Annular combustor for an aircraft turbine

Abstract

Annular combustion chamber (1) for an aircraft turbine (3), said chamber having two coaxial annular walls, namely an inner annular wall (11) and an outer annular wall (12) respectively, the inner annular wall and the outer annular wall being connected upstream by an annular bottom wall (10) of the chamber (1), wherein injection means (13) pass through the axis (X) and comprise an air injection system (16) and a frustoconical bowl-shaped part (19'), the frustoconical bowl-shaped part flaring out downstream and having an air passage opening (190), the chamber (1) further having an annular deflector (14) which is arranged downstream of the bottom wall (10) and is substantially parallel to the bottom wall, and wherein the air injection system (16), the bottom wall (10), the deflector (14) and the bowl-shaped part (19') are integral.

Description

Field of the Invention

[0001] The present invention relates to an annular combustion chamber for an aircraft turbine. Background Art

[0002] The prior art particularly includes the documents WO-A1-2019 / 224484, EP-A1-0821201 and EP-A2-0724119.

[0003] The turbine includes a gas generator which particularly includes one or more compressors, such as a low-pressure compressor and a high-pressure compressor, arranged upstream of the combustion chamber.

[0004] In the present application, by convention, the terms "upstream" and "downstream" are defined relative to the direction of the gas flow in the turbine. Similarly, according to the convention in the present application, the terms "inner" and "outer" are defined radially relative to the longitudinal axis of the turbine, which is in particular the axis of rotation of the compressor rotor.

[0005] Figure 1 The combustion chamber 1 is partially shown, which has an annular shape around the axis of rotation A. The chamber 1 is arranged in an annular enclosure 4 radially delimited by an outer annular housing 5 and an inner annular housing 6. The chamber 1 is delimited by a coaxial inner annular wall 11 and an outer annular wall 12, which are joined upstream by an annular bottom wall 10 of the chamber. The bottom wall 10 of the chamber 1 is generally referred to as the chamber bottom 10.

[0006] Reference Figure 2 , the chamber bottom 10 includes holes 100 angularly distributed around the axis A, which are configured to be respectively aligned with the injection devices 13 of the fuel and air mixture. Each injection device 13 may include a fuel injector 15 and an air injection system 16.

[0007] The injector 15 is angled and has one end fixed to the outer housing and an opposite end forming a head, which is engaged and centered in the injection system 16.

[0008] The injection system 16 is installed in the holes 100 of the chamber bottom 10. The injection system 16 includes, from upstream to downstream with respect to the gas flow, a support and centering device 17 for the head of the injector 15, an air injection device 18, and an air-fuel mixture diffusion device 19 inside the chamber 1.

[0009] In Figure 2In [the device], device 19 may include a frustoconical bowl-shaped portion 19', which tapers and expands downstream and has air passage orifices 190, 190'. The bowl-shaped portion 19' includes an outer annular collar 196 and a frustoconical wall 191. Orifice 190' is formed in wall 191, and orifice 190 opens in front of collar 196.

[0010] Compressed air 7 from a high-pressure compressor (not shown) is supplied to chamber 1 through an annular diffuser 8, and fuel is supplied to chamber 1 through injectors 15 angularly distributed about axis A. Combustion of the air / fuel mixture is initiated by an ignition device 22, and heat radiation is generated from downstream to upstream in the direction of chamber bottom 10. Accordingly, chamber bottom 10 is subjected to high temperatures (usually between 1200 °C and 2000 °C).

[0011] To protect chamber bottom 10, at least one annular deflector 14 (also referred to as a heat shield) is arranged in chamber 1 in a substantially parallel manner, downstream of and facing chamber bottom 10, and is located at a short distance from chamber bottom. Deflector 14 may be annular or may be divided into a plurality of deflector segments angularly distributed about axis A.

[0012] Referring Figure 3 , deflector 14 is cooled by the impact of an air jet, which also comes from the high-pressure compressor and enters chamber 1 through cooling air passage holes 20 formed in chamber bottom 10. Accordingly, the cooling air flowing from upstream to downstream of deflector 14 passes through chamber bottom 10 through holes 20 and then impinges on a part of the upstream face 142a of deflector 14. Then, the air is guided to flow radially inwards and radially outwards in chamber 1 to generate a cooling air film flowing from upstream to downstream on each of inner wall 11 and outer wall 12.

