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公开(公告)号：US20110318181A1
公开(公告)日：2011-12-29
申请号：US13226641
申请日：2011-09-07
申请人： Simon Read , Alison J. McMillan , Eric Ravey
发明人： Simon Read , Alison J. McMillan , Eric Ravey
IPC分类号： F01D5/18
CPC分类号： F01D25/02 , F01D5/26 , F04D29/023 , F04D29/324 , F05D2230/90 , F05D2300/43 , F05D2300/505 , F05D2300/507 , F05D2300/611 , Y02T50/672 , Y02T50/673
摘要： Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in the aerofoils (22). The viscoelastic material (34, 44) damps this vibration, and in so doing generates heat, which melts the ice away from the aerofoils (22). Heat-conducting members conduct the heat to regions of the component in which ice accretion is to be prevented. Alternative embodiments are described in which the pseudoelastic behaviour of a shape memory alloy (56), or eddy currents arising from the rotor blades' rotation in an axisymmetric magnetic field, are used as sources of heat.
摘要翻译： 燃气涡轮发动机的机翼（22）设置有粘弹性材料的涂层（34）或填料（44）。 由于在运行过程中机翼（22）上积冰，所产生的空气动力学稳定性失衡会引起机翼中的振动（22）。 粘弹性材料（34,44）阻止该振动，并且在这样做时产生热量，其将冰从机翼（22）熔化。 导热构件将热量传导到要防止积冰的部件的区域。 描述了替代实施例，其中形状记忆合金（56）的伪弹性行为或由轴对称磁场中的转子叶片旋转产生的涡流被用作热源。
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公开(公告)号：US08435003B2
公开(公告)日：2013-05-07
申请号：US13226641
申请日：2011-09-07
申请人： Simon Read , Alison J. McMillan , Eric Ravey
发明人： Simon Read , Alison J. McMillan , Eric Ravey
CPC分类号： F01D25/02 , F01D5/26 , F04D29/023 , F04D29/324 , F05D2230/90 , F05D2300/43 , F05D2300/505 , F05D2300/507 , F05D2300/611 , Y02T50/672 , Y02T50/673
摘要： Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in the aerofoils (22). The viscoelastic material (34, 44) damps this vibration, and in so doing generates heat, which melts the ice away from the aerofoils (22). Heat-conducting members conduct the heat to regions of the component in which ice accretion is to be prevented. Alternative embodiments are described in which the pseudoelastic behavior of a shape memory alloy (56), or eddy currents arising from the rotor blades' rotation in an axisymmetric magnetic field, are used as sources of heat.
摘要翻译： 燃气涡轮发动机的机翼（22）设置有粘弹性材料的涂层（34）或填料（44）。 由于在运行过程中机翼（22）上积冰，所产生的空气动力学稳定性失衡会引起机翼中的振动（22）。 粘弹性材料（34,44）阻止该振动，并且在这样做时产生热量，其将冰从机翼（22）熔化。 导热构件将热量传导到要防止积冰的部件的区域。 描述了替代实施例，其中形状记忆合金（56）的伪弹性行为或由轴对称磁场中的转子叶片旋转产生的涡流被用作热源。
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公开(公告)号：US08033789B2
公开(公告)日：2011-10-11
申请号：US11798552
申请日：2007-05-15
申请人： Simon Read , Alison J McMillan , Eric Ravey
发明人： Simon Read , Alison J McMillan , Eric Ravey
CPC分类号： F01D25/02 , F01D5/26 , F04D29/023 , F04D29/324 , F05D2230/90 , F05D2300/43 , F05D2300/505 , F05D2300/507 , F05D2300/611 , Y02T50/672 , Y02T50/673
摘要： Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in the aerofoils (22). The viscoelastic material (34, 44) damps this vibration, and in so doing generates heat, which melts the ice away from the aerofoils (22). Heat-conducting members conduct the heat to regions of the component in which ice accretion is to be prevented. Alternative embodiments are described in which the pseudoelastic behaviour of a shape memory alloy (56), or eddy currents arising from the rotor blades' rotation in an axisymmetric magnetic field, are used as sources of heat.
