초록 ▼

In a gas turbine having a transition region between a combustor and turbine stage including a transition piece duct extending between a combustor liner and the turbine stage; an impingement sleeve surrounding the transition piece, the impingement sleeve having a plurality of apertures therein; and a

In a gas turbine having a transition region between a combustor and turbine stage including a transition piece duct extending between a combustor liner and the turbine stage; an impingement sleeve surrounding the transition piece, the impingement sleeve having a plurality of apertures therein; and a compressor diffuser directing compressor discharge air into the transition region, an improvement wherein the diffuser includes a pair of outer walls flaring outwardly in a direction of compressor discharge air flow; and a pair of baffles within a flow area defined by the pair of outer diffuser walls which divide the flow area into three discrete flow passages. One passage has a substantially radial flow component; a second passage has both radial and axial flow components; and a third passage has a substantially axial flow component.

대표청구항 ▼

[ What is claimed is:] [1.] A compressor discharge diffuser for a gas turbine comprising:an internal casing defining a pair of outer diffuser walls flaring outwardly in a direction of compressor discharge air flow; anda pair of baffles within a flow area defined by said pair of outer diffuser walls

[ What is claimed is:] [1.] A compressor discharge diffuser for a gas turbine comprising:an internal casing defining a pair of outer diffuser walls flaring outwardly in a direction of compressor discharge air flow; anda pair of baffles within a flow area defined by said pair of outer diffuser walls which divide said flow area into three discrete flow passage, wherein one of said three passages diverts compressor discharge air flow substantially radially; and further wherein another of said three passages diverts compressor discharge flow primarily in an axial direction.