Patent ID: 7237387

Claim:
A gas turbine comprising: an annular combustion chamber having an inner wall and an outer wall; a high pressure turbine nozzle having a plurality of stationary vanes distributed around an axis that coincides with the axis of the combustion chamber, the vanes having airfoils secured to inner and outer platforms in the form of juxtaposed ring sectors with inside faces defining between them a flow path through the turbine nozzle for the gas stream coming from the combustion chamber; and connection means for mechanically connecting the turbine nozzle to downstream end portions of the inner and outer walls of the combustion chamber; wherein: the downstream end portions of the inner and outer walls of the combustion chamber are pressed against the inner and outer platforms respectively of the vanes of the turbine nozzle substantially all the way to the downstream ends of the platforms; and the connection means are formed by substantially radial connection screws implanted in vane airfoils of the turbine nozzle, passing through holes formed in the end portions of the inner and outer walls of the combustion chamber.