公开(公告)号：US09970359B2

公开(公告)日：2018-05-15

申请号：US14343635

申请日：2012-09-07

申请人： Cedric Plaindoux ,  Simon Schers ,  Benjamin Moura

发明人： Cedric Plaindoux ,  Simon Schers ,  Benjamin Moura

IPC分类号： B32B7/00 ,  B32B7/02 ,  F02C7/25 ,  B64C7/02

CPC分类号： F02C7/25 ,  B64C7/02 ,  F05D2300/131 ,  F05D2300/30 ,  F05D2300/5024 ,  F05D2300/522 ,  F05D2300/603 ,  Y10T428/24008 ,  Y10T428/266

摘要： A flame resistant shield includes two opposing walls between which are positioned at least: a first insulating layer, the first layer being capable of distributing heat in the plane formed by the first layer and being insulating across its thickness, a second insulating layer, one of the opposing walls which covers the first layer being produced from a refractory antioxidant material or having at least the surface intended to be exposed to flames covered with a material preventing this surface from being oxidized, the other wall being a support.

公开(公告)号：US20160169008A1

公开(公告)日：2016-06-16

申请号：US15048533

申请日：2016-02-19

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： BLAKE M. MANTEL

IPC分类号： F01D5/28 ,  C23C4/134 ,  F01D5/30

CPC分类号： F01D5/288 ,  C23C4/134 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3092 ,  F05D2220/32 ,  F05D2230/312 ,  F05D2230/80 ,  F05D2240/30 ,  F05D2300/522 ,  Y02T50/672

摘要： A ceramic matrix composite blade may include an airfoil and a root. A protective metallic layer may be coupled to the root. The protective metallic layer may be plasma sprayed on the root. A portion of the protective metallic layer may be removed.

摘要翻译： 陶瓷基复合叶片可包括翼型件和根部。 保护性金属层可以连接到根部。 保护金属层可以等离子体喷在根部上。 保护金属层的一部分可以被去除。

公开(公告)号：US20150104306A1

公开(公告)日：2015-04-16

申请号：US14505956

申请日：2014-10-03

申请人： ROLLS-ROYCE PLC

发明人： Steven Aleksy RADOMSKI ,  Simon READ

IPC分类号： F04D29/64 ,  F04D19/00 ,  F04D29/02

CPC分类号： F01D25/24 ,  F01D11/122 ,  F01D21/045 ,  F02C7/04 ,  F04D19/002 ,  F04D29/023 ,  F05D2220/36 ,  F05D2250/25 ,  F05D2300/522 ,  F05D2300/615 ,  Y10T29/49245

摘要： A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

摘要翻译： 一种用于具有推进风扇的燃气涡轮发动机的风扇壳体装置，该装置具有风扇壳体和风扇轨道衬套，并且构造成围绕风扇，其中，风扇履带衬套围绕风扇壳体的内部设置，以便采用 风扇和风扇外壳之间的径向位置。 风扇履带板包括细长构件，其以多个匝螺旋缠绕在风扇壳体的内部。 一种在具有推进风扇的燃气涡轮发动机的风扇壳体装置中安装风扇轨道衬套的方法，所述方法包括：提供风扇壳体以包围风扇，提供柔性和细长的衬垫构件，以及螺旋地卷绕衬套构件 以多个匝相对于风扇壳体的内部限定至少一部分风扇轨道衬套。

公开(公告)号：US08747586B2

公开(公告)日：2014-06-10

申请号：US12883367

申请日：2010-09-16

申请人： Ross Collins ,  Ruth A. Barcock

发明人： Ross Collins ,  Ruth A. Barcock

IPC分类号： F01D25/24 ,  B32B37/18

CPC分类号： F02C7/045 ,  F01D11/127 ,  F02C7/24 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2300/506 ,  F05D2300/522 ,  F05D2300/603 ,  F05D2300/612 ,  F05D2300/615

摘要： A liner panel, such as a cassette 120 of a fan track liner of a gas turbine engine, is secured to a casing of the engine at flanges 124 and 126. Foam pads 42 are disposed between the casing 40 and the cassette 120 to support the cassette 120 from the casing 40. The pads 42 may be made from a reticulated polyurethane foam which is sufficiently resilient to be compressed and to expand to remain in contact with the cassette 120 and the casing 40 as the cassette 120 moves towards and away from the casing 40 during the assembly process. The foam is impregnated with a hardener composition which is uncured during installation of the cassette 120, but subsequently cures to increase the rigidity of the pads 42.

