| 摘要 |
The invention is a cooling airflow modulation system for use on gas turbine engines. The system utilizes one or more circumferential manifolds for collecting and providing a source of high-pressure cooling air to hot turbine parts. The cooling air is directed to the manifolds through valved passageways that collect compressor discharge air and direct that air radially inwardly and axially downstream to manifold locations. Multiple passageways aand manifolds provide a means for maintaining pressure in the hot turbine parts while cooling airflow volume is being modulated through selected manifold and passageway combinations.
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