EP 0207799 A3 19880914 - IMPROVED COOLANT PASSAGE STRUCTURE FOR ROTOR BLADES IN A COMBUSTION TURBINE
Title (en)
IMPROVED COOLANT PASSAGE STRUCTURE FOR ROTOR BLADES IN A COMBUSTION TURBINE
Publication
Application
Priority
US 75165785 A 19850703
Abstract (en)
[origin: EP0207799A2] A combustion turbine rotor blade is provided with an airfoil portion having a plurality of coolant holes extending radially outwardly therethrough. The coolant holes are tapered to a smaller flow cross-section in the radially outward direction to produce more uniform cooling action over the length of the holes over which tapering is provided.
IPC 1-7
IPC 8 full level
F01D 5/18 (2006.01)
CPC (source: EP)
F01D 5/187 (2013.01); F05D 2250/231 (2013.01); F05D 2250/232 (2013.01)
Citation (search report)
[X] US 3301528 A 19670131 - HARTLEY MALLEY HARRY
Designated contracting state (EPC)
DE FR GB IT NL
DOCDB simple family (publication)
EP 0207799 A2 19870107; EP 0207799 A3 19880914; CA 1262868 A 19891114; CN 86104500 A 19870204; IE 861475 L 19870103; JP S6210402 A 19870119
DOCDB simple family (application)
EP 86305182 A 19860703; CA 512386 A 19860625; CN 86104500 A 19860701; IE 147586 A 19860604; JP 15185286 A 19860630