Turbomachine comprising an alternator between two counter-rotating elements

Patent metadata

Field	Value
Publication number	US-11041400-B2
Application number	US-201916709990-A
Country	US
Kind code	B2
Filing date	Dec 11, 2019
Priority date	Dec 12, 2018
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A geared turbomachine includes: a fan, a low pressure shaft which drives the fan rotationally around the main axis of the turbomachine, a speed reducer interposed between the fan and the low pressure shaft, and an alternator driven by the low pressure shaft. The alternator includes an inductor and an armature of which one of the inductor and the armature is integral with the fan and the other of the inductor and the armature is integral with the low pressure shaft.

First claim

The invention claimed is:

1. A geared turbomachine comprising:
a fan delivering air to a primary flow path and to a secondary flow path which are coaxial with each other and to a main axis of the turbomachine;
a low pressure shaft connecting a low pressure turbine in the primary flow path to a low pressure compressor in the primary flow path, which drives the fan rotationally around the main axis of the turbomachine;
a speed reducer interposed between the fan and the low pressure shaft, the speed reducer being an epicyclic gear train comprising three components among a ring, a satellite carrier and a sun pinion, of which a first component is integral with the low pressure shaft, a second component is integral with the fan and the third component is fixed in the turbomachine; and
an alternator driven by the low pressure shaft,
wherein the alternator comprises an inductor and an armature, the inductor being integral with the fan and the armature being integral with the low pressure shaft,
wherein the speed reducer is designed so that a direction of rotation of the fan is opposite to a direction of rotation of the low pressure shaft, and
wherein the sun pinion is integral with the low pressure shaft, the ring is integral with the fan, and the satellite carrier is fixed in the turbomachine.

2. The turbomachine according to claim 1 , wherein the fan comprises a fan disc bearing a plurality of vanes, which is guided rotationally with respect to a stator of the turbomachine by a guide bearing which is situated at a level of an axial downstream end of the fan disc, and
wherein the alternator is situated axially along the main axis of the turbomachine near to the guide bearing.

3. The turbomachine according to claim 2 , further comprising an inter-shaft bearing interposed between an axial upstream end of the low pressure shaft and the fan disc, said inter-shaft bearing being situated axially upstream of the guide bearing and upstream of the alternator.

4. The turbomachine according to claim 2 , further comprising an inter-shaft bearing interposed between an axial upstream end of the low pressure shaft and the fan disc,
wherein the alternator is situated axially upstream of the guide bearing and the inter-shaft bearing.

5. The turbomachine according to claim 1 , wherein the fan comprises a fan disc bearing a plurality of vanes and an inlet cone extending upstream of the fan disc, and
wherein the alternator is situated axially inside a volume delimited by the inlet cone.

6. The turbomachine according to claim 5 , wherein the alternator supplies electricity to a system for de-icing the inlet cone.

7. The turbomachine according to claim 1 , further comprising means for electrically connecting the alternator with at least one fixed component of the turbomachine.

8. The turbomachine according to claim 1 , further comprising means for electrically connecting the alternator with at least one moveable component of the turbomachine.

9. The turbomachine according to claim 1 , wherein a rotational speed of the armature is less than a rotational speed of the inductor.

10. The turbomachine according to claim 1 , wherein electrical power generated by the alternator is between 100 kW and 500 kW at a frequency between 500 Hz and 2 kHz.

Assignees

• Safran Aircraft Engines

Inventors

• Tan-Kim Alexandre Jean-Marie
• Becoulet Julien Fabien Patrick

Classifications

• F01D1/24

  characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02K3/06

  with front fan · CPC title

• F16H2057/02073

  Reduction gearboxes for industry · CPC title