Multi-point injection device for an aircraft engine

Patent metadata

Field	Value
Publication number	US-10465910-B2
Application number	US-201415037736-A
Country	US
Kind code	B2
Filing date	Nov 20, 2014
Priority date	Nov 20, 2013
Publication date	Nov 5, 2019
Grant date	Nov 5, 2019

Abstract

A multi-point fuel injection device for an aircraft engine, including an inlet line, at least two injection lines, and a purge line, a fuel distributor member connected to each line and including a moveable element which includes an injection passage, in which the moveable element additionally includes a purge passage, and is configured to adopt a first range of positions in which the injection passage interconnects the inlet line and the injection lines, and a second range of positions in which the injection passage interconnects the inlet line and at least a first injection line while the purge passage interconnects the purge line and at least a second injection line, the device additionally includes an actuator adapted to move the moveable element into a safety position when a failure of the distribution member is detected, the injection passage interconnecting, in this safety position of the moveable element, the inlet line and the first injection line while the purge passage does not interconnect the purge line to any of the injection lines.

First claim

The invention claimed is:

1. A multi-point fuel injection device for an aircraft engine, comprising:
an intake line, first and second injection lines, and a purge line;
a fuel distributor connected to each line and comprising a movable element which includes an injection passage and a purge passage, the movable element being configured to assume:
a first range of positions wherein the injection passage interconnects the intake line and the first and second injection lines, and
a second range of positions wherein the injection passage interconnects the intake line and the first injection line while the purge passage interconnects the purge line and the second injection line; and

an actuator configured to move and secure the movable element into a safety position when a failure of the fuel distributor is detected, the injection passage interconnecting, in said safety position of the movable element, the intake line and at least one of the first and second injection lines while the purge passage does not interconnect the purge line with any of the first and second injection lines.

2. The fuel injection device according to claim 1 , wherein the injection passage interconnects the intake line and only the first injection line when the movable element assumes the safety position.

3. The fuel injection device according to claim 1 , wherein the intake line is terminated by an intake port leading entirely into the injection passage when the movable element assumes the safety position.

4. The fuel injection device according to claim 1 , wherein the first injection line is terminated by an injection port leading entirely into the injection passage when the movable element assumes the safety position.

5. The fuel injection device according to claim 1 , wherein the movable element is configured to assume a third range of positions wherein the injection passage interconnects the intake line with only the first injection line, and wherein the purge passage does not interconnect the purge line with any of the two injection lines.

6. The fuel injection device according to claim 1 , wherein the movable element is a drawer sliding in a sheath along a longitudinal axis and wherein, in the safety position, the drawer comes into abutment against an end of the sheath.

7. The fuel injection device according to claim 6 , wherein the injection lines are two in number and are each terminated by an injection port leading into the sheath, the injection passage extending transversely to the longitudinal axis and includes a width along said axis which is equal to the sum of the length along said axis separating the closest edges of the two injection ports and a diameter of the two injection ports along said axis, the two ports having the same diameter.

8. The fuel injection device according to claim 6 , wherein the injection lines are two in number and are each terminated by an injection port leading into the sheath, wherein the intake line is terminated by an intake port leading into the sheath at a longitudinal position which is comprised between the respective longitudinal positions of the injection ports, the injection passage having a length along the longitudinal axis which is greater than a length of the intake port along said longitudinal axis.

9. The fuel injection device according to claim 6 , wherein the intake line is terminated by an intake port leading into the sheath and wherein the purge line is terminated by a purge port also leading into the sheath, the closest edges of the intake and purge ports being separated by a distance along the longitudinal axis which is greater than a length of the injection passage along said longitudinal axis.

10. The fuel injection device according to claim 6 , wherein the injection lines are two in number and are each terminated by an injection port leading into the sheath, wherein the drawer includes a median portion separating the injection and purge passages, the length of the median portion along the longitudinal axis being greater than the diameter of each injection port along said longitudinal axis and less than a distance separating closest edges of the two injection ports along said longitudinal axis.

11. The fuel injection device according to claim 10 , wherein the length of the median portion along the longitudinal axis is further less than the distance along said longitudinal axis separating the intake port and the injection port that terminates the second injection line.

12. An aircraft engine comprising at least one multi-point fuel injection device according to claim 1 .

13. The aircraft engine according to claim 12 , wherein the first injection line is designed to deliver a constant fuel flow optimized for low engine power settings, and the second injection line is designed to deliver an intermittent fuel flow optimized for high engine power settings.

14. The fuel injection device according to claim 1 , further comprising:
a controller which controls movement of the movable element based on a distribution command and a purge command; and
a sensor which detects a position of the movable element in the fuel distributor.

15. The fuel injection device according to claim 14 , wherein the sensor is provided on an end of the movable element,
wherein the end of the movable element is closer to the purge passage in the second range of positions than in the first range of positions, and
wherein the end of the movable element is closer to the purge passage in the safety position than in the second range of positions.

16. The fuel injection device according to claim 1 , wherein the safety position of the movable element, the injection passage interconnects the intake line and the first injection line.

Assignees

• Safran Aircraft Engines

Inventors

• Chalaud Sebastien

Classifications

• F23K2300/203

  Purging · CPC title

• F23D11/00

  Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space · CPC title

• F23D2209/30

  Purging · CPC title

• F23K2203/105

  Flow splitting devices to feed a plurality of burners · CPC title

• F23K5/06

  from a central source to a plurality of burners · CPC title