公开(公告)号：US08333558B2

公开(公告)日：2012-12-18

申请号：US12042692

申请日：2008-03-05

申请人： Scott Roger Finn ,  Deepali Bhate ,  Curt Brian Curtis ,  Stephen Mark Whiteker ,  Qi Zhu ,  Lee Alan Blanton ,  Edward Atwood Rainous

发明人： Scott Roger Finn ,  Deepali Bhate ,  Curt Brian Curtis ,  Stephen Mark Whiteker ,  Qi Zhu ,  Lee Alan Blanton ,  Edward Atwood Rainous

IPC分类号： F01D21/00

CPC分类号： F01D21/045 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/601 ,  F05D2300/603 ,  Y02T50/67 ,  Y02T50/672 ,  Y10T29/49323

摘要： A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.

摘要翻译： 容纳壳体包括具有内表面的复合芯和与复合芯一体化的至少一个陶瓷层。 至少一个陶瓷层用树脂粘合到复合芯的内表面上。 在另一个实施例中，容纳壳包括具有内表面的复合芯和包含至少一种陶瓷材料和至少一种非陶瓷材料的混合材料。 混合材料设置在复合芯的内表面上。 混合材料用树脂粘合到复合芯的内表面上。 一种制造容纳壳体的方法包括以下步骤：在复合芯的内表面上设置一层或多层陶瓷织物，将树脂复合芯和一层或多层陶瓷织物浸渍，并固化树脂。

公开(公告)号：US20090226310A1

公开(公告)日：2009-09-10

申请号：US12042692

申请日：2008-03-05

申请人： Scott Roger Finn ,  Deepali Bhate ,  Curt Brian Curtis ,  Stephen Mark Whiteker ,  Qi Zhu ,  Lee Alan Blanton ,  Edward Atwood Rainous

发明人： Scott Roger Finn ,  Deepali Bhate ,  Curt Brian Curtis ,  Stephen Mark Whiteker ,  Qi Zhu ,  Lee Alan Blanton ,  Edward Atwood Rainous

IPC分类号： F01D25/24 ,  B23P15/04

CPC分类号： F01D21/045 ,  F05D2230/90 ,  F05D2300/21 ,  F05D2300/601 ,  F05D2300/603 ,  Y02T50/67 ,  Y02T50/672 ,  Y10T29/49323

摘要： A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.

摘要翻译： 容纳壳体包括具有内表面的复合芯和与复合芯一体化的至少一个陶瓷层。 至少一个陶瓷层用树脂粘合到复合芯的内表面上。 在另一个实施例中，容纳壳包括具有内表面的复合芯和包含至少一种陶瓷材料和至少一种非陶瓷材料的混合材料。 混合材料设置在复合芯的内表面上。 混合材料用树脂粘合到复合芯的内表面上。 一种制造容纳壳体的方法包括以下步骤：在复合芯的内表面上设置一层或多层陶瓷织物，将复合芯和一层或多层陶瓷织物注入树脂，并固化树脂。

公开(公告)号：US20080152853A1

公开(公告)日：2008-06-26

申请号：US11614439

申请日：2006-12-21

申请人： Lee Alan Blanton ,  Stephen Mark Whiteker ,  Matthew Bernard Buczek ,  Warren Ronk ,  Curt Brian Curtis ,  David Scott Miller

发明人： Lee Alan Blanton ,  Stephen Mark Whiteker ,  Matthew Bernard Buczek ,  Warren Ronk ,  Curt Brian Curtis ,  David Scott Miller

IPC分类号： B05D3/12 ,  B28B23/02

CPC分类号： B29C70/44 ,  Y10T428/1372

摘要： A method for fabricating a turbine engine composite containment casing is provided. The method comprising impregnating a plurality of fiber-reinforced layers with a resin to form a preform, heating the preform to a first temperature, applying a vacuum to the preform, varying an amount of pressure applied to the preform when the temperature reaches the first temperature, heating the preform from the first temperature to a second temperature at a first temperature rate, and heating the preform from the second temperature to a third temperature at a second temperature rate to facilitate curing of the preform.

摘要翻译： 提供一种制造涡轮发动机复合容纳壳体的方法。 所述方法包括用树脂浸渍多个纤维增强层以形成预制件，将预成型件加热到第一温度，向预成型件施加真空，当温度达到第一温度时改变施加到预成型件的压力量 ，以第一温度将预成型件从第一温度加热到第二温度，并以第二温度将预成型件从第二温度加热到第三温度，以便于预成型件的固化。

公开(公告)号：US20120312924A1

公开(公告)日：2012-12-13

申请号：US13590970

申请日：2012-08-21

申请人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

发明人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

IPC分类号： B64D15/00

CPC分类号： B64D15/00 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286 ,  F01D9/04 ,  F01D25/02 ,  F01D25/162 ,  F02C7/047 ,  F05D2300/50212

摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定了在操作期间适于面对空气流的前缘以及相对的内表面。 主体被分割成具有变化的热性能和/或机械不连续性的多个部分，以促进附着在流路表面上的冰中的应力集中。

公开(公告)号：US08245981B2

公开(公告)日：2012-08-21

申请号：US12112733

申请日：2008-04-30

申请人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

发明人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

IPC分类号： B64C21/00 ,  B64C1/38

CPC分类号： B64D15/00 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286 ,  F01D9/04 ,  F01D25/02 ,  F01D25/162 ,  F02C7/047 ,  F05D2300/50212

摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定了在操作期间适于面对空气流的前缘以及相对的内表面。 主体被分割成具有变化的热性能和/或机械不连续性的多个部分，以促进附着在流路表面上的冰中的应力集中。

公开(公告)号：US07992823B2

公开(公告)日：2011-08-09

申请号：US12112660

申请日：2008-04-30

申请人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

发明人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

IPC分类号： B64D15/00

CPC分类号： B64D15/00

摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface.

摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定在操作期间适于面对空气流的前缘; 以及包含施加到所述流路表面的至少一部分的镍的金属冰敷电镀。

公开(公告)号：US20090272095A1

公开(公告)日：2009-11-05

申请号：US12112660

申请日：2008-04-30

申请人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

发明人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

IPC分类号： F02C7/04

CPC分类号： B64D15/00

摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface.

摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定在操作期间适于面对空气流的前缘; 以及包含施加到所述流路表面的至少一部分的镍的金属冰敷电镀。

公开(公告)号：US20090272850A1

公开(公告)日：2009-11-05

申请号：US12112733

申请日：2008-04-30

申请人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

发明人： Edward Atwood Rainous ,  Barry Lynn Allmon ,  Jeffre Gerry Loewe ,  William Clarke Brooks ,  Lee Alan Blanton ,  Courtney James Tudor ,  Vicky Showalter Budinger

IPC分类号： B64D15/18 ,  F02G3/00

CPC分类号： B64D15/00 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/0286 ,  F01D9/04 ,  F01D25/02 ,  F01D25/162 ,  F02C7/047 ,  F05D2300/50212

摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定了在操作期间适于面对空气流的前缘以及相对的内表面。 主体被分割成具有变化的热性能和/或机械不连续性的多个部分，以促进附着在流路表面上的冰中的应力集中。

公开(公告)号：US07332049B2

公开(公告)日：2008-02-19

申请号：US11021804

申请日：2004-12-22

申请人： Lee Alan Blanton ,  Gregory Joseph Meibers ,  Robert Paul Fairbanks ,  Stephen Mark Whiteker ,  Richard Thomas Price ,  Matthew Bernard Buczek ,  Warren Rosal Ronk

发明人： Lee Alan Blanton ,  Gregory Joseph Meibers ,  Robert Paul Fairbanks ,  Stephen Mark Whiteker ,  Richard Thomas Price ,  Matthew Bernard Buczek ,  Warren Rosal Ronk

IPC分类号： B32B37/00 ,  B22D19/00

CPC分类号： B29C70/546 ,  B29C70/44 ,  B29C70/465 ,  B29L2031/7504 ,  F01D21/045 ,  F05D2300/614 ,  F05D2300/702 ,  Y02T50/672 ,  Y10T428/249928 ,  Y10T428/249933 ,  Y10T428/24994 ,  Y10T428/249944

摘要： A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution.

摘要翻译： 一种用于制造增强基质复合材料的方法，包括提供具有纤维结构的复合预型件并将基体材料施加到预制件上的预型件沿着预制件的位置的步骤。 将阻挡材料施加到涂覆预型件的至少一部分以将基体材料流引导到预成型件中。 将复合预制件加热到足以使基质材料粘稠并且不足以固化基质材料的温度。 对复合预制件内部的压力降低，同时对阻挡材料的压力增加。 保持温度以使基质材料流入复合预制件并迫使来自纤维结构的气体。 然后将复合预成型件固化并冷却以形成具有低空隙含量和基本均匀的基体分布的增强基质复合材料。

公开(公告)号：US07867566B2

公开(公告)日：2011-01-11

申请号：US11925331

申请日：2007-10-26

申请人： Lee Alan Blanton ,  Gregory Joseph Meibers ,  Robert Paul Fairbanks ,  Stephen Mark Whiteker ,  Richard Thomas Price ,  Matthew Bernard Buczek ,  Warren Rosal Ronk

发明人： Lee Alan Blanton ,  Gregory Joseph Meibers ,  Robert Paul Fairbanks ,  Stephen Mark Whiteker ,  Richard Thomas Price ,  Matthew Bernard Buczek ,  Warren Rosal Ronk

IPC分类号： B05D3/00 ,  B05D3/12

CPC分类号： B29C70/546 ,  B29C70/44 ,  B29C70/465 ,  B29L2031/7504 ,  F01D21/045 ,  F05D2300/614 ,  F05D2300/702 ,  Y02T50/672 ,  Y10T428/249928 ,  Y10T428/249933 ,  Y10T428/24994 ,  Y10T428/249944

摘要： A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution.

摘要翻译： 一种用于制造增强基质复合材料的方法，包括提供具有纤维结构的复合预型件并将基体材料施加到预制件上的预型件沿着预制件的位置的步骤。 将阻挡材料施加到涂覆预型件的至少一部分以将基体材料流引导到预成型件中。 将复合预制件加热到足以使基质材料粘稠并且不足以固化基质材料的温度。 对复合预制件内部的压力降低，同时对阻挡材料的压力增加。 保持温度以使基质材料流入复合预制件并迫使来自纤维结构的气体。 然后将复合预成型件固化并冷却以形成具有低空隙含量和基本均匀的基体分布的增强基质复合材料。