Claims
- 1. A gas turbine combustion chamber comprising a burner, means for the supply of fuel and an atomizer, wherein the means for the supply of fuel are provided such that the fuel is injected in areas with maximum airflow velocity.
- 2. A gas turbine combustion chamber comprising a burner, means for the supply of fuel and an atomizer, wherein the means for the supply of fuel are provided such that the fuel is injected in areas with maximum local air mass flow.
- 3. A gas turbine combustion chamber in accordance with claim 1, wherein a primary air passage of the burner feeds the combustion chamber with a major amount of the air required for mixing and burning.
- 4. A gas turbine combustion chamber in accordance with claim 1, wherein the means for the supply of fuel comprises at least one of individual feed tubes and exit openings protruding into a free cross-section of the atomizer.
- 5. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and the exit openings issue from an outside into the area of airflow.
- 6. A gas turbine combustion chamber in accordance with claim 5, wherein the at least one of the feed tubes and the exit openings are combined with a central fuel injection.
- 7. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and exit openings are arranged in a single row.
- 8. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and the exit openings are arranged in multiple rows.
- 9. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and the exit openings are provided with different outlet diameters.
- 10. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and the exit openings are provided in different arrangements.
- 11. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and the exit openings comprise a device for active cooling.
- 12. A gas turbine combustion chamber in accordance with claim 4, wherein the at least one of the feed tubes and the exit openings comprise an air flushing device for the purging of fuel.
- 13. A gas turbine combustion chamber in accordance with claim 4, wherein the feed tubes are arranged radially starting out from a central fuel line.
- 14. A gas turbine combustion chamber in accordance with claim 4, wherein the feed tubes have at least one of an aerodynamic and profiled design.
- 15. A gas turbine combustion chamber in accordance with claim 4, wherein the feed tubes extend at least one of radially and axially to a nozzle axis.
- 16. A gas turbine combustion chamber in accordance with claim 4, wherein the exit openings are combined with a central fuel injection.
- 17. A gas turbine combustion chamber in accordance with claim 1, wherein fuel is injected into a primary air passage carrying a major amount of the airflow.
- 18. A gas turbine combustion chamber in accordance with claim 1, and comprising a pilot swirler and a pilot nozzle arranged centrally for central fuel injection.
- 19. A method for introducing fuel into a gas turbine combustion chamber comprising a burner, means for the supply of fuel and an atomizer, comprising:
injecting fuel from the means for the supply of fuel into areas having at least one of maximum airflow velocity and maximum local air mass flow.
Priority Claims (1)
Number |
Date |
Country |
Kind |
10219354.1 |
Apr 2002 |
DE |
|
Parent Case Info
[0001] This application is a Continuation-In-Part of U.S. patent application Ser. No. ______ (number unknown at the time of filing) by DORR et al., entitled Gas Turbine Combustion Chamber with Defined Fuel Input for the Improvement of the Homogeneity of the Fuel-Air Mixture, filed Apr. 30, 2003, the entirety of which is incorporated by reference herein.
[0002] This application claims priority to German Patent Application DE10219354.1 filed Apr. 30, 2002, the entirety of which is incorporated by reference herein.