公开(公告)号：US20160069192A1

公开(公告)日：2016-03-10

申请号：US14944503

申请日：2015-11-18

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA ,  B&B AGEMA GmbH

Inventor： Ryozo TANAKA ,  Takao SUGIMOTO ,  Masahide KAZARI ,  Tomoki TANIGUCHI ,  Karsten KUSTERER ,  Dieter BOHN ,  Nurettin TEKIN

IPC: F01D5/18 ,  B23H1/04

CPC classification number: F01D5/186 ,  B23H1/04 ,  B23H9/10 ,  B23H9/14 ,  F01D9/065 ,  F05D2230/12 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2250/14 ,  F05D2250/231 ,  F05D2250/75 ,  F05D2260/202 ,  F23R3/06 ,  F23R2900/03042

Abstract: A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.

Abstract translation: 双喷射薄膜冷却结构包括：形成在面向高温气体通道的壁面上的喷射口; 主通道作为直的圆孔向冷却介质供给喷射口; 一对分支通道为直圆孔; 以及将主通道连接到分支通道的连通通道。 主通道和分支通道具有相同的恒定内径。 每个连通通道具有通过连续地布置通过分支点并具有恒定内径的直圆孔而获得的包络面。 分支通道相对于沿着壁表面的气流的横向喷射角度被定向在相反的方向。 主通道的轴向与壁面之间的角度大于在分支通道的轴向方向和壁面之间形成的角度。

公开(公告)号：US20160115796A1

公开(公告)日：2016-04-28

申请号：US14944441

申请日：2015-11-18

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA ,  B&B AGEMA GmbH

Inventor： Tomoki TANIGUCHI ,  Ryozo TANAKA ,  Takeshi HORIUCHI ,  Takao SUGIMOTO ,  Masahide KAZARI ,  Karsten KUSTERER ,  Dieter BOHN ,  Gang LIN

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/303 ,  F05D2250/141 ,  F05D2250/15 ,  F05D2250/231 ,  F05D2250/25 ,  F05D2250/312 ,  F05D2250/314 ,  F05D2250/72 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/2214

Abstract: In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.

Abstract translation: 在用于内部冷却涡轮机叶片的结构中，在涡轮机叶片中设置有冷却介质通道。 冷却介质通道具有彼此平行延伸的多个圆柱形状的多个圆柱形空间部分地彼此重叠的形状。 将冷却介质供给到冷却介质通路的冷却介质供给通路与包括周壁的冷却介质通路的相对于冷却介质通路的长度方向成锐角的方向连接 。

公开(公告)号：US20240344482A1

公开(公告)日：2024-10-17

申请号：US18755155

申请日：2024-06-26

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Hiromitsu ARAI ,  Ryozo TANk ,  Tomoki TANIGUCHI ,  Yoshihiko MUTOU

IPC: F02C7/18 ,  F23R3/14

CPC classification number: F02C7/18 ,  F23R3/14 ,  F05D2260/232

Abstract: A gas turbine engine includes a cooling air supply passage that feeds air from a compressor, as a cooling medium, to a turbine by swirling the air in a circumferential direction. The cooling air supply passage includes an entry zone to which the air enters, and a swirl zone in which the air flowing past the entry zone is circumferentially redirected. The gas turbine engine also includes a chamber branching from the swirl zone to capture foreign particles in the air. The chamber is formed to meet the relation: α≥β where, when viewed in a radial direction, α is an angle defined by the swirl zone relative to a horizontal direction and β is an angle defined between the chamber and the swirl zone.