Patent ID: 6334297
Filing Date: 2002-01-01
Classification: F23R,Y02T

Abstract:
A combustor arrangement for a gas turbine engine comprising a combustion chamber, fuel nozzles, and a bled diffuser located upstream of said combustion chamber to, in use, direct an airflow from an upstream compressor into the combustor with the fuel nozzles arranged in use to supply fuel into the combustion chamber where it is mixed and combusted with the airflow from the compressor, a bled diffuser adapted to bleed off a portion of said airflow from a main airflow into the combustion chamber; wherein the combustor arrangement comprises at least one bleed duct, the at least one bleed duct is connected to the bled diffuser to, in use, return and direct air bled from the diffuser to a main gas flow through the engine at a location downstream of the fuel nozzles, said bled diffuser being defined by radially inner and outer diffuser duct walls and, in use, the main airflow flowing between said inner and outer diffuser duct walls, at least one opening being defined in each of the diffuser duct walls through which, in use, air is bled with said radially inner duct wall surrounding a path for the main air flow from said upstream compressor and said openings in said diffuser duct walls being of a size to increase the pressure of the air in said bled diffuser to a magnitude to allow the air fed through said at least one bleed duct to enter the main airflow downstream of said fuel nozzles, said radially inner and radially outer walls of said bled diffuser being shaped to provide a chamber of a size that will slow the velocity of the air entering from said upstream compressor.