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：US09149223B2

公开(公告)日：2015-10-06

申请号：US14125972

申请日：2012-06-18

Applicant: Iain R. Spears ,  Pierre Lagadec ,  Simon W. Bateson ,  Simon Read

Inventor： Iain R. Spears ,  Pierre Lagadec ,  Simon W. Bateson ,  Simon Read

IPC: G01D1/00 ,  A61B5/22 ,  A61B5/00 ,  A61B5/11 ,  A63B21/055 ,  A63B21/00 ,  A63B71/06 ,  A63B21/04 ,  A63B23/035 ,  A63B23/12 ,  A63B24/00

CPC classification number: A61B5/4866 ,  A61B5/1112 ,  A61B5/1114 ,  A61B5/1118 ,  A61B5/1121 ,  A61B5/1127 ,  A61B5/22 ,  A61B5/221 ,  A61B5/6804 ,  A61B5/6895 ,  A61B5/7278 ,  A61B2562/0219 ,  A61B2562/222 ,  A63B21/0442 ,  A63B21/0552 ,  A63B21/0557 ,  A63B21/4009 ,  A63B21/4025 ,  A63B21/4035 ,  A63B23/03541 ,  A63B23/1209 ,  A63B24/0062 ,  A63B71/0622 ,  A63B2024/0096 ,  A63B2220/12 ,  A63B2220/13 ,  A63B2220/16 ,  A63B2220/40 ,  A63B2220/806 ,  A63B2225/20 ,  A63B2225/50 ,  A63B2230/75

Abstract: A method of measuring expended energy of a moving body, including providing a first sensor for measuring data of a first part of the moving body; providing a second sensor for measuring data of a second part of the moving body, wherein the second part is moveable relative to the first part and connected to the first part by a first resistive deformable element that is external to the moving body; using the first sensor to make a first measurement and subsequently calculating a global expended energy of the first part relative to a reference frame; using the second sensor to make a second measurement and subsequently calculating a relative expended energy of the second part relative to the first part; and calculating the total expended energy of the moving body by summing the global expended energy with the relative expended energy.

Abstract translation: 一种测量移动体的消耗能量的方法，包括提供用于测量移动体的第一部分的数据的第一传感器; 提供用于测量所述移动体的第二部分的数据的第二传感器，其中所述第二部分可相对于所述第一部分移动并且通过位于所述移动体外部的第一电阻可变形元件连接到所述第一部分; 使用所述第一传感器进行第一测量并随后计算所述第一部分相对于参考帧的全局消耗能量; 使用所述第二传感器进行第二测量并随后计算所述第二部分相对于所述第一部分的相对耗费能量; 并通过将全球消耗能量与相对消耗的能量相加来计算移动体的总消耗能量。

公开(公告)号：US09045991B2

公开(公告)日：2015-06-02

申请号：US13546647

申请日：2012-07-11

Applicant: Simon Read ,  Bijoysri Khan

Inventor： Simon Read ,  Bijoysri Khan

IPC: F01D5/28

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 fibers, 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：US08668456B2

公开(公告)日：2014-03-11

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 ,  F01D5/28 ,  F04D29/32 ,  F04D29/38 ,  F01D5/16

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：US08297931B2

公开(公告)日：2012-10-30

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: F01D5/02

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 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：US07972116B2

公开(公告)日：2011-07-05

申请号：US11826487

申请日：2007-07-16

Applicant: Simon Read ,  Sivasubramaniam K Sathianathan

Inventor： Simon Read ,  Sivasubramaniam K Sathianathan

IPC: F01D5/14 ,  B21D53/78

CPC classification number: F04D29/388 ,  F01D5/147 ,  F01D5/3007 ,  F05D2230/23 ,  F05D2230/236 ,  F05D2230/25 ,  Y10T29/49337 ,  Y10T29/49339

Abstract: A blade for a gas turbine engine includes an aerofoil portion and a root portion defined by concave and convex walls having opposing inner surfaces. A reinforcing member is located between the concave and convex walls and is bonded to the inner surfaces of the concave and convex walls, and the root portion includes an unbonded region in which the reinforcing member contacts an inner surface of one of the concave and convex walls but is not bonded to the concave and convex walls.

