1) Can-annular combustion chamber:
As depicted in the cross section of a gas turbine, the can-annular combustor is essentially an array of cylindrical burners installed sequentially at the exit of the compressor's discharge passage. The chamber consists of an upstream section followed by a downstream section separated by a swirl cone. The downstream section consists of a cylindrical liner followed by a dome which is formed by a number of individual flame tubes.
2) Annular combustion chamber:
The annular combustion chamber is a continuous chamber that wraps around the outer periphery of the gas turbine. It is made up of a series of cylindrical liners that are arranged in a circular pattern. Each liner has a series of fuel nozzles that inject fuel into the air. The fuel and air are mixed and burned, creating a hot gas that expands and turns the turbine blades.
The type of combustion chamber used in a gas turbine is typically determined by the size of the turbine and the fuel that is being used. Can-annular combustors are generally used in smaller turbines, while annular combustors are used in larger turbines.
