Back to results
US 2022/0178331 A1Published application
Gas turbine for twin-rotor aircraft
AssigneeSafran Aircraft Engines
InventorsPatrick SULTANA, Olivier RENON, Laurent Cédric ZAMAI, Clément Charles Jérémy COIFFIER
Life of this patent
Estimating the term…
Abstract
A turbine includes a first rotor and a second rotor that can rotate in opposite directions and are interleaved. The turbine further includes a ring to which abradable material is secured, the ring, unsegmented, extending between the first impellers of the first rotor and the second rotor, over a sector of between 350 and 360°, and, axially between an upstream end and a downstream end of the ring, the ring is held with the second rotor.
Claims12
A gas turbine for an aircraft, the turbine extending about an axis (X) and comprising:
- a first rotor comprising first impellers and a second rotor comprising second impellers, the first and second rotors being rotatably mounted about said axis (X), the first rotor and the second rotor being configured to rotate in opposite directions, with at least some of the second impellers being axially interposed between at least some of the first impellers;
- and
- a ring to which an abradable material is secured, the ring extending around one of the first impellers with which the abradable material cooperates, and axially between an upstream end and a downstream end of the ring, wherein the ring is held with the second rotor.
Dependencies are inferred from the claim text.