公开(公告)号：US08435003B2

公开(公告)日：2013-05-07

申请号：US13226641

申请日：2011-09-07

Applicant: Simon Read ,  Alison J. McMillan ,  Eric Ravey

Inventor： Simon Read ,  Alison J. McMillan ,  Eric Ravey

IPC: F01D5/16 ,  F01D5/18

CPC classification number: F01D25/02 ,  F01D5/26 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/90 ,  F05D2300/43 ,  F05D2300/505 ,  F05D2300/507 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20130029117A1

公开(公告)日：2013-01-31

申请号：US13546647

申请日：2012-07-11

Applicant: Simon READ ,  Bijoysri KHAN

Inventor： Simon READ ,  Bijoysri KHAN

IPC: B32B7/02 ,  B32B37/06

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/28 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T428/24942

Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibres, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater than that of the resin impregnating the plies in the structural core.

Abstract translation: 复合机翼，具有前缘的机翼，后缘，压力侧和吸力侧，并且包括沿着压力侧或吸入侧的一个或两个的外部侵蚀保护层，具有多个树脂浸渍层的结构芯 的单向纤维，并且在外部侵蚀保护层和结构芯之间，浸渍有树脂的织造复合材料的弹性模量大于在结构芯中浸渍层的树脂的弹性模量。

公开(公告)号：US08033789B2

公开(公告)日：2011-10-11

申请号：US11798552

申请日：2007-05-15

Applicant: Simon Read ,  Alison J McMillan ,  Eric Ravey

Inventor： Simon Read ,  Alison J McMillan ,  Eric Ravey

IPC: F01D5/16 ,  F01D5/18

CPC classification number: F01D25/02 ,  F01D5/26 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/90 ,  F05D2300/43 ,  F05D2300/505 ,  F05D2300/507 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20110217517A1

公开(公告)日：2011-09-08

申请号：US13030651

申请日：2011-02-18

Applicant: Alison J. MCMILLAN ,  Simon READ

Inventor： Alison J. MCMILLAN ,  Simon READ

IPC: B32B3/30 ,  B32B27/04 ,  B29C71/00

CPC classification number: B29C70/54 ,  B29C70/88 ,  B32B3/30 ,  B32B5/022 ,  B32B5/024 ,  B32B5/026 ,  B32B5/12 ,  B32B5/28 ,  B32B27/04 ,  B32B2260/046 ,  B32B2307/302 ,  B32B2307/50 ,  B32B2307/732 ,  Y10T156/1041 ,  Y10T428/24471

Abstract: A process for manufacturing a layered composite component includes introducing a plurality of micro cracks into a predetermined region of the component in order to provide an increase in strength of the component at certain critical regions of high loading within the component. The micro cracks may be introduced using mechanical means, a pre conditioning load, or by manipulation of process parameters, material properties or stacking sequences.

Abstract translation: 制造层状复合部件的方法包括将多个微裂纹引入到部件的预定区域中，以便在部件内的高负荷的某些关键区域提供部件的强度增加。 可以使用机械装置，预调节负载或通过操纵工艺参数，材料性质或堆叠顺序引入微裂纹。

公开(公告)号：US07845207B2

公开(公告)日：2010-12-07

申请号：US12292108

申请日：2008-11-12

Applicant: Simon Read

Inventor： Simon Read

IPC: G01N3/30

CPC classification number: G01M7/08 ,  G01N3/30 ,  G01N3/313

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20090232657A1

公开(公告)日：2009-09-17

申请号：US12083095

申请日：2006-09-29

Applicant: Simon Read ,  Peter R Beckford

Inventor： Simon Read ,  Peter R Beckford

IPC: F01D5/14 ,  B21K3/04

CPC classification number: F01D21/045 ,  B21D26/055 ,  F01D5/147 ,  F01D5/30 ,  F05D2230/236 ,  Y02T50/672 ,  Y10T29/49339