[0013] In addition, collar 196 is also cooled by the impact of an air jet, which comes from the high-pressure compressor and penetrates chamber 1 through cooling air passage orifice 190'.

[0014] Although this architecture enables deflector 14, bowl-shaped portion 19' and a part of chamber bottom 10 to be cooled, this architecture does pose some difficulties, especially some areas of the chamber bottom may not be effectively cooled. For example, the areas where deflector 14 and injection device 13 are attached to chamber bottom 10 are difficult to be cooled by holes 20 and orifices 190, 190'.

[0015] In fact, generally, area 10a of chamber bottom 10 is cooled, while area 10b of chamber bottom 10 is not cooled ( Figure 3)。The cooling zone 10a corresponds to the upstream face 142a of the deflector 14 and the upstream face 196a of the collar 196. The non-cooling zone 10b corresponds to the bowl-shaped part 19' of each injection device 13 and the zone where the deflector 14 is attached to the chamber bottom 10. This attachment zone 10b is particularly subject to high thermal stresses, which can alter the performance of the chamber bottom when this attachment zone is not properly cooled.

[0016] Thus, insufficient cooling of this attachment zone can reduce the lifespan of the chamber bottom and degrade the performance of the combustion chamber of the turbine.

[0017] An object of the present invention is to at least partially remedy these drawbacks. Summary of the Invention

[0018] The present invention proposes an annular combustion chamber for an aircraft turbine, the chamber comprising two coaxial annular walls, namely an inner annular wall and an outer annular wall respectively. The inner annular wall and the outer annular wall are connected by an annular bottom wall of the chamber upstream. The injection device passes through the axis X and comprises an air injection system and a frustoconical bowl-shaped part, the frustoconical bowl-shaped part tapering downstream and comprising an air passage orifice. The chamber further comprises an annular deflector, which is arranged downstream of the annular bottom wall of the chamber and is substantially parallel to the annular bottom wall of the chamber.

[0019] Thus, the air injection system, the bottom wall, the deflector and the bowl-shaped part of the chamber are integrated.

[0020] This configuration enables effective cooling of the entire annular bottom wall of the chamber while maintaining the integration of the air passage orifices of the frustoconical bowl-shaped part, in favor of combustion efficiency and more generally in favor of the turbine. This configuration also enables reduction of the size of the combustion chamber.

[0021] The chamber according to the present invention may comprise one or more of the following features, which are adopted independently of each other or in combination with each other:

[0022] - The deflector comprises an annular part, which is substantially parallel to the bottom wall and is separated from the bottom wall by a first space;

[0023] - The annular part comprises an inner end relative to the axis X, which is connected to the bowl-shaped part and the bottom wall;

[0024] - The bowl-shaped part comprises a first frustoconical wall and a second frustoconical wall, the first frustoconical wall and the second frustoconical wall being substantially parallel to each other and separated from each other by a second space. The bottom wall and the first frustoconical wall of the bowl-shaped part have air passage holes in the said first space and the said second space;

[0025] - The walls at the bottom of the chamber and the first frustoconical wall of the bowl-shaped part include air passage holes in the first space and the second space;

[0026] - The orifice of the bowl-shaped part extends through the frustoconical wall of the bowl-shaped part until it leads to the chamber;

[0027] - The outlet of the orifice of the bowl-shaped part is located at the joint between the wall of the annular part of the deflector and the second frustoconical wall of the bowl-shaped part;

[0028] - Each air injection system includes a main swirler, which is integral with the bottom wall, the bowl-shaped part, and the deflector;

[0029] - Each air injection system includes a secondary swirler and a Venturi tube, which are integral with the bottom wall, the bowl-shaped part, and the deflector, and the Venturi tube is arranged between the two swirlers;

[0030] - The deflector includes an annular edge at its outer peripheral edge that extends parallel to and is spaced apart from the outer wall, and an annular edge at its inner peripheral edge that extends parallel to and is spaced apart from the inner wall;

[0031] - The orifice of the bowl-shaped part is inclined at an angle between 15° and 75°, and this angle is measured with respect to the axis X of the injection device.

