公开(公告)号：US08845280B2

公开(公告)日：2014-09-30

申请号：US13069011

申请日：2011-03-22

Applicant: Stephen C. Diamond ,  Caner H. Helvaci ,  Roderick M. Townes ,  Ian Tibbott ,  Dougal R. Jackson

Inventor： Stephen C. Diamond ,  Caner H. Helvaci ,  Roderick M. Townes ,  Ian Tibbott ,  Dougal R. Jackson

IPC: F01D11/08 ,  F01D5/20

CPC classification number: F01D5/20

Abstract: A turbine blade for a gas turbine engine has an aerofoil portion extending from a root to a tip. The tip carries winglets. A gutter extends across the tip to entrain gas leaking around the tip (over tip leakage). The aerofoil portion has a mean camber line and the gutter has a center line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the center line are parallel at the exit when viewed as aforesaid, are not both fulfilled.

Abstract translation: 用于燃气涡轮发动机的涡轮机叶片具有从根部延伸到尖端的机翼部分。 小提示带有小翼。 沟槽延伸穿过尖端以夹带气体在尖端周围泄漏（超过尖端泄漏）。 机翼部分具有平均曲线，并且沟槽具有中心线。 在所描述的例子中，（a）平均弧线和中心线在从尖端朝向根部的出口处重合，和（b）平均弧线和中心线在出口处平行， 如上所述，并不都是满足的。

公开(公告)号：US20100047078A1

公开(公告)日：2010-02-25

申请号：US12458412

申请日：2009-07-10

Applicant: Roderick M. Townes ,  Ian Tibbott ,  Edwin Dane

Inventor： Roderick M. Townes ,  Ian Tibbott ,  Edwin Dane

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  Y02T50/676

Abstract: Cooling arrangements have been provided for blades and in particular turbine blades utilising gas turbine engines. Generally for internal strength a leading passage has been separate by a solid wall from a feed passage as impingement apertures may diminish structural strength as centres for stress concentration. However, impingement apertures allow impingement jets which have improved cooling efficiency. By providing a leading passage which is divided at least into a lower section and an upper section the lower section can have a wall which is solid for structural integrity whilst an upper section has impingement apertures for greater cooling efficiency.

Abstract translation: 已经为叶片，特别是利用燃气涡轮发动机的涡轮叶片提供了冷却装置。 通常，对于内部强度，引导通道由进料通道的实心壁分离，因为冲击孔可能会减小作为应力集中中心的结构强度。 然而，冲击孔允许具有改善的冷却效率的冲击射流。 通过提供至少分成下部和上部的引导通道，下部可以具有用于结构完整性的实心的壁，而上部具有用于更高冷却效率的冲击孔。

公开(公告)号：US20090317258A1

公开(公告)日：2009-12-24

申请号：US12457450

申请日：2009-06-11

Applicant: Ian Tibbott ,  Roderick M. Townes

Inventor： Ian Tibbott ,  Roderick M. Townes

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201

Abstract: Cooling within aerofoils (30, 47, 67, 87) is a requirement in order that the materials from which the aerofoil (30, 47, 67, 87) is created can remain within acceptable operational parameters. Traditionally static pressure as well as enhanced dynamic pressure impingement flows have been utilised but there are problems with regard to achieving a necessary over pressure to avoid hot gas ingestion or reduced cooling effect. It will be appreciated that fluid flows and in particular coolant fluid flows must be used most appropriately in order to maintain operational efficiency. By providing a plurality of feed apertures (41, 61, 81) which are shaped to have an entry portion (51, 71, 91) which is generally elliptical and an exit portion (52, 72, 92) it is possible to grab and turn a proportion of a feed flow (44, 64, 84) for substantially perpendicular or other angular presentation to an opposed surface of a cooling chamber (42, 62, 82) within which cooling is required.

Abstract translation: 在机翼（30,77,67,87）内的冷却是要求，以便制造机翼（30,47,67,87）的材料可以保持在可接受的操作参数内。 已经使用传统的静压力和增强的动态压力冲击流，但是在实现必要的过压以避免热气体吸入或降低冷却效果方面存在问题。 应当理解，流体流动，特别是冷却剂流体流必须最适当地使用以保持操作效率。 通过设置多个进给孔（41,61,81），其形状为具有大致椭圆形的入口部分（51,71,91）和出口部分（52,72,92），可以抓取和 将进给流（44,64,84）的一部分用于基本垂直或其他角度呈现到需要冷却的冷却室（42,62,82）的相对表面。

