摘要：
A combustor assembly 100 for a gas turbine engine (10 Fig. 1) has an inner liner wall 111 and an outer liner wall 112, both extending annularly around the combustor centreline 11. Together, the inner liner wall and the outer liner wall define an involute wall 110 extending at least partially as a spiral curve from a circumferential reference line 95 to form an involute combustion chamber 105. One or more of the inner liner wall and the outer liner wall each define a first dilution opening 121 and a shaped dilution opening 122, for the flow of oxidizer/air into the combustion chamber. Further dilution openings may be in the form of slotted openings 123, which may be arranged in a herringbone pattern 124, 125. The arrangement of dilution holes allows quench air to enter the combustor and lower the combustion gas temperature, and as such reduces nitrogen oxide (NOx).
权利要求：
WHAT IS CLAIMED IS:
1. A combustor assembly, the combustor assembly comprising:
an inner liner wall extended annularly around a combustor centerline; and
an outer liner wall extended annularly around the combustor centerline, wherein the inner liner wall and the outer liner wall together define an involute wall extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline, wherein the involute wall defines an involute combustion chamber therewithin, and wherein one or more of the inner liner wall and the outer liner wall each define a first dilution opening therethrough and a shaped dilution opening therethrough.
2. The combustor assembly of claim 1, wherein the first dilution opening and the shaped dilution opening are in alternating circumferential arrangement through the involute wall.
3. The combustor assembly of claim 1 or claim 2, wherein the first dilution opening and the shaped dilution opening are defined through the inner liner wall and the outer liner wall.
4. The combustor assembly of any preceding claim, wherein the first dilution opening through the inner liner wall is directly across the combustion chamber from the shaped dilution opening through the outer liner wall.
5 The combustor assembly of any preceding claim, wherein the involute wall defines a plurality of slotted openings in circumferential arrangement therethrough. 6. The combustor assembly of claim 5, wherein the plurality of slotted openings is disposed downstream of the first dilution opening and the shaped dilution opening. 2: The combustor assembly of claim 5 or claim 6, wherein the plurality of slotted openings is disposed downstream of the first dilution opening and the shaped dilution opening within three diameter-lengths of the first dilution opening.
8. The combustor assembly of any of claims 5 to 7, wherein the plurality of slotted openings defines a substantially herringbone pattern through one or more of the inner liner wall or the outer liner wall.
8. The combustor assembly of any of claims 5 to 8, wherein the plurality of slotted openings comprises a plurality of first slotted opening in circumferential
arrangement and a second slotted opening in circumferential arrangement disposed downstream of the first slotted opening.
10. The combustor assembly of claim 9, wherein the second slotted opening is disposed between approximately 75 degrees to approximately 105 degrees offset from the first slotted opening.
11. The combustor assembly of any of claims 5 to 10, wherein the first slotted opening is disposed between approximately 30 degrees and approximately 60 degrees offset relative to an axial reference line of the combustor assembly.
12. The combustor assembly of any preceding claim, wherein the first dilution opening (121) defines a substantially circular cross-sectional area, a substantially U- shaped cross-sectional area, a substantially V-shaped cross-sectional area, or a substantially crescent-shaped cross-sectional area, or combinations thereof. 13. The combustor assembly of any preceding claim, wherein the involute wall defines a shearing protrusion at the shaped dilution opening, wherein the shearing protrusion defines a shape of the shaped dilution opening.
14. The combustor assembly of any preceding claim, wherein the shearing protrusion at the volute wall defines a substantially triangular cross-sectional area. 15. The combustor assembly of any preceding claim, wherein the combustor assembly defines a trapped vortex combustor assembly.
16. The combustor assembly of any preceding claim, wherein the combustor assembly defines a primary combustion zone and a secondary combustion zone downstream of the primary combustion zone, and wherein the first dilution opening and the shaped dilution opening are each defined in fluid communication with the secondary combustion zone.
17. The combustor assembly of any preceding claim, further comprising:
an outer shell substantially surrounding the involute wall defined by the inner liner wall and the outer liner wall, wherein the involute wall is attached to the outer shell, and wherein the outer shell defines a cooling opening therethrough in fluid communication with the involute wall
18. The combustor assembly of any preceding claim, further comprising:
an outer diffuser wall extended radially outward of the outer shell; and
an inner diffuser wall extended radially inward of the outer shell, wherein the outer diffuser wall and the inner diffuser wall together define a pressure vessel surrounding the outer shell and the involute wall.
