Patent ID: 7234304

Claim:
An aerodynamic trip for a gas turbine engine, the engine having a compressor, an annular combustor having an inside wall and an outside wall, and a turbine, the engine having a centreline axis and defining an annular gas path adapted to guide a flow of hot gas from the compressor through the annular combustor to the turbine, the aerodynamic trip comprising: a plurality of cross flow ports disposed only on the inside wall of the annular combustor adjacent to a combustor exit and in communication with the compressor upstream of the turbine, each cross flow port adapted to emit a jet of compressed air into the gas path in a direction substantially perpendicular to the flow of gas in the gas path and adjacent an exit of the annular combustor to thereby introduce turbulence radially asymmetrically into the flow of hot gas substantially downstream of the annular combustor.