초록

A fuel lance (7) for introducing fuel into a gas flow in a combustor (1) of a gas turbine engine includes a region of the lance (7) through which the fuel is introduced into the gas flow having a generally helical formation (12).

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1. A fuel lance useful for introducing fuel into a gas flow in a combustor of a gas turbine engine, the lance comprising: an elongate lance body including a generally helically shaped region through which fuel can be introduced into the gas flow, wherein the helically shaped region comprises a helic

1. A fuel lance useful for introducing fuel into a gas flow in a combustor of a gas turbine engine, the lance comprising: an elongate lance body including a generally helically shaped region through which fuel can be introduced into the gas flow, wherein the helically shaped region comprises a helical groove on the outer surface of the lance extending generally in the axial direction of the lance;at least one fuel outlet configured and arranged to introduce fuel into the gas flow, positioned on the surface of the helical groove; andwherein the at least one fuel outlet comprises a plurality of fuel outlets arranged on the surface of the helical groove and spaced apart in the axial and/or circumferential and/or radial directions. 2. A fuel lance according to claim 1, wherein a diameter of the fuel lance in a region where fuel is introduced into the gas flow is not constant in the axial direction. 3. A fuel lance according to claim 1, wherein the helically shaped region includes a projection on the outer surface of the lance extending generally in the axial direction of the lance. 4. A fuel lance according to claim 1, further comprising: multiple fuel passages extending through the lance body, configured and arranged to introduce different fuels into the gas flow. 5. A fuel lance according to claim 4, further comprising: a first fuel outlet in the surface of the groove and a second fuel outlet in the outer surface of the lance;wherein the multiple fuel passages comprise a first fuel passage configured and arranged to supply a first fuel to the first fuel outlet and a second fuel passage configured and arranged to supply a second fuel to the second fuel outlet. 6. A fuel lance according to claim 1, further comprising: a lance tip; anda central passage configured and arranged to supply oil to the lance tip. 7. A fuel lance according to claim 1, wherein each of the plurality of fuel outlets comprises a hole or slot. 8. A fuel lance according to claim 1, wherein each of the plurality of fuel outlets is arranged so that fuel is introduced into the groove in an axial or radial direction. 9. A fuel lance according to claim 1, wherein each of the plurality of fuel outlets is arranged so that the fuel is introduced into the groove in a tangential direction. 10. A fuel lance according to claim 1, further comprising: a hydrogen rich fuel flowing through the lance body and into the gas flow. 11. A gas turbine engine having sequential combustion, the engine comprising: a first combustor configured and arranged to produce hot gas;a second combustor downstream of the first combustor, configured and arranged to receive said hot gas from the first combustor; anda fuel lance according to claim 1 in the second combustor, configured and arranged to introduce fuel into the hot gas. 12. A method of operating a sequential combustion gas turbine, the method comprising: producing hot gas in a first combustor;receiving said hot gas in a second combustor downstream of the first combustor; anddirectly introducing fuel into the hot gas in the second combustor with a fuel lance according to claim 1, said hot gas flowing around the lance. 13. A method according to claim 12, further comprising: receiving hot gas formed in the first combustor in a first turbine downstream of the first combustor and upstream of the second combustor; andpassing said hot gas from said first turbine to said second combustor. 14. A method according to claim 13, further comprising: receiving hot gas formed in the second combustor in a second turbine downstream of the second combustor.