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公开(公告)号：US6149380A
公开(公告)日：2000-11-21
申请号：US244132
申请日：1999-02-04
CPC分类号： F01D21/045 , F05D2200/13 , F05D2250/60
摘要： The invention provides a novel hardwall fan case for encasing the radial periphery of a forward fan in a gas turbine engine. The fan case includes a rigid annular fan case shell spaced a selected radial distance from the tips of the fan blades, thus defining an annular internal air path surface of the fan case. The shell has a rigid hardwall fore section generally parallel to the blade tips and coated with a fore layer of abradable material. The fore section serves as a hardwall to limit the radial movement of fan blades deflecting under bird strike conditions and thereby to control the erosion of fan case linings. Limiting the radial blade deflection thus maintains the resulting fan tip clearance within acceptable limits. Uncontrolled or excessive erosion of fan case linings during bird strike conditions has in the past led to potentially catastrophic engine surge conditions where highly aerodynamically loaded fans are used that are very sensitive to enlarged tip clearances. The aft section of the rigid shell is radially spaced from the fore section thus defining a recess between the aft section of the rigid shell and the air path surface. The recess houses compressible material that absorbs the impact of the broken blade fragment propelled radially, and can retain the fragment in certain conditions. However, the rigid shell includes a novel rigid bumper between the fore and aft sections. The bumper has a rigid rear edge disposed an offset distance forwardly of the fan blade centers of gravity. When a broken blade fragment is propelled radially under centrifugal force, the fragment strikes the bumper edge. The blade fragment is rotated about the bumper edge under a force moment equal to the centrifugal force multiplied by the offset distance. As a result, the blade fragment is redirected from a radial trajectory and is rotated rearwardly to be ejected axially through the gaspath, or alternatively is retained within the compressible material housed in the rigid shell. Both the rigid hardwall fore section and the aft compressible material are preferably covered with a relatively thin layer of abradable material that allows the rotating fan blades on initial operation to achieve close tip tolerance with the hardwall fan case.
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公开(公告)号：US20080086880A1
公开(公告)日：2008-04-17
申请号：US11537884
申请日：2006-10-02
申请人： Barry Barnett , Steven Hunt , Czeslaw Wojtyczka
发明人： Barry Barnett , Steven Hunt , Czeslaw Wojtyczka
IPC分类号： B23P15/04
CPC分类号： F01D25/24 , F05D2230/232 , F05D2230/26 , F05D2240/14 , F05D2250/231 , F05D2250/232 , Y02T50/671 , Y10T29/4932
摘要： The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform.
摘要翻译： 该方法用于从预制件制造环形燃气涡轮发动机壳体。 该方法包括流动成形预成型件的至少一个部分，然后向外弯曲该部件的至少一部分。
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公开(公告)号：US08202041B2
公开(公告)日：2012-06-19
申请号：US12262583
申请日：2008-10-31
申请人： Czeslaw Wojtyczka , Andrew Marshall
发明人： Czeslaw Wojtyczka , Andrew Marshall
IPC分类号： F01D29/66
CPC分类号： F04D29/526 , F04D29/023 , F04D29/664 , F05D2300/6012 , F05D2300/614
摘要： A gas turbine engine rotor containment structure comprises an inner structurally supporting case having an inner surface positioned adjacent to a gas turbine engine rotor component to be contained. A layer of acoustic material is wrapped around and bounded to a radially outer surface of the inner case. A thin walled outer ring is bounded to a radially outer surface the layer of acoustic material. A layer of fibrous containment material surrounds a radially outer surface of the outer ring.
摘要翻译： 燃气涡轮发动机转子容纳结构包括内结构支撑壳体，其具有邻近要包含的燃气涡轮发动机转子部件定位的内表面。 一层声学材料缠绕并限定在内壳的径向外表面上。 薄壁外环与声学材料层的径向外表面相连。 纤维状容纳材料层围绕外圈的径向外表面。
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公开(公告)号：US20110286839A1
公开(公告)日：2011-11-24
申请号：US12783937
申请日：2010-05-20
申请人： Czeslaw Wojtyczka , Andrew Marshall
发明人： Czeslaw Wojtyczka , Andrew Marshall
IPC分类号： F01D11/08
CPC分类号： F01D21/045 , F01D11/122 , F01D11/127 , F04D29/526 , F05D2260/96
摘要： A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer wall surrounding the insulating material and concentric to the inner wall and at least two annular rub elements extending radially inwardly from the outer wall through only part of a radial thickness of the layer of insulating material, at least two of the rub elements being in axial alignment with the blade tips at every point around a circumference of the fan, each rub element having a radially inner end spaced apart from the inner wall and made of a material harder than that of the blades, and a containment fabric layer wrapped around a support structure of the outer wall.
