公开(公告)号：US09255479B2

公开(公告)日：2016-02-09

申请号：US13705573

申请日：2012-12-05

Applicant: ALSTOM Technology Ltd.

Inventor： Ernst Pauli ,  Sergey Shchukin ,  Daniel Seng

IPC: F04D29/58 ,  F01D5/08 ,  F04D29/053 ,  F04D29/32

CPC classification number: F01D5/08 ,  F01D5/082 ,  F04D29/053 ,  F04D29/321 ,  F04D29/584 ,  F05B2260/201 ,  F05B2260/2241 ,  F05D2260/201 ,  F05D2260/22141

Abstract: A high-pressure compressor (12), in particular in a gas turbine (10), has a compressor rotor (17) which is surrounded by a stator (18, 19) thereby forming a main flow channel (25) and which is delimited at the compressor outlet by an end face (30) substantially extending in the radial direction, along which end face cooling air (21) is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face (30) is provided with a first system (23, 24) for improving the heat transfer between the cooling air (21) and the end face (30).

Abstract translation: 特别是在燃气轮机（10）中的高压压缩机（12）具有由定子（18,19）围绕的压缩机转子（17），从而形成主流道（25）并被界定 在压缩机出口处，通过沿径向方向大致延伸的端面（30），为了冷却目的沿其沿径向方向输送端面冷却空气（21）。 实现了延长的使用寿命，其中端面（30）设置有用于改善冷却空气（21）和端面（30）之间的热传递的第一系统（23,24）。

公开(公告)号：US20130170954A1

公开(公告)日：2013-07-04

申请号：US13705573

申请日：2012-12-05

Applicant: ALSTOM TECHNOLOGY LTD.

Inventor： Ernst Pauli ,  Sergey Shchukin ,  Daniel Seng

IPC: F01D5/08

CPC classification number: F01D5/08 ,  F01D5/082 ,  F04D29/053 ,  F04D29/321 ,  F04D29/584 ,  F05B2260/201 ,  F05B2260/2241 ,  F05D2260/201 ,  F05D2260/22141

Abstract: A high-pressure compressor (12), in particular in a gas turbine (10), has a compressor rotor (17) which is surrounded by a stator (18, 19) thereby forming a main flow channel (25) and which is delimited at the compressor outlet by an end face (30) substantially extending in the radial direction, along which end face cooling air (21) is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face (30) is provided with a first system (23, 24) for improving the heat transfer between the cooling air (21) and the end face (30).

Abstract translation: 特别是在燃气轮机（10）中的高压压缩机（12）具有由定子（18,19）围绕的压缩机转子（17），从而形成主流道（25）并被界定 在压缩机出口处，通过沿径向方向大致延伸的端面（30），为了冷却目的沿其沿径向方向输送端面冷却空气（21）。 实现了延长的使用寿命，其中端面（30）设置有用于改善冷却空气（21）和端面（30）之间的热传递的第一系统（23,24）。

公开(公告)号：US09835088B2

公开(公告)日：2017-12-05

申请号：US14491040

申请日：2014-09-19

Applicant: ALSTOM Technology Ltd

Inventor： Sergey Shchukin ,  Robert Marmilic

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/12

CPC classification number: F02C7/12 ,  F01D5/18 ,  F01D5/187 ,  F01D25/12 ,  F05D2240/127 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: The disclosure pertains to a cooled wall for separating a hot gas flow path of a gas turbine from a cooling flow including at least one turbulator rib extending from the wall into the cooling flow, and having a height, a width for providing heat transfer enhancement for the cooled wall. The turbulator rib has filets at its root with a filet radius. In order to increase the heat transfer enhancement of the turbulator rib, the filet at the downstream side of turbulator rib is extending into the cooled wall with a penetration depth. Further, the disclosure relates to specific embodiments in which the cooled wall with turbulator ribs is configured as the sidewall of an airfoil, a combustor wall or a heat shield.