초록 ▼

A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction hav

A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.

대표청구항 ▼

1. A combustor comprising: an inner liner, at least a portion of the inner liner being a single inner annular wall;an outer liner spaced apart from the inner liner, at least a portion of the outer liner being a single outer annular wall;a single annular combustor chamber formed between the single in

1. A combustor comprising: an inner liner, at least a portion of the inner liner being a single inner annular wall;an outer liner spaced apart from the inner liner, at least a portion of the outer liner being a single outer annular wall;a single annular combustor chamber formed between the single inner annular wall and the single outer annular wall of the inner and outer liners, the annular combustor chamber having a central axis;fuel nozzles each having an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber;a plurality of nozzle air holes defined through the single inner annular wall and the single outer annular wall, the plurality of nozzle air holes adjacent to and downstream of the fuel nozzles, the nozzle air holes configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber, a central axis of the nozzle air holes having a tangential component relative to the central axis of the annular combustor chamber. 2. The combustor according to claim 1, wherein the central axes of a substantial number of said nozzle air holes have the tangential component. 3. The combustor according to claim 1, wherein the central axis of said at least one of the nozzle air holes has an axial component relative to the central axis of the annular combustor chamber, the axial component being in a same direction as the axial component of the fuel flow. 4. The combustor according to claim 1, wherein the nozzle air holes are circumferentially distributed in the single inner annular wall and the single outer annular wall so as to be in sets opposite one another, to form a first circumferential band. 5. The combustor according to claim 4, further comprising a second circumferential band of nozzle air holes circumferentially distributed in the single inner annular wall and the single outer annular wall, the second circumferential band being downstream of the first circumferential band. 6. The combustor according to claim 1, wherein the number of nozzle air holes in the inner liner substantially exceeds the number of fuel nozzles. 7. The combustor according to claim 1, wherein the fuel nozzles are part of an annular fuel manifold, the fuel manifold being positioned inside the annular combustor chamber. 8. The combustor according to claim 1, further comprising a mixing zone of reduced radial height in the annular combustor chamber, downstream of the plurality of nozzle air holes. 9. A gas turbine engine of the type having a fan, a compressor section, a combustor, and a turbine section, the combustor comprising: an inner liner, at least a portion of the inner liner being a single inner annular wall;an outer liner spaced apart from the inner liner, at least a portion of the outer liner being a single outer annular wall;an annular combustor chamber formed between the single inner annular wall and the single outer annular wall of the inner and outer liners, the annular combustor chamber having a central axis;fuel nozzles each having an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber;a plurality of nozzle air holes defined through the single inner annular wall and the single outer annular wall, the plurality of nozzle air holes adjacent to and downstream of the fuel nozzles, the nozzle air holes configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber, a central axis of the nozzle air holes having a tangential component relative to the central axis of the annular combustor chamber. 10. The gas turbine engine according to claim 9, wherein the central axes of a substantial number of said nozzle air holes have the tangential component. 11. The gas turbine engine according to claim 9, wherein the central axis of said at least one of the nozzle air holes has an axial component relative to the central axis of the annular combustor chamber, the axial component being in a same direction as the axial component of the fuel flow. 12. The gas turbine engine according to claim 9, wherein the nozzle air holes are circumferentially distributed in the single inner annular wall and the single outer annular wall, to form a first circumferential band. 13. The gas turbine engine according to claim 12, further comprising a second circumferential band of nozzle air holes circumferentially distributed in single inner annular wall and the single outer annular wall, the second circumferential band being downstream of the first circumferential band. 14. The gas turbine engine according to claim 9, wherein the number of nozzle air holes in the inner liner substantially exceeds the number of fuel nozzles. 15. The gas turbine engine according to claim 9, wherein the fuel nozzles are part of an annular fuel manifold, the fuel manifold being positioned inside the annular combustor chamber. 16. The gas turbine engine according to claim 9, further comprising a mixing zone of reduced radial height in the annular combustor chamber, downstream of the plurality of nozzle air holes. 17. A method for mixing fuel and nozzle air in an annular combustor chamber formed between a single inner annular wall and a single outer annular wall of inner and outer liners, comprising: injecting fuel in a fuel direction having at least an axial component relative to a central axis of the annular combustor chamber;injecting high pressure nozzle air from an exterior of the annular combustor chamber through holes made in the single inner annular wall of the annular combustor chamber into a fuel flow, the holes being oriented such that nozzle air is generally radially injected and has a tangential component relative to a central axis of the annular combustor chamber; andinjecting high pressure nozzle air from an exterior of the annular combustor chamber through holes made in the single outer annular wall of the annular combustor chamber into a fuel flow, the holes being oriented such that nozzle air is generally radially injected and has a tangential component relative to a central axis of the annular combustor chamber, the tangential components of the nozzle air of the inner liner and outer liner being in a same direction. 18. The method according to claim 17, wherein the holes through the inner liner and outer liner are oriented such that injecting nozzle air comprises injecting nozzle air with an axial component in a same direction as the fuel flow. 19. The method according to claim 17, wherein injecting nozzle air comprises injecting nozzle air from at least two circumferential bands, each circumferential band comprising a circumferential distribution of said holes in the inner liner and oppositely in the outer liner.