초록 ▼

A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream e

A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

대표청구항 ▼

1. A compressor diffuser for a gas turbine comprising a casing for directing compressor discharge air to one or more combustors, said casing having an upstream end and a downstream end, the downstream end of said casing defined by a peripheral annular edge, said peripheral annular edge formed with a

1. A compressor diffuser for a gas turbine comprising a casing for directing compressor discharge air to one or more combustors, said casing having an upstream end and a downstream end, the downstream end of said casing defined by a peripheral annular edge, said peripheral annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at said peripheral annular edge in an upstream direction to thereby increase flow path area for compressor discharge air exiting said casing, wherein one or more of said plurality of substantially axially-oriented slots is fitted with at least one flow-directing vane for facilitating a reversal of direction of air exiting said casing, said at least one flow-directing vane projecting through said slot inwardly toward a closed end of the slot and outwardly toward an open end of the slot. 2. The compressor diffuser of claim 1 wherein said downstream end is provided with a plurality of radially outwardly extending support struts, wherein each of said plurality of substantially axially-oriented slots lies adjacent one of said support struts. 3. The compressor diffuser of claim 2 wherein one or more struts is provided with a flow-direction vane in substantially axial alignment with a corresponding one of said substantially axially-oriented slot. 4. The compressor diffuser of claim 1 wherein said at least one flow-directing vane comprises at least two flow directing vanes. 5. The compressor diffuser of claim 2 wherein between each pair of said plurality of support struts, there are two of said substantially axially-oriented slots. 6. The compressor diffuser of claim 1 wherein each flow-directing vane presents a concave surface to air flow from the compressor, such that the air flow is turned substantially 180°. 7. The compressor diffuser of claim 6 wherein each flow directing vane projects above and below a corresponding one of said substantially axially-oriented slots. 8. The compressor diffuser of claim 6 wherein each flow-directing vane is located axially closer to said annular edge than to an upstream end of a corresponding one of said substantially axially-oriented slots. 9. The compressor diffuser of claim 5 wherein each of said two substantially axially-oriented slots is provided with a single turning vane. 10. A gas turbine comprising a compressor, an annular array of combustor cans arranged to supply combustion gases to a first stage of the turbine in a first direction, wherein said compressor includes a diffuser shaped to direct compressor discharge air in a second opposite direction to an aft end of said combustor cans for use in combustion; said diffuser having an upstream end and a downstream end, the downstream end defined by an annular peripheral edge formed with a plurality of circumferentially-spaced, substantially axially-oriented slots, wherein one or more of said plurality of circumferentially-spaced, substantially axially-oriented slots is associated with at least one flow-directing vane, aligned with an open end of the slot and projecting outward away from the slot. 11. The gas turbine of claim 10 wherein said downstream end is provided with a plurality of radially outwardly extending support struts, wherein each of said plurality of substantially axially-oriented slots lies adjacent one of said support struts. 12. The gas turbine of claim 11 wherein one or more of said struts is provided with a flow-direction vane is supported on one of said support struts in substantially axial alignment with a corresponding one of said substantially axially-oriented slots. 13. The gas turbine of claim 10 wherein said at least one flow-directing vane comprises at least two flow directing vanes. 14. The gas turbine of claim 11 wherein between each pair of said plurality support struts, there are two of said circumferentially-spaced, substantially axially-oriented slots. 15. The gas turbine of claim 10 wherein each flow-directing vane presents a concave surface to air flow from the compressor, such that the air flow is turned substantially 180°. 16. The gas turbine of claim 15 wherein each flow directing vane projects above and below a corresponding one of said circumferentially-spaced, substantially axially-oriented slots. 17. A gas turbine comprising a compressor, an annular array of combustor cans arranged to supply combustion gases to a first stage of the turbine in a first direction, wherein said compressor includes a diffuser shaped to direct compressor discharge air in a second opposite direction to an aft end of said combustor cans for use in combustion; said diffuser having an upstream end and a downstream end defined by an annular peripheral edge; andmeans located within said annular peripheral edge for enhancing reversal of compressor discharge air from said first direction to said second direction. 18. A method for enhancing air flow reversal in a gas turbine combustion system where compressor discharge air is reverse-flowed to a combustor comprising: forming a downstream annular peripheral edge of a compressor diffuser with a plurality of substantially axially-oriented slots extending from a downstream end of said diffuser in an upstream direction; andassociating at least one flow direction vane with one or more of said substantially axially-oriented slots, said at least one flow directing vane projecting through said slot inwardly toward a closed end of the slot and outwardly toward an open end of the slot.