公开(公告)号：US11913346B2

公开(公告)日：2024-02-27

申请号：US16891665

申请日：2020-06-03

Applicant: General Electric Company

Inventor： Frank Worthoff ,  Benjamin James Roby ,  Scott Roger Finn

IPC: F01D21/04 ,  F04D29/52 ,  F04D29/02 ,  B32B5/12 ,  B32B5/26

CPC classification number: F01D21/045 ,  B32B5/12 ,  B32B5/263 ,  F04D29/023 ,  F04D29/526 ,  B32B2260/023 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/558 ,  B32B2605/18 ,  F05D2220/36 ,  F05D2230/50 ,  F05D2240/14 ,  F05D2300/2102 ,  F05D2300/603 ,  F05D2300/6012

Abstract: An apparatus a multiple layer structure having a sub-portion defining an impact zone, and having an inner composite fiber layer, an outer composite fiber layer overlying the inner composite fiber layer, and a woven glass layer, where the inner composite fiber layer, outer composite fiber layer, and the woven glass layer overly the impact zone.

公开(公告)号：US20180328176A1

公开(公告)日：2018-11-15

申请号：US15591275

申请日：2017-05-10

Applicant: General Electric Company

Inventor： Viswanadha Gupta Sakala ,  Wendy Wenling Lin ,  Raghuveer Chinta

IPC: F01D5/02 ,  F02C3/04 ,  F01D25/00

CPC classification number: F01D25/005 ,  F01D5/147 ,  F01D5/28 ,  F01D5/282 ,  F02C7/04 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/10 ,  F05D2300/2102 ,  F05D2300/50212 ,  F05D2300/603

Abstract: An annular rotatable component for a machine includes a first element formed of a composite material, is ring-shaped, and is formed of one or more first ring segments. The first element includes a first interface surface. A second element is formed of a metallic material, is ring-shaped, and is formed of one or more second ring segments. The second element includes a second interface surface complementary to the first interface surface. The annular rotatable component also includes an interface comprising an interface material disposed between the first interface surface and the second interface surface. The interface material, the first element and the second element are co-bonded together to form a unitary structure of the annular rotatable component.

公开(公告)号：US20180274387A1

公开(公告)日：2018-09-27

申请号：US15465995

申请日：2017-03-22

Applicant: The Boeing Company

Inventor： Scott D. Hartshorn ,  Keith D. Humfeld

IPC: F01D25/08 ,  F01D5/12 ,  F01D25/24 ,  C23C4/134

CPC classification number: C23C28/042 ,  C23C28/046 ,  C23C28/322 ,  C23C28/3455 ,  F01D5/02 ,  F01D5/08 ,  F01D25/12 ,  F01D25/26 ,  F05D2300/20 ,  F05D2300/2102 ,  F05D2300/2118 ,  F05D2300/5024 ,  Y02T50/673 ,  Y02T50/676

Abstract: An engine shaft assembly for an engine is provided. The engine shaft assembly includes a shaft and a thermal distribution layer. The thermal distribution layer is provided on the shaft, and is configured to minimize the effect of distortion of the shaft caused by asymmetric cooling on shutdown of the engine.

公开(公告)号：US20180209292A1

公开(公告)日：2018-07-26

申请号：US15873442

申请日：2018-01-17

Applicant: Safran Aero Boosters SA

Inventor： Stephane Hiernaux

IPC: F01D11/24 ,  F01D25/18 ,  F02C7/14 ,  F01D11/12

CPC classification number: F01D11/24 ,  F01D11/122 ,  F01D25/125 ,  F01D25/18 ,  F02C7/14 ,  F05D2220/36 ,  F05D2240/55 ,  F05D2260/205 ,  F05D2260/30 ,  F05D2260/98 ,  F05D2300/2102 ,  F05D2300/2261 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/675

Abstract: A system for active control of radial gap around an annular row of rotor blades of a turbine engine, notably rotor blades of a low-pressure compressor of an aircraft turbojet engine. The system comprises an annular row of rotor blades; an outer casing around the annular row of rotor blades; a radial gap between the rotor blades and the outer casing; an oil circuit which is suitable for recovering the calories from a reduction gear box such as a planetary gear train which drives the fan. The oil circuit includes an expansion module which is configured to be expanded by the calories recovered from the oil. The expansion module is placed inside the outer casing so as to modulate its diameter around the rotor blades.