[0032] A second object of the present invention is a turbine that includes a combustion chamber as described above. Description of the Drawings

[0033] The present invention will be better understood and other details, features, and advantages of the present invention will become clearer by reading the following description given by way of non-limiting example and referring to the drawings, in which:

[0034] Figure 1 Figure 1 is a schematic semi-view of an axial section of a combustion chamber of an aircraft turbine according to the prior art;

[0035] Figure 2 Figure 2 is Figure 1 a partial schematic view of an axial section of the bottom of the chamber of the combustion chamber;

[0036] Figure 3 Figure 3 is a view similar to Figure 2 and shows the cooling area and non-cooling area of the bottom of the chamber of the prior art;

[0037] Figure 4 Figure 4 ​​​​​​​​is a schematic axial sectional view of a combustion chamber according to the present invention;

[0038] Figure 5 Figure 5 is Figure 4 a schematic partial axial sectional view of the combustion chamber;

[0039] Figure 6 Figure 6 is a schematic axial cross-sectional view along the C-C sectional plane of Figure 4 and shows the upstream side of the combustion chamber;

[0040] Figure 7 Figure 7 is a view similar to Figure 5 and shows the cooling area at the bottom of the chamber according to the present invention. DETAILED DESCRIPTION

[0041] The above has described Figures 1 to 3 .

[0042] Figures 4 to 7 Schematically shows an embodiment of a combustion chamber 1 according to the present invention.

[0043] Figure 4 Shows an annular combustion chamber 1 of a gas generator 2 of an aircraft turbine 3 having a rotational axis A.

[0044] The chamber 1 is located downstream of one or more compressors (e.g., a low-pressure compressor and a high-pressure compressor) and upstream of one or more turbines (e.g., a high-pressure turbine and a low-pressure turbine).

[0045] The rotational axis A of the chamber 1 coincides with the longitudinal axis of the turbine 3, which is in particular the rotational axis of the rotors of the compressor and the turbine.

[0046] The chamber 1 is arranged in an annular enclosure 4 radially defined by an outer annular housing 5 and an inner annular housing 6. A compressed air flow 7 generated by the compressor enters the enclosure 4 via an annular diffuser 8.

[0047] The chamber 1 is defined by a coaxial annular inner wall 11 and an annular outer wall 12. The walls 11, 12 are connected upstream by an annular bottom wall of the chamber 10 (also referred to as "chamber bottom 10" or "bottom wall 10"), which is substantially transverse to the axis A.

[0048] According to the embodiment shown in Figures 4 to 7 , the chamber 1 defines on the one hand an annular inner air passage 9a radially defined by the inner wall 11 and the inner housing 6, and on the other hand an annular outer air passage 9b radially defined by the outer wall 12 and the outer housing 5.

[0049] ​​​​​​A mixture of air and fuel is supplied to chamber 1 through a plurality of air and fuel injection devices 13, which are angularly distributed around axis A in a regular manner. In Figure 1 each injection device 13 passes through an axis X that is substantially inclined with respect to the axis A of chamber 1. Each injection device 13 includes a fuel injector 15 and an air injection system 16.

[0050] The injector 15 is angled and has one end fixed to the outer housing 5 and an opposite end forming a head, which is engaged and centered in the injection system 16 so that the fuel / air mixture can be sprayed into chamber 1.

[0051] In Figure 4 and Figure 5 the injection system 16 may include, from upstream to downstream, means 17 for supporting and centering the head of the injector 15, means 18 for injecting air, and means 19 for diffusing the air-fuel mixture into chamber 1. More specifically, means 19 includes a frustoconical bowl-shaped portion 19', which tapers downstream and has an air passage orifice 190( Figure 5 ).

[0052] Thus, compressed air is supplied to chamber 1 through injection system 19, which mixes with the fuel supplied by injector 15.

[0053] Referring to Figure 4 compressed air can also be supplied to chamber 1 via so-called "main" holes 21a (e.g., circumferential rows on the inner wall 11 and outer wall 12) and via "dilution" holes 21b (e.g., circumferential rows on the inner wall 11 and outer wall 12) located downstream of the main holes 20a. Air is supplied to the main holes 20a and dilution holes 20b via channels 9a, 9b.

