Dual fuel nozzle with liquid filming atomization for a gas turbine engine
A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, the outer wall defines a convergent-divergent nozzle. An inner air swirler along the axis to define an annular liquid passage therebetween, the annular liquid passage terminates upstream of the convergent-divergent nozzle and an annular fuel gas passage around the axis between the outer air swirler and the inner air swirler.
1. A fuel nozzle for a combustor of a gas turbine engine comprising:
an outer air swirler along a nozzle axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, said outer wall defines a convergent-divergent nozzle;
an inner air swirler along said nozzle axis to define an annular fuel gas passage around said nozzle axis between said outer air swirler and said inner air swirler, said annular fuel gas passage terminates with a multiple of skewed slots, oriented axially and upstream of the convergent-divergent nozzle, to direct a fuel gas and impart a swirl thereto;
an annular liquid passage surrounding a helical inflow vane and defined around said nozzle axis and within the inner air swirler; and
an air inflow tube with the helical inflow vane along said nozzle axis within said inner air swirler, said air inflow tube defines a central air passage.
2. The fuel nozzle as recited in claim 1 , wherein said outer wall axially extends beyond said inner air swirler.
3. The fuel nozzle as recited in claim 2 , wherein said outer wall defines a filming region from about 0-55% of a length of said outer wall axially beyond said inner air swirler.
4. The fuel nozzle as recited in claim 2 , wherein a divergent section of said outer wall defines an angle of between 0-30 degrees with respect to said axis.
5. The fuel nozzle as recited in claim 4 , wherein said inner air swirler defines said annular liquid passage therebetween, said annular liquid passage receives a liquid fuel from within a second tube that terminates in the inner air swirler and separates the liquid fuel from the fuel gas.
6. The fuel nozzle as recited in claim 5 , wherein said second tube is transverse to said nozzle axis.
7. The fuel nozzle as recited in claim 6 , wherein an end section of said annular liquid passage is turned radially inward toward said nozzle axis to direct the liquid fuel at least partially radially inward.
8. A fuel nozzle for a combustor of a gas turbine engine comprising:
an outer air swirler along a nozzle axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, said outer wall defines a convergent-divergent nozzle; and
an inner air swirler along said axis to define an annular liquid passage therebetween and an annular fuel gas passage, said annular liquid passage surrounding a helical inflow vane and defined around said nozzle axis and within the inner swirler, said annular liquid passage terminates upstream of said convergent-divergent nozzle;
said annular fuel gas passage around said axis between said outer air swirler and said inner air swirler, said annular fuel gas passage terminates with a multiple of skewed slots, oriented axially and upstream of the convergent-divergent nozzle, to direct a fuel gas and impart a swirl thereto; and
an air inflow tube with the helical inflow vane along said nozzle axis within said inner air swirler, said air inflow tube defines a central air passage.
9. The fuel nozzle as recited in claim 8 , wherein said outer wall axially extends beyond said inner air swirler.
10. The fuel nozzle as recited in claim 8 , wherein said outer wall defines a filming region from about 0-55% of a length of said outer wall axially beyond said inner air swirler.
11. The fuel nozzle as recited in claim 8 , wherein said outer wall defines a divergent section at an angle of between about 0-30 degrees with respect to said axis.
12. The fuel nozzle as recited in claim 8 , wherein said outer wall defines a divergent section with a filming region from about 0-55% of a length of said outer wall axially beyond said inner air swirler, said divergent section defined at an angle of between about 0-30 degrees with respect to said axis.
13. A method of directing a fuel gas and a liquid through a fuel nozzle and into a combustor of a gas turbine engine, comprising:
directing an airflow through an outer annular air passage around a nozzle axis;
directing the fuel gas through an annular fuel gas passage radially within the outer annular air passage; and
directing the liquid though an annular liquid passage radially within the annular fuel gas passage, the liquid at least partially impacting upon a filming region of a convergent-divergent nozzle;
the fuel nozzle comprising an outer air swirler along the nozzle axis, said outer air swirler defines the outer annular air passage between an outer wall and an inner wall, said outer wall defines the convergent-divergent nozzle;
an inner air swirler along said nozzle axis to define the annular fuel gas passage around said nozzle axis between said outer air swirler and said inner air swirler, said annular fuel gas passage terminates with a multiple of skewed slots, oriented axially and upstream of the convergent-divergent nozzle, to direct the fuel gas and impart a swirl thereto;
the annular liquid passage surrounding a helical inflow vane and defined around said nozzle axis and within the inner air swirler; and
an air inflow tube with the helical inflow vane along said nozzle axis within said inner air swirler, said air inflow tube defines a central air passage.
14. The method as recited in claim 13 , further comprising: swirling airflow through a central the air inflow tube along the axis.
15. The method as recited in claim 13 , further comprising: directing the airflow through the outer annular air passage at least partially radially inward, the outer annular air passage at least partially defined by the outer wall which forms the convergent divergent nozzle.
16. The method as recited in claim 15 , further comprising: directing the liquid at least partially radially inward.
17. A fuel nozzle for a combustor of a gas turbine engine comprising:
an outer air swirler along a nozzle axis, said outer air swirler defines an outer annular air passage between an outer wall and an inner wall, said outer wall defines a convergent-divergent nozzle;
an inner air swirler along said nozzle axis to define an annular fuel gas passage around said nozzle axis between said outer air swirler and said inner air swirler, said annular fuel gas passage terminates with a multiple of skewed slots, oriented axially and upstream of the convergent-divergent nozzle, to direct a fuel gas and impart a swirl thereto;
an annular liquid passage surrounding a helical inflow vane and defined around said nozzle axis and within the inner air swirler, said annular liquid passage receives the liquid fuel from within a tube that terminates in the inner air swirler and separates the liquid fuel from the fuel gas; and
an air inflow tube with the helical inflow vane along said nozzle axis within said annular liquid passage, said air inflow tube defines a central air passage.
18. The fuel nozzle as recited in claim 17 , wherein said outer wall defines a filming region from about 0-55% of a length of said outer wall axially beyond said inner air swirler.
19. The fuel nozzle as recited in claim 18 , wherein said inner air swirler defines the annular liquid passage therebetween.
20. The fuel nozzle as recited in claim 19 , wherein an end section of said annular liquid passage is turned radially inward.
21. The fuel nozzle as recited in claim 17 , wherein said outer wall extends beyond said inner air swirler and defines a divergent section at an angle of between 0-30 degrees with respect to said axis.
22. The fuel nozzle as recited in claim 17 , wherein said outer wall defines a filming region from about 0-55% of a length of said outer wall axially beyond said inner air swirler.