公开(公告)号：WO2014197037A2

公开(公告)日：2014-12-11

申请号：PCT/US2014/023065

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： CONWAY, Chuong ,  LILES, Jason David ,  SCOTT, Jonathan Ariel

IPC: F01D9/04 ,  F01D25/28 ,  F01D25/30 ,  F02C7/20

CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/246 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/50 ,  F05D2240/90

Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.

Abstract translation: 用于涡轮机框架的整流罩子组件88包括内环50，外环48和多个支柱。 内环由多个内部段82形成。外环由多个外部段80形成。多个支撑壳84,86连接内部环48和外部环50.在另一个实施例中， 整流罩子组件包括连接多个内部部分82和多个支柱86的内部带45，以形成外部狭槽，以及连接多个外部部分80和多个支柱86的外部带44 形成内槽。 组装整流罩46的方法包括将上述整流罩子组件38插入涡轮机框架42的后端，在涡轮机架42的前端将多个前支柱84插入外槽和内槽中 并且将前支撑杆84连接到整流罩子组件88。

公开(公告)号：EP3170974A1

公开(公告)日：2017-05-24

申请号：EP16200356.0

申请日：2016-11-23

Applicant: United Technologies Corporation

Inventor： LEWIS, Scott D. ,  LANA, Kyle C. ,  LILES, Jason David

IPC: F01D5/14 ,  F01D5/20

CPC classification number: F01D5/145 ,  F01D5/141 ,  F01D5/20 ,  F01D5/22 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/307 ,  F05D2250/711 ,  Y02T50/671 ,  Y02T50/673

Abstract: A rotor blade (32) for a gas turbine engine (10) is provided. The rotor blade having: an attachment (34); an airfoil (36) extending from the attachment to a tip (46); and a squealer pocket (200) located in a surface of the tip, wherein the squealer pocket is at least partially surrounded by a first surface (206) of a wall (202) located between the squealer pocket and a pressure side of the airfoil, wherein the first surface of the wall has a convex configuration with respect to the pressure side of the airfoil as it extends from a leading edge (38) to a trailing edge (40) of the airfoil.

Abstract translation: 提供了一种用于燃气涡轮发动机（10）的转子叶片（32）。 该转子叶片具有：附件（34）; 从所述附件延伸到尖端（46）的翼型件（36）; 以及位于所述尖端的表面中的鸣声器袋（200），其中所述鸣声器袋至少部分地由位于所述鸣音器袋与所述翼型件的压力侧之间的壁（202）的第一表面（206）围绕， 其中当所述壁从所述翼型的前缘（38）延伸到后缘（40）时，所述壁的所述第一表面相对于所述翼型的所述压力侧具有凸起构型。

公开(公告)号：EP2971579A2

公开(公告)日：2016-01-20

申请号：EP14807208.5

申请日：2014-03-11

Applicant: United Technologies Corporation

Inventor： CONWAY, Chuong ,  LILES, Jason David ,  SCOTT, Jonathan Ariel

IPC: F01D9/04 ,  F01D25/28 ,  F01D25/30 ,  F02C7/20

CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/246 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/50 ,  F05D2240/90

Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.

Abstract translation: 用于涡轮机框架的整流子组件88包括内环50，外环48和多个支柱壳。 内圈由多个内段82形成。外圈由多个外段80形成。多个支柱壳84,86连接内环48和外环50.在另一个实施例中， 整流子组件包括连接多个内部节段82和多个支柱壳体86以形成外部缝隙的内部带子45以及连接多个外部节段80和多个支柱壳体86的外部带子44 形成内槽。 组装整流装置46的方法包括将上述整流装置子组件38插入涡轮机框架42的后端，将多个前支柱壳体84插入涡轮机框架42的前端处的外部槽和内部槽中 ，并且将前支撑壳体84连接到整流装置子组件88。