Sealing device between two elements of a turbomachine
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsAndre A. M. L. Camboulives, Claude C. Hallinger, Roger A. J. Vandenbroucke
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Abstract
A sealing device disposed between two turbomachine elements traversed by gases, particularly between a combustion chamber and a high pressure turbine nozzle support. The device includes an independent collar supported by first and second bearing surfaces on the elements which are to be connected in leaktight manner, the collar being constructed of a material having a thermal expansion coefficient which is different from that of the elements which it interconnects so as to ensure a leaktight connection between the elements.
Claims9
A sealing device for sealing gases within a turbomachine comprising:
- an axially extending collar disposed within said turbomachine;
- first and second bearing surfaces integral with and protruding from said axially extending collar;
- a combustion chamber wall having a collar member with an exterior surface portion in contact with said first bearing surface;
- a turbine nozzle housing having an exterior surface portion in contact with said second bearing surface wherein said axially extending collar further comprises a material having a lower coefficient of thermal expansion than said exterior surface portion of said collar member of said combustion chamber and said exterior portion of said turbine nozzle support housing such that said gases are sealed within said turbomachine between said combustion chamber wall and said support housing by said axially extending collar.
Dependencies are inferred from the claim text.