摘要翻译： 燃气涡轮发动机的机翼（22）设置有粘弹性材料的涂层（34）或填料（44）。 由于在运行过程中机翼（22）上积冰，所产生的空气动力学稳定性失衡会引起机翼中的振动（22）。 粘弹性材料（34,44）阻止该振动，并且在这样做时产生热量，其将冰从机翼（22）熔化。 导热构件将热量传导到要防止积冰的部件的区域。 描述了替代实施例，其中形状记忆合金（56）的伪弹性行为或由轴对称磁场中的转子叶片旋转产生的涡流被用作热源。
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公开(公告)号：US07329102B2
公开(公告)日：2008-02-12
申请号：US11252718
申请日：2005-10-19
申请人： Alison J. McMillan , Simon Read
发明人： Alison J. McMillan , Simon Read
CPC分类号： F01D5/18 , F01D5/147 , F05D2240/126 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y10S416/50
摘要： With regard to hollow blades for turbine engines, it will be understood there is a problem with respect to percussive impact resulting in excessive distortion of the blade as well as potential failure as a result of blade tip bulging. By provision of ridges 107, 207, 307 which coincide and engage each other under impact, the extent of impact deformation is limited as well as a result of the narrowing between the ridges, a reduction in the possibility for fragmentary insert movement to bulge the cavity towards the tip 102, 202, 302 of a blade 100, 200, 300.
摘要翻译： 关于用于涡轮发动机的中空叶片，应当理解，对于由于叶片尖端膨胀而导致叶片过度变形以及潜在故障的冲击冲击存在问题。 通过设置在冲击下相互重合并相互啮合的脊107,207,307，冲击变形的程度受到限制，并且由于脊之间的变窄而导致的部分插入运动的可能性降低，从而使空腔膨胀 朝向叶片100,200,300的尖端102,202,302。
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公开(公告)号：US20080075593A1
公开(公告)日：2008-03-27
申请号：US11798552
申请日：2007-05-15
申请人： Simon Read , Alison McMillan , Eric Ravey
发明人： Simon Read , Alison McMillan , Eric Ravey
IPC分类号： F01D5/18
CPC分类号： F01D25/02 , F01D5/26 , F04D29/023 , F04D29/324 , F05D2230/90 , F05D2300/43 , F05D2300/505 , F05D2300/507 , F05D2300/611 , Y02T50/672 , Y02T50/673
摘要： Aerofoils (22) of a gas turbine engine are provided with a coating (34) or filler (44) of viscoelastic material. As ice accretes on the aerofoils (22) during operation, the resulting aerodynamic stability imbalance induces vibration in the aerofoils (22). The viscoelastic material (34, 44) damps this vibration, and in so doing generates heat, which melts the ice away from the aerofoils (22). Heat-conducting members conduct the heat to regions of the component in which ice accretion is to be prevented. Alternative embodiments are described in which the pseudoelastic behaviour of a shape memory alloy (56), or eddy currents arising from the rotor blades' rotation in an axisymmetric magnetic field, are used as sources of heat.
摘要翻译： 燃气涡轮发动机的机翼（22）设置有粘弹性材料的涂层（34）或填料（44）。 由于在运行过程中机翼（22）上积冰，所产生的空气动力学稳定性失衡会引起机翼中的振动（22）。 粘弹性材料（34,44）阻止该振动，并且在这样做时产生热量，其将冰从机翼（22）熔化。 导热构件将热量传导到要防止积冰的部件的区域。 描述了替代实施例，其中形状记忆合金（56）的伪弹性行为或由轴对称磁场中的转子叶片旋转产生的涡流被用作热源。
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公开(公告)号：US08430623B2
公开(公告)日：2013-04-30
申请号：US12547573
申请日：2009-08-26
IPC分类号： F01D5/30
CPC分类号： F01D5/147 , F01D5/14 , F01D21/045 , F05D2300/612
摘要： A fan blade for a gas turbine engine has an aerofoil part and a root part. The root part includes a root former; the root former 18 includes a zone of weakness, which reduces the ability of the root part to withstand an impact force. Thus, in an impact situation in which the fan blade has separated from the fan rotor and the fan blade has itself separated into fragments, the root part will fracture or buckle more easily than would be the case with conventional arrangements. This will lower the impact force of the root part upon the fan casing, thus permitting the fan casing to be designed to withstand lower impact forces. The fan casing can therefore be made lighter, and cheaper, than in conventional arrangements.
