Gas turbine engine having a minimal blade tip clearance

Power plants – Combustion products used as motive fluid – Combined with regulation of power output feature

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Details

415134, 415170R, F02C 728, F02C 706, F01D 1108

Patent

active

045789428

ABSTRACT:
A gas turbine engine is so constructed that the clearance or gap between the rotor and stator, especially at the outer diameter range of a radial flow end stage, is optimally maintained under all operating conditions. For this purpose the housing in the axial-flow/radial-flow compressor is constructed as a two shell housing. The outer housing shell is mounted as part of the engine structure, whereby the inner housing shell is exposed substantially only to forces or loads caused by compressor fluid flow. The material of the outer housing shell has a heat expansion coefficient in the axial direction of the rotational engine axis, which is distinctly lower than the heat expansion coefficient of the material of the compressor rotor. The heat expansion coefficient of the material of the inner housing shell is lower in the circumferential direction and approximately equal in the axial direction relative to the heat expansion coefficient of the rotor. The fixed bearing of the compressor rotor is arranged in the zone of the compressor inlet.

REFERENCES:
patent: 3304054 (1967-02-01), Oechsun et al.
patent: 3709637 (1973-01-01), Petrie et al.
patent: 4101242 (1978-07-01), Coplin et al.
patent: 4439981 (1984-04-01), Weiler et al.

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