EP1634021A1

EP1634021A1 - Annular combustion chamber for a turbomachine

Info

Publication number: EP1634021A1
Application number: EP04767843A
Authority: EP
Inventors: Yves Salan; Denis Sandelis
Original assignee: SNECMA SAS
Current assignee: Safran Aircraft Engines SAS
Priority date: 2003-06-18
Filing date: 2004-06-18
Publication date: 2006-03-15
Anticipated expiration: 2024-06-18
Also published as: RU2005107793A; RU2351849C2; JP2006527834A; EP1634021B1; FR2856467A1; CN1701203A; KR20060029203A; US20070056289A1; US7328582B2; WO2004113794A1; FR2856467B1

Abstract

The invention relates to an annular combustion chamber (1) for a turbomachine. Said combustion chamber (1) is configured such that, from the perspective of an axial cross section, the value of the acute angles (A) formed between a line that runs substantially along the centerline (32) of the cross section located between an external axial wall (2) and an internal axial wall (4), and the main directions (34) in which the perforations (26) of an external portion (28) of a bottom (8) of the chamber extend within said cross section, decreases as a function of the distance between the perforations (26) and said line running substantially along the centerline (32) while the value of the acute angles (B) formed between the line running substantially along the centerline (32) and the main directions (36) in which the perforations (26) of an internal portion (30) of the bottom (8) of the chamber extend within said cross section decreases as a function of the distance between the perforations (26) and said line running substantially along the centerline (32).

Description

ANNULAR COMBUSTION CHAMBER OF TURBOMACHINE

DESCRIPTION

TECHNICAL FIELD The present invention relates generally to the field of annular combustion chambers of a turbomachine, and more particularly to that of the means making it possible to thermally protect these combustion chambers.

STATE OF THE PRIOR ART

Typically, an annular combustion chamber of a turbomachine comprises an external axial wall and an internal axial wall, these walls being arranged coaxially and connected to each other via a chamber bottom.

At the level of this chamber bottom, also of annular shape, the combustion chamber is provided with angularly spaced injection orifices, each of them being intended to receive a fuel injector in order to allow combustion reactions to inside this combustion chamber. It is also noted that these injectors can also make it possible to introduce at least part of the air intended for combustion, the latter occurring in a primary zone of the combustion chamber, located upstream of a secondary zone. said dilution zone.

In this regard, it is noted that apart from the air requirements for the combustion reactions inside the primary zone of the combustion chamber, the latter moreover requires dilution air generally introduced via dilution orifices made on the external and internal axial walls, and also cooling air capable of protecting all of the constituent elements of the combustion chamber.

According to a known embodiment of the prior art, deflectors are arranged on the chamber bottom, in order to protect it from thermal radiation. Each deflector, also called a cup or heat shield, then has at least one injection orifice intended to receive a fuel injector, as well as a plurality of perforations making it possible to allow cooling air to pass inside the combustion chamber.

However, the addition of such deflectors generates major drawbacks. Indeed, among these drawbacks, it can be mentioned the fact that it is imperative to allocate a large flow of cooling air to cool these deflectors. In such a case, the cooling air flow passing through the perforations made is then evacuated in the form of an equally abundant "flow under deflector", which generates freezing effects near the wall and which therefore results in the creation of species of the CO and CH _{X type} . Consequently, the appearance of such species inside the combustion chamber causes a non-negligible reduction in the combustion efficiency. On the other hand, it is also indicated that the presence of deflectors directly results in the creation of a strong thermal gradient between the cold parts and the hot parts of the chamber, as well as by a very detrimental increase in the total mass of this combustion chamber.

In an attempt to overcome these drawbacks, another type of combustion chamber has been proposed, in which the deflectors have been eliminated. Thus, the injection orifices are made directly in the bottom of the chamber, in the same way as the perforations which are then intended to allow the passage of a flow of cooling air capable of cooling the bottom of the chamber itself, this cooling air flow being advantageously less than that required in the case of the use of deflectors.