[0054] According to this example, the chamber bottom 10 is covered upstream by an annular shroud 24 (around axis A) to form an annular compartment 241 together with the chamber bottom 10. In the region of each injection device 13, the shroud 26 includes openings 242 for allowing air flow through and for mounting the injector 15.

[0055] Combustion of the air / fuel mixture is initiated by one or more ignition devices 22 attached to the outer wall 12. According to the example shown, the ignition device 22 is longitudinally located at the main hole 20a.

[0056] In particular, to protect the chamber bottom 10 from the thermal radiation generated by combustion, chamber 1 also includes at least one annular deflector 14, which is arranged in chamber 1 and is substantially opposite to the hole 20 formed in the chamber bottom 10( Figure 5 ).

[0057] Reference Figure 4 , the bottom wall 10 of the chamber can be segmented circumferentially relative to the axis A of the chamber 1. Each segmented bottom wall in the segmented bottom wall 10 can include, on the one hand, holes 100 for aligning the air and fuel injection devices 13, and on the other hand, be connected to the deflector 14. Advantageously, each hole 100 in the bottom wall 10 of the chamber is configured for mounting the injector 15.

[0058] A special feature of the present invention is that each segmented bottom wall in the segmented bottom wall 10 is integral with the air injection system 16 and the deflector 14. The air injection system 16 can be mounted in the holes 100 of the associated bottom wall 10 of the chamber.

[0059] More particularly, the air injection system 16, the bottom wall 10, the deflector 14, and the bowl-shaped portion 19' are integral.

[0060] According to the embodiment shown in Figures 4 to 7 , the air injection device 18 of the injection system 16, the frustoconical bowl-shaped portion 19', the bottom portion 10 of the chamber, and the deflector 14 are integral. Alternatively (not shown), the devices 17 and 18 of the injection system 16, the bowl-shaped portion 19', the bottom portion 10 of the chamber, and the deflector 14 are integral.

[0061] Reference Figure 5 , the deflector 14 includes an annular portion 142 that is substantially parallel to the bottom 10.

[0062] The annular portion 142 includes an annular edge 144 at the outer periphery of the annular portion relative to the axis X, which is referred to as the "outer edge 144" and extends substantially parallel to the outer wall 12 of the chamber 1 downstream. The outer edge 144 is spaced from the outer wall 12 by an annular space 23 for the air passage ( Figure 5 ). The portion 142 also includes an annular edge 146 at the inner periphery of the portion relative to the axis X, which is referred to as the "inner edge 146" ( Figure 6 ) and extends substantially parallel to the inner wall 11 of the chamber 1 downstream. The inner edge is spaced from the inner wall 11 by another annular space 23 for the air passage.

[0063] The annular portion 142 is separated from the bottom 10 by a first annular space 140. The first space 140 is in fluid communication with the space 23.

[0064] In addition, the upstream face 142a of the portion 142 is arranged to be substantially opposite to the bottom wall 10 of the wall and downstream of the bottom wall. The upstream face 142a is separated from the bottom wall 10 by the first space 140.

[0065] The annular part 142 includes opposite outer and inner ends 148 relative to the axis X. The outer edge 144 and / or the inner edge 146 are located on the outer end of the part 142. The inner end 148 connects the deflector 14 to the chamber bottom 10 and the bowl part 19'.

[0066] In Figure 5 it, the chamber bottom 10 includes an annular wall 101 substantially transverse to the axis X and annular extensions 102 at the outer and inner perimeters of the chamber bottom, the annular extensions extending substantially parallel to the outer wall 12 and the inner wall 11 of the chamber 1.

[0067] The chamber bottom 10 is fixed upstream to each of the two outer walls 12 and the inner wall 11 of the chamber 1 through the extensions 102.

[0068] The wall 101 is opposite to the part 142 of the deflector 14 and upstream of this part of the deflector. As described above, the wall 101 is connected to the end 148 of the annular part 142 of the deflector 14. Holes 20 are formed in the wall 101, and these holes 20 lead to the upstream face 142a of the deflector 14. The wall 101 is connected to the outer peripheral edge 195b of the downstream end 195 of the bowl part 19'. In particular, this enables a connection to be formed between the wall 101 arranged around the orifice 190 and the bowl part 19'. Thus, between the orifices 190, each connection in the connection includes a passage for an air flow (such as an air flow from the second space 198 and / or the orifice 190).

