COMPONENT, CORRESPONDING GAS TURBINE ENGINE AND SEALING METHOD

摘要

A component (161) for a gas turbine engine (20) includes a body including a cold side surface (184) adjacent to a mate face (180). A plurality of ridges (185) extends from the cold side surface. A seal member (182) abuts the plurality of ridges to define a plurality of cooling passages (187). The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet (188) defined at the first position and a second, different inlet (188) defined at the second position. A method of sealing between adjacent components (161A,161B) of a gas turbine engine is also disclosed.