ANNULAR COMBUSTION CHAMBER OF GAS TURBINE ENGINE AND METHOD OF ITS OPERATION Russian patent published in 2009 - IPC F23R3/50 

FIELD: pumps and engines.

SUBSTANCE: combustion chamber is designed for operation in aviation and surface gas turbine engines and gas turbine plants. Annular combustion chamber of gas turbine engine comprises the following components: coaxially installed external and internal bodies, annular diffuser installed at the combustion chamber inlet and formed by walls of internal and external circuits, flame tube installed in annular space between bodies, which separates the space into two parts with creation of external and internal annular channels and is made of external and internal shells, every of which is equipped with annular niche flame stabiliser in front part, which is formed by annular front, bottom and back walls, with openings for air supply on back wall of every niche and shells of flame tube, having inlet channel with flame tube head that comprises annular front grid fixed on walls of inlet channel upstream niches and formed of guiding and stabilising elements with longitudinal channels installed evenly along circumference between them, front and niche fuel systems comprising separate annular headers with nozzles installed along circumference for fuel supply from front system upstream niche stabilisers, and from the niche one - to cavities of niche stabilisers. Front grid of guiding and stabilising elements is made of two adjacent crowns of radial flame stabilisers inverted with their free ends opposite to each other, formed in their cross section by wedge-shaped profiles with blunt leading edges pointed to diffuser side, and end sections installed opposite to them and inverted to the side of flame tube outlet, at that plane of every separate radial stabiliser end is installed at the angle from 30° to 90° to generatrices of internal surfaces of flame tube inlet channel walls upstream annular niches, besides, every separate radial stabiliser is turned around vertical axis that lies in plane passing through the middle of its end and leading edge top, at the angle from 45° to 60° relative to longitudinal axis of combustion chamber, external and internal annular channels of combustion chamber are additionally separated into two parts by separate profiled annular walls, every of which is fixed to its flame tube shell downstream the first belts of transverse openings in it behind niche back wall, nozzles of niche fuel system are arranged as pneumatic and installed on walls of every niche.

EFFECT: higher burning efficiency and specified temperature field at the outlet, lower level of smoking.

25 cl, 5 dwg