[0069] The bowl part 19' includes a first frustoconical wall 192 and a second frustoconical wall 194 that are substantially parallel to each other. The frustoconical walls each flare from upstream to downstream from the air injection device 18 towards the chamber bottom 10 and the deflector 14. The frustoconical walls 192, 194 are separated from each other by the second space 198. As described above, the first wall 192 is arranged opposite to the second wall 192 and separated from this second wall by the second space 198. The frustoconical walls 192, 194 are connected to each other through an upstream end 193 and an opposite downstream end 195 separated by the second space 198.

[0070] Advantageously, the first wall 192 includes holes 20' leading to the opposite second wall 194.

[0071] The downstream end 195 of the bowl part 19' includes an inner peripheral edge 195a and an outer peripheral edge 195b that are opposite to each other. As described above, the outer edge 195b is connected to the wall 101 of the chamber bottom 10, while the inner edge 195a of the bowl part 19' is connected to the wall 142 of the deflector 14.

[0072] The downstream end 195 of the bowl-shaped part 19' further includes air passage orifices 190 formed and distributed around the axis X (e.g., in a circumferential arrangement). These orifices 190 extend through the frustoconical walls 192, 194 of the bowl-shaped part 19' to lead to the chamber 1( Figure 5 and Figure 6 ). These orifices 190 can also provide a partition on the one hand between the chamber bottom 10 and the bowl-shaped part 19', and on the other hand between the deflector 14 and the bowl-shaped part 19'( Figure 5 ). Thus, the orifices 190 open downstream at the connection part between the second frustoconical wall 194 of the bowl-shaped part 19' and the part 142 of the deflector 14, and open upstream at the connection part between the first frustoconical wall 192 of the bowl-shaped part 19' and the wall 101 of the chamber bottom 10.

[0073] In particular, each of the orifices 190 includes an upstream peripheral opening and a downstream peripheral opening, the upstream peripheral opening facing the end 195 and the wall 101, and the downstream peripheral opening facing the end 195 and the end 148 of the part 142.

[0074] These orifices 190 can be circumferentially inclined relative to the axis X. In particular, the inclination of the orifices 190 enables the air flow leaving the bowl-shaped part 19' to rotate and hold the flame in the chamber 1. Preferably, the orifices 190 are inclined at an angle between 15° and 75°, in particular at an angle of about 45°( Figure 5 ). This angle is measured relative to the axis X.

[0075] The upstream end 193 of the bowl-shaped part 19' is particularly connected to the downstream of the air injection device 18 through the inner peripheral edge 193a and the outer peripheral edge 193b of the bowl-shaped part 19'.

[0076] Figure 4 and Figure 5 The injection system 16 is shown, in which the air injection device 18 includes a radial swirler (relative to the axis X). In an alternative embodiment (not shown), the device 18 can include an axial swirler (relative to the axis X).

[0077] According to this example, the radial swirlers of the device 18 (the main radial swirler 181 and the secondary radial swirler 182 respectively) are coaxial and each define a radial air flow relative to the axis X. The annular Venturi tube 183 is inserted between the two swirlers 181, 182. This configuration enables the mixture of air from the air flow of the swirlers and the fuel from the injector 15 to be injected and then burned in the chamber 1.

[0078] Referring to Figure 5, the cross-section of the Venturi tube 183 is substantially "L"-shaped and includes a substantially radial annular edge 183a that is axially inserted between the two swirlers 181, 182. The Venturi tube 183 extends axially downstream relative to the axis X inside the secondary swirler 182 and separates the air flow from the swirlers 181, 182. In particular, the Venturi tube 183 includes an inner surface 183b that has a neck and defines a premixing compartment 186 in which a portion of the fuel injected from the injector 15 is mixed with the air flow conveyed by the primary swirler 181. Then, this air / fuel premix is mixed with the air flow from the secondary swirler 182 downstream of the Venturi tube 183 to form a cone of atomized fuel in chamber 1.