公开(公告)号：US08657576B2

公开(公告)日：2014-02-25

申请号：US12457450

申请日：2009-06-11

Applicant: Ian Tibbott ,  Roderick M. Townes

Inventor： Ian Tibbott ,  Roderick M. Townes

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/201

Abstract: Cooling within aerofoils (30, 47, 67, 87) is a requirement in order that the materials from which the aerofoil (30, 47, 67, 87) is created can remain within acceptable operational parameters. Traditionally static pressure as well as enhanced dynamic pressure impingement flows have been utilized but there are problems with regard to achieving a necessary over pressure to avoid hot gas ingestion or reduced cooling effect. It will be appreciated that fluid flows and in particular coolant fluid flows must be used most appropriately in order to maintain operational efficiency. By providing a plurality of feed apertures (41, 61, 81) which are shaped to have an entry portion (51, 71, 91) which is generally elliptical and an exit portion (52, 72, 92) it is possible to grab and turn a proportion of a feed flow (44, 64, 84) for substantially perpendicular or other angular presentation to an opposed surface of a cooling chamber (42, 62, 82) within which cooling is required.

Abstract translation: 在机翼（30,77,67,87）内的冷却是要求，以便制造机翼（30,47,67,87）的材料可以保持在可接受的操作参数内。 已经使用传统的静压力和增强的动态压力冲击流，但是在实现必要的过压以避免热气体吸入或降低冷却效果方面存在问题。 应当理解，流体流动，特别是冷却剂流体流必须最适当地使用以保持操作效率。 通过设置多个进给孔（41,61,81），其形状为具有大致椭圆形的入口部分（51,71,91）和出口部分（52,72,92），可以抓取和 将进给流（44,64,84）的一部分用于基本垂直或其他角度呈现到需要冷却的冷却室（42,62,82）的相对表面。

公开(公告)号：US08419366B2

公开(公告)日：2013-04-16

申请号：US12458412

申请日：2009-07-10

Applicant: Roderick M. Townes ,  Ian Tibbott ,  Edwin Dane

Inventor： Roderick M. Townes ,  Ian Tibbott ,  Edwin Dane

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  Y02T50/676

Abstract: Cooling arrangements for blades, and in particular turbine blades utilizing gas turbine engines include impingement apertures with impingement jets, which improve cooling efficiency. By providing a leading passage, which is divided at least into a lower section and an upper section, the lower section can have a wall, which is solid for structural integrity while an upper section has impingement apertures for greater cooling efficiency.

Abstract translation: 叶片，特别是利用燃气涡轮发动机的涡轮叶片的冷却装置包括具有冲击射流的冲击孔，这提高了冷却效率。 通过提供至少分为下部和上部的引导通道，下部可具有壁，该壁为结构完整性而牢固，而上部具有用于更高冷却效率的冲击孔。

公开(公告)号：US08322987B2

公开(公告)日：2012-12-04

申请号：US12457585

申请日：2009-06-16

Applicant: Adrian J. Webster ,  Roderick M. Townes ,  Ian Tibbott

Inventor： Adrian J. Webster ,  Roderick M. Townes ,  Ian Tibbott

IPC: F04D29/58

CPC classification number: F01D5/187 ,  F01D5/186 ,  Y02T50/676

Abstract: With regard to cooling turbine blades in a gas turbine engine a compromise has to be made between convective cooling within the inner cavity defining a flow path for coolant and the blow rates for developing film cooling on an outer surface of the aerofoil. By providing a chamber between the flow cavity and external apertures reconciliation between the necessary flow rates for convective cooling within the cavity defining the pathway for coolant flow within the aerofoil and the necessary coolant blowing rate for film development can be achieved.

Abstract translation: 关于燃气涡轮发动机中的冷却涡轮机叶片，必须在限定用于冷却剂的流动路径的内腔内的对流冷却和用于在机翼的外表面上显影膜冷却的吹扫速率之间做出折衷。 通过在流动空腔和外部孔之间设置一个室，可以实现限定用于机翼内冷却剂流动的通道的空腔内的对流冷却所需的流量和用于膜显影的必要的冷却剂吹送速率之间的调节。

公开(公告)号：US20100054955A1

公开(公告)日：2010-03-04

申请号：US12458540

申请日：2009-07-15

Applicant: Caner H. Helvaci ,  Roderick M. Townes ,  Stephen Diamond

Inventor： Caner H. Helvaci ,  Roderick M. Townes ,  Stephen Diamond

IPC: F01D5/18 ,  B23P15/04

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/185 ,  Y10T29/49341

Abstract: A rotary blade, such as a turbine blade for a gas turbine engine, has an aerofoil portion with a tip partly shrouded by winglets. A gutter extends across the radially outer face of the tip to leave upstands. Cooling air feed galleries are drilled into each upstand, from the trailing edge, toward the upper end of a cooling air feed void, which is spaced from the trailing edge. Cooling passages are drilled from the winglet edges to the gallery. Cooling air supplied through the void passes along the gallery, through the passages and leaves the blade at the cooling holes. This allows cooling to be provided near the trailing edge of the tip without requiring the geometry around the trailing edge to be thickened to accommodate a cooling air void.

