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公开(公告)号：US20100077832A1
公开(公告)日：2010-04-01
申请号：US12585201
申请日：2009-09-08
CPC分类号： F42B12/745 , F42B12/34 , G01M7/08 , Y10T428/249994 , Y10T428/249995
摘要： An artificial bird projectile is provided for simulating bird strike events. The projectile has a solid foam phase and a gel or liquid phase. The gel or liquid phase is supported by the foam phase. The projectile may be suitable for simulating bird strike events on aero gas turbine engines.
摘要翻译： 提供一种人造鸟类弹药，用于模拟罢工事件。 抛射体具有固体泡沫相和凝胶或液相。 凝胶或液相由泡沫相支撑。 射弹可能适用于模拟航空燃气涡轮发动机上的罢工事件。
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公开(公告)号：US20100028130A1
公开(公告)日：2010-02-04
申请号：US12457748
申请日：2009-06-19
申请人： Julian M. Reed
发明人： Julian M. Reed
IPC分类号： F01D25/24
CPC分类号： F01D21/045 , F01D11/122 , F01D11/127 , F01D25/24 , F04D27/0292 , F04D29/023 , F04D29/526 , F05D2220/36 , F05D2240/303 , F05D2260/96
摘要： A fan casing for a gas turbine engine has a fan track radially outward of the fan blades, and the fan track has sufficient strength and stiffness that, if a blade is released, it is broken up and deflected by the fan track rather than passing through to a containment system as in known arrangements. Optionally, a weakened region in the fan track may be provided, so that the leading edge portion of the blade will penetrate the fan track and be contained within the fan casing. This is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap.
摘要翻译： 用于燃气涡轮发动机的风扇壳体具有风扇叶片径向向外的风扇轨道，并且风扇轨道具有足够的强度和刚度，如果叶片被释放，则其被风扇轨道分解和偏转，而不是通过 到已知安排的遏制系统。 可选地，可以设置风扇轨道中的弱化区域，使得叶片的前缘部分将穿过风扇轨道并容纳在风扇壳体内。 这特别适合于风扇叶片，其中前缘区域的刚度和抗压强度显着高于叶片的其余部分; 例如，具有金属前缘帽的中空金属风扇叶片或复合风扇叶片。
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公开(公告)号：US08434995B2
公开(公告)日：2013-05-07
申请号：US12768316
申请日：2010-04-27
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , F01D5/16 , F01D25/06
摘要： A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section.
摘要翻译： 燃气涡轮发动机风扇壳体管道壁包括分别设置有凸缘的进气部分和容纳壳体。 声波阻尼器固定在凸缘之间。 声波阻尼器具有容纳内部结构的皮肤，其阻尼风扇叶片的颤动。 皮肤在不同的位置固定在法兰上。 在发动机的正常操作中，内部结构足够坚固以支撑通过吸气部分和容纳壳体之间的声波阻尼器传递的载荷。 如果叶片或叶片碎片分离，则容纳壳体中产生的偏转波使内部结构破裂，并且进气部分和收容壳体之间的载荷路径沿着皮肤通过，从而保持进气管道与容纳物之间的连接 同时允许容纳壳体相对于进气部分的大量径向偏转。
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公开(公告)号：US08297912B2
公开(公告)日：2012-10-30
申请号：US12457748
申请日：2009-06-19
申请人： Julian M. Reed
发明人： Julian M. Reed
IPC分类号： F01D25/24
CPC分类号： F01D21/045 , F01D11/122 , F01D11/127 , F01D25/24 , F04D27/0292 , F04D29/023 , F04D29/526 , F05D2220/36 , F05D2240/303 , F05D2260/96
摘要： A fan casing for a gas turbine engine has a fan track radially outward of the fan blades, and the fan track has sufficient strength and stiffness that, if a blade is released, it is broken up and deflected by the fan track rather than passing through to a containment system as in known arrangements. Optionally, a weakened region in the fan track may be provided, so that the leading edge portion of the blade will penetrate the fan track and be contained within the fan casing. This is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap.
摘要翻译： 用于燃气涡轮发动机的风扇壳体具有风扇叶片径向向外的风扇轨道，并且风扇轨道具有足够的强度和刚度，如果叶片被释放，则其被风扇轨道分解和偏转，而不是通过 到已知安排的遏制系统。 可选地，可以设置风扇轨道中的弱化区域，使得叶片的前缘部分将穿过风扇轨道并容纳在风扇壳体内。 这特别适合于风扇叶片，其中前缘区域的刚度和抗压强度显着高于叶片的其余部分; 例如，具有金属前缘帽的中空金属风扇叶片或复合风扇叶片。
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公开(公告)号：US08926263B2
公开(公告)日：2015-01-06
申请号：US13358080
申请日：2012-01-25
申请人： Julian M. Reed , Cedric B. Harper
发明人： Julian M. Reed , Cedric B. Harper
CPC分类号： F01D25/24 , F01D21/045 , F01D25/243 , F02K3/06 , F05D2250/283 , Y02T50/672
摘要： A turbomachine casing assembly including: a first casing element arrangeable adjacent to one or more rotating aerofoil structures of a turbomachine; a second casing element provided at a radially outer position with respect to the first casing element; and an infill member disposed between the first and second casing elements, wherein an end of the infill member is set back from an end of the first casing element such that a void is provided between the first and second casing elements.
