Impingement cooled transition duct
An impingement cooling apparatus for cooling a surface of a transition duct disposed between a combustor and a turbine stage of a gas turbine engine is described. The transition duct being disposed in a compressed air plenum, comprising: an impingement sleeve surrounding the transition duct and spaced a distance therefrom to form a flow volume therebetween: apertures in the impingement sleeve; each of the apertures having an area: adjacent ones of apertures being separated by a spacing: a closed end at a turbine end of the flow volume; an exit at a combustor end of the flow volume; a flow sleeve within the compressed air-plention surrounding the combustor; a flared entry portion at an end of the flow sleeve overlapping the exit and forming an aerodynamic converging shape therebetween; a flow of air through the aerodynamic converging shape flowing toward the combustor being effective to reduce a pressure at the exit below a pressure in the compressed air plenum whereby a pressure drop across the impingement sleeve produces an impingement jet of air from each of the plurality of apertures directed toward the transition duct; and at least one of the distance, the area and the spacing being non-uniform over the impingement sleeve to control a cooling in the surface.
- Assignee:
- General Electric Co., Schenectady, NY
- Patent Number(s):
- US 4719748
- OSTI ID:
- 5420793
- Resource Relation:
- Patent File Date: Filed date 15 Dec 1986
- Country of Publication:
- United States
- Language:
- English
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