COMBUSTION CHAMBER OF GAS TURBINE, AND METHOD OF REDUCTION OF PRESSURE ON IT Russian patent published in 2013 - IPC F02C1/00 

FIELD: machine building.

SUBSTANCE: combustion chamber of a gas turbine with increased stability of a combustion process includes a casing, a flame tube, at least one flame injector for injection of fuel to mix with air in the flame tube, and blades. Casing has the first end, the second end and the first holes located near the second end. Flame tube is arranged radially inside the casing so that the first pass is formed between them. Blades are attached to the casing near the first holes and branched from it radially to the first pass in the direction to the flame tube so that blades suppress larger part of tangential component of velocity of air flow entering the first pass through the first holes; as a result, air is supplied in axial direction to the first end of the casing. At that, blades are equally space with equal pitch in the ring enveloping the casing and have length in longitudinal direction, the first and the second walls that determine the blade thickness. The first and the second walls end on the edge that is opposite to the casing. Edges of blades are located at some distance radially from the flame tube. The first holes are equally spaced with some pitch along annular rows enveloping the casing and throughout its length. Number of blades is equal to number of the first holes in each of the annular rows.

EFFECT: improving homogeneity of a flow in a combustion chamber and reducing pressure losses.

12 cl, 4 dwg