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.
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
OG exemplary drawing
 
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.