Patent ID: 7665962
Filing Date: 2010-02-23
Classification: F01D,F05D,Y02T

Abstract:
1. A blade outer air seal for a gas turbine engine comprising: a blade ring carrier having a cooling air feed hole to supply cooling air to a blade ring air seal; a ring segment held in place by the blade ring carrier and forming the blade outer air seal with a tip of a turbine blade; the ring segment having a plurality of pockets formed by stiffener ribs and including at least one leading edge pocket, at least one middle pocket, and at least one trailing edge pocket; a metering plate secured to the stiffener ribs and forming closed pockets on leading and trailing edges and forming an open pocket on the middle pocket; an impingement ring secured between the cooling air feed hole and the metering plate, the impingement ring having a first group of impingement holes positioned over the middle pocket; and, the metering plate including a plurality of second groups of impingement holes positioned over the edge pockets.