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US 4,376,375 AGranted
Multiple flow turbojet with adjustable bypass ratio
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorSerge Boudigues
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Abstract
A multiple-flow turbojet with adjustable bypass ratio comprising a low pressure spool and a high pressure spool casing. Aerodynamic surfaces mechanically integral with the high pressure spool are disposed in a cold secondary flow whose characteristics vary as a function of the setting of a guide means and cause a variation in the bypass ratio.
Claims6
A multiple flow turbojet with an adjustable bypass ratio for a fluid, said turbojet comprising a housing containing:
- a low pressure rotary spool including at least one turbine and one compressor;
- a high pressure rotary spool including at least one turbine and one compressor;
- burner means acting on the turbine of at least said high pressure spool;
- a primary fluid path defined by said low and high pressure spools and said burner means;
- a secondary fluid path radially outside of said primary fluid path;
- at least one vane in said secondary fluid path, said vane mechanically integral with said high pressure spool and interacting with said fluid;
- and
- at least one adjustable guide means in said secondary fluid path;
- whereby the ratio of fluid flow characteristics in said primary and second fluid paths is varied as a function of the setting of said at least one guide means.
6 more elements
Dependencies are inferred from the claim text.