EP 0182588 B1 19880928 - MULTI-CHAMBER AIRFOIL COOLING INSERT FOR TURBINE VANE
Title (en)
MULTI-CHAMBER AIRFOIL COOLING INSERT FOR TURBINE VANE
Publication
Application
Priority
US 67184684 A 19841115
Abstract (en)
[origin: EP0182588A1] An airfoil-shaped combustion turbine vane has a single, unitary insert 22 which is divided by a plurality of radially extending ribs 38, 40, and 42 into a forward chamber 30, and successively rearward chambers 32, 34, and 36, with throttling means 48 being provided at the inlet to the rearward chambers while the airflow 46 to the forward chamber is not restricted, with the forward chamber being at a higher pressure than the rearward chambers so that the impingement jets through the impingement ports 56 are at a higher velocity than the impingement jets through the impingement ports 58 and 60 from the lower pressure rearward chambers.
IPC 1-7
IPC 8 full level
CPC (source: EP KR)
F01D 5/00 (2013.01 - KR); F01D 5/189 (2013.01 - EP); F05D 2260/201 (2013.01 - EP)
Designated contracting state (EPC)
CH DE FR GB LI SE
DOCDB simple family (publication)
EP 0182588 A1 19860528; EP 0182588 B1 19880928; CA 1221915 A 19870519; CN 1004291 B 19890524; CN 85108282 A 19860827; DE 3565298 D1 19881103; IN 163070 B 19880806; IT 1186049 B 19871118; IT 8522785 A0 19851111; JP H0379522 B2 19911219; JP S61126302 A 19860613; KR 860004224 A 19860618; MX 161444 A 19900927
DOCDB simple family (application)
EP 85308230 A 19851113; CA 495185 A 19851113; CN 85108282 A 19851114; DE 3565298 T 19851113; IN 755CA1985 A 19851022; IT 2278585 A 19851111; JP 24817185 A 19851107; KR 850008558 A 19851115; MX 37585 A 19851024