However, with such an embodiment, it has been found that the perforations presented generate either a disturbance of the combustion reactions in the primary zone, or thermal discontinuities at the junctions between the chamber bottom and the external and internal axial walls.

PRESENTATION OF THE INVENTION The object of the invention is therefore to propose an annular combustion chamber for a turbomachine, at least partially remedying the drawbacks mentioned above relating to the embodiments of the prior art. More specifically, the object of the invention is to present an annular combustion chamber of turbomachine, the means of which used to cool the chamber bottom generate neither significant disturbance of the combustion reactions inside the combustion chamber, nor thermal discontinuities at the junctions between the chamber bottom and the external axial walls and internal.

To do this, the invention relates to an annular combustion chamber of a turbomachine, comprising an external axial wall, an internal axial wall and a chamber bottom connecting the axial walls, the chamber bottom having a plurality of orifices injection as well as a plurality of perforations, the injection orifices being intended to allow at least the injection of fuel inside the combustion chamber and the perforations being intended to allow the passage of a flow cooling air capable of cooling the bottom of the chamber. According to the invention, the chamber bottom is provided on the one hand with an external portion on which the perforations are made so as to direct part of the cooling air flow in the direction of the external axial wall, and other part of an internal portion on which the perforations are formed so as to direct another part of the cooling air flow towards the internal axial wall, and the chamber is designed so that in axial half-section , taken in any way between two directly consecutive injection orifices, the value of the acute angles formed between a substantially median line of the half-section situated between the external axial wall and the axial wall internal, and of the main directions, in this half-section, of the perforations of the external portion, evolves in a decreasing fashion as a function of the distance between the perforations and this substantially median line, and the value of the acute angles formed between the substantially median and main directions, in this half-section, of the perforations of the internal portion, decreases as a function of the distance between the perforations and this substantially median line.

In other words, the combustion chamber according to the invention is such that the perforations located near a junction between the external portion and the internal portion of the chamber bottom, that is to say substantially facing 'a central annular ring of the combustion chamber, are more inclined towards the axial walls than can be the perforations located near these same axial walls, that is to say substantially opposite annular rings d end of this same combustion chamber.

Advantageously, the perforations located near the junction between the external portion and the internal portion of the chamber bottom can therefore be strongly inclined in the direction of the axial walls, and consequently allow the cooling air coming from these perforations of s '' flow easily and directly along the inner surface of the chamber bottom, substantially radially to the external and internal axial walls. In the same way, this strong possible tilt indicates that the air from cooling is only very little directed towards the center of the primary zone of the combustion chamber, so that it does not cause a significant disturbance of the combustion reactions. Furthermore, the perforations located near the axial walls may be inclined only slightly towards these axial walls, so that the cooling air coming from these perforations can easily and directly flow along the surfaces interior of these same axial walls. It is specified that at these levels of the chamber bottom where the cooling air can be ejected inside the combustion chamber in a substantially axial direction 'of the latter, that is to say substantially parallel to the axial walls, the primary zone is far enough away that the cooling air introduced does not cause significant disturbance of the combustion reactions.

On the other hand, it is advantageously possible to perform a gradual inclination of these perforations as they approach the external and internal axial walls, so as to obtain a substantially homogeneous cooling flow over the entire internal surface. of the chamber bottom, as well as on the entire interior hot surface of the axial walls, located near the chamber bottom.

The combustion chamber according to the invention is therefore perfectly adapted so as not to generate significant disturbance of the combustion reactions inside the primary zone, which is essential for the stability and ignition of the combustion chamber. In addition, the specific design of this chamber simultaneously ensures satisfactory thermal continuity at the junctions between the chamber bottom and the external and internal axial walls.

Preferably, for any two directly consecutive perforations of the external portion, the two acute angles formed between the main directions of these perforations and the substantially median line have different values, and for any two direct perforations of the internal portion, the two acute angles formed between the main directions of these perforations and the substantially median line have different values.

This particular configuration makes it possible to obtain a very gradual inclination of the perforations of the chamber bottom. Of course, it could also be envisaged to provide different solutions in which several any directly consecutive perforations would have the same inclination in the plane of the axial half-section concerned, without departing from the scope of the invention.

