1. Field of the Invention
The present invention relates to a turbomachine combustion chamber shell ring.
The shell ring in question herein defines a flame tube, which is thus subject to considerable overheating on the inner face thereof, whereas the outer face thereof is crossed by a cool gas flow, originating from the turbomachine compressors and mixing with the combustion gases downstream from the shell ring before entering the turbines.
2. Description of the Related Art
Such a shell ring is traversed by a plurality of types of holes, including dilution holes having a relatively large diameter intended to allow the entry of a portion of the outer flow into the flame tube so as to improve the composition of the combustion mixture, and finer ventilation holes, which are more numerous and distributed on most of the surface area of the shell ring, to also enable the entry of air from the outer flow, but which have the effect of protecting the shell ring from overheating, by forming a flush flow in the downstream direction on the inner face of the shell ring and thus a boundary layer cooler than the combustion gases.
This boundary layer is reformed poorly downstream from the large diameter holes, interrupting the flush flow, and the corresponding portions of the shell ring, all or almost all subject to overheating, are subject to deformation and stress arising from differential expansions, which may give rise to cracks.
The document EP-A-1 703 207 describes a combustion chamber whereon the invention may be implanted. In addition, the above problems are mentioned in the French patent application registered under the number 11 53232 disclosing a modification of the conventional shell ring arrangement to reform the boundary layer immediately downstream from the large-diameter holes and thus relieve the shell ring. A further solution is however proposed with the present invention.
In a general form, it relates to a turbomachine combustion chamber shell ring, comprising dilution holes and ventilation holes surrounding the dilution holes and finer and more numerous than said holes, characterised in that it comprises inserts extending over and around the dilution holes on an outer face of the shell ring, the shell ring is devoid of ventilation holes at portions situated above the inserts, the inserts each comprising an edge for attaching to the shell ring and an orifice extending over one of the respective dilution holes, and the inserts are traversed by holes directed towards said portions of the shell ring.
The essential effect obtained is that the high pressure present around the shell ring allows the entry of air via the holes of the insert, in streams striking the outer face of the shell ring and producing the sought cooling at this location, with a greater intensity than ventilation holes arranged through the shell ring, traversed very quickly by the air. Instead, the air sucked in below the insert flows on the outer face of the shell ring after reaching same, towards the dilution hole, and this flow time causes a greater elimination of heat. When the air enters the dilution hole, the relatively low speed driving same may make it possible for it to resume a tangent downstream direction relatively easily, which will help restore the boundary layer on the inner face of the shell ring and will enhance the ventilation further.
According to requirements, the inserts may be parallel with the shell ring or inclined relative thereto in an axial direction of the shell ring. The holes of the inserts are advantageously perpendicular to the shell ring, but they may also be positioned obliquely; all these adaptations are to be decided in each design.
Advantageously, the inserts extend more in the downstream direction of the shell ring than in other directions from the centres of the dilution holes, since the portions of the shell ring subject to intense overheating are specifically downstream from these holes. The inserts may however be subject to retraction in this downstream direction of the shell ring, since the boundary layer is reformed according to the same shape, bypassing the dilution holes.
A further favourable feature is obtained if the inserts each comprise an inner edge surrounding the respective orifice and extending towards the respective dilution passage, making it possible to channel both the air sucked in directly by the dilution holes via the insert orifice, and the air sucked in by the insert holes and blowing onto the shell ring, then flowing around this inner edge.
Satisfactory cohesion is obtained if the inner edge is enclosed between the attachment sectors situated in the respective dilution hole, flow sectors being defined in said respective dilution hole by the inner edge and between the attachment sectors. In order to help continue the flow on the downstream side of the dilution hole, more advantageously, the dilution holes and the inner edge have centres offset in an axial direction of the shell ring, such that the flow sectors have a main surface area downstream from the inner edge.
A further aspect of the invention is a turbomachine combustion chamber comprising such a shell ring.
The invention will now be described with reference to the following figures:
A turbomachine combustion chamber where the invention may be present is represented schematically in
The shell rings 2 and 3 are traversed by numerous holes, including numerous fine ventilation holes 38 and less numerous larger diameter dilution holes 39, distributed on a circle or a small number of circles. The common effect of these holes is that of allowing air from the streams 8 and 9 to enter the flame tube 16 at a lower pressure for a variety of purposes.
The invention may be used on either of the shell rings 2 and 3.
Remarks will now be made in relation to
The specific flow provided by the insert 40 is as follows. Air from the flow of the flow of the stream 8 or 9 at a high pressure is blown into the chamber 49 via the holes of the inserts 45 and cools the shell ring 2 or 3 around the respective dilution hole 39, and particularly the portion downstream therefrom, via the outer face thereof. This air then flows into the flame tube 16 via the flow sectors 47 and 48 and particularly through same. On reaching the flame tube 16, the flow thereof may rapidly return to an axial direction downstream from the combustion chamber and reform a boundary layer in the above-mentioned area of the shell ring 2 or 3 downstream from the dilution hole 38 and helps protect same further.
The main portions 41 of the inserts 40 may be optionally parallel with the portion opposite the shell ring 2 or 3, and the holes 45 optionally perpendicular to this portion. The main portions 41 may particularly be inclined in relation to the shell ring 2 or 3, along the contour 41′ rising in a downstream direction, to better intercept the flow air by creating a larger obstacle.
Number | Date | Country | Kind |
---|---|---|---|
12 54847 | May 2012 | FR | national |
Filing Document | Filing Date | Country | Kind |
---|---|---|---|
PCT/FR2013/051117 | 5/23/2013 | WO | 00 |
Publishing Document | Publishing Date | Country | Kind |
---|---|---|---|
WO2013/175126 | 11/28/2013 | WO | A |
Number | Name | Date | Kind |
---|---|---|---|
4132066 | Austin, Jr. et al. | Jan 1979 | A |
4875339 | Rasmussen | Oct 1989 | A |
4887432 | Mumford | Dec 1989 | A |
20070084219 | Bernier et al. | Apr 2007 | A1 |
20070227149 | Biebel et al. | Oct 2007 | A1 |
20090013530 | Rudrapatna | Jan 2009 | A1 |
Number | Date | Country |
---|---|---|
2 404 110 | Apr 1979 | FR |
2 892 180 | Apr 2007 | FR |
2 899 315 | Oct 2007 | FR |
Entry |
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International Search Report Issued Mar. 5, 2014 in PCT/FR13/051117 Filed May 23, 2013. |
French Search Report Issued Jan. 4, 2013 in French Patent Application No. 12 54847 Filed May 25, 2012. |
Number | Date | Country | |
---|---|---|---|
20150059344 A1 | Mar 2015 | US |