초록 ▼

A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls

A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge and at least one channel is formed between the airfoil sidewalls for channeling cooling air. The cooling air is directed to flow substantially perpendicularly to a direction of air flowing around the airfoil in a portion of the combustor assembly that is to be cooled. The method also includes coupling the at least one sleeve around the portion of the combustor assembly to be cooled. Also provided are a sleeve and an airfoil for use in a combustor assembly.

대표청구항 ▼

1. A method for assembling a combustor assembly, said method comprises: providing at least one sleeve having a plurality of inlets;coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve, wherein the at least one airfoil includes a pair of opposing

1. A method for assembling a combustor assembly, said method comprises: providing at least one sleeve having a plurality of inlets;coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve, wherein the at least one airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge, a first end portion and a second end portion, each of the end portions extends substantially perpendicularly between the pair of opposing sidewalls, at least one first channel and at least one second channel that are each formed between the airfoil sidewalls and extend between the first end and second end portions for channeling cooling air therethrough, and at least one recessed section defined between the pair of opposing sidewalls for joining the at least one first channel to the at least one second channel, wherein at least a portion of the at least one recessed section extends a depth into a cooling passage that is shallower than a depth of each of the at least one first channel and the at least one second channel such that each of the at least one first channel and the at least one second channel channels the air in a direction that is substantially perpendicular to a direction of air flowing around said airfoil in said cooling passage; andcoupling the at least one sleeve around the portion of the combustor assembly to be cooled. 2. A method in accordance with claim 1 wherein coupling at least one airfoil to at least one of the plurality of inlets further comprises coupling the at least one airfoil such that the leading edge and the trailing edge are substantially aligned with the direction of the air flowing in the portion of the combustor assembly to be cooled. 3. A method in accordance with claim 1 wherein coupling at least one airfoil to at least one of the plurality of inlets comprises coupling at least one airfoil to at least a plurality of inlets, wherein the at least one airfoil includes said at least one first channel and said at least one second channel for each inlet of the plurality of inlets. 4. A method in accordance with claim 1 wherein coupling at least one airfoil to at least one of the plurality of inlets comprises coupling a plurality of airfoils wherein at least a portion of the airfoils are aligned such that the leading edge and the trailing edge of each airfoil of the plurality of airfoils are substantially aligned with respect to each other. 5. A method in accordance with claim 4 wherein coupling a plurality of airfoils comprises coupling the airfoils so that the airfoils facilitate a turbulent flow of the air in the cooling passage. 6. A sleeve for use in a combustor assembly, said sleeve comprising a plurality of airfoil projections defined in said sleeve, each airfoil projection configured to channel cooling air into a cooling passage of said combustor assembly, each airfoil projection comprising: a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge;a first end portion and a second end portion, each of said end portions extends substantially perpendicularly to and extends between said pair of opposing sidewalls;at least one first channel and at least one second channel that are each defined between said pair of opposing sidewalls and extend from said first end portion to said second end portion for channeling cooling air therethrough; andat least one recessed section defined between said pair of opposing sidewalls and configured to join said at least one first channel and said at least one second channel, wherein at least a portion of said at least one recessed section extends a depth into said cooling passage that is shallower than a depth of each of said at least one first channel and said at least one second channel such that each of said at least one first channel and said at least one second channel channels the air in a direction that is substantially perpendicular to a direction of air flowing around said airfoil in said cooling passage. 7. A sleeve in accordance with claim 6 wherein said airfoil projection is substantially symmetrical about a center plane extending between said opposing sidewalls. 8. A sleeve in accordance with claim 6 wherein said leading edge of each airfoil projection is cusp-shaped. 9. A sleeve in accordance with claim 6 wherein each airfoil projection comprises a plurality of channels defined between said pair of opposing sidewalls. 10. A sleeve in accordance with claim 9 wherein each said channel of said plurality of channels for each airfoil projection has an airflow direction, wherein each said channel airflow direction is parallel with one another.