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20080075593A1

公开(公告)日：2008-03-27

申请号：US11798552

申请日：2007-05-15

Applicant: Simon Read ,  Alison McMillan ,  Eric Ravey

Inventor： Simon Read ,  Alison McMillan ,  Eric Ravey

IPC: F01D5/18

CPC classification number: F01D25/02 ,  F01D5/26 ,  F04D29/023 ,  F04D29/324 ,  F05D2230/90 ,  F05D2300/43 ,  F05D2300/505 ,  F05D2300/507 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07329102B2

公开(公告)日：2008-02-12

申请号：US11252718

申请日：2005-10-19

Applicant: Alison J. McMillan ,  Simon Read

Inventor： Alison J. McMillan ,  Simon Read

IPC: F01D5/16 ,  F01D5/14

CPC classification number: F01D5/18 ,  F01D5/147 ,  F05D2240/126 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S416/50

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08568082B2

公开(公告)日：2013-10-29

申请号：US12547697

申请日：2009-08-26

Applicant: Peter Rowland Beckford ,  Simon Read ,  Ian Colin Deuchar Care

Inventor： Peter Rowland Beckford ,  Simon Read ,  Ian Colin Deuchar Care

IPC: F01D5/30

CPC classification number: F01D21/045 ,  F01D5/147 ,  F01D5/282 ,  Y02T50/672

Abstract: International regulations for aerofoils within gas turbine engines require the safe containment of a released aerofoil. The blade fragments must be contained within an engine casing. Smaller fragments will generally be easier to contain within the casing and therefore reduce the weight of that casing. However introducing lines of weakness may result in cavities and holes which are subject to moisture ingress and problems associated therewith. By providing a root section which incorporates a core having shear surfaces, blades can be designed which in normal use are subject to compressive loads and remain operational, but when subject to impact loads or bending forces create tension forces which cause fragmentation along the shear surfaces after initial energy losses by slippage. By providing the shear surfaces in cores their location is encapsulated avoiding problems with moisture ingress.

Abstract translation: 燃气涡轮发动机中的机翼的国际规定要求安全地容纳释放的机翼。 叶片碎片必须包含在发动机外壳内。 较小的碎片通常在壳体内更容易包含，因此减小了该套管的重量。 然而，引入弱点可能导致受到湿气侵入的空穴和孔以及与之相关的问题。 通过提供包括具有剪切表面的芯的根部，可以设计叶片，其在正常使用中受到压缩载荷并保持操作，但是当受到冲击载荷或弯曲力产生张力时，沿着剪切面产生断裂 初始能量损失通过滑移。 通过在芯中提供剪切表面，其位置被封装，避免了水分侵入的问题。

公开(公告)号：US20110081249A1

公开(公告)日：2011-04-07

申请号：US12870115

申请日：2010-08-27

Applicant: Simon READ

Inventor： Simon READ

IPC: F01D5/18 ,  F01D5/16 ,  B23P15/04

CPC classification number: F01D5/147 ,  B21D26/055 ,  B21D53/78 ,  F01D5/16 ,  F01D5/18 ,  F05D2230/236 ,  F05D2300/133 ,  Y10T29/49339

Abstract: A blade for a turbine engine made by the diffusion-bonding/superplastic-forming (DB/SPF) process has a hollow skin made of front and back panels 1, 3 and internal reinforcement in the form of webs 5 extending between the two faces or panels at an angle to the plane of the blade. The cavities are filled with viscoelastic damping filler 7. In order to allow the blade to deform more easily so that the filler can take up the strain, the webs are pre-buckled so as to compress at least some of the webs. When the blade is deformed, the webs straighten or buckle further, applying a deformation to the filler as they do so and thus dissipating energy. The blade is thus well reinforced against impact but still capable of damping vibrations.

Abstract translation: 用于通过扩散粘结/超塑性成形（DB / SPF）工艺制造的涡轮发动机的叶片具有由前面板和后面板1,3制成的中空皮，以及在两个面之间延伸的腹板5形式的内部加强件， 面板与叶片的平面成一定角度。 空腔填充有粘弹性阻尼填料7.为了允许叶片变得更容易变形，使得填料可以承受应变，网状物被预先弯曲，以便压缩至少一些网。 当叶片变形时，织物进一步拉直或弯曲，因此在填充物上施加变形并因此耗散能量。 因此，刀片可以很好地抵抗冲击，但仍然能够阻尼振动。