| 摘要 |
<p>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.</p> |
