MULTIPOINT FUEL INJECTION DEVICE

Abstract

The fuel injection conduits in a multipoint device surrounding a so-called pilot central injection device include tubes of circumferential orientation. By separating the injection conduits from each other, it is possible to attribute to them different head losses which compensate the differences in length that the fuel has to travel: a uniform flow of fuel may be hoped for, for each of the injection holes. The tubes are individual but joined to form a crown that is unitary or composed of two almost symmetrical unitary portions, which lends itself well to manufacture by addition of material.

Claims

1) Fuel injection device for a combustion chamber of an aircraft engine, including a first, central, so-called pilot injection part (11), a second so-called multipoint injection part (6) surrounding the pilot part, the multipoint part being connected to a fuel supply conduit (2) and including holes for injecting (16) fuel into the combustion chamber, characterised in that the multipoint part includes, between said injection holes and said supply conduit, a plurality of conduits (15) parallel with each other and each connected to a respective injection hole (16), the conduits extending circumferentially around the pilot part over different angular sectors; a part of the parallel conduits is composed of joined and rigid tubes forming a unitary portion and is manufactured by a material addition method.

2) Fuel injection device according to claim 1, characterised in that the multipoint part (6) is crown shaped.

3) Fuel injection device according to claim 2, characterised in that the parallel conduits (15) are connected to the holes (16) by connecting tubes (23) which are oriented in a direction essentially identical to a central axis (X) of the crown.

4) Fuel injection device according to claim 3, characterised in that the connecting tubes (23) have identical length over diameter ratios $\frac{L}{D}.$

5) Fuel injection device according to claim 2, characterised in that the parallel conduits (15) form two groups of which each extends into a respective angular half of the crown.

6) Fuel injection device according to claim 1, characterised in that the parallel conduits have different sections, increasing for increasing values of the angular sectors.

7) Fuel injection device according to claim 1, characterised in that one at least of the parallel conduits (15) extends over an angular sector of at least 135.

8) Fuel injection device according to claim 1, characterised in that the supply conduit (2) emerges in a supply chamber (17) of the multipoint part, to which are connected all the conduits (15)

9) Fuel injection device according to claim 1, characterised in that it includes an outer crown (8) for supplying the pilot part with fuel, said parallel conduits (15) of the multipoint part being comprised in said outer supply crown.

Description

[0014] The invention will now be described more fully in relation to the comments of the following figures, which describe a purely illustrative particular embodiment thereof:

[0015] FIGS. 1, 2, 3 and 4 represent the device, respectively in median section, in partial perspective, in complete perspective, and from above;

[0016] FIG. 5 schematically illustrates the environment of the device including the combustion chamber;

[0017] and FIG. 6 is an enlargement of the end of a part of the multipoint injection tubes.

[0018] The injection device is established through a wall 1 of a combustion chamber 25. FIG. 5 schematically represents the combustion chamber 25 surrounded by the gas flow path 28 of the turbomachine of which a part surrounds the combustion chamber 25. The injection device emerges at the bottom of the combustion chamber 25, opposite the outlet 29 of the combustion chamber 25. A supply conduit 2 is at the centre of an injection arm 3, and it supplies with fuel a so-called multipoint injection part including a multipoint injection crown 6. The latter is arranged in a cavity 7 of an outer crown 8 which envelopes it and which is the seat of a permanent flow of fuel during flight, itself also supplied by the supply conduit 2, which supplies a so-called pilot injection part, including a pilot injection conduit 9 which ends in a pilot injection jet 11 at the centre of the device, directed towards the inner volume 12 of the combustion chamber. The injection device is supported by an envelope 13 that surrounds the crowns 6 and 8, is connected to the wall 1 and flares out into a lodge 14 towards the inner combustion volume 12. The pilot injection conduit 9 has a shape bent at 180 and extends into a region diametrically opposite to the supply conduit 2 with respect to a central axis X of the multipoint injection crown 6 and the outer crown 8, passing through the pilot injection jet 11 and horizontal in FIG. 1. This central axis X conventionally makes it possible to define axial, radial and tangential (or angular) directions, which will be used to describe the device.

[0019] The crown 6 is composed of two unitary portions, of which one is represented in a clearly visible manner in FIG. 2. Each unitary portion includes a group of juxtaposed and joined tubes 15 forming parallel conduits, which extend in the tangential direction of the injection device. The tubes 15 of the portion have however different lengths and stop at locations regularly distributed on the circumference of the multipoint injection crown 6 and which comprise multipoint injection holes 16. In the embodiment represented, this half of the multipoint injection crown 6 includes six tubes 15 and as many multipoint injection holes 16, of which one of them, noted 16a, is diametrically opposite to the supply conduit 2 and depends on a tube, noted 15a, of which the lengthnearly 180 of angular extensionis greater. In this embodiment, the multipoint injection part includes eleven multipoint injection holes 16 in total, regularly distributed over the complete circumference of the multipoint injection crown 6, and the other half of the crown 6 may be virtually symmetrical thereto, except that there is no symmetric tube of the longest tube 15a (FIG. 3). The five tubes (in this embodiment) of the group of tubes of the unitary portion, not represented, of the multipoint injection crown 6 may have angular lengths respectively similar to those of the tubes 15 represented (the tube 15a being excluded), or not, a greater dissymmetry of the halves of the multipoint injection crown 6 then being accepted. It is thereby possible to obtain a device including an even or odd number of multipoint injection holes 16.