摘要翻译： 一种涡轮风扇发动机，其包括围绕所述风扇叶片的尖端的环形内壁，围绕所述内壁的绝缘材料层，以及外壳，所述外壳包括围绕所述绝缘材料并与所述内壁同心的环形外壁和至少两个环形摩擦 元件从外壁径向向内延伸穿过绝缘材料层的径向厚度的一部分，至少两个摩擦元件在风扇圆周周围的每个点处与叶片尖端轴向对准，每个摩擦元件 具有与所述内壁间隔开并由比所述叶片更硬的材料制成的径向内端，以及围绕所述外壁的支撑结构缠绕的容纳织物层。
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公开(公告)号：US06652222B1
公开(公告)日：2003-11-25
申请号：US10200460
申请日：2002-09-03
申请人： Czeslaw Wojtyczka , Samy Amin
发明人： Czeslaw Wojtyczka , Samy Amin
IPC分类号： F01D2100
CPC分类号： F01D21/045 , B32B3/12 , B32B5/18 , F05D2220/326 , F05D2220/327 , F05D2300/433 , F05D2300/601 , F05D2300/612 , F05D2300/614
摘要： A fan blade fragment containment assembly for a gas turbine engine having a fan case surrounding the fan and having a circumferential axially extending blade fragment impact zone. An inner relatively slack or low tension deformable layer of Kevlar™ or Zylon™ fabric is mounted to the fan case outer surface and envelopes the impact zone. A compressible (ex. metal foam or honeycomb) layer is mounted on an outer surface of the deformable layer. A friction reduction layer of Teflon™ is mounted on an outer surface of the compressible layer and an outer relatively taut higher tension containment layer of Kevlar™ or Zylon™ fabric is mounted on an outer surface of the friction reduction layer. The friction reduction layer enhances the distribution of impact forces about the circumference of the compressible layer by reducing local shear stresses between the compressible layer and the containment layer.
摘要翻译： 一种用于燃气涡轮发动机的风扇叶片碎片容纳组件，其具有围绕所述风扇且具有周向轴向延伸的叶片碎片冲击区的风扇壳体。 Kevlar TM或Zylon TM织物的内部相对松弛或低张力可变形层被安装到风扇壳体外表面并且包围冲击区域。 可压缩（例如金属泡沫或蜂窝）层安装在可变形层的外表面上。 Teflon TM的摩擦减小层安装在可压缩层的外表面上，Kevlar TM或Zylon TM织物的外部较紧张的较高张力的容纳层安装在摩擦减小层的外表面上 。 摩擦减小层通过减小可压缩层和容纳层之间的局部剪切应力来增强围绕可压缩层的圆周的冲击力的分布。
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公开(公告)号：US20100111675A1
公开(公告)日：2010-05-06
申请号：US12262583
申请日：2008-10-31
申请人： Czeslaw Wojtyczka , Andrew Marshall
发明人： Czeslaw Wojtyczka , Andrew Marshall
CPC分类号： F04D29/526 , F04D29/023 , F04D29/664 , F05D2300/6012 , F05D2300/614
摘要： A gas turbine engine rotor containment structure comprises an inner structurally supporting case having an inner surface positioned adjacent to a gas turbine engine rotor component to be contained. A layer of acoustic material is wrapped around and bounded to a radially outer surface of the inner case. A thin walled outer ring is bounded to a radially outer surface the layer of acoustic material. A layer of fibrous containment material surrounds a radially outer surface of the outer ring.
摘要翻译： 燃气涡轮发动机转子容纳结构包括内结构支撑壳体，其具有邻近要包含的燃气涡轮发动机转子部件定位的内表面。 一层声学材料缠绕并限定在内壳的径向外表面上。 薄壁外环与声学材料层的径向外表面相连。 纤维状容纳材料层围绕外圈的径向外表面。
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公开(公告)号：US08500390B2
公开(公告)日：2013-08-06
申请号：US12783937
申请日：2010-05-20
申请人： Czeslaw Wojtyczka , Andrew Marshall
发明人： Czeslaw Wojtyczka , Andrew Marshall
CPC分类号： F01D21/045 , F01D11/122 , F01D11/127 , F04D29/526 , F05D2260/96
摘要： A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer wall surrounding the insulating material and concentric to the inner wall and at least two annular rub elements extending radially inwardly from the outer wall through only part of a radial thickness of the layer of insulating material, at least two of the rub elements being in axial alignment with the blade tips at every point around a circumference of the fan, each rub element having a radially inner end spaced apart from the inner wall and made of a material harder than that of the blades, and a containment fabric layer wrapped around a support structure of the outer wall.
