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。