Preferably, the chamber bottom is provided with primary sectors of perforations as well as secondary sectors of perforations, the primary sectors being located substantially between two directly consecutive injection orifices, and the secondary sectors being on either side of each. injection orifice, in a substantially radial direction of the combustion chamber.

With such an arrangement, it is possible to further reinforce the homogeneity of the cooling air flow going towards the external and internal axial walls of the combustion chamber. This homogeneity can in particular be obtained by providing that the perforations of the secondary sectors are larger than those of the perforations of the primary sectors, due to their presence in small quantities.

Other advantages and characteristics of the invention will appear in the detailed non-limiting description below.

BRIEF DESCRIPTION OF THE DRAWINGS

This description will be made with reference to the accompanying drawings, among which;

FIG. 1 represents a partial view in axial half-section of an annular combustion chamber of a turbomachine, according to a preferred embodiment of the present invention,

- Figure 2 shows a partial sectional view taken along line II-II of Figure

1, - Figure 3 shows a sectional view taken along line III-III of Figure 2, and

- Figure 4 shows a sectional view taken along line IV-IV of Figure 2. DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT

With reference jointly to Figures 1 and 2, there is shown an annular combustion chamber 1 of a turbomachine, according to a preferred embodiment of the present invention.

The combustion chamber 1 comprises an external axial wall 2, as well as an internal axial wall 4, these two walls 2 and 4 being arranged coaxially along a longitudinal main axis 6 of the chamber 1, this axis 6 also corresponding to the axis main longitudinal of the turbomachine.

The axial walls 2 and 4 are interconnected by means of a chamber bottom 8, the latter being assembled for example by welding to an upstream part of each of the axial walls 2 and 4.

The chamber bottom 8 preferably takes the form of a substantially planar annular ring, with an axis identical to the main longitudinal axis 6 of the chamber 1. Of course, this chamber wav 8 could also have any other suitable shape, such as a frustoconical shape of the same axis, without departing from the scope of the invention.

A plurality of injection orifices 10, preferably of cylindrical shape and of circular section, are distributed angularly and in a substantially regular manner on the chamber bottom 8. Each of these injection orifices 10 is designed so as to be able to cooperate with a fuel injector 12, in order to allow the combustion reactions inside this combustion chamber 1. It is specified that these injectors 12 are also designed to so as to allow the introduction of at least part of the air intended for combustion, the latter occurring in a primary zone 14 situated in an upstream part of the combustion chamber 1. Furthermore, it is also indicated that the air intended for combustion can also be introduced inside the chamber 1 by means of primary orifices 16, situated all around the external axial 2 and internal 4 walls. As can be seen in the figure 1, the primary orifices 16 are arranged upstream of a plurality of dilution orifices 18, the latter also being placed all around the external axial 2 and internal 4 walls, and having the main function of allowing the supply of air d a dilution zone 20 located downstream of the primary zone 14.

In addition, it is specified that another part of the air supplied to the combustion chamber 1 is in the form of a cooling air flow D, serving mainly to cool the interior surface 21 of the chamber bottom 8. As such, even if the air used to cool the chamber bottom 8 also makes it possible to cool an upstream portion of the interior surfaces 22 and 24 of the external axial 2 and internal 4 walls, an additional cooling air flow ( not shown) is generally allocated to cool all of these hot interior surfaces 22 and 24.

More specifically with reference to FIG. 2, it can be seen that the bottom of the chamber 8 is of the ultra-perforated type, namely that it has a plurality of perforations 26, preferably cylindrical with circular sections, and intended to allow the passage of the cooling air flow D inside the combustion chamber 1. As can be seen in this figure, the chamber bottom 8 is divided into an external portion 28 connected to the external axial wall 2, and into an internal portion 30 connected to the internal axial wall. Of course, these annular portions 28 and 30 are usually formed in one piece, and their virtual separation can then consist of a circle C with a center located on the main longitudinal axis 6, and with radius R corresponding to an average radius between an outer radius and an inner radius of the chamber bottom 8. On this chamber bottom 8, the perforations

26 located on the external portion 28 are then made so as to direct a part Dl of the cooling air flow D in the direction of the external axial wall 2, in order to cool the whole of this external portion 28, as well as a upstream portion of the external axial wall 2. In the same way, the perforations 26 located on the internal portion 30 are formed so as to direct another part D2 of the cooling air flow D towards the internal axial wall 4, in order to cool the whole of this internal portion 30, as well as an upstream portion of the internal axial wall 4.

