Device for checking the clearances of a gas turbine compressor casing
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsJean-Louis Charbonnel, Jacky Naudet, Gerard J. Stangalini
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Abstract
A gas turbine compressor casing has two inner and outer envelopes forming at least one closed cavity and a locking or clamping ring having a thermal inertia higher than that of the envelopes and mounted in the closed cavity in such a way as to limit its contraction during a lowering of the temperature. The thermal inertia difference can be obtained by using for the locking ring a material having a thermal expansion coefficient lower than the coefficient of the envelopes. It can also be controlled by a ventilation means device for ensuring hot air flow in the cavity.
Claims9
Gas turbine compressor casing having a structure forming a casing, which comprises:
- a locking member having a thermal inertia higher than that of said structure and mounted in said structure so as to limit contraction of the casing during a temperature drop wherein said structure forming the casing has an inner envelope and an outer envelope forming at least one closed cavity.
Gas turbine compressor casing having a structure forming a casing, which comprises:
- a locking member having a thermal inertia higher than that of said structure and mounted in said structure so as to limit contraction of the casing during a temperature drop wherein said structure forming the casing has an inner envelope and an outer envelope forming at least one closed cavity, and wherein said locking member is independent of the structure which forms said casing.
Dependencies are inferred from the claim text.