General Electric Company

Tony Keith Davis

Wei A Chen

Predrag Popovic

William Kirk Hessler

Wiliam K Hessler

A method for assembling a gas turbine engine includes coupling a transition piece between a combustor liner and a nozzle assembly. The method also includes extending a first portion of a flow sleeve from the transition piece about at least a portion of the combustor liner. The method further includes coupling a second portion of the flow sleeve to the first portion of the flow sleeve such that the flow sleeve second portion extends from the flow sleeve first portion and at least partially about at least a portion of the transition piece. The flow sleeve second portion includes a scoop that cooperates with the transition piece to at least partially define a unitary cooling air passage that includes a unitary scoop-shaped opening. The scoop is oriented to introduce a substantially uniform cooling air flow to the transition piece.

Flow device for turbine engine and method of assembling same

The present application provides a liner for a combustor. The combustor liner may include a mouth, a passage for a flow of fuel, a passage for a flow of air, a first zone for mixing the flow of fuel and the flow of air, and the first zone having a constant diameter. The combustor liner may have at least one transition zone with first and second side walls angled substantially in the same direction, and an off center exit. This configuration will provide a more stable flow when exiting the combustor liner.

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Greenville, SC, United States of America

Tony Keith Davis