EP 0207799 A2 19870107 - Improved coolant passage structure for rotor blades in a combustion turbine.
Title (en)
Improved coolant passage structure for rotor blades in a combustion turbine.
Title (de)
Kühlkanäle für die Schaufeln einer Gasturbine.
Title (fr)
Canaux de refroidissement pour les aubes d'une turbine à gaz.
Publication
Application
Priority
US 75165785 A 19850703
Abstract (en)
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)
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