公开(公告)号：EP2834498A4

公开(公告)日：2016-07-06

申请号：EP13772338

申请日：2013-03-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BERGMAN RUSSELL J ,  GREGG SHAWN J ,  PAPPLE MICHAEL ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO

IPC: F02C7/12 ,  F01D5/18 ,  F01D25/08 ,  F01D25/14 ,  F01D25/24

CPC classification number: F01D25/246 ,  F01D25/14 ,  F05D2240/81

Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

Abstract translation: 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一增压室流体连通，并且与定子叶片的翼型内的第一翼型冷却通道形成流体连通。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

公开(公告)号：SG11201404364TA

公开(公告)日：2014-10-30

申请号：SG11201404364T

申请日：2013-03-25

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PAPPLE MICHAEL ,  ENNACER MOHAMMED ,  DABBS THURMAN CARLO ,  LUTJEN PAUL M ,  CAPRARIO JOSEPH T ,  BERGMAN RUSSELL J ,  GREGG SHAWN J

IPC: F01D25/08 ,  F01D5/18 ,  F01D9/06 ,  F02C7/12

Abstract: A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.