Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator

Patent metadata

Field	Value
Publication number	US-10584641-B2
Application number	US-201615566861-A
Country	US
Kind code	B2
Filing date	Apr 14, 2016
Priority date	Apr 17, 2015
Publication date	Mar 10, 2020
Grant date	Mar 10, 2020

Abstract

Engine comprising a propeller unit with a pair of contrarotating propellers ( 31, 32 ), a gas generator ( 5 ) supplying a power turbine ( 53 ), the pair of propellers being rotationally driven by the shaft ( 53 A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset ( 7 ) and a first stage ( 6 ) comprising a simple gearset connecting the turbine shaft ( 53 A) and the differential gearset ( 7 ), the engine air intake comprising an air intake duct ( 11 ), the air intake duct ( 11 ) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset ( 7 ).

First claim

The invention claimed is:

1. An engine comprising:
a propeller unit with a pair of contrarotating propellers;
a power turbine;
a power turbine shaft coupled to the power turbine;
a gas generator configured to supply exhaust gases to the power turbine,
a speed reduction gearbox comprising a differential gearset and a simple gearset, the speed reduction gearbox coupled to the pair of contrarotating propellers and the power turbine shaft such that the power turbine is configured to drive the pair of contrarotating propellers through the speed reduction gearbox, wherein the simple gearset is coupled to the power turbine shaft and the differential gearset; and
an air intake comprising an air intake duct, the air intake duct having a shape of a lobe, the air intake duct being positioned adjacent to the speed reduction gearbox;
wherein an axis of rotation of the pair of contrarotating propellers is not coaxial with an axis of rotation of the power turbine,
wherein the simple gearset comprises a first toothed wheel, the first toothed wheel being integral with the power turbine shaft, said first toothed wheel in meshing engagement with a second toothed wheel of the simple gearset, said second toothed wheel being mounted coaxially with the axis of rotation of the pair of contrarotating propellers.

2. The engine according to claim 1 , wherein the simple gearset and the differential gearset are located to one side of the air intake duct.

3. The engine according to claim 1 , wherein the simple gearset and the differential gearset are located between the pair of contrarotating propellers and the gas generator.

4. The engine according to claim 1 , wherein an angle defined between the axis of rotation of the power turbine and a straight line connecting an apex of a compressor of the gas generator to an inner elbow of the air intake duct is between 20° and 60°.

5. The engine according to claim 1 , wherein the second toothed wheel of the simple gearset is coupled to a sun gear of the differential gearset.

6. The engine according to claim 1 , wherein at least one of the differential gearset or the simple gearset comprises duplicated toothed wheels.

7. The engine according to claim 6 , wherein the simple gearset comprises two toothed wheels in parallel meshing engagement with a toothed wheel connected to a sun gear of the differential gearset.

8. The engine according to claim 1 , wherein the differential gearset comprises a sun gear, a planet carrier and a ring, the planet carrier being connected to an upstream propeller of the pair of contrarotating propellers and the ring being connected to a downstream propeller of the pair of contrarotating propellers.

9. The engine according to claim 1 , in wherein the differential gearset comprises a sun gear, a planet carrier and a ring, the planet carrier being connected to a downstream propeller of the pair of contrarotating propellers and the ring being connected to an upstream propeller of the pair of contrarotating propellers.

10. The engine according to claim 1 , wherein the engine further comprises a fixed structure with a sleeve, a first shaft member being supported via bearings inside the sleeve, said first shaft member connecting a ring of the differential gearset to a first propeller of the pair of contrarotating propellers.

11. The engine according to claim 10 , wherein the engine further comprises a second shaft member supported via bearings inside the first shaft member, the second shaft member connecting a planet carrier of the differential gearset to a second propeller of the pair of contrarotating propellers.

12. The engine according to claim 10 , wherein the engine further comprises an additional shaft member supported via bearings on the fixed structure, said additional shaft member connecting the second toothed wheel of the simple gearset to a sun gear of the differential gearset.

13. The engine according to claim 8 , further comprising a sleeve containing services, the sleeve being housed within an innermost shaft member of a plurality of shaft members.

14. The engine according to claim 1 , wherein the sleeve is a fixed sleeve.

Assignees

• Safran Aircraft Engines

Inventors

• Escure Didier Rene Andre
• Bersot Jean-Francois Endy
• Boudebiza Tewfik
• Charier Gilles Alain
• Nguyen Van Thomas Julien
• Reigner Jean Philippe Pierre-Alain

Classifications

• B64D35/06

  the propellers or rotors being counter-rotating · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• F02C7/36 Primary

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F05D2250/34

  translated · CPC title

• F05D2220/324

  to drive unshrouded, low solidity propeller · CPC title