# US 12,006,873 B2 · Fuel supply circuit of an aircraft engine

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- Number: US 12,006,873 B2
- Document ID: US12006873B2
- Status: Granted
- Kind: B2
- Application number: 17/759,208
- Filed: 2021-01-15
- Published: 2023-03-02
- Granted: 2024-06-11
- Earliest claimed: 2020-01-27
- Assignees: Safran Helicopter Engines
- Applicants: Safran Helicopter Engines
- Inventors: Franck Albert Robert Dupeu; Jean-Marie André Robert Gigon; David Simon Serge Taieb
- Web page: https://patentgrep.com/patent/US12006873B2

## CPC

- F02C 7/236: Fuel delivery systems comprising two or more pumps
- F02C 7/26: Starting; Ignition
- F02C 9/30: characterised by variable fuel pump output
- F05D 2220/76: an electrical generator
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A fuel supply circuit of an aircraft engine includes a centrifugal pump mechanically coupled with an engine shaft delivering mechanical power. The circuit further includes at least one electromagnetic pump including at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor and at least a plurality of coils annularly distributed inside the stator face-to-face with the magnets. The rotor is connected to the engine shaft by a one-way clutching element.

## Claims

### Claim 1

A fuel supply circuit of an aircraft engine connecting a fuel reservoir to a combustion chamber of a turbomachine, comprising:
a low-pressure centrifugal pump mechanically coupled with an engine shaft; and
an electromagnetic pump comprising a stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor, and a plurality of coils annularly distributed inside the stator face-to-face with the plurality of magnets,
wherein the rotor is connected to the engine shaft by a one-way clutching element,
wherein an inlet of the low-pressure centrifugal pump and an inlet of the electromagnetic pump are connected to the fuel reservoir such that the turbomachine can be supplied with fuel by the low-pressure centrifugal pump, by the electromagnetic pump, or by both the low-pressure centrifugal pump and the electromagnetic pump simultaneously, and
wherein the rotor comprises an inner pinion interacting with an outer ring with an inner toothing, the magnets of the plurality of magnets being retained on the inner pinion, the coils of the plurality of coils being face-to-face with the magnets along an axial direction.

### Claim 2 (depends on 1)

The circuit as claimed in claim 1, wherein the electromagnetic pump comprises first and second pluralities of coils present on either side of the pinion respectively, the coils of the first and second plurality of coils being face-to-face with the magnets along the axial direction.

### Claim 3 (depends on 1)

The circuit as claimed in claim 1, wherein the electromagnetic pump is able to generate an electrical current.

### Claim 4 (depends on 1)

An aircraft engine including a fuel supply circuit as claimed in claim 1.

### Claim 5 (depends on 4)

The aircraft engine according to claim 4, wherein said fuel supply circuit is connected to the fuel reservoir without any priming pump.

### Claim 6 (depends on 1)

The circuit as claimed in claim 1, wherein in a first operating mode, the electromagnetic pump is powered by an independent source of electrical energy, the rotor of the electromagnetic pump rotates freely about the engine shaft, and the engine shaft is immobile due to the one-way clutching element,
wherein in a second operating mode, the low-pressure centrifugal pump is driven by the engine shaft, the electromagnetic pump is powered by the independent source of electrical energy, and the rotor of the electromagnetic pump rotates at a higher speed than a rotation speed of the engine shaft, and
wherein in a third operating mode, the low-pressure centrifugal pump is driven by the engine shaft, the electromagnetic pump is not powered by the independent source of electrical energy, and the rotor of the electromagnetic pump is rotationally driven by the engine shaft due to the one-way clutching element to produce an electrical current.