US 7,320,222 B2 | ||
Burner, method for operating a burner and gas turbine | ||
Patrick Flohr, Winter Springs, Fla. (US); Werner Krebs, Mülheim (Germany); and Günther Schulze, Seukendorf (Germany) | ||
Assigned to Siemens Aktiengesellschaft, Munich (Germany) | ||
Appl. No. 10/506,122 PCT Filed Feb. 28, 2003, PCT No. PCT/EP03/02079 § 371(c)(1), (2), (4) Date Aug. 31, 2004, PCT Pub. No. WO03/074937, PCT Pub. Date Sep. 12, 2003. |
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Claims priority of application No. 02005136 (EP), filed on Mar. 07, 2002. | ||
Prior Publication US 2005/0106519 A1, May 19, 2005 | ||
Int. Cl. F02C 7/045 (2006.01); F23R 3/14 (2006.01); F23D 1/00 (2006.01) |
U.S. Cl. 60—725 [60/737; 60/748; 431/114] | 20 Claims |
1. A gas turbine combustor, comprising:
a combustor channel;
an air inlet position adapted to provide combustion air;
a fuel inlet position adapted to provide fuel;
a mixing region fluidly coupled with the air inlet position and the fuel inlet position, and adapted to allow mixing of the
fuel and combustion air; and
a first Helmholtz resonator located within the combustor channel at a resonator position and comprising resonator ports, not
supplying fuel, located downstream of the mixing region and sized and configured to decouple the air ratio fluctuations and
combustion oscillations.
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