COMBUSTION CHAMBER OF GAS TURBINE ENGINE WITH SPIRAL-SHAPED AIR CIRCULATION Russian patent published in 2013 - IPC F23R3/50 

FIELD: engines and pumps.

SUBSTANCE: combustion chamber of gas turbine engine includes an internal annular wall with longitudinal axis (X-X), an external annular wall, and a variety of fuel spray systems. External annular wall is centred along longitudinal axis and encloses the internal wall so that their common annular space forming a flame tube can be restricted. Variety of fuel spray systems includes pilot injectors alternating with pilot gas injectors in circumferential direction. In addition, combustion chamber includes at least one air inlet hole opening to the flame tube on its front end and essentially in longitudinal direction. External wall includes a variety of pilot cavities uniformly distributed around longitudinal axis. Each pilot cavity passes in longitudinal direction between two longitudinal ends of the external wall and in radial direction to the outside of that wall. Pilot cavities are fed with air that is outside in relation to the combustion chamber in one and the same circumferential direction. Each pilot injector opens in radial direction to pilot cavity. Each injector of full throttle opens in radial direction between two adjacent pilot cavities.

EFFECT: improving gas turbine engine efficiency, reducing the weight and production costs by creating the combustion chamber that is fed with air having rotational movement around longitudinal axis.

7 cl, 6 dwg