Patent ID: 8099943

Claim:
A method of redirecting a stream of swirling combustion gases flowing through an exhaust duct of a gas turbine engine, the method comprising the steps of: a) receiving an annular stream of combustion gases from a turbine section into an annular inlet portion of a passage defined by the exhaust duct, the annular inlet portion having an inlet axis, the annular stream of combustion gases having a swirling motion about the inlet axis; b) splitting the stream of combustion gases so as to obstruct the swirling motion of the stream by providing a flow splitter at one circumferential location in the passage, the flow splitter dividing the passage into first and second annular side portions; c) reducing a pressure differential in the combustion gases in which the swirling motion has been obstructed by allowing the annular stream of combustion gases to flow from the first annular side portion to the second annular side portion via at least one bypass channel; and d) discharging the combustion gases from the exhaust duct.