摘要翻译： 用于燃气涡轮发动机的风扇叶片具有机翼部分和根部部分。 根部包括根部; 根部18包括弱点区域，这降低了根部部分承受冲击力的能力。 因此，在风扇叶片与风扇转子分离并且风扇叶片本身分离成碎片的冲击情况下，根部将比常规布置的情况更容易断裂或弯曲。 这将降低根部对风扇壳体的冲击力，从而允许风扇壳体设计成承受较低的冲击力。 因此，风扇壳体可以比常规布置更轻，更便宜。
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公开(公告)号：US08366378B2
公开(公告)日：2013-02-05
申请号：US12547644
申请日：2009-08-26
IPC分类号： F01D5/30
CPC分类号： F01D21/045 , F01D5/282 , F01D5/34 , F04D29/321 , F04D29/324 , Y02T50/672
摘要： Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by these rings, drums or disks can fragment and it is necessary to contain such fragments within a casing. Impact energy has a significant effect upon the necessary thickness of the casing to ensure containment. By providing blades as well as rotor elements which incorporate discontinuities which provide flexing under impact, energy is absorbed prior to further fragmentation upon impact engagement with a casing surface; flexing is about the discontinuity. In such circumstances casings may be thinner and therefore significant weight savings achieved with regard to aircraft incorporating gas turbine engines having blade assemblies with discontinuities.
摘要翻译： 刀片组件以多种形式提供。 这些刀片组件可以具有固定到盘（叶片），环（bling）和鼓（blum）的刀片。 由这些环，鼓或盘形成的叶片和/或转子元件可能会碎裂，并且必须在壳体内容纳这种碎片。 冲击能对壳体的必要厚度有重要的影响，以确保密封。 通过提供叶片以及转子元件，其包括在冲击下提供弯曲的不连续性，在与壳体表面冲击接合之后，能量被进一步分解之前被吸收; 屈曲是关于不连续的。 在这种情况下，外壳可能更薄，因此对于具有具有具有不连续性的叶片组件的燃气涡轮发动机的飞机，实现了显着的重量节省。
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公开(公告)号：US20100040472A1
公开(公告)日：2010-02-18
申请号：US12461111
申请日：2009-07-31
IPC分类号： F01D5/22
CPC分类号： F01D11/008 , F01D5/3007 , F02K3/06 , F05D2240/80
摘要： An annulus filler (101) is provided for mounting to a rotor disc (102) of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc (102). The annulus filler (101) has an outer part (106) which defines an airflow surface for air being drawn through the engine, and a separate, support part (105) which is connectable to the outer part (106) and to the rotor disc (102) to support the outer part (106) on the lo rotor disc (102). The outer (106) and support parts (105) are configured to allow a procedure for mounting the annulus filler (101) to the rotor disc (102). In a first step the support part (105) is connected to the rotor disc (102) without the outer part (106), and in a subsequent second step the outer part (106) is connected to the support part (105).