公开(公告)号：US20170073278A1

公开(公告)日：2017-03-16

申请号：US15265134

申请日：2016-09-14

Applicant: Rolls-Royce Corporation

Inventor： Sean E. Landwehr ,  Adam Lee Chamberlain ,  Ann Bolcavage

IPC: C04B41/86 ,  C23C16/44 ,  C23C14/22 ,  C25D13/02 ,  C04B41/00 ,  C23C14/32 ,  C03C8/02 ,  C03C3/091 ,  C03C3/093 ,  C04B41/50 ,  C23C4/134 ,  C23C14/06

CPC classification number: C04B41/86 ,  C03C3/064 ,  C03C3/091 ,  C03C3/093 ,  C03C8/02 ,  C03C2209/00 ,  C04B41/009 ,  C04B41/5022 ,  C04B41/52 ,  C04B41/89 ,  C23C4/134 ,  C23C14/06 ,  C23C14/221 ,  C23C14/325 ,  C23C16/44 ,  C25D13/02 ,  F01D5/282 ,  F01D5/284 ,  F01D5/288 ,  F05D2300/2102 ,  F05D2300/211 ,  C04B35/14 ,  C04B35/10 ,  C04B35/565 ,  C04B35/806 ,  C04B35/584 ,  C04B41/5096 ,  C04B41/4582 ,  C04B41/5045 ,  C04B41/5024 ,  C04B41/522 ,  C04B41/4523

Abstract: In some examples, method including forming an EBC layer on a substrate, wherein the EBC layer exhibits an initial porosity; forming a layer of silicate glass on a surface of the EBC layer; and melting the silicate glass on the surface of the EBC layer to infiltrate the EBC layer with the molten silicate glass to decrease the porosity of the EBC layer from the initial porosity to a final porosity.

Abstract translation: 在一些实例中，包括在基底上形成EBC层的方法，其中EBC层表现出初始孔隙率; 在EBC层的表面上形成硅酸盐玻璃层; 并且在EBC层的表面上熔化硅酸盐玻璃以用熔融的硅酸盐玻璃渗透EBC层，以将EBC层的孔隙率从初始孔隙度降低到最终的孔隙率。

公开(公告)号：US20160290160A1

公开(公告)日：2016-10-06

申请号：US15033292

申请日：2014-09-18

Applicant: SIEMENS AKTIENGESELLSCHAFT

Inventor： Manuel ETTLER ,  Bora KOCDEMIR ,  Alexander LITINSKY ,  Andrey MASHKIN ,  Dieter MINNINGER ,  Adam ZIMMERMANN

IPC: F01D25/14 ,  F01D25/00 ,  F01D25/24

CPC classification number: F01D25/145 ,  B05D1/28 ,  F01D25/005 ,  F01D25/24 ,  F01D25/26 ,  F02K1/822 ,  F05D2220/31 ,  F05D2230/90 ,  F05D2250/241 ,  F05D2300/20 ,  F05D2300/21 ,  F05D2300/2102 ,  F05D2300/43 ,  F05D2300/432 ,  F05D2300/44 ,  F05D2300/48 ,  F05D2300/5023 ,  F05D2300/5024 ,  F05D2300/514

Abstract: A turbomachine includes an inner housing which radially defines the flow channel of the turbomachine. A thermal barrier coating is arranged about the inner housing. The thermal barrier coating of the inner housing is made of microporous plastic coating which can be added to hollow spheres made of different materials and have different sizes. A method for applying a thermal barrier coating to the inner casing of a turbomachine includes preparing a material having a base material which has a microporous plastic; coating the outside of the wall of the inner casing by applying the base material to the inner casing; and curing the applied material, thus forming the thermal barrier coating.

