Fuel injector arrangement having an igniter
An arrangement for a combustion chamber the arrangement comprising a combustion chamber, an injector for injecting fuel into the combustion chamber and an igniter for supplying a spark for igniting fuel so injected, wherein the injector has a passage through which air is supplied to the combustion chamber in use, the igniter being positioned upstream of the combustion chamber such that a spark generated by the igniter is conveyed along the passage by the injector air.
1. An arrangement for a gas turbine engine, the arrangement comprising:
a combustion chamber.,
an injector for injecting fuel into the combustion chamber, and
an igniter for supplying a spark for igniting fuel so injected, wherein
the injector has a passage through which air is supplied to the combustion chamber in use, the igniter being positioned upstream of the combustion chamber such that a spark generated by the igniter is conveyed along the passage by the air, and
the igniter has a tip for generating the spark, the tip terminating upstream of the injector.
2. An arrangement according to claim 1 , wherein the passage has a length between 5 mm and 40 mm.
3. An arrangement according to claim 1 , wherein the injector is a concentric injector having an axial pilot injector and a coaxially located mains injector positioned radially outside the pilot injector.
4. An arrangement according to claim 3 , wherein the passage conveys air to the pilot injector.
5. An arrangement according to claim 1 , wherein the injector has an upstream edge past which air flows in use to enter the injector and a downstream edge facing the combustor and the passage extends axially from the upstream edge to the downstream edge.
6. An arrangement according to claim 1 , wherein the injector has an outer circumference and a downstream edge facing the combustor, wherein the passage extends first radially and then axially from the outer circumference to the downstream edge.
7. An arrangement according to claim 3 , wherein the injector has a coating of a dielectric material downstream of the igniter tip to prevent the spark earthing to the injector.
8. An arrangement according to claim 7 , wherein the dielectric material is a thermal barrier coating of yttria stabilised zirconia.
9. A gas turbine having an arrangement according to claim 3 .
10. A method of supplying a spark to ignite a fuel, the method comprising the steps of:
providing a combustor, an injector, and an igniter;
supplying fuel from the injector into the combustor; and
supplying air to the combustor through a passage in the injector,
the air mixing with the fuel to provide a combustible mixture and conveying with the air supplied through the passage a spark generated by the igniter,
the igniter being disposed upstream of an injector fuel supply opening, and
the igniter has a tip for generating the spark, the tip terminating upstream of the injector.
11. A method according to claim 10 , wherein the igniter has a tip generating the spark and the tip is located within the passage.
12. A method of supplying a spark to ignite a fuel, the method comprising the steps of:
providing a combustor, an injector, and an igniter;
supplying fuel from the injector into the combustor; and
supplying air to the combustor through a passage in the injector, the air mixing with the fuel to provide a combustible mixture and conveying with the air supplied through the passage a spark generated by the igniter,
wherein the igniter has a tip generating the spark and the tip is located upstream of the passage.
13. A method according to claim 10 , wherein the spark exists for at least 2 ms.
14. A method according to claim 13 , wherein the time taken for the spark to travel from the igniter to the combustor through the passage is less than 2 ms.
15. A method according to claim 10 , wherein the fuel is supplied by the injector to the combustor as atomised droplets.