Hybrid transmission turbojet engine

Patent metadata

Field	Value
Publication number	US-11313282-B2
Application number	US-201916758749-A
Country	US
Kind code	B2
Filing date	Jun 21, 2019
Priority date	Jun 22, 2018
Publication date	Apr 26, 2022
Grant date	Apr 26, 2022

Abstract

A turbojet engine ( 2 ), such as an aircraft turbojet engine, comprising: an epicyclic gear train ( 36 ); a turbine rotating a transmission shaft ( 34 ) constrained to rotate with the inner planetary gear ( 60 ) of the epicyclic gear train ( 36 ); a fan ( 18 ) rigidly connected to the ring gear ( 66 ) of the epicyclic gear train ( 36 ); and an electric machine ( 70 ) comprising a rotor ( 72 ) and a stator ( 74 ), the rotor ( 72 ) being rigidly connected to the planet carrier ( 68 ) of the epicyclic gear train ( 36 ). Alternatively, the fan ( 18 ) is rigidly connected to the planet carrier and the electric machine ( 70 ) is rigidly connected to the ring gear. The invention also relates to methods for using said turbojet engine, in particular for controlling the reduction ratio between the transmission shaft and the turbine, in order to recover kinetic energy or for taxiing.

First claim

The invention claimed is:

1. Turbofan engine, comprising:
an epicyclic gear comprising:
a sun gear;
an outer ring; and
at least one planet gear and a planet carrier;

a turbine, driving in rotation a transmission shaft rotationally fixed to the sun gear;
a fan rotationally fixed to the outer ring; and
an electric motor comprising:
a rotor and a stator, the rotor being rotationally fixed to the planet carrier, the axis of rotation of the rotor of the electric motor being coincident with the axis of rotation of the transmission shaft.

2. The turbofan engine according to claim 1 , further comprising:
control means for varying the speed and the direction of rotation of the rotor of the electric motor.

3. The turbofan engine according to claim 1 , further comprising:
a low-pressure compressor and a high-pressure compressor, the low-pressure compressor being driven in rotation directly by the transmission shaft and the high-pressure compressor being driven in rotation by the transmission shaft via a gear.

4. The turbofan engine according to claim 3 , wherein the gear is a further epicyclic gear.

5. The turbofan engine according to claim 3 , wherein the gear is such that the low-pressure compressor and the high-pressure compressor rotate in directions opposite from one another.

6. The turbofan engine according to claim 1 , further comprising:
a casing that is stationary;
wherein the stator of the electric motor is integral with the casing.

7. The turbofan engine according to claim 1 , further comprising:
a low-pressure turbine and a high-pressure turbine;
wherein the transmission shaft that is integral with the sun gear is driven by the low-pressure turbine.

8. The turbofan engine according to claim 1 , further comprising:
a low-pressure compressor and a high-pressure compressor, wherein at least one of the low-pressure compressor and the high-pressure compressor is provided with at least two rows of rotor blades, wherein at least one row of rotor blades is driven in a direction of rotation by the transmission shaft and at least one row of rotor blades is driven by the electric motor in a direction of rotation opposite the direction of rotation of the at least one row of rotor blades driven by the transmission shaft.

9. A turbofan engine, comprising:
an epicyclic gear comprising:
a sun gear;
an outer ring; and
at least one planet gear and a planet carrier;

a turbine, driving in rotation a transmission shaft integral in rotation with the sun gear;
a fan integral with the planet carrier; and
an electric motor comprising:
a rotor and a stator, the rotor being integral with the outer ring, the axis of rotation of the rotor of the electric motor being coincident with the axis of rotation of the transmission shaft, the turbofan engine further comprising a low-pressure compressor and a high-pressure compressor, the low-pressure compressor being driven in rotation directly by the transmission shaft and the high-pressure compressor being driven in rotation by the transmission shaft via a gear.

10. The turbofan engine according to claim 9 , further comprising:
control means for varying the speed and the direction of rotation of the rotor of the electric motor.

11. The turbofan engine according to claim 9 , wherein the gear is a further epicyclic gear.

12. The turbofan engine according to claim 9 , wherein the gear is such that the low-pressure compressor and the high-pressure compressor rotate in directions opposite from one another.

13. The turbofan engine according to claim 9 , further comprising:
a casing that is stationary;
wherein and the stator of the electric motor is integral with the casing.

14. The turbofan engine according to claim 9 , further comprising:
a low-pressure turbine and a high-pressure turbine;
wherein the transmission shaft that is integral with the sun gear is driven by the low-pressure turbine.

15. A turbofan engine, comprising:
an epicyclic gear comprising:
a sun gear;
an outer ring; and
at least one planet gear and a planet carrier;

a turbine, driving in rotation a transmission shaft integral in rotation with the sun gear;
a fan integral with the planet carrier;
an electric motor comprising:
a rotor and a stator, the rotor being integral with the outer ring; and

at least one compressor provided with at least two rows of rotor blades, wherein at least one row of rotor blades is driven in a direction of rotation by the transmission shaft and at least one row of rotor blades is driven by the electric motor in a direction of rotation opposite the direction of rotation of the at least one row of rotor blades driven by the transmission shaft.

Assignees

• Safran Aero Boosters Sa

Inventors

• Maljean Stephane

Classifications

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title

• H02K7/116

  with gears · CPC title

• H02K7/1823

  structurally associated with turbines or similar engines · CPC title