Gas turbine fuel injector comprising a splitter having a cavity
A fuel injector comprising a first air swirler passage and a second air swirler passage extending axially through the fuel injector and arranged to direct air through the fuel injector, a splitter arranged between the first air swirler passage and the second air swirler passage and comprising a first splitter surface having a first divergent portion which is divergent in the downstream direction, a second splitter surface located radially inward of the first splitter surface and having a second divergent portion which is divergent in the downstream direction, a third splitter surface located radially inward of the first and second splitter surface, and a first connecting surface extending between the second and third splitter surfaces, wherein a first cavity is formed between the first and second splitter surfaces, and the second divergent portion comprises at least one opening in fluid communication with the first cavity.
1. A fuel injector comprising:
a first air swirler passage and a second air swirler passage extending axially through the fuel injector and arranged to direct air through the fuel injector;
a splitter arranged between the first air swirler passage and the second air swirler passage and comprising:
a first splitter surface having a first divergent portion which is divergent in a downstream direction;
a second splitter surface located radially inward of the first splitter surface and having a second divergent portion which is divergent in the downstream direction;
a third splitter surface located radially inward of the first and second splitter surfaces; and
a first connecting surface extending between the second and third splitter surfaces; wherein
a first cavity is formed between the first and second splitter surfaces, and the second divergent portion comprises at least one opening in fluid communication with the first cavity, and
the second splitter surface further comprises a dividing portion so as to define a second cavity between the second and third splitter surfaces and the first connecting surface.
2. The fuel injector according to claim 1 , wherein the second splitter surface comprises a plurality of openings in fluid communication with the first cavity.
3. The fuel injector according to claim 2 , wherein the openings are distributed circumferentially around the second splitter surface.
4. The fuel injector according to any one of the preceding claim 1 , wherein the first divergent portion is frustoconical.
5. The fuel injector according to claim 1 , wherein the second divergent portion is frustoconical.
6. The fuel injector according to claim 1 , wherein the first divergent portion extends substantially parallel to the second divergent portion.
7. The fuel injector according to claim 1 , further comprising a second connecting surface extending between the first and second splitter surfaces.
8. The fuel injector according to claim 1 , wherein the first connecting surface extends substantially perpendicularly to the second divergent portion.
9. The fuel injector according to claim 1 , wherein the third splitter surface comprises a third divergent portion which is divergent in the downstream direction.
10. The fuel injector according to claim 1 , wherein the second cavity is sealed from the first cavity.
11. The fuel injector according to claim 1 , wherein the second splitter surface is divided into a plurality of circumferential arcuate segments, with the at least one opening being provided at a join between two circumferential sections.
12. The fuel injector according to claim 11 , wherein the radius of each of the arcuate segments varies along a length of each of the arcuate segments.
13. A gas turbine engine for an aircraft comprising:
an engine core comprising combustion equipment, a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades; and
a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft,
wherein the combustion equipment comprises at least one fuel injector according to claim 1 .
14. The gas turbine engine according to claim 13 , wherein:
the turbine is a first turbine, the compressor is a first compressor, and the core shaft is a first core shaft;
the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor; and
the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.
15. A fuel injector comprising:
a first air swirler passage and a second air swirler passage extending axially through the fuel injector and arranged to direct air through the fuel injector;
a splitter arranged between the first air swirler passage and the second air swirler passage and comprising:
a first splitter surface having a first divergent portion which is divergent in a downstream direction;
a second splitter surface located radially inward of the first splitter surface and having a second divergent portion which is divergent in the downstream direction;
a third splitter surface located radially inward of the first and second splitter surfaces; and
a first connecting surface extending between the second and third splitter surfaces; wherein
a first cavity is formed between the first and second splitter surfaces, and the second divergent portion comprises at least one opening in fluid communication with the first cavity, and
the second splitter surface is divided into a plurality of circumferential arcuate segments, with the at least one opening being provided at a join between two circumferential sections.
16. The fuel injector according to claim 15 , wherein the radius of each of the arcuate segments varies along a length of each of the arcuate segments.