A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented
A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.
대표청구항▼
1. A combustor comprising: an inner liner;an outer liner spaced apart from the inner liner;an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis;fuel nozzles in fluid communication with the annular combustor chamber to inject fuel
1. A combustor comprising: an inner liner;an outer liner spaced apart from the inner liner;an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis;fuel nozzles in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented axially to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber;nozzle air inlets in fluid communication with the annular combustor chamber to inject nozzle air in the annular combustor chamber, the nozzle air inlets configured for high pressure air to be injected from an exterior of the liners through the nozzle air inlets into the annular combustor chamber and impinge on the injected fuel so as to encourage mixing of injected fuel and injected air, a central axis of each of a plurality of the nozzle air inlets having a tangential component and an axial component relative to the central axis of the annular combustion chamber, the tangential component of the central axes of the nozzle air inlets being oriented in a same common direction;a plurality of dilution air holes defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes into the combustor chamber, a central axis of each of a plurality of the dilution air holes having a tangential component relative to the annular combustor chamber, the tangential component of the central axes of the dilution air holes being oriented in a same common direction opposite to that of the tangential component of the nozzle air inlets; anda plurality of cooling air inlets defined through the inner and outer liner at least downstream of the dilution air holes, the cooling air inlets being substantially smaller than the dilution air holes. 2. The combustor according to claim 1, further comprising a mixing zone of reduced radial height between the nozzle air inlets and the dilution air holes. 3. The combustor according to claim 2, wherein the inner and outer liners concurrently defining a flaring zone in the annular combustion chamber, the dilution air holes being downstream of the flaring zone, and the nozzle air inlets and the mixing zone being upstream of the flaring zone. 4. The combustor according to claim 1, wherein the central axis of said dilution 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. 5. The combustor according to claim 1, wherein the dilution air holes are circumferentially distributed in the inner liner and in the outer liner so as to be in sets opposite one another, to form a first circumferential band. 6. The combustor according to claim 5, wherein the dilution air holes in the outer liner are provided in a set of larger-dimension holes and in another set of smaller-dimension holes, the larger-dimension holes and smaller-dimension holes being circumferentially distributed in an alternating sequence. 7. The combustor according to claim 1, wherein the number of dilution air holes in the outer liner exceeds the number of dilution air holes in the inner liner. 8. 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. 9. The combustor according to claim 1, wherein the dilution air holes are circumferentially distributed in the inner liner to form a circumferential band. 10. The combustor according to claim 9, wherein the dilution air holes are circumferentially distributed in the outer liner to form the circumferential band opposite the circumferential band in the inner liner. 11. The combustor according to claim 1, wherein the dilution air holes are circumferentially distributed in the outer liner to form a circumferential band. 12. The combustor according to claim 1, wherein the fuel nozzles are in fuel injection sites, with an axis of an opening of each of the fuel injection sites being substantially parallel to the central axis. 13. The combustor according to claim 1, wherein the fuel nozzles are located at a first position along the central axis, with the annular chamber extending toward a second position along the central axis, the plurality of dilution air holes all being located between the first position and the second position. 14. The combustor according to claim 1, wherein the fuel nozzles are not oriented toward the central axis.
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이 특허에 인용된 특허 (21)
Harris Mark M. (Phoenix AZ) Marsh David N. (Phoenix AZ), Annular combustor with outer transition liner cooling.
Waslo Jennifer (Scotia NY) Kuwata Masayoshi (Ballston Lake NY) Washam Roy M. (Schenectady NY), Impingement cooled liner for dry low NOx venturi combustor.
Prociw Lev A. (Willowdale CAX) Bouchard Alain (St. Charles Borromee CAX) Bolduc Pierre (St. Amable CAX) Stastny Honze (West St. Bruno CAX), Radially mounted air blast fuel injector.
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