摘要翻译： 衬套板，例如燃气涡轮发动机的风扇轨道衬套的盒120，在凸缘124和126处固定到发动机的壳体上。泡沫垫42设置在壳体40和盒120之间，以支撑 垫片42可以由网状聚氨酯泡沫制成，其具有足够的弹性以被压缩并且随着盒120朝向和远离的方向移动而膨胀以保持与盒120和壳体40接触 套管40在装配过程中。 泡沫浸渍有在安装盒120期间未固化的固化剂组合物，但随后固化以增加垫42的刚度。

公开(公告)号：US20090016894A1

公开(公告)日：2009-01-15

申请号：US12216505

申请日：2008-07-07

申请人： Oliver M. Strother

发明人： Oliver M. Strother

IPC分类号： F01D5/14 ,  B21K3/04

CPC分类号： B21D53/78 ,  B21D26/055 ,  B21D47/00 ,  B23P15/04 ,  F01D5/147 ,  F01D5/16 ,  F02K3/06 ,  F04D29/023 ,  F04D29/388 ,  F04D29/668 ,  F05D2300/43 ,  F05D2300/501 ,  F05D2300/522 ,  Y10T29/49337

摘要： A method of manufacturing a component such as a gas turbine fan blade. The method comprises: disposing a plurality of webs between a plurality of panels; and deforming the panels and the webs by applying internal pressure between the panels, thereby forming a series of internal cavities (15) partitioned by the webs (20-22). Weakened regions (30a,30b,30c) are formed in the webs which open to form holes (30) in the webs (20-22) during the deformation step. A damping material (17) is introduced into at least one of the cavities (15) whereby it flows from the cavity into the other cavities via the holes in the webs.

摘要翻译： 一种制造诸如燃气轮机风扇叶片的部件的方法。 该方法包括：在多个面板之间布置多个腹板; 以及通过在所述面板之间施加内部压力来使所述面板和所述腹板变形，从而形成由所述腹板（20-22）分隔的一系列内部空腔（15）。 弱化区域（30a，30b，30c）形成在所述腹板中，所述腹板在变形步骤期间打开以在腹板（20-22）中形成孔（30）。 阻尼材料（17）被引入到空腔（15）中的至少一个中，由此其通过腹板中的孔从空腔流入其它空腔。

公开(公告)号：US11767764B1

公开(公告)日：2023-09-26

申请号：US17031221

申请日：2020-09-24

申请人： Raytheon Technologies Corporation

发明人： Haiyun Li ,  Eliannah Hunderfund ,  Sean Nolan

IPC分类号： F01D5/16 ,  F01D5/34 ,  F01D5/14 ,  F02C3/06

CPC分类号： F01D5/16 ,  F01D5/141 ,  F01D5/34 ,  F02C3/06 ,  F05D2220/321 ,  F05D2230/80 ,  F05D2240/30 ,  F05D2260/96 ,  F05D2300/175 ,  F05D2300/522

摘要： A turbomachine airfoil element includes an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.83-0.93 inch (21.1-23.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.80-0.90 inch (20.4-22.9 mm). The airfoil element includes at least two of a first mode with a frequency is 3135±10% Hz, a second mode with a frequency is 6634±10% Hz, a third mode with a frequency is 13260±10% Hz, a fourth mode with a frequency is 16838±10% Hz and a fifth mode with a frequency is 17980±10% Hz.

公开(公告)号：US20180328383A1

公开(公告)日：2018-11-15

申请号：US15493719

申请日：2017-04-21

申请人： General Electric Company

发明人： Scott Allen Jones

IPC分类号： F04D29/52 ,  F01D25/00 ,  F04D29/02 ,  C23C4/10 ,  C23C4/134 ,  C23C4/08

CPC分类号： F04D29/526 ,  C23C4/02 ,  C23C4/08 ,  C23C4/10 ,  C23C4/134 ,  F01D11/122 ,  F01D25/007 ,  F01D25/24 ,  F04D29/023 ,  F04D29/164 ,  F05D2220/323 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2240/14 ,  F05D2260/95 ,  F05D2300/173 ,  F05D2300/522 ,  F05D2300/611

摘要： Coating systems for components of a gas turbine engine, such as a compressor case, are provided. The coating system can include a dense layer disposed along the inner surface of the compressor case as well as an abradable, top coat disposed along the dense layer. The combination of dense layer and abradable top coat can reduce the occurrence of galvanic corrosion of the coating system and thereby increase the lifetime of the coating system and preserve blade clearances within the compressor. Methods are also provided for applying the coating system onto a compressor case.

