Structure for separating the internal areas of a high pressure and a low pressure turbine

Abstract

Convex sealing bottom (10) for a twin-shaft turbine of the type comprising a series of convex disks constrained to each other by means of a series of pins, each disk of said disks comprises an outer shaped edge which is engaged with a corresponding annular surface (71) of an inner grooved surface (72) of a ring (70) for obtaining an axial seal. The series of disks comprises three disks, a first disk (12), a second disk (13) and a third disk (14) respectively. The three disks are fixed to each other centrally by means of a series of spokes (30) and are constrained in pairs respectively by means of a series of pins which are arranged orthogonally to the three disks to minimize the relative movements of the three disks in an axial direction at the same time allowing the radial dilatations of the three disks themselves.

Description

technical field [0001] The present invention relates to a convex sealing bottom of a twin-shaft gas turbine. Background technique [0002] A gas turbine is a rotary heat engine that uses the gases produced by combustion to convert the enthalpy of the gases into useful work and provides mechanical work on a rotating shaft. [0003] Thus, a turbomachine typically includes a compressor or turbocompressor into which air is brought under pressure from the outside into the interior of the compressor. [0004] Various nozzles deliver fuel, which mixes with air to form an air-fuel combustible mixture. [0005] A so-called turbine or turboexpander with an axial compressor converts the enthalpy of the gases combusted in the combustion chamber to provide mechanical energy to the user. [0006] In applications that generate mechanical energy, the expansion break is split into two local breaks, each of which takes place inside the turbine. The high pressure turbine, downstream of the ...

AI Technical Summary

Problems solved by technology

[0020] A disadvantage of the bottoms of known turbines is that they deform due to thermal gradients, which will cause sealing losses in the areas where sealing is obtained by a specific geometry

[0021] The reason for this is that when the turbine is running, the originally axially positioned pins rotate, especially because of the uneven thermal deformation of the discs, impairing the correct sealing of the sealing rings

[0022] Another disadvantage is that in this way, the intake of hot gases can damage the life of the bottom and other parts of the gas turbine

[0023] This is because high temperatures cause oxidation phenomena which, along with fatigue phenomena, increase stress and over time cause cracks and splits that ultimately impair the correct function of the sole and other components

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