Aircraft turbine engine comprising a discharge device
AssigneeSafran Aircraft Engines
InventorsArnaud Nicolas NEGRI, Nils Edouard Romain BORDONI, Michel Gilbert Rolland BRAULT, Guillaume Patrice KUBIAK, Nathalie NOWAKOWSKI, Romain Guillaume CUVILLIER
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Abstract
Aircraft turbine engine (10), comprising at least one first compressor, an annular combustion chamber (70) and at least one first turbine (46), which define a first flow duct (22) for a primary flow, characterised in that it comprises, between said combustion chamber (70) and said first turbine (46), a device (55, 55′) for discharging at least part of said primary flow.
Claims7
An aircraft turbine engine, comprising at least one first compressor, an annular combustion chamber and at least one first turbine, which define a first flow duct for a primary flow, wherein it comprises, between said combustion chamber and said first turbine, a device for discharging at least part of said primary flow, said device comprising at least one valve or an annular row of valves, the or each valve comprising at least one scooping gate which is movable between a first position, in which it has no influence on the supply of primary flow to said first turbine, and a second position, in which it diverts at least part of the primary flow, which then does not supply the first turbine, radially towards the outside with respect to a longitudinal axis of the turbine engine,
- wherein the discharge device comprises a means for locking/unlocking the or each gate, and a means for controlling said locking/unlocking means.
Dependencies are inferred from the claim text.