：用于涡轮机械的弹簧式耐磨密封件
公开(公告)号：US20020192074A1
公开(公告)日：2002-12-19
申请号：US09681851
申请日：2001-06-18
发明人： Norman Arnold Turnquist , Mahmut Faruk Aksit , Farshad Ghasripoor , Raymond Edward Chupp
IPC分类号： F01D011/12
CPC分类号： F01D11/122 , F05C2201/0466 , F05D2240/56 , F05D2260/30 , F05D2300/224 , F05D2300/43 , F05D2300/434 , F05D2300/44 , F05D2300/614 , F05D2300/702 , F16J15/3288 , F16J15/445
摘要： The present invention provides, in one embodiment, an annular turbine seal for disposition in a turbine between a rotatable component having an axis of rotation and a turbine housing about the same axis of rotation. The turbine seal has a plurality of arcuate seal carrier segments that have an abradable portion secured to the seal carrier segments. In addition, at least one spring is disposed on the seal carrier segment to exert a force and maintain the seal carrier segment adjacent to the rotatable component.
摘要翻译：在一个实施例中，本发明提供了一种环形涡轮密封件，用于在具有旋转轴线的可旋转部件和围绕相同旋转轴线的涡轮机壳体之间配置在涡轮机中。涡轮密封件具有多个弓形密封载体段，其具有固定到密封载体段的可磨损部分。此外，至少一个弹簧设置在密封件承载部分上以施加力并将密封载体部分保持在可旋转部件附近。

9. 发明申请

US20010016091A1 Variable vane seal and washer materials 失效
公开(公告)号：US20010016091A1
公开(公告)日：2001-08-23
申请号：US09821570
申请日：2001-03-29
发明人： Thomas C. Mesing , Wayne R. Bowen , David B. Hester
IPC分类号： F16C033/18
CPC分类号： F01D17/162 , F04D29/023 , F04D29/083 , F05D2230/31 , F05D2300/432 , F05D2300/434 , F05D2300/603 , Y10S384/908 , Y10S384/911 , Y10T29/49297 , Y10T29/49668 , Y10T29/4967 , Y10T29/49702 , Y10T428/12035 , Y10T428/12049
摘要： A multi-layer seal and washer that provide a seal between a vane stem and a casing in a turbine engine are disclosed. The seal and washer are fabricated from materials such as Teflon fibers and glass fibers and are impregnated with a polyimide resin. The seal and washer are durable and have a low coefficient of friction.

10. 发明申请

US20170096968A1 SOLID PROPELLANT GRAIN 审中-公开
公开(公告)号：US20170096968A1
公开(公告)日：2017-04-06
申请号：US14873522
申请日：2015-10-02
申请人： Andrew William McBain , Zachary Keith Wingard
发明人： Andrew William McBain , Zachary Keith Wingard
IPC分类号： F02K9/95
CPC分类号： C06B45/18 , C06B45/00 , F02K9/10 , F02K9/14 , F02K9/26 , F05D2300/121 , F05D2300/141 , F05D2300/43 , F05D2300/434 , F05D2300/5024
摘要： A solid rocket propellant grain having rocket propellant and a membrane in contact with the rocket propellant. The membrane includes a highly heat conductive pattern which affects the propellant burning rate through localized conductive heat transfer from the combustion zone and into the uncombusted propellant. Different geometries for the thermally conductive pattern produce different combustion results.

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