摘要翻译： 一种涡轮机壳体组件，包括：第一壳体元件，其可布置成与涡轮机的一个或多个旋转机翼结构相邻; 第二壳体元件，设置在相对于所述第一壳体元件的径向外部位置; 以及设置在所述第一和第二壳体元件之间的填充构件，其中所述填充构件的端部从所述第一壳体元件的端部回缩，使得在所述第一和第二壳体元件之间设置空隙。
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公开(公告)号：US08231328B2
公开(公告)日：2012-07-31
申请号：US12457691
申请日：2009-06-18
申请人： Julian M. Reed
发明人： Julian M. Reed
IPC分类号： F01D25/24
CPC分类号： F01D21/045 , F01D25/24 , F04D27/0292 , F04D29/023 , F04D29/526 , F05D2240/121 , F05D2240/303 , F05D2250/283
摘要： A fan casing for a gas turbine engine has a fan track liner extending only over an upstream part of the fan blades, and the local stiffness and internal shape of the casing are arranged to promote the break-up of a released fan blade while permitting the leading edge region of the blade to pass through the fan track liner and be contained by the fan casing. This arrangement is particularly suitable for fan blades in which the stiffness and compressive strength are significantly higher in the leading edge region than in the remainder of the blade; for example, hollow metal fan blades or composite fan blades having a metal leading edge cap.
摘要翻译： 用于燃气涡轮发动机的风扇壳体具有仅在风扇叶片的上游部分上延伸的风扇轨道衬套，并且壳体的局部刚度和内部形状被布置成促进释放的风扇叶片的分解，同时允许 叶片的前缘区域通过风扇轨道衬垫并被风扇壳体容纳。 这种布置特别适合于风扇叶片，其中前缘区域的刚度和抗压强度显着高于叶片的其余部分; 例如，具有金属前缘帽的中空金属风扇叶片或复合风扇叶片。
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公开(公告)号：US09133731B2
公开(公告)日：2015-09-15
申请号：US13368712
申请日：2012-02-08
申请人： Julian M. Reed
发明人： Julian M. Reed
CPC分类号： F01D25/243 , F01D21/04 , F01D21/045 , F01D25/24 , F01D25/246 , F02C7/05 , F05D2260/38 , F16B5/0241 , F16B39/24 , F16B2200/506
摘要： A joint assembly for securing flanges of two casings comprising a plurality of bolts, a plurality of collars and a plurality of nuts. Each bolt extends through an aperture in the first flange and an aperture in the second flange, each collar being arranged around a shank of a respective bolt and each nut being secured on a respective one of the bolts. Each collar being arranged between one of the flanges and a nut or a head of a bolt. Each collar comprises a first member and a second member, the second member being arranged at a first end of the first member. The second member being substantially U-shaped in cross-section, the second member having first and second radially inner ends and a radially outer mid portion and an axial space is defined between the first radially inner end and the second radially inner end of the second member.
摘要翻译： 一种用于固定两个壳体的凸缘的接头组件，包括多个螺栓，多个凸环和多个螺母。 每个螺栓延伸穿过第一凸缘中的孔和第二凸缘中的孔，每个凸缘围绕相应螺栓的柄设置，并且每个螺母固定在相应的一个螺栓上。 每个凸缘布置在其中一个凸缘和螺母或螺栓的头部之间。 每个衣领包括第一构件和第二构件，第二构件布置在第一构件的第一端。 所述第二构件的横截面基本上为U形，所述第二构件具有第一和第二径向内端以及径向外部中间部分，并且轴向空间限定在所述第二构件的第二径向内端和第二径向内端之间 会员。
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公开(公告)号：US20110178780A1
公开(公告)日：2011-07-21
申请号：US12382936
申请日：2009-03-26
IPC分类号： G06F17/10
CPC分类号： F01D21/003 , G01M7/08 , Y02T50/671
摘要： The fragmentation of a bird or similar soft body, following its impact on an angled target plate, is modelled by representing the body as a combination of fragments and slurry, their relative proportions depending on the severity and angle of impact. The method is particularly suitable for modelling the behaviour of a bird striking an obscuring intake of a gas turbine engine.
摘要翻译： 通过将身体作为碎片和浆料的组合表示，其对相对比例取决于严重性和冲击角度，来对其对成角度目标板的影响的鸟类或类似软体的碎裂进行建模。 该方法特别适用于对打入燃气涡轮发动机的模糊入口的鸟的行为进行建模。
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公开(公告)号：US20100284790A1
公开(公告)日：2010-11-11
申请号：US12768316
申请日：2010-04-27
IPC分类号： F04D29/66
CPC分类号： F01D21/045 , F01D5/16 , F01D25/06
摘要： A gas turbine engine fan casing duct wall comprises an intake section and a containment casing, provided respectively with flanges. An acoustic flutter damper is secured between the flanges. The acoustic flutter damper has a skin accommodating an internal structure that dampens fan blade flutter. The skin is secured to the flanges at separate locations. In normal operation of the engine, the internal structure is sufficiently robust to support loads transmitted through the acoustic flutter damper between the intake section and the containment casing. If a blade or blade fragment detaches, the resulting deflection wave in the containment case ruptures the internal structure, and the load path between the intake section and the containment casing passes along the skin, which consequently maintains the connection between the intake duct and the containment casing, while permitting substantial radial deflection of the containment casing relative to the intake section.
摘要翻译： 燃气涡轮发动机风扇壳体管道壁包括分别设置有凸缘的进气部分和容纳壳体。 声波阻尼器固定在凸缘之间。 声波阻尼器具有容纳内部结构的皮肤，其阻尼风扇叶片的颤动。 皮肤在不同的位置固定在法兰上。 在发动机的正常操作中，内部结构足够坚固以支撑通过吸气部分和容纳壳体之间的声波阻尼器传递的载荷。 如果叶片或叶片碎片分离，则容纳壳体中产生的偏转波使内部结构破裂，并且进气部分和收容壳体之间的载荷路径沿着皮肤通过，从而保持进气管道与容纳物之间的连接 同时允许容纳壳体相对于进气部分的大量径向偏转。
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