With reference now to FIG. 3, it can be seen that in the axial half-section, the perforations 26 of the external portion 28 are such that the value of the acute angles A formed between a line substantially median 32 of the half-section and of the main directions 34 of the perforations 26 in this half-section, decreases as a function of the distance between these perforations 26 and this substantially median line 32.

In other words, in each axial half-section of the combustion chamber 1, taken between any two injection orifices 10 and directly consecutive, the inclination of the perforations 26 relative to the external axial wall 2 gradually decreases as and as these perforations 26 of the external portion 28 move away from the substantially central line 32, the latter being mentioned essentially for reference. Indeed, by substantially median line 32 of the half-section, it is naturally to understand that it is the virtual line situated at approximately equal distance from the upstream parts of the external axial 2 and internal 4 walls considered in half-section, this line 32 can also be noted in the sense that, in addition to constituting an axis of symmetry of the half-section shown, it virtually separates the external 28 and internal 30 portions of the chamber bottom 8. It is specified that in the mode of preferred embodiment described, this substantially central line 32, passing through the circle C, is also substantially perpendicular to the chamber bottom 8, insofar as it itself is substantially perpendicular to the axial walls 2 and 4. On the other hand, it is also indicated that in the axial half-section shown in the figure 3, the main directions 34 of the perforations 26 respectively correspond to their main axes, in the sense that these perforations 26 are all crossed diametrically by the section plane. However, in any other axial half-section where one or more perforations 26 can be cut other than diametrically, each main direction 34 can then be considered to be a line substantially parallel to the two straight segments symbolizing the perforation 26 concerned.

Thus, the perforations 26 located near the substantially central line 32 can therefore be strongly inclined, for example so that the acute angle A reaches a value of about 60 °. The cooling air coming from these perforations 26 can therefore flow easily and directly along the internal surface 21 of the external portion 28 of the chamber bottom 8, substantially radially up to the external axial wall 2, without disturbing combustion reactions in the primary zone 14.

In addition, the perforations 26 located near the external axial wall 2 may be inclined only slightly towards this wall 2, for example so that the acute angle A reaches a value of approximately 5 °. The cooling air coming from these perforations 26 can then easily and directly flow along the hot internal surface 22 of the external axial wall 2, without stagnating at the junction between the chamber bottom 8 and this same wall. axial 2. By providing a value for the acute angle A which decreases progressively as it approaches the external axial wall 2, it is then possible to obtain a very homogeneous portion Dl of the cooling flow rate D, not creating any thermal discontinuity at the level of the various constituents of the combustion chamber 1.

In the same way and in order to take advantage of the same effects on the internal portion 30 of the chamber bottom 8 as well as on the internal axial wall 4, in axial half-section, the perforations 26 of the internal portion 30 are such that the value of the acute angles B formed between the substantially median line 32 and the main directions 36 of the perforations 26 in this half-section, decreases as a function of the distance between these perforations 26 and this substantially median line 32.

Similarly to that encountered with the external portion 28 of the chamber bottom 8, the value of the acute angles B formed between on the one hand the main directions 36 of the perforations 26 of the internal portion 30, and on the other hand the line substantially median 32, can progressively evolve from approximately 60 ° to approximately 5 °, approaching the internal axial wall 4. Referring again to FIG. 2, it can be seen that the chamber bottom 8 is provided with primary sectors 38 of perforations 26, these primary sectors 38 being situated substantially between two directly consecutive injection orifices 10. As can be seen in this figure, at least part of the perforations 26 of each primary sector 38 (only one of them being shown) are arranged so as to define rows taking the form of curved lines centered on the center of the injection orifice 10 near which these perforations 26 are located. In addition, the chamber bottom 8 is also provided with secondary sectors 40 of perforations 26, these secondary sectors 40 each lying between two consecutive primary sectors 38, on either side of an injection orifice 10 in a direction. substantially radial from the combustion chamber 1.