19. A gas turbine engine, the engine comprising the combustor assembly of any preceding claim, wherein the combustor assembly (100) defines a trapped vortex combustor.
Amendments have been filed as follows:-
WHAT IS CLAIMED IS:
1. A combustor assembly, the combustor assembly comprising:
an inner liner wall extended annularly around a combustor centerline; and
an outer liner wall extended annularly around the combustor centerline,
wherein the inner liner wall and the outer liner wall together define an involute wall
extended at least partially as a spiral curve from a circumferential reference line
around the combustor centerline, wherein the involute wall defines an involute
combustion chamber therewithin, and wherein the inner liner wall defines a first
dilution opening therethrough and the outer liner wall defines a second dilution
opening therethrough; wherein
the first dilution opening defines a first cross-sectional area;
the involute wall includes a shearing protrusion at the second dilution opening,
wherein the shearing protrusion defines a second cross-sectional area of the second
dilution opening; and
the first cross-sectional area defines a first shape and the second cross-
sectional area defines a second shape, the second shape being a different shape other
than the first shape.
2. The combustor assembly of claim 1, wherein each of the inner liner wall and
the outer liner wall defines one or more first dilution openings therethrough and one
or more second dilution openings therethrough.
3. The combustor assembly of claim 2, wherein the first dilution opening and the
second dilution opening are in alternating circumferential arrangement through each
of the inner liner wall and the outer liner wall.
4. The combustor assembly of any preceding claim, wherein the first dilution
opening through the inner liner wall is directly across the combustion chamber from
the second dilution opening through the outer liner wall.
5. The combustor assembly of any preceding claim, wherein the involute wall
defines a plurality of slotted openings in circumferential arrangement therethrough.
6. The combustor assembly of claim 5, wherein the plurality of slotted openings
1s disposed downstream of the first dilution opening and the second dilution opening.
7. The combustor assembly of claim 35 or claim 6, wherein the plurality of slotted openings is disposed downstream of the first dilution opening and the second dilution opening within three diameter-lengths of the first dilution opening.
8. The combustor assembly of any of claims 5 to 7, wherein the plurality of slotted openings defines a substantially herringbone pattern through one or more of the inner liner wall or the outer liner wall.
9, The combustor assembly of any of claims 5 to 8, wherein the plurality of slotted openings comprises a plurality of first slotted opening in circumferential arrangement and a second slotted opening in circumferential arrangement disposed downstream of the first slotted opening.
10. The combustor assembly of claim 9, wherein the second slotted opening is disposed between approximately 75 degrees to approximately 105 degrees offset from the first slotted opening.
11. The combustor assembly of any of claims 5 to 10, wherein the first slotted opening is disposed between approximately 30 degrees and approximately 60 degrees offset relative to an axial reference line of the combustor assembly.
12. The combustor assembly of any preceding claim, wherein the first shape is substantially circular, and wherein the second shape is substantially U-shaped, substantially V-shaped, or substantially crescent-shaped, or combinations thereof. 13. The combustor assembly of any preceding claim, wherein the shearing protrusion at the volute wall defines a substantially triangular cross-sectional area. 14. The combustor assembly of any preceding claim, wherein the combustor assembly defines a trapped vortex combustor assembly.
15. The combustor assembly of any preceding claim, wherein the combustor assembly defines a primary combustion zone and a secondary combustion zone downstream of the primary combustion zone, and wherein the first dilution opening and the second dilution opening are each defined in fluid communication with the secondary combustion zone.
16. The combustor assembly of any preceding claim, further comprising:
an outer shell substantially surrounding the involute wall defined by the inner liner wall and the outer liner wall, wherein the involute wall is attached to the outer
shell, and wherein the outer shell defines a cooling opening therethrough in fluid communication with the involute wall.
17. The combustor assembly of any preceding claim, further comprising:
an outer diffuser wall extended radially outward of the outer shell; and
an inner diffuser wall extended radially inward of the outer shell, wherein the outer diffuser wall and the inner diffuser wall together define a pressure vessel surrounding the outer shell and the involute wall.
18. A gas turbine engine, the engine comprising the combustor assembly of any preceding claim, wherein the combustor assembly defines a trapped vortex combustor.