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AssigneeSafran Aircraft Engines
InventorsJérémy Philippe Pierre EDYNAK, François Marie Paul MARLIN, Cécile THIRIET, Mustapha HAMMOUCH
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An assembly for a turbine engine including an intermediate casing with a primary duct portion, a tertiary duct portion, an intermediate hub, an inter-duct shroud, an outer shroud, structural arms connecting the intermediate hub and the outer shroud, and an exhaust duct extending between the primary duct and the tertiary duct, and bypass valves capable of drawing fluid from the primary duct portion in order to direct it toward the exhaust duct. The intermediate casing is formed as a single piece and has a cavity located between the intermediate hub and the inter-duct shroud that opens onto the upstream face of the intermediate casing via an opening, wherein the bypass valves are able to be inserted into the cavity via the opening.
An assembly for a turbine engine comprising an intermediate casing extending along a longitudinal axis, said intermediate casing comprising a primary flow stream portion, a tertiary flow stream portion an exhaust duct extending between said primary flow stream and said tertiary flow stream, an intermediate hub, an inter-stream shroud, an outer shroud structural arms connecting said intermediate hub and said outer shroud, and said assembly further comprising an exhaust duct extending between said primary flow stream and said tertiary flow stream and bypass valves capable of drawing fluid from said primary flow stream portion and directing it towards said exhaust duct, wherein said intermediate casing is formed as a single piece and has a cavity located between said intermediate hub and said inter-stream shroud, which cavity opens out onto the upstream face of said intermediate casing via an opening located between said intermediate hub and said inter-stream shroud, said bypass valves being able to be inserted into said cavity through said opening
Dependencies are inferred from the claim text.