Abstract translation: 涡轮机包括径向地限定涡轮机的流动通道的内壳体。 围绕内壳布置隔热涂层。 内壳的隔热涂层由微孔塑料涂层制成，可以添加到由不同材料制成并具有不同尺寸的中空球体上。 一种将热障涂层施加到涡轮机的内壳的方法包括制备具有具有微孔塑料的基材的材料; 通过将基材施加到内壳来涂覆内壳的壁的外部; 并固化所施加的材料，从而形成热障涂层。

公开(公告)号：US20160230670A1

公开(公告)日：2016-08-11

申请号：US14617640

申请日：2015-02-09

Applicant: THE BOEING COMPANY

Inventor： Christopher WHEATON ,  Mark Stephen SHANDER

IPC: F02C7/24 ,  B64D41/00 ,  F02C7/32 ,  F16L59/14 ,  B64C3/18 ,  F16L9/10 ,  F16L9/14 ,  B64D27/12 ,  B64C3/32

CPC classification number: F02C7/24 ,  B64D13/00 ,  F01D25/00 ,  F02C7/00 ,  F02C7/32 ,  F05D2300/2102 ,  F05D2300/614 ,  F16L57/00 ,  Y02T50/672

Abstract: Apparatus and system for containing a rupture of a duct. The apparatus includes an air-permeable sheet, such as a wide-weave fiberglass sheet. The air-permeable sheet includes a strap arranged on a first side of the sheet such that it forms diamond-shaped patterns along a longitudinal axis. The strap can be made of a tight-weave fiberglass. Laterally-spaced corners of the diamond-shaped patterns include connection members that can be engaged to affix the strap and the air-permeable sheet around a duct. Various aspects include an air-impermeable air barrier surrounding the wide-weave fiberglass sheet and strap. The air barrier can include a window that directs air from a ruptured duct. Various aspects can be used on a bleed-air duct of an aircraft. The window of the air barrier can be aimed at a temperature sensor. A valve can close the bleed-air duct if the temperature sensor detects a high temperature leak.

Abstract translation: 用于容纳管道破裂的装置和系统。 该装置包括透气性片材，例如宽织物玻璃纤维片材。 透气片包括布置在片材的第一侧上的带，使得其沿着纵向轴线形成菱形图案。 表带可以由紧密编织的玻璃纤维制成。 菱形图案的横向间隔的角部包括能够接合的连接构件，用于将带和透气片附接到管道周围。 各种方面包括围绕宽织物玻璃纤维板和带子的不透气的空气屏障。 空气障碍物可以包括从破裂的管道引导空气的窗口。 飞机的排气管道可以使用各种方面。 空气屏障的窗口可以瞄准温度传感器。 如果温度传感器检测到高温泄漏，阀门可以关闭排气管道。

公开(公告)号：US08939728B2

公开(公告)日：2015-01-27

申请号：US13173269

申请日：2011-06-30

Applicant: Michael G. McCaffrey ,  John E. Holowczak

Inventor： Michael G. McCaffrey ,  John E. Holowczak

IPC: F03B3/12 ,  F01D5/28 ,  F01D5/30 ,  B28B1/00 ,  C04B35/80

CPC classification number: B28B23/02 ,  B28B1/008 ,  B28B1/14 ,  B28B7/18 ,  B28B11/243 ,  B28B23/0006 ,  C04B35/565 ,  C04B35/584 ,  C04B35/80 ,  C04B35/803 ,  C04B35/806 ,  C04B2235/36 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/602 ,  C04B2235/614 ,  C04B2235/616 ,  F01D5/28 ,  F01D5/282 ,  F01D5/284 ,  F01D5/3084 ,  F05D2230/21 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2283 ,  F05D2300/6033

Abstract: A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material. A ceramic matrix composite material is located adjacent interior portions of the platform and the attachment feature and is bonded to the monolithic ceramic material.