Abstract translation: 用于燃气涡轮发动机的叶片包括机翼部分和由具有相对的内表面的凹凸壁限定的根部分。 加强构件位于凹凸壁之间并且被结合到凹壁和凸壁的内表面，并且根部包括非粘合区域，加强构件中的一个凹壁和凸壁的内表面 但不粘合到凹凸壁。

公开(公告)号：US20100143097A1

公开(公告)日：2010-06-10

申请号：US11648600

申请日：2007-01-03

Applicant: Simon Read ,  Peter R. Beckford

Inventor： Simon Read ,  Peter R. Beckford

IPC: F01D25/06 ,  B23P15/04

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：US07594325B2

公开(公告)日：2009-09-29

申请号：US11210872

申请日：2005-08-25

Applicant: Simon Read

Inventor： Simon Read

IPC: B21D53/78 ,  B63H1/26 ,  B22F3/00

CPC classification number: F04D29/542 ,  B21D26/055 ,  B21D53/78 ,  F04D29/023 ,  F04D29/38 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2300/10 ,  F05D2300/522 ,  F05D2300/61 ,  F05D2300/612 ,  Y10T29/49316 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T428/12021 ,  Y10T428/12028 ,  Y10T428/12042

Abstract: An aerofoil (35) for example a fan blade (26) comprises a leading edge (36), a trailing edge (38), a concave pressure surface extending (40) from the leading edge (36) to the trailing edge (38) and a convex suction surface (42) extending from the leading edge (36) to the trailing edge (38). The aerofoil (35) comprises a metal foam (50) arranged within a cavity defined by metal workpieces (52, 54). The metal foam (50) of the aerofoil (26) ideally has a density of less than 1g/cm3, is cheaper to manufacture and has improved fatigue behaviour and impact capability.

Abstract translation: 例如风扇叶片（26）的机翼（35）包括前缘（36​​），后缘（38），从前缘（36​​）延伸到后缘（38）延伸（40）的凹形压力表面， 以及从前缘（36​​）延伸到后缘（38）的凸形吸入表面（42）。 机翼（35）包括布置在由金属工件（52,54）限定的空腔内的金属泡沫（50）。 机翼（26）的金属泡沫（50）理想地具有小于1g / cm 3的密度，制造成本更低，并且具有改善的疲劳行为和冲击能力。

公开(公告)号：US20070243069A1

公开(公告)日：2007-10-18

申请号：US11210872

申请日：2005-08-25

Applicant: Simon Read

Inventor： Simon Read

IPC: F04D29/38

CPC classification number: F04D29/542 ,  B21D26/055 ,  B21D53/78 ,  F04D29/023 ,  F04D29/38 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2300/10 ,  F05D2300/522 ,  F05D2300/61 ,  F05D2300/612 ,  Y10T29/49316 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T428/12021 ,  Y10T428/12028 ,  Y10T428/12042

Abstract: An aerofoil (35) for example a fan blade (26) comprises a leading edge (36), a trailing edge (38), a concave pressure surface extending (40) from the leading edge (36) to the trailing edge (38) and a convex suction surface (42) extending from the leading edge (36) to the trailing edge (38). The aerofoil (35) comprises a metal foam (50) arranged within a cavity defined by metal workpieces (52, 54). The metal foam (50) of the aerofoil (26) ideally has a density of less than 1g/cm3, is cheaper to manufacture and has improved fatigue behaviour and impact capability.

Abstract translation: 例如风扇叶片（26）的机翼（35）包括前缘（36​​），后缘（38），从前缘（36​​）延伸到后缘（38）延伸（40）的凹形压力表面， 以及从前缘（36​​）延伸到后缘（38）的凸形吸入表面（42）。 机翼（35）包括布置在由金属工件（52,54）限定的空腔内的金属泡沫（50）。 机翼（26）的金属泡沫（50）理想地具有小于1g / cm 3的密度，制造成本更低，并且具有改善的疲劳行为和冲击能力。

公开(公告)号：US20050008492A1

公开(公告)日：2005-01-13

申请号：US10872557

申请日：2004-06-22

Applicant: Christopher Whitehead ,  Simon Read

Inventor： Christopher Whitehead ,  Simon Read

IPC: F01D5/14 ,  F01D5/16 ,  F01D5/18 ,  F04D29/38 ,  F04D29/66 ,  B63H1/26

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。