Patent ID: 7827801

Claim:
A transition for a gas turbine engine, the transition comprising a transition wall having an outer surface and an inner surface and comprising an inboard side, an outboard side, and a first lateral side and a second lateral side connecting the inboard and the outboard sides, the transition wall further comprising: a. a first entry port through the outer surface along the inboard side communicating with at least one first cooling channel within the transition wall originating at the first entry port and terminating at a first exit port through the outer surface disposed along the first lateral side; and b. a second entry port through the outer surface along the first lateral side, disposed relative to an inboardly opening scoop extending from the first lateral side for entrapment of a portion of air passing over the transition from the inboard side toward the outboard side, the second entry port communicating with at least one second cooling channel originating at the second entry port and extending from the second entry port to a second exit port through the outer surface disposed along the outboard side.