摘要翻译： 提供了一种环形填料（101），用于安装到燃气涡轮发动机的转子盘（102）并用于桥接附接到转子盘（102）的两个相邻叶片之间的间隙。 环形填料（101）具有外部部分（106），其限定用于空气被引导通过发动机的气流表面，以及分开的支撑部分（105），其可连接到外部部分（106）和转子盘 （102）以支撑所述转子盘（102）上的外部部分（106）。 外部（106）和支撑部件（105）构造成允许将环形填料（101）安装到转子盘（102）上的过程。 在第一步骤中，支撑部分（105）没有外部部分（106）连接到转子盘（102），并且在随后的第二步骤中，外部部分（106）连接到支撑部分（105）。
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公开(公告)号：US07845207B2
公开(公告)日：2010-12-07
申请号：US12292108
申请日：2008-11-12
申请人： Simon Read
发明人： Simon Read
IPC分类号： G01N3/30
摘要： With regard to components it is necessary to test specimens of materials in order to determine acceptability for objective component performance. Previously such testing generally involved fixing and clamping of the test specimen which produced artificial stressing conditions. By providing a specimen component typically in the form of an elongate member which is suspended between mounting ends a combination is provided which has inertia. In such circumstances when a projectile impacts upon the elongate member that elongate member flexes and deforms and this deformation can be monitored for testing purposes. The projectile is arranged to have a relatively facile compliant nature upon impact with the component such that there is no local stressing of the component whilst suspending the mounting ends substantially avoids clamp resilience distorting objective or realistic stressing conditions.
摘要翻译： 关于部件，为了确定客观部件性能的可接受性，必须对材料样品进行测试。 以前，这种测试通常涉及产生人为应力条件的测试样品的固定和夹紧。 通过提供通常为细长构件形式的试样部件，悬挂在安装端之间，提供具有惯性的组合。 在这种情况下，当弹丸撞击细长构件时，细长构件弯曲并变形，并且该变形可以被监测用于测试目的。 抛射体被布置成在与部件碰撞时具有相对容易的顺应性，使得在悬挂安装端的情况下，部件的局部应力基本上避免了夹紧弹性变形的目标或现实的应力条件。
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公开(公告)号：US20090232657A1
公开(公告)日：2009-09-17
申请号：US12083095
申请日：2006-09-29
申请人： Simon Read , Peter R Beckford
发明人： Simon Read , Peter R Beckford
CPC分类号： F01D21/045 , B21D26/055 , F01D5/147 , F01D5/30 , F05D2230/236 , Y02T50/672 , Y10T29/49339
摘要： Reduction in weight is an important factor with respect to turbine engines used in aircraft. Blades (20) used in such turbine engines may fragment such that it is necessary that the containment casing (42) can resist such fragmentation. Root portions of blades are generally less deformable and therefore require conventionally more robust containment casings. Use of super plastically formed blades allows provision of slots (4, 14, 24, 46) in the root portion which facilitate fragmentation and deformation by the root portion under impact reducing the necessity for greater reinforcement of the containment casing. The slots (4, 14, 24, 24, 46) are created in a membrane utilised for web reinforcement of the blade rather than through intrusive drilling and cutting processes which may introduce machining stresses into their creation and potential tool loss within the high value blade. Additionally, by providing such slots (4, 14, 24, 46) it will be appreciated that the cavity formed within the blade may be sealed without additional machining or other processes.
摘要翻译： 相对于在飞行器中使用的涡轮发动机，减重是重要的因素。 在这种涡轮发动机中使用的叶片（20）可能会碎裂，使得密封壳体42必须抵抗这种破碎。 叶片的根部通常较不易变形，因此需要传统上更坚固的容纳壳体。 使用超级塑性叶片允许在根部中设置槽（4,14,24,46），这有助于在冲击下根部分裂和变形，从而减少了对密封壳体进行更大的加固的必要性。 狭槽（4,14,24,24,46）被形成在用于叶片的腹板加强件的膜中，而不是通过侵入式钻孔和切割过程，其可以将加工应力引入其创建中并且在高值刀片内潜在的刀具损失 。 另外，通过提供这种槽（4,14,24,46），应当理解，形成在叶片内的空腔可以在没有附加的加工或其它工艺的情况下被密封。
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