摘要翻译： 一种涡轮风扇发动机，其包括围绕所述风扇叶片的尖端的环形内壁，围绕所述内壁的绝缘材料层，以及外壳，所述外壳包括围绕所述绝缘材料并与所述内壁同心的环形外壁和至少两个环形摩擦 元件从外壁径向向内延伸穿过绝缘材料层的径向厚度的一部分，至少两个摩擦元件在风扇圆周周围的每个点处与叶片尖端轴向对准，每个摩擦元件 具有与所述内壁间隔开并由比所述叶片更硬的材料制成的径向内端，以及围绕所述外壁的支撑结构缠绕的容纳织物层。
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公开(公告)号：US08397383B2
公开(公告)日：2013-03-19
申请号：US11537884
申请日：2006-10-02
申请人： Barry Barnett , Steven Hunt , Czeslaw Wojtyczka
发明人： Barry Barnett , Steven Hunt , Czeslaw Wojtyczka
IPC分类号： B21K25/00
CPC分类号： F01D25/24 , F05D2230/232 , F05D2230/26 , F05D2240/14 , F05D2250/231 , F05D2250/232 , Y02T50/671 , Y10T29/4932
摘要： The method is used for making an annular gas turbine engine case from a preform. The method comprises comprising flowforming at least one section of the preform, and then outwardly bending at least one portion of the perform.
摘要翻译： 该方法用于从预成型件制造环形燃气涡轮发动机壳体。 该方法包括流动成形预成型件的至少一个部分，然后向外弯曲该部件的至少一部分。
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公开(公告)号：US20080086881A1
公开(公告)日：2008-04-17
申请号：US11537890
申请日：2006-10-02
申请人： Andreas Eleftheriou , Steven Bokan , Barry Barnett , Steven Hunt , Czeslaw Wojtyczka , John Paterson
发明人： Andreas Eleftheriou , Steven Bokan , Barry Barnett , Steven Hunt , Czeslaw Wojtyczka , John Paterson
IPC分类号： B23P15/04
CPC分类号： F01D25/24 , F01D21/045 , F05D2230/20 , F05D2230/26 , F05D2230/50 , F05D2240/14 , Y02T50/671 , Y10T29/4932
摘要： The method is used for making an annular gas turbine engine case, the method comprises flowforming a first area of the preform to provide a first annular case portion having a first thickness and a second area having a second thickness, the first and the second average thickness being different.
摘要翻译： 该方法用于制造环形燃气涡轮发动机壳体，该方法包括流动成形预成型件的第一区域以提供具有第一厚度的第一环形壳体部分和具有第二厚度的第二区域，第一和第二平均厚度 不同
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公开(公告)号：US06227794B1
公开(公告)日：2001-05-08
申请号：US09466001
申请日：1999-12-16
IPC分类号： F01D2100
CPC分类号： F01D11/122 , F01D21/045 , F05B2260/3011 , F05D2220/327 , F05D2240/14 , F05D2250/232 , F05D2300/501
摘要： There is provided a hardwall fan case for encasing a forward fan in a gas turbine engine. The fan case has a stiff annular shell spaced radially outward from the tips of the fan blades and a flexible ring which is an integral structural part of the shell. The flexible ring has a frusto-conical shape with a lip adjacent to the blade trailing edge. The ring extends axially rearwardly from the fixed root to the free inner edge forming a cantilevering resilient ring. A hollow cavity defined between an inner surface of the shell and an outer surface of the flexible ring provides clearance for the flexible ring to deform radially outwardly on impact with a released blade, or to elastically flex on contact with the trailing edge blade tip during bird strike events.
摘要翻译： 提供了用于在燃气涡轮发动机中封装前风扇的硬壁风扇壳。 风扇壳体具有从风扇叶片的尖端径向向外间隔开的刚性环形壳体和作为壳体的整体结构部分的柔性环。 柔性环具有截头圆锥形状，其具有与叶片后缘相邻的唇缘。 环从固定根部轴向向后延伸到形成悬臂弹性环的自由内边缘。 限定在外壳的内表面和柔性环的外表面之间的中空腔提供了间隙，以使柔性环在与释放的刀片碰撞时径向向外变形，或者在鸟期间与后缘刀片尖端弹性弯曲 罢工事件。
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