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公开(公告)号：US20110146230A1
公开(公告)日：2011-06-23
申请号：US12827801
申请日：2010-06-30
申请人： Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
发明人： Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
摘要： An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.
摘要翻译： 组件包括单一的机舱结构和用于燃气涡轮发动机组件的集成风扇壳体。 整体式机舱结构包括入口区域和风扇整流罩区域，并且被配置为至少部分地围绕集成风扇壳体。 集成风扇壳体包括整体复合结构，并且包括风扇壳体，其尺寸和构造用于环绕相关联的燃气涡轮发动机，风扇轮毂和多个风扇出口导叶的风扇叶片组件。 整体式机舱结构与集成的风扇壳体配合，将静态和动态载荷直接传递到支撑结构，而不是通过发动机芯，以最大限度地减少主干弯曲。
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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。
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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
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。
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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。
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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。
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公开(公告)号：US06773228B2
公开(公告)日：2004-08-10
申请号：US10188438
申请日：2002-07-03
申请人： Edward Atwood Rainous , Charles Louis Williams , Michael Peter Murphy , Janice Ilene Pirtle , James Harold Joy
发明人： Edward Atwood Rainous , Charles Louis Williams , Michael Peter Murphy , Janice Ilene Pirtle , James Harold Joy
IPC分类号： F01D904
CPC分类号： F01D9/042 , Y10T29/49323
摘要： A method enables a gas turbine engine nozzle to be secured within an engine casing that includes an exterior surface. The method comprises the steps of forming a first opening to extend through the engine casing, inserting a nozzle lock through the first opening from the casing exterior surface, coupling the nozzle lock to a portion of the nozzle, and securing the nozzle lock to the engine casing.
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公开(公告)号：US08876042B2
公开(公告)日：2014-11-04
申请号：US12827801
申请日：2010-06-30
申请人： Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
发明人： Donald George LaChapelle , Christopher Charles Glynn , Donald Lee Gardner , Stephen Craig Mitchell , Mullahalli Venkataramaniah Srinivas , Edward Atwood Rainous , David Lance Pennekamp
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264 , B64D2027/266 , B64D2027/268
摘要： An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending.
摘要翻译： 组件包括单一的机舱结构和用于燃气涡轮发动机组件的集成风扇壳体。 整体式机舱结构包括入口区域和风扇整流罩区域，并且被配置为至少部分地围绕集成风扇壳体。 集成风扇壳体包括整体复合结构，并且包括风扇壳体，其尺寸和构造用于环绕相关联的燃气涡轮发动机，风扇轮毂和多个风扇出口导叶的风扇叶片组件。 整体式机舱结构与集成的风扇壳体配合，将静态和动态载荷直接传递到支撑结构，而不是通过发动机芯，以最大程度减少主干弯曲。
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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。
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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
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。
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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
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。
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