公开(公告)号：JP2002349205A

公开(公告)日：2002-12-04

申请号：JP2002113376

申请日：2002-04-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BALKCUM III J TYSON ,  LIANG GEORGE ,  REMLEY TIMOTHY J ,  WILLIAMS CHRISTOPHER CHARLES ,  PRZIREMBEL HANS R

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/22

Abstract: PROBLEM TO BE SOLVED: To provide a lightweight hollow shrouded turbine blade. SOLUTION: A turbine blade 10 includes an airfoil part 16 and a hollow blade tip shroud 18 connected to the airfoil part 16. The hollow tip shroud 18 preferably has a cast partitioned structure and a plurality of ribs 22. Those rib 22 function as load bearing structures and form a plurality of shroud core parts 42, 44, 46, 48, 50, and 52. Each shroud core part is connected to a cooling fluid supply source and includes a plurality of holes for supplying cooling fluid to an outer surface part of the shroud.

公开(公告)号：DE60213328T2

公开(公告)日：2007-07-26

申请号：DE60213328

申请日：2002-04-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BALKCUM J TYSON III ,  LIANG GEORGE ,  REMLEY TIMOTHY J ,  WILLIAMS CHRISTOPHER CHARLES ,  PRZIREMBEL HANS R

IPC: F01D5/22 ,  F01D5/18 ,  F01D5/20 ,  F01D11/08

Abstract: The turbine blade (10) comprises an airfoil section (16) and a hollow blade tip shroud (18) joined to the airfoil section (16). The hollow tip shroud (18) is preferably a cast, compartmentalized structure and has a plurality of ribs (40) acting as load bearing structures and defining a plurality of shroud core sections (42,44,46,48,50,52). Each of the shroud core sections (42,44,46,48,50,52) communicates with a supply of cooling fluid and has a plurality of apertures (66) for supplying cooling fluid to exterior portions of the shroud.

公开(公告)号：DE60213328D1

公开(公告)日：2006-09-07

申请号：DE60213328

申请日：2002-04-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BALKCUM J TYSON III ,  LIANG GEORGE ,  REMLEY TIMOTHY J ,  WILLIAMS CHRISTOPHER CHARLES ,  PRZIREMBEL HANS R

IPC: F01D5/22 ,  F01D5/18 ,  F01D5/20 ,  F01D11/08

Abstract: The turbine blade (10) comprises an airfoil section (16) and a hollow blade tip shroud (18) joined to the airfoil section (16). The hollow tip shroud (18) is preferably a cast, compartmentalized structure and has a plurality of ribs (40) acting as load bearing structures and defining a plurality of shroud core sections (42,44,46,48,50,52). Each of the shroud core sections (42,44,46,48,50,52) communicates with a supply of cooling fluid and has a plurality of apertures (66) for supplying cooling fluid to exterior portions of the shroud.