Abstract translation: 诸如用于燃气涡轮发动机的涡轮机叶片的旋转叶片具有机翼部分，其尖端部分地被小翼罩住。 沟槽延伸穿过尖端的径向外表面以离开竖立。 从后缘到冷却空气供给空隙的上端钻出冷却空气供给库，后者与后缘间隔开。 从小翼边缘到画廊钻出冷却通道。 通过空气供应的冷却空气沿着通道通过通道，并将叶片留在冷却孔处。 这允许在尖端的后缘附近提供冷却，而不需要使后缘附近的几何形状加厚以适应冷却空气空隙。

公开(公告)号：US20090136358A1

公开(公告)日：2009-05-28

申请号：US12318722

申请日：2009-01-07

Applicant: Roderick M Townes

Inventor： Roderick M Townes

IPC: F01D5/18

CPC classification number: F01D5/081 ,  F01D5/187 ,  F05D2260/221 ,  F05D2260/60 ,  Y02T50/676

Abstract: In order to couple coolant air flow presented through a coolant gallery 4, 24 through an opening 7, 27 into a passage 8, 28 a flow deflector 6, 26 is provided. The flow deflector 6, 26 progressively deflects the coolant air flow 5, 25 through the opening 7, 27 such that there is reduced loss in coolant flow 5, 25 pressure.

Abstract translation: 为了使通过冷却剂槽4,24通过开口7,27呈现的冷却剂空气流耦合到通道8,28中，提供了导流板6,26。 导流板6,26通过开口7,27逐渐偏转冷却剂空气流5,25，使得冷却剂流5,25的压力降低。

公开(公告)号：US07037075B2

公开(公告)日：2006-05-02

申请号：US10724100

申请日：2003-12-01

Applicant: Roderick M Townes ,  Ian Tibbott

Inventor： Roderick M Townes ,  Ian Tibbott

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/141 ,  F01D5/225 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/22141 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: Turbine blades used in jet engines generally require cooling in order to achieve desired engine performance. Cooling of blade tip areas is difficult due to the limited space available such that thickening tip areas in order to allow passages and holes to be incorporated adds to weight and therefore stressing along with causing additional manufacturing costs. The present cooling arrangement includes coolant release passages 5 which present coolant flow to coolant entrainment elements or fins 2 such that the coolant flow is entrained close to the blade tip surface 12. Thus, turbulent air flow caused by adjacent shrouds and edges are inhibited from diluting the coolant flow and therefore reducing thermal efficiency.

Abstract translation: 在喷气发动机中使用的涡轮叶片通常需要冷却以实现期望的发动机性能。 叶片尖端区域的冷却是困难的，因为可用的空间有限，使得增加顶端区域以允许通道和孔被结合，增加了重量并因此产生压力并导致额外的制造成本。 当前的冷却装置包括冷却剂释放通道5，冷却剂释放通道5向冷却剂夹带元件或翅片2提供冷却剂流，使得冷却剂流被夹带靠近叶片顶端表面12。 因此，防止由相邻的护罩和边缘引起的紊流气流稀释冷却剂流并因此降低热效率。

公开(公告)号：US08851833B2

公开(公告)日：2014-10-07

申请号：US13053928

申请日：2011-03-22

Applicant: Stephen C. Diamond ,  Caner H. Helvaci ,  Roderick M. Townes ,  Ian Tibbott ,  Dougal R. Jackson

Inventor： Stephen C. Diamond ,  Caner H. Helvaci ,  Roderick M. Townes ,  Ian Tibbott ,  Dougal R. Jackson

IPC: F01D11/08 ,  F01D5/20

CPC classification number: F01D5/20

Abstract: A rotor blade 40 for a gas turbine engine has an aerofoil portion 42 from a root 48 to a tip 54. In use, combustion gas may leak over the tip 54 from the pressure face 52 to the suction face 50. A gutter 62 extends across the tip 54 to entrain any over tip leakage gap. The floor of the gutter defines an increased depth portion 72 at the exit end of the gutter 62.

Abstract translation: 用于燃气涡轮发动机的转子叶片40具有从根部48到尖端54的机翼部分42.在使用中，燃烧气体可能在尖端54上从压力面52泄漏到吸力面50.沟槽62延伸越过 尖端54夹带任何过度的尖端泄漏间隙。 沟槽的地板在沟槽62的出口处限定增加的深度部分72。