公开(公告)号：US08444390B2

公开(公告)日：2013-05-21

申请号：US12870115

申请日：2010-08-27

Applicant: Simon Read

Inventor： Simon Read

IPC: F01D5/18

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。

公开(公告)号：US20110318181A1

公开(公告)日：2011-12-29

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: F01D5/18

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：US20080057230A1

公开(公告)日：2008-03-06

申请号：US11719069

申请日：2005-11-10

Applicant: Simon Read ,  Eva Clorley

Inventor： Simon Read ,  Eva Clorley

IPC: B41M5/00 ,  B41M5/40

CPC classification number: B41M5/5254 ,  B41M5/42 ,  B41M5/5218 ,  Y10T428/265

Abstract: The invention provides a coating on a polymeric substrate forming a non-porous print receptive layer on the polymeric substrate, printability, thermal conductivity. Tg, surface hardness and surface smoothness of the print receptive layer being regulated by forming the print receptive layer from a dispersion containing a mixture of at least two acrylic latexes, at least one chosen to have an acid value of 20 to 60 mg KOH/g resin and a Tg less than 35 centigrade degrees, and at least one having a Tg greater than 90 centigrade degrees so as to adjust the hardness/Tg of the print receptive layer the acrylic polymer being present in each latex in the discontinuous phase so that the latexes are only partially miscible with one another, the dispersion further containing as essential components a metal containing cross linking agent to cross link the acrylic latexes and thereby further regulate both the thermal conductivity and the surface hardness of the print receptive layer, hollow polymeric particles to regulate the thermal conductivity of the print receptive layer and silica particles with a primary particle size of less than 100 nm to regulate the surface smoothness of the print receptive layer.

Abstract translation: 本发明提供了在聚合物基材上形成在聚合物基材上的无孔印刷接收层的涂层，可印刷性，导热性。 通过从包含至少两种丙烯酸胶乳的混合物的分散体形成印刷接受层来调节印刷接受层的Tg，表面硬度和表面平滑度，至少一种选自具有20至60mg KOH / g酸值 树脂，Tg小于35摄氏度，Tg至少为90摄氏度以上的至少一种，以便调节不连续相中每个胶乳中存在的丙烯酸类聚合物的印刷接受层的硬度/ Tg，使得 胶乳仅相互部分混溶，分散体还含有作为必需组分的金属含交联剂以交联丙烯酸胶乳，从而进一步调节印刷接收层的热导率和表面硬度，中空聚合物颗粒至 调节印刷接受层和一次粒径小于100nm的二氧化硅颗粒的热导率以调节s 打印接受层的表面平滑度。

公开(公告)号：US07118346B2

公开(公告)日：2006-10-10

申请号：US10793907

申请日：2004-03-08

Applicant: Simon Read

Inventor： Simon Read

IPC: F01D5/18 ,  F01D5/16

CPC classification number: F01D21/045 ,  F01D5/16 ,  F01D5/18 ,  F04D29/324 ,  Y10S416/50

Abstract: A compressor blade (26) comprises an aerofoil (36) and a root (38). The aerofoil (36) comprises a concave wall (40) extending from a leading edge (44) to a trailing edge (46) and a convex wall (42) extending from the leading edge (44) to the trailing edge (46). The aerofoil (36) defines at least one internal chamber (48). The root (38) is connected to the aerofoil (36) and the root (38) has a base (50) remote from the aerofoil (38) and at least one aperture (52) extends from the base (50) to the at least one internal chamber (48) in the aerofoil (36). The dimensions, shape and position of the least one aperture (52) are selected such that the root (38) is deformable. This reduces the weight of the containment region of a fan casing (28).