Abstract translation: 用于燃气涡轮发动机的混合部件具有平台和附接特征。 平台和附件特征的外部部分由单块陶瓷材料形成。 陶瓷基质复合材料位于平台的内部和附着特征附近并且结合到整体陶瓷材料上。

公开(公告)号：US08591196B2

公开(公告)日：2013-11-26

申请号：US12141524

申请日：2008-06-18

Applicant: Canan Hardwicke

Inventor： Canan Hardwicke

IPC: F03B3/12

CPC classification number: C23C30/00 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/34 ,  C23C28/345 ,  C23C28/3455 ,  C23C28/42 ,  F01D5/26 ,  F01D5/288 ,  F05C2201/0466 ,  F05D2230/90 ,  F05D2260/96 ,  F05D2300/133 ,  F05D2300/21 ,  F05D2300/2102

Abstract: A gas turbine or turbine component partially or fully coated with a damping surface layer. The damping surface layer may have a thickness between 0.1 and 2000 microns and may be capable of dissipating vibration or modifying a resonance frequency of the gas turbine or turbine component at ambient room temperatures including operational temperatures greater than 500° F., and the damping surface layer comprises at least one of (a) at least two layers comprising a first layer of at least one hard material and a second layer comprising at least one soft material, (b) a composite comprising a nickel alloy with a heat softenable chemistry, (c) a fine-grained nickel-based superalloy, or (d) a porous metallic coating, a porous metallic and ceramic coating, or a ceramic coating.

Abstract translation: 部分或全部涂覆有阻尼表面层的燃气轮机或涡轮机部件。 阻尼表面层可以具有0.1至2000微米的厚度，并且可以在包括大于500°F的操作温度的环境室温下消散振动或改变燃气轮机或涡轮机部件的共振频率，并且阻尼表面 至少一层包括至少两层，包括至少一种硬质材料的第一层和包含至少一种软材料的第二层，（b）包含镍合金和可热化学化学的复合材料（ c）细晶镍基超级合金，或（d）多孔金属涂层，多孔金属和陶瓷涂层或陶瓷涂层。

公开(公告)号：US08034273B2

公开(公告)日：2011-10-11

申请号：US12298249

申请日：2007-04-25

Applicant: Joëlle Lalande ,  Frédéric Ballion ,  Dirk Feltin

Inventor： Joëlle Lalande ,  Frédéric Ballion ,  Dirk Feltin

IPC: B29C45/02 ,  B29C69/00

CPC classification number: B29C70/34 ,  B29C70/24 ,  B29C70/30 ,  B29C70/543 ,  B29C70/545 ,  F02K9/97 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/614 ,  Y10T428/24124

Abstract: The invention provides a method of making a fiber ply for forming a preform of a composite part in the form of a body of revolution having a non-developable surface, the method being characterized in that it comprises the steps consisting in: defining an annular space (23) with first and second canvases (20, 21) respectively defining an inner periphery and an outer periphery thereof; placing fibers between the canvases (20, 21) by placing the fibers in the annular space in at least one direction and by holding said fibers on the canvases by stitching; implementing circular connection stitching in the vicinity of the inner periphery of the annular space (23); and cutting out the fiber ply as made in this way in the annular space (23) in order to extract it from the canvases.

Abstract translation: 本发明提供一种制造纤维帘布层的方法，用于形成具有不可展开表面的具有旋转体形式的复合部件的预成型件，该方法的特征在于包括以下步骤：限定环形空间 （23）具有分别限定其内周和外周的第一和第二帆布（20,21）; 通过将纤维沿至少一个方向放置在环形空间中并通过缝合将所述纤维保持在帆布上，将纤维放置在帆布（20,21）之间; 在环形空间（23）的内周附近实施圆形连接缝合; 并且在环形空间（23）中切割出如此制造的纤维层，以便将其从帆布中提取出来。