Turbine assembly of an aircraft turbine engine

Patent metadata

Field	Value
Publication number	US-10280776-B2
Application number	US-201515536096-A
Country	US
Kind code	B2
Filing date	Dec 17, 2015
Priority date	Dec 17, 2014
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

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 (C1) arranged between the first rotor (12) and the stator (13), from a second recess (C2) arranged between the stator (13) and the second rotor (14); and pressure-reducing means (300, 31) positioned inside the first recess (C1), 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 (C1).

First claim

The invention claimed is:

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.

Assignees

• Safran Aircraft Engines

Inventors

• Quelven Damien Bernard
• Desforges Jean-Baptiste Vincent
• Judet Maurice Guy
• Tang Ba-Phuc

Classifications

• F01D11/02

  by non-contact sealings, e.g. of labyrinth type (for sealing space between rotor blade tips and stator F01D11/08) · CPC title

• F01D11/006 Primary

  Sealing the gap between rotor blades or blades and rotor · CPC title

• F01D5/087

  in the radial passages of the rotor disc · CPC title

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title