公开(公告)号：US08430623B2

公开(公告)日：2013-04-30

申请号：US12547573

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: F01D5/147 ,  F01D5/14 ,  F01D21/045 ,  F05D2300/612

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US08366378B2

公开(公告)日：2013-02-05

申请号：US12547644

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 ,  F01D5/282 ,  F01D5/34 ,  F04D29/321 ,  F04D29/324 ,  Y02T50/672

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20100040472A1

公开(公告)日：2010-02-18

申请号：US12461111

申请日：2009-07-31

Applicant: Simon Read ,  Ewan F. Thompson ,  Christopher S. Brown

Inventor： Simon Read ,  Ewan F. Thompson ,  Christopher S. Brown

IPC: F01D5/22

CPC classification number: F01D11/008 ,  F01D5/3007 ,  F02K3/06 ,  F05D2240/80

Abstract: 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).

Abstract translation: 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）。

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：US20120100006A1

公开(公告)日：2012-04-26

申请号：US13267375

申请日：2011-10-06

Applicant: Nicholas M. MERRIMAN ,  Simon READ

Inventor： Nicholas M. MERRIMAN ,  Simon READ

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F01D5/16 ,  F01D5/282 ,  F04D29/324 ,  F04D29/38 ,  F04D29/382 ,  F05D2240/303 ,  Y10S416/50

Abstract: A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced.

Abstract translation: 一种涡轮机叶片，其具有布置成当外来物体在前缘上撞击时引导前缘朝向压力表面弯曲的特征。 特征可以是比位于中厚线的压力表面侧的前缘的材料更弱的特征。 通过在冲击时使前缘朝向压力表面弯曲，减小了越过吸力表面的异物（通常为鸟）的体积。

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：US20100054942A1

公开(公告)日：2010-03-04

申请号：US12547644

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 ,  F01D5/282 ,  F01D5/34 ,  F04D29/321 ,  F04D29/324 ,  Y02T50/672

Abstract: 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.

Abstract translation: 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。

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。