Patent ID: 7013652
Filing Date: 2006-03-21
Classification: F01D,F02C,F05D

Abstract:
1. A gas turbo set comprising at least one compressor, at least one combustion chamber, at least one turbine, a common rotor shaft, and a supporting structure surrounding the rotor shaft, the rotor shaft bearing a plurality of rows of compressor moving blades within the compressor and a plurality of turbine moving blades within the turbine, the moving blades arranged in rows alternating in a throughflow direction of the gas turbo set, the rows including compressor guide vane rows and turbine guide vane rows, wherein guide vanes of a guide vane row are fastened on a plurality of separate annulus-segment shaped elements, said elements being releasably fastened to the supporting structure, with a plurality of annulus-segment shaped elements being contiguously arranged in a circumferential direction of the gas turbo set and forming a complete annulus with at least one guide vane row, the annulus-segment shaped elements being individually removable from the supporting structure while maintaining the supporting structure; wherein the combustion chamber has an annular design, the combustion chamber comprising a plurality of combustion chamber annulus-segment shaped elements that are releasably coupled to the supporting structure and are removable from the supporting structure while maintaining the supporting structure; and wherein the combustion chamber further comprises a plurality of coaxially disposed carrying disks and a plurality of burners, each burner being attached to a separate combustion chamber annulus-segment shaped element and each combustion chamber annulus-shaped element being disposed in space between the disks and independently removable from the space.