Patent ID: 9500099
Filing Date: 2016-11-22
CPC Classification: F01D,F01L,F02C,F04D,F05D

Claim Text:
1. A method of cooling a component of a gas turbine engine, comprising the steps of: (a) communicating a first portion of a cooling air through a first plurality of openings of a cover plate positioned relative to a platform of the component to impingement cool a first cooling cavity of the platform; (b) communicating a second portion of the cooling air through a second plurality of openings of the cover plate to cool a second cooling cavity of the platform using a cooling method different from impingement cooling; and wherein said step (b) includes: communicating the second portion of the cooling air radially through the second plurality of openings, then circulating the second portion axially, and then communicating the second portion of the cooling air circumferentially through the second cooling cavity.