Turbine assembly of an aircraft turbine engine
The present invention relates to a turbine assembly ( 10 ) of a turbine engine ( 1 ), comprising at least: a first bladed rotor ( 12 ), a bladed stator ( 13 ) and a second bladed rotor ( 14 ) arranged in series, the rotors ( 12, 14 ) being mounted on a shaft ( 2 ); a sealing plate ( 20 ) extending between the stator ( 13 ) and the shaft ( 2 ) and separating a first recess (C 1 ) arranged between the first rotor ( 12 ) and the stator ( 13 ), from a second recess (C 2 ) arranged between the stator ( 13 ) and the second rotor ( 14 ); and pressure-reducing means ( 300, 31 ) positioned inside the first recess (C 1 ), the assembly being characterized in that said pressure-reducing means ( 300, 31 ) comprise a plurality of substantially radial recompression fins ( 300 ) extending into the first recess (C 1 ).
1. A turbine assembly for an aircraft turbine engine, comprising at least a first bladed rotor, a bladed stator and a second bladed rotor arranged successively, the rotors being mounted on a shaft, a sealing plate extending between the stator and the shaft and separating a first recess arranged between the first rotor and the stator, from a second recess arranged between the stator and the second rotor, pressure-reducing means being positioned inside the first recess wherein said pressure-reducing means comprise a plurality of substantially radial recompression fins extending into the first recess.
2. The assembly according to claim 1 , wherein said fins are arranged on a downstream face of the first rotor.
3. The assembly according to claim 2 , wherein the fins are arranged at a thinned portion of the first rotor.
4. The assembly according to claim 2 , wherein the first rotor comprises a plurality of blades, the turbine assembly comprising one fin for each blade of the first rotor.
5. The assembly according to claim 2 , wherein the fins have a curved distal end.
6. The assembly according to claim 1 , wherein said pressure-reducing means inside the first recess also comprise an auxiliary sealing plate arranged into the first recess facing the recompression fins.
7. The assembly according to claim 1 , wherein said pressure-reducing means inside the first recess also comprise an auxiliary sealing plate arranged into the first recess facing the recompression fins, wherein the fins and the auxiliary sealing plate have a complementary shape.
8. The assembly according to claim 1 , wherein the pressure-reducing means inside the first recess are configured to reduce by at least 50% a pressure difference between the first recess and the second recess.
9. The assembly according to claim 8 , wherein the pressure-reducing means inside the first recess are configured to reduce by at least 90% the pressure difference between the first recess and the second recess.
10. The assembly according to claim 1 , wherein the bladed stator is a second stator, the turbine assembly also comprising a first bladed stator arranged upstream of the first rotor.
11. The assembly according to claim 1 , wherein the pressure upstream of the stator is greater than the pressure downstream of the stator.