Patent ID: 8689560

Claim:
A gas turbo set, comprising: a first, high pressure, turbine; a second, low pressure, turbine positioned to receive air which has passed through the first high pressure turbine; a combustion chamber connected between the first turbine and the second turbine and operated by auto-ignition such that the second, low pressure turbine is positioned to receive the air after the air first passes from the first, high pressure turbine, and then through the combustion chamber before being received by the second, low pressure turbine; and a first shaft, wherein the first turbine and the second turbine are arranged on the first shaft which may be rotated about an axis, wherein a second outer periphery of the second, low pressure, turbine is larger than a first outer periphery of the first, high pressure, turbine with respect to the axis, wherein the second, low pressure, turbine is arranged radially further outwards from the axis than the first, high pressure, turbine, and wherein the combustion chamber includes a stream area arranged next to the first turbine, a mixing region positioned between the stream area and the second turbine, with the stream area embodied as a diffuser for which a first radial distance of a stream area radial outer wall increases in a flow direction with respect to the axis while the mixing region and the combustion region extend both along an outer wall along which a second radial distance remains constant with respect to the axis while the combustion region extends along an inner wall having a third radial distance which increases in the flow direction with respect to the axis so there is a narrowing of the cross section of the combustion region in the flow direction, wherein fuel-ducting means lead into the diffuser to lead fuel into the diffuser.