Burner system and method for damping such a burner system

• US 8,631,654 B2
• Filed: 03/07/2011
• Issued: 01/21/2014
• Est. Priority Date: 04/28/2010
• Status: Expired due to Fees

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Bethke, Sven
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): WALTHOUR, SCOTT J
• Application Number:
  US13/388,347
• Publication Number:
  US 20120291438A1
• Time in Patent Office: 1,051 Days
• Field of Search: 607/37, 607/48, 607/56, 60/393.7, 607/25, 181/213, 244/1.N
• US Class Current: 60/725
• CPC Class Codes: F23M 20/005 Noise absorbing means
• CPC Class Codes: F23R 2900/00014 Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators silence apparatus using resonance F01N1/023
• CPC Class Codes: F23R 3/286 having fuel-air premixing devices F23R3/30 takes precedence
• CPC Class Codes: F23R 3/46 Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
• CPC Class Codes: F23R 3/54 Reverse-flow combustion chambers

Abstract

A burner system is provided that includes at least two adjacent burners that are separate from each other. Each of the two burners has at least one combustion chamber and a head end. The head end includes at least a fuel injection and a fuel-air premix. Each burner has a cap with a cap side and cap upper side, wherein at least the cap upper side is arranged ahead of the head end, seen in the direction of flow. In this manner, a burner plenum is formed between the cap upper side and the head end. The at least two burner plenums thus formed have an acoustic connection. A method for damping such a burner system is also provided.

Claims

1. A burner system, comprising:

at least two adjacent burners that are separate from each other, each of the at least two burners comprising;

at least one combustion chamber,

a head end comprising at least one fuel injection means and a fuel-air premix means, and

a cap having a cap side and a cap top side,

wherein at least the cap top side is arranged ahead of the head end, viewed in the direction of flow, such that a respective burner plenum is formed between the cap top side and the head end, wherein the cap side is arranged at least partially around the head end, and wherein the cap side is spaced apart from the head end in a radial direction,

wherein the respective burner plenum of each burner has an acoustic connection to the separate and adjacent at least one other burner'"'"'s respective burner plenum, wherein the acoustic connection is a ring shaped tube connecting the burner plenums, the ring shaped tube forming an annular channel passing from one burner plenum through the next adjacent burner plenum and ending in the same burner plenum in which it began, and

wherein an annular passage for compressor air is defined by the cap side and the head end.

2. A gas turbine comprising:

a compressor for compressing air ingested through an intake,

a burner system where the compressed air is mixed with a fuel, the burner system comprising;

at least two adjacent burners that are separate from each other, each of the at least two burners comprising;

at least one combustion chamber,

a head end comprising at least one fuel injection means and a fuel-air premix means, and

a cap having a cap side and a cop top side,

wherein at least the cap top side is arranged ahead of the head end, viewed in the direction of flow, such that a respective burner plenum is formed between the cap top side and the head end, wherein the cap side is arranged at least partially around the head end, and wherein the cap side is spaced apart from the head end in a radial direction,

wherein the respective burner plenum of each burner has an acoustic connection to the separate and adjacent at least one other burner'"'"'s respective burner plenum, wherein the acoustic connection is a ring shaped tube connecting the burner plenums, the ring shaped tube defining an annular channel passing from one burner plenum through the next adjacent burner plenum and ending in the same burner plenum in which it began, and

wherein an annular passage for compressor air is defined by the cap side and the head end,

a combustion chamber for combusting the mixture of air and fuel to produce a working medium, and

a turbine for expanding the working medium.