Combustion chamber of a gas turbine

• US 6,192,669 B1
• Filed: 03/20/1998
• Issued: 02/27/2001
• Est. Priority Date: 03/20/1997
• Status: Expired due to Fees

• Current Assignee: Alstom SA
• Original Assignee: Asea Brown Boveri AG (ABB Limited)
• Inventors: Keller, Jakob, Suter, Roger
• Primary Examiner(s): Thorpe, Timothy S.
• Assistant Examiner(s): Gartenberg, Ehud
• Application Number:
  US09/044,910
• Time in Patent Office: 1,075 Days
• Field of Search: 60/39, 60/36
• US Class Current: 60/804
• CPC Class Codes: F23R 3/425 Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
• CPC Class Codes: F23R 3/52 Toroidal combustion chambers

Abstract

A combustion chamber in a gas-turbine, wherein the combustion chamber has an annular-toroidal-shaped interior space. A plurality of burners are arranged on the periphery of the combustion chamber, wherein the burners are operatively connected to the annular-toroidal-shaped interior space so as to initiate a swirl flow. The swirl flow forms a vortex core and the vortex core ensures the stability of the flame front.

Claims

1. A combustion chamber of a gas-turbine, said combustion chamber comprising:

at least one annular toroidal interior space of quasi-circular cross-section;

a plurality of burners, wherein each burner of said plurality of burners is in operative connection with said at least one annular toroidal interior space so as to be tangentially arranged on a periphery of said combustion chamber and wherein each burner of said plurality of burners is a pre-mix burner;

a hot-gas outlet duct defining an incident-flow plane of a downstream turbine of said gas-tuxbine, said hot-gas duct connected to said annular toroidal interior space, wherein said hot-gas duct is branched off in a peripheral tangential direction of said annular toroidal interior space; and

wherein in cross-sectional of said annular toroidal interior space, the axis vector pointing out of any of said burners and the axis vector pointing into said hot-gas outlet duct, point in the same direction.

2. The combustion chamber as claimed in claim 1, wherein said hot-gas duct has guide blades at first end thereof, said guide blades being in operative connection with moving blades of said downstream turbine.

3. The combustion chamber as claimed in claim 1, wherein said at least one annular toroidal interior space is encased by a shell, and wherein a cooling medium flows in an intermediate space formed between said shell and an external shape of said at least one annular toroidal interior space.

4. The combustion chamber as claimed in claim 1, wherein said burners are in operative connection with a plenum, and wherein combustion air from said plenum feeds said burners.