公开(公告)号：US09777599B2

公开(公告)日：2017-10-03

申请号：US14505956

申请日：2014-10-03

申请人： ROLLS-ROYCE PLC

发明人： Steven Aleksy Radomski ,  Simon Read

IPC分类号： F01D25/24 ,  F01D21/04 ,  F01D11/12 ,  F02C7/04 ,  F04D19/00 ,  F04D29/02

CPC分类号： F01D25/24 ,  F01D11/122 ,  F01D21/045 ,  F02C7/04 ,  F04D19/002 ,  F04D29/023 ,  F05D2220/36 ,  F05D2250/25 ,  F05D2300/522 ,  F05D2300/615 ,  Y10T29/49245

摘要： A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

公开(公告)号：US20120107103A1

公开(公告)日：2012-05-03

申请号：US13242951

申请日：2011-09-23

申请人： Yoshitaka Kojima ,  Hideyuki Arikawa ,  Akira Mebata ,  Tadashi Kasuya ,  Hiroyuki Doi ,  Kunihiro Ichikawa ,  Takao Endo ,  Kazuto Mikazuki ,  Hidetoshi Kuroki

发明人： Yoshitaka Kojima ,  Hideyuki Arikawa ,  Akira Mebata ,  Tadashi Kasuya ,  Hiroyuki Doi ,  Kunihiro Ichikawa ,  Takao Endo ,  Kazuto Mikazuki ,  Hidetoshi Kuroki

IPC分类号： F01D11/12 ,  B23P15/00

CPC分类号： F01D11/122 ,  F05D2230/311 ,  F05D2240/11 ,  F05D2300/514 ,  F05D2300/522 ,  Y10T29/49323

摘要： A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (hardness RC15Y: 80±3), the porous ceramic abradable layer is provided with slit grooves by machining work, and a slit groove width is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved.

摘要翻译： 燃气轮机罩包括耐磨性和耐久性优异的陶瓷耐磨涂层。 本发明的燃气轮机陶瓷耐磨涂层由耐磨金属层和多孔陶瓷耐磨层（硬度RC15Y：80±3）构成，多孔陶瓷耐磨层通过加工加工而形成狭缝槽，狭缝槽 宽度为0.5〜5mm。 由此，能够提高耐磨损性，耐热循环性和耐高温氧化性。

公开(公告)号：US07594325B2

公开(公告)日：2009-09-29

申请号：US11210872

申请日：2005-08-25

申请人： Simon Read

发明人： Simon Read

IPC分类号： B21D53/78 ,  B63H1/26 ,  B22F3/00

CPC分类号： F04D29/542 ,  B21D26/055 ,  B21D53/78 ,  F04D29/023 ,  F04D29/38 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2300/10 ,  F05D2300/522 ,  F05D2300/61 ,  F05D2300/612 ,  Y10T29/49316 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T428/12021 ,  Y10T428/12028 ,  Y10T428/12042

摘要： An aerofoil (35) for example a fan blade (26) comprises a leading edge (36), a trailing edge (38), a concave pressure surface extending (40) from the leading edge (36) to the trailing edge (38) and a convex suction surface (42) extending from the leading edge (36) to the trailing edge (38). The aerofoil (35) comprises a metal foam (50) arranged within a cavity defined by metal workpieces (52, 54). The metal foam (50) of the aerofoil (26) ideally has a density of less than 1g/cm3, is cheaper to manufacture and has improved fatigue behaviour and impact capability.

摘要翻译： 例如风扇叶片（26）的机翼（35）包括前缘（36​​），后缘（38），从前缘（36​​）延伸到后缘（38）延伸（40）的凹形压力表面， 以及从前缘（36​​）延伸到后缘（38）的凸形吸入表面（42）。 机翼（35）包括布置在由金属工件（52,54）限定的空腔内的金属泡沫（50）。 机翼（26）的金属泡沫（50）理想地具有小于1g / cm 3的密度，制造成本更低，并且具有改善的疲劳行为和冲击能力。