[0020] The outer crown 8 forms a continuous ring, but the multipoint injection crown 6 is limited by two walls 10 which separate its two portions and between which extend a distribution chamber 17 of low angular extension (at the most an interval between two multipoint injection holes 16). The supply conduit 2 emerges in the distribution chamber 17 by at least one supply tube 4 which prolongs it in the arm 3, and the tubes 15 also emerge in the distribution chamber 17 after having passed through the walls 10. Also, the fuel circulates freely from the supply conduit 2 to the multipoint injection holes 16 by spreading out in an equitable manner in the tubes 15. A valve, not represented, makes it possible however to stop this circulation at will, by closing the supply tube 4. The supply conduit 2 is provided with other supply tubes 18, which emerge in the outer crown 8 outside of the multipoint injection crown 6 of the two sides of the distribution chamber 17 and ensure the pilot injection of fuel.

[0021] The outer crown 8 includes an open side in front of an end piece 19 at the end of the arm 3 and on its side, and the supply tubes 4 and 18 pass through this end piece 19. The end piece 19 has a circular end 20 corresponding to this open side. When this circular end 20 is driven into a flange 21 projecting on the outer edge of the outer crown 8 towards the arm 3, a leak tight adjustment may be obtained. And the circular end 20 comprises a hole 22 diametrically opposite to the supply conduit 2, in which one end of the pilot injection conduit 9 is driven in, whereas the opposite end of the pilot injection conduit 9, which is bent, is adjusted on the pilot injection jet 11. The result is a circulation of fuel without obstacle from the two sides of the outer crown 8 around the multipoint injection crown 6 up to the pilot injection jet 11. Bathed by external fuel, the multipoint injection crown 6 escapes coking and the risks of clogging of the tubes 15 which could have appeared when the fuel that is present therein stagnates while the multipoint injection is stopped. The fuel circulating in the pilot injection and notably around the multipoint injection crown 6 remains at a temperature of less than 100 C., much less than that of the ambient air, and it thus maintains a sufficient exchange of heat to ensure this protection against coking.

[0022] A uniform distribution of fuel may be hoped for in the different tubes 15 of the two parts of the multipoint injection crown 6, in accordance with the objective of the invention which is to ensure an equal flow rate in the different injection holes 16 thanks to the early division of the multipoint injection flow. It is possible if necessary to construct the tubes 15 with different geometric characteristics, in order to level out there in head losses and to reinforce this desired flow rate equality: it is thus possible to envisage compensating the effects of the differences in lengths between the tubes 15, for example by constructing them with different sections, greater for the longest tubes 15, or greater sectional irregularities or other obstacles in the shortest tubes 15, since the head losses are proportional to the widths of the conduits, and inversely proportional to their diameter. A great freedom in design is available to do this, which is made possible by manufacturing the multipoint injection crown 6 by a material addition method, of a part with the outer crown 8 or separately. Such a manufacturing facility does not exist with conventional construction methods, where tubes would be connected independently to a distribution device, since the choice of the diameters would then be limited, and the distribution device provided with different connections, more complicated to construct. It is to be noted that head losses may also be caused in the shortest tubes 15 by irregularities of section or other obstacles, but it is simpler and surer to construct them with a judiciously chosen constant section, with identical length over diameter ratios

[00003]$\frac{L}{D}.$

[0023] The tubes 15 are connected to the multipoint injection holes 16 by connecting tubes 23 which extend essentially in the direction of the central axis of the multipoint injection crown 6 and form a bend with the tubes 15.

[0024] A dimensioning rule that can favourably be applied thereto is to assign them a ratio

[00004]$\frac{L}{D}$

(length, between each multipoint injection hole 16 and the junction bend to the respective tube 15, over diameter: FIG. 6) that is identical

[00005]$\left(\frac{L_1}{D_1}=\frac{L_2}{D_2}=\frac{L_3}{D_3}\right),$

in order that the penetration heights of the fuel jets in the inner volume 12 of the combustion chamber 25 are also identical and that a regular injection is thus obtained. This rule is all the more justified if the tubes 5 are grouped together into bundles in the outer crown 8 at different depths under the multipoint injection holes 16.

[0025] The respect of these length/diameter ratios

[00006]$\frac{L}{D}$

also produces identical head losses in the connecting tubes 23 when they exist.