Patent ID: 9470419
Filing Date: 2016-10-18
CPC Classification: F23C,F23L,F23R,Y02E

Claim Text:
1. A combustion chamber in a gas turbine system for burning an air-fuel mixture, a gas mixture or a gas-liquid mixture, comprising: an outer casing provided with an inner space, an inlet end and an outlet end, whereby the inner space tapers towards the outlet end over a determined section of the length of the casing; a flame tube located in the inner space of the outer casing and provided with an inner space, an inlet end and an outlet end on sides corresponding to those of the inlet end and the outlet end of the outer casing, whereby the flame tube tapers towards its outlet end over a determined section of the length of the flame tube, and whereby an inner surface of the outer casing and an outer surface of the flame tube form an annular channel therebetween, the flame tube comprising flow apertures which penetrate through its casing and interconnect the annular channel and the inner space of the flame tube; a cover part arranged in the inlet ends of the outer casing and the flame tube and provided with flow apertures opening up into the annular channel; a combustion air inlet part which is arranged in an outer surface of the cover part and which is in connection with the flow apertures of the cover part; a fuel jet located in the middle of the cover part and ex-tending inside the flame tube for feeding fuel into the flame tube; and an outlet part which is arranged in the outlet ends of the outer casing and the flame tube and which is provided with an outlet channel connected to the outlet end of the flame tube, wherein the combustion air inlet part comprises an inlet channel whose initial part is located substantially perpendicularly and eccentrically with respect to a longitudinal axis of the combustion chamber and which continues on a surface of the cover part spirally towards an end of the channel such that its volume decreases, and whereby a side of the inlet channel facing the cover part is in connection with the flow apertures of the cover part, and that the flow apertures of the flame tube are formed by means of protrusions which project radially from the flame tube and in which the flow apertures of the flame tube are located substantially perpendicularly against a combustion air flow coming spirally from the flow apertures of the cover part.