Multi-chamber airfoil cooling insert for turbine vane

Details Multi-chamber airfoil cooling insert for turbine vane Multi-chamber airfoil cooling insert for turbine vane

F - Mech Eng,Light,Heat,Weapons

01

D

170/81

F01D 5/12 (2006.01) F01D 5/18 (2006.01)

Patent

CA 1221915

ABSTRACT OF THE DISCLOSURE An airfoil-shaped turbine vane has a single, unitary insert 22 therein 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, so that the forward chamber is 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 rear- ward chambers.

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