In other words, in this same substantially radial direction of the combustion chamber 1, a secondary sector 40 is located both above and below the injection orifice 10 concerned.

In this regard, as shown in FIG. 4 and similarly to that described above, it can also be provided that in an axial half-section taken so as to pass through an injection orifice 10, the perforations 26 of the outer portion 28 are such that the value of the acute angles C formed between a substantially median line 42 of the half-section and the main directions 44 of the perforations 26 in this half-section, decreases as a function of the distance between these perforations 26 and this substantially median line 42.

In the same way, the perforations 26 of the internal portion 28 are then such that the value of the acute angles D formed between the substantially median line 42 of the half-section and of the directions main 46 of the perforations 26 in this half-section, evolves in a decreasing fashion as a function of the distance between these perforations 26 and this substantially median line 42. Finally, it is specified that in order to have the most homogeneous flow portions D1 and D2 circumferentially possible, the perforations 26 of the secondary sectors 38 are preferably of larger dimensions than those of the perforations 26 of the primary sectors 40, because of their presence in smaller numbers.

Of course, various modifications can be made by those skilled in the art to the annular combustion chamber 1 which has just been described, only by way of nonlimiting example.

Claims

1. annular combustion chamber (1) of a turbomachine, said chamber (1) comprising an external axial wall (2), an internal axial wall (4) and a chamber bottom (8) connecting said axial walls (2,4) , the chamber bottom (8) having a plurality of injection orifices (10) as well as a plurality of perforations (26), said injection orifices (10) being intended to allow at least the injection of fuel inside the combustion chamber (1) and said perforations (26) being intended to allow the passage of a cooling air flow (D) capable of cooling the bottom of the chamber (8), characterized in that the chamber bottom (8) is provided on the one hand with an external portion (28) on which the perforations (26) are formed so as to direct a part (Dl) of the cooling air flow (D) towards the external axial wall (2), and on the other hand an internal portion (30) on which the perforations (26) are practiced es so as to direct another part (D2) of the cooling air flow (D) towards the internal axial wall (4), and in that the chamber (1) is designed so that in half -axial section, taken in any way between two directly consecutive injection orifices (10), the value of the acute angles (A) formed between a substantially median line of the half-section (32) located between the external axial wall (2 ) and the internal axial wall (4), and main directions (34), in this half-section, perforations (26) of the external portion (28), evolves from decreasing according to the distance between the perforations (26) and this substantially median line (32), and the value of the acute angles (B) formed between the substantially median line (32) and main directions (36), in this half-section, of the perforations (26) of the internal portion (30), evolves in a decreasing fashion as a function of the distance between the perforations (26) and this substantially median line (32).

2. annular combustion chamber (1) according to claim 1, characterized in that for any two perforations (26) directly consecutive of the external portion (28), the two acute angles (A) formed between the main directions (34) of these perforations (26) and the substantially central line (32) have different values, and in that for any two perforations (26) directly consecutive from the internal portion (30), the two acute angles (B) formed between the main directions (36) of these perforations (26) and the substantially median line (32) have different values.

3. annular combustion chamber (1) according to claim 1 or claim 2, characterized in that the chamber bottom (8) is provided with primary sectors (38) of perforations (26) as well as secondary sectors (40) of perforations (26), the primary sectors (38) being located substantially between two directly consecutive injection orifices (10), and the secondary sectors (40) being located on either side of each orifice injection (10), in a substantially radial direction of said combustion chamber (1).

4. annular combustion chamber (1) according to claim 3, characterized in that the perforations (26) of the secondary sectors (40) are larger than those of the perforations

(26) primary sectors (38).