FIELD: machine building.
SUBSTANCE: gas-turbine engine includes an annular combustion chamber, a sectoral turbine nozzle guide vanes located at the chamber outlet and sealing devices axially arranged between combustion chamber and nozzle guide vanes. Sealing devices include a circumferential seal with axial elasticity, which includes axial support devices on exit edge of the combustion chamber and exit circumferential edge that is of sectoral type. Each sector of exit edge is arranged in one line with sector of nozzle guide vanes and includes axial support devices on entry edge of the sector of the nozzle guide vanes. The other invention of the group refers to a seal packing for the above gas-turbine engine, which is made as a single part and contains two circumferential edges. One of the edges has radial slots setting the sectors between themselves, which has the possibility of free movement irrespective of each other.
EFFECT: inventions allow improving tightness between a combustion chamber and nozzle guide vanes and simplifying installation of sealing devices.
15 cl, 10 dwg
