Abstract: The present invention pertains to a thermoelastic connection of a hot gas-carrying injector tube (8) to the flame tube (1) suspended in the combustion chamber housing (10) of a gas turbine. The injector tube (8) is connected by corrugated spacers (7) to a circumferential intermediate ring (6), which is attached to the lower flange of the flame tube (1) by detachable fastening elements (3, 4, 5). A circumferential cooling channel (annular space 15), into which cooling air is admitted, is formed between the cone of the injector tube (8) and the intermediate ring (6). The compressor air enters the combustion space (1, 8) of the combustion chamber (10) through the annular space (15) from below, as well as through the holes (11), especially through the circumferential gap (12).

Abstract: The present invention pertains to a combustion chamber housing of a gas turbine with a laterally arranged inlet elbow (8) for compressor air, which is uniformly distributed over the perforated cone (9) via an intake heart (6), impacts on the injector tube (10) there, and is deflected in the upward direction in the direction of the flame tube and the burner. It is necessary under certain operating conditions of the gas turbine to regulate the primary air flow to the burner, without having to reduce the output of the upstream compressor. This is accomplished according to the present invention by connecting a bypass line (3) with a compensator (1) and a regulating fixture (2), through which part of the air is sent from the air inlet elbow (8) directly into the interior of the injector tube (10) via an inlet tube (4), to the lower part of the combustion chamber.

Abstract: A cylindrical combustion chamber housing of a gas turbine, in which the compressor air is fed into the lower, conical part of the combustion chamber housing, the perforated cone (5), through a lateral, arc-shaped inlet elbow (2). The inlet elbow (2) is directly joined by the intake distribution element (1), in which the compressor air is led around the perforated cone (5) on both sides. The tangential flow is converted around a cone into an axial flow through the holes (7) in the perforated cone (5). The conversion of the direction of flow of the compressor air is supported by radially arranged ribs (3). As a result, optimal cooling of the entire injector tube (6) is achieved, while the pressure drop in the air feed area (1, 2 and 5) is minimized, and the efficiency of the gas turbine is increased at the same time.