Abstract translation: 压缩机叶片（26）包括机翼（36）和根部（38）。 机翼（36）包括从前缘（44）延伸到后缘（46）的凹壁（40）和从前缘（44）延伸到后缘（46）的凸壁（42）。 机翼（36）限定至少一个内部腔室（48）。 根（38）连接到机翼（36），根（38）具有远离机翼（38）的基座（50），并且至少一个孔（52）从基座（50）延伸到 机翼（36）中的至少一个内室（48）。 选择最小孔径（52）的尺寸，形状和位置使得根部（38）可变形。 这减小了风扇壳体（28）的容纳区域的重量。

公开(公告)号：US07112044B2

公开(公告)日：2006-09-26

申请号：US10872557

申请日：2004-06-22

Applicant: Christopher M Whitehead ,  Simon Read

Inventor： Christopher M Whitehead ,  Simon Read

IPC: B64C11/16

CPC classification number: F04D29/668 ,  F01D5/147 ,  F01D5/16 ,  F01D5/18 ,  F04D29/388 ,  Y02T50/671 ,  Y02T50/676

Abstract: Percussive impacts due to bird strikes upon the hollow fan blades 20 are a well known problem. These percussive impacts not only deform previous fan blades but also reduce their stiffness. In accordance with the present invention, hollow fan blades 20 incorporate a cavity 23 within which, a matrix 24 with embedded expandable elements 25, is located. Thus, upon a percussive impact these expandable elements 25 are released in order to create an internal pressure within the cavity 25 which acts outwardly in order to relieve deformation and also stiffen the blade 20 as a result of the over pressure within the cavity 23.

Abstract translation: 鸟撞击中空风扇叶片20时的冲击响应是众所周知的问题。 这些冲击影响不仅​​使先前的风扇叶片变形，而且还降低了其刚度。 根据本发明，空心风扇叶片20包括空腔23，在其中具有嵌入的可膨胀元件25的矩阵24。 因此，在撞击冲击时，这些可膨胀元件25被释放，以便在空腔25内产生内部压力，该内部压力向外作用，以便减轻变形并且由于空腔23内的过压而使叶片20变硬。

公开(公告)号：US20060104818A1

公开(公告)日：2006-05-18

申请号：US11252718

申请日：2005-10-19

Applicant: Alison McMillan ,  Simon Read

Inventor： Alison McMillan ,  Simon Read

IPC: B64C11/24

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：US07794197B2

公开(公告)日：2010-09-14

申请号：US11484728

申请日：2006-07-12

Applicant: Ewan F Thompson ,  Simon Read

Inventor： Ewan F Thompson ,  Simon Read

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2270/09 ,  F05D2300/603 ,  F05D2300/612 ,  F05D2300/614 ,  F05D2300/702

Abstract: An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibrous internal containment device allows the blade to fragment progressively thereby spreading the load imparted by the blade to a casing should the blade fragment upon impact.

Abstract translation: 一种用于燃气涡轮发动机的机翼叶片，该叶片具有限定多个包含发泡材料的空腔的金属芯。 空腔成形为使得在叶片的一个表面上的冲击力通过泡沫散发并传递到金属芯。 纤维内部容纳装置允许叶片逐渐碎裂，从而当刀片在冲击时碎片被分散，从而将叶片施加的载荷扩展到壳体。

公开(公告)号：US07753654B2

公开(公告)日：2010-07-13

申请号：US11648600

申请日：2007-01-03

Applicant: Simon Read ,  Peter R Beckford

Inventor： Simon Read ,  Peter R Beckford

IPC: B64C11/24

CPC classification number: F01D5/282 ,  F01D5/147 ,  F01D5/16 ,  F01D5/26 ,  F02C7/045 ,  F05D2300/43 ,  F05D2300/612 ,  Y10S416/50 ,  Y10T29/4932

Abstract: An aerofoil 26 for a gas turbine engine (10, FIG. 1) comprises a cavity 38, a cellular material 42 located in the cavity 38 for stiffening the aerofoil 26, and a vibration damping medium 44 located in the cavity 38 for damping the aerofoil. The cellular material 42 is preferably a metal foam bonded to the inner surface 34a, 36a of the hollow aerofoil 26, and the vibration damping medium 44 is preferably a viscoelastic material. Various methods for fabricating the aerofoil 26 are also described.

Abstract translation: 用于燃气涡轮发动机（图1中的10）的机翼26包括空腔38，位于空腔38中用于加强机翼26的多孔材料42和位于空腔38中的减振介质44，用于阻尼机翼 。 多孔材料42优选是结合到中空机翼26的内表面34a，36a的金属泡沫，并且减震介质44优选为粘弹性材料。 还描述了用于制造机翼26的各种方法。

公开(公告)号：US20100054938A1

公开(公告)日：2010-03-04

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: F01D5/14 ,  B23P15/04

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。