Electric connection of an electric machine in an aircraft turbomachine

Patent metadata

Field	Value
Publication number	US-11753175-B2
Application number	US-202017781170-A
Country	US
Kind code	B2
Filing date	Nov 24, 2020
Priority date	Dec 3, 2019
Publication date	Sep 12, 2023
Grant date	Sep 12, 2023

Abstract

An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

First claim

The invention claimed is:

1. An aircraft turbomachine, comprising:
a gas generator having a longitudinal axis,
a fan located at an upstream end of the gas generator and configured to rotate about said axis, and
an electric machine having an annular shape mounted coaxially downstream of the fan, and which comprises a rotor rotatably coupled to the fan, and a stator,
the fan configured to generate a main gas flow, a portion of which flows into a primary annular duct of the gas generator to form a primary flow, and another portion of which flows around the gas generator to form a secondary flow,
the primary duct being delimited by first and second annular envelopes coaxial with the gas generator, the primary duct being passed through by bladings, referred to as IGV, configured to connect the first and second envelopes, as well as by tubular arms of an inlet casing located downstream of the IGV arms,
the gas generator comprising a third annular envelope which coaxially surrounds the second envelope, the second and third envelopes being connected together at their upstream ends to form an annular splitter nose that separates the primary and secondary flows,
wherein the stator of the electric machine is connected to a power electronic circuit by at least one rigid electroconductive bar, the bar comprising a first portion extending radially with respect to said axis inside one of the IGV arms, and a second portion extending parallel to said axis between the second and third envelopes.

2. The turbomachine of claim 1 , wherein the bar is L-shaped, said first and second portions being straight and connected together by a junction located directly downstream of said splitter nose.

3. The turbomachine of claim 1 , wherein the bar has a polygonal and constant cross-section, and can be twisted.

4. The turbomachine according to claim 1 , further comprising a nacelle casing that surrounds the gas generator, as well as bladings, referred to as OGV, connecting the nacelle casing to said third annular envelope.

5. The turbomachine according to claim 4 , wherein the gas generator comprises annular flanges attaching the OGV which are located between said second and third envelopes and which comprise notches configured for the passage of said second portion of the bar.

6. The turbomachine according to claim 1 , wherein the bar is surrounded by an insulating sheath and comprises a first end exposed and configured for releasable attachment to an element for electric connection to said stator, and a second end exposed and configured for releasable attachment to a harness for electric connection to said circuit.

7. The turbomachine according to claim 1 , wherein the electric machine is located upstream of said splitter nose.

8. The turbomachine according to claim 1 , wherein the stator of the electric machine is connected to the power electronic circuit by a plurality of rigid electroconductive bars regularly distributed around said axis (A).

9. The turbomachine according to claim 1 , wherein the IGV through which the bar passes is tubular and oversized relative to the other IGV arms.

10. The turbomachine according to claim 1 , wherein said power circuit is located between the second and third envelopes.

11. A method for maintaining a turbomachine according to claim 1 , comprising the steps consisting of:
disassembling and removing at least one portion of the third envelope at the level of said bar ( 80 ),
disassembling and removing the OGV located in line with the bar, and
disassembling and removing the bar for maintenance.

Assignees

• Safran Aircraft Engines

Inventors

• Millier Vincent François Georges
• Guillotel Loïc Paul Yves

Classifications

• B64D27/33

  Hybrid electric aircraft · CPC title

• F01D9/065 Primary

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F01D15/10

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

• F05D2220/76

  an electrical generator · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title