[0079] The device 18 includes a first annular surface 184 upstream of the primary swirler 181 and a second annular surface 185 downstream of the secondary swirler 182. This second surface 185 can be integral with the upstream end 192 of the bowl-shaped portion 19'. The first surface 184 is configured to be mounted on the device 17 for supporting and centering the head of the injector 15.

[0080] The support and centering device 17 includes coaxial inner and outer annular surfaces 171 and 172. The surface 171 is configured to be mounted on the first surface 184 of the air injection device 18. The surface 172 includes an inner surface configured to position the head of the injector 15. For example, the device 17 is an annular centering ring.

[0081] To protect various regions of the chamber bottom from the temperature of the combustion gases and the radiation of the flame, a portion of the air supplied by the compressor is used to cool these walls.

[0082] As shown in Figure 4 and Figure 7 , at each injection device 13, the compressed air flow 7 generated by the compressor is thus divided into three flows at the output of the diffuser 8, namely a central air flow 70 entering the compartment 241 via the opening 242, an inner bypass air flow 71 using the inner channel 9a, and an outer bypass air flow 72 using the outer channel 9b.

[0083] Referring to Figure 7, the central air flow 70 is divided at each injection device 13 into an air flow 73 for supplying the combustion chamber 1 through the main swirler 181 and the secondary swirler 182 respectively, and on the other hand, an air flow 74 for cooling part 142 of the deflector 14 through the holes 20 and for cooling the second frustoconical wall 194 of the bowl-shaped part 19' through the holes 20'. In fact, the air flow 74 cools the upstream surface 142a through the holes 20 in the wall 101 by the impact of air jets and cools the outer surface (relative to the axis X) of the second wall 194 through the holes 20' in the first wall 192.

[0084] In particular, the cooling air flow 74 passing through the holes 20 enters the first space 140 and then passes through the space 23. This enables the inner and outer walls of the chamber to be cooled by convection. The air flow 74 passing through the holes 20' can also enter the first space 140 and then pass through the space 23. Advantageously, the second space 198 and / or the first space 140 can be in fluid communication at least partially through the orifice 190.

[0085] Thus, referring to Figure 7 , since the air flow 74 can effectively cool the entire wall of the deflector 14 and is then guided to flow radially inwards and radially outwards from the chamber 1 to generate a cooling air film on the inner wall 11 and the outer wall 12, the cooling area 10a' is wider (compared with Figure 3 ) to ensure the cooling of the entire chamber bottom 10.

[0086] Advantageously, the cooling air flow 74 also passes through the orifice 190 of the bowl-shaped part 19'. This enables the orifice 190 to contribute to the performance of the combustion chamber, because the orifice enables the air flow in the conical part of the sprayed fuel to be enriched upstream of the combustion chamber. In fact, the uniformity of the air / fuel mixture is thus improved, thereby reducing, for example, the generation of soot and unburned hydrocarbon emissions (usually entrained by the cooling air films on the inner and outer walls of the chamber approximately at the space 23).

[0087] The combustion chamber according to the present invention offers several advantages, in particular:

[0088] - Optimizing the life of the chamber bottom by improving the cooling of the chamber bottom;

[0089] - Retaining the air passage orifices of the bowl-shaped part of the injection device;

[0090] - Ensuring an optimal connection between the chamber bottom, the injection device, and the deflector;

[0091] - Simplifying the manufacture of the chamber bottom in an integral part;

[0092] - Limiting the number of components attached to the chamber bottom;

[0093] - Reduces the number of components at the bottom of the chamber and decreases the overall size of the combustion chamber;

[0094] - Is easily adaptable to existing gas generators.

[0095] In summary, the proposed solution is simple, effective and economical for construction and assembly on aircraft turbines, while ensuring optimal and uniform cooling over the entire combustion chamber bottom.

Claims

1. An annular combustion chamber (1) for an aircraft turbine (3), the annular combustion chamber (1) comprising two coaxial annular walls, namely an inner annular wall (11) and an outer annular wall (12), the inner annular wall and the outer annular wall being connected upstream by an annular bottom wall (10) of the annular combustion chamber (1), injection means (13) passing through the axis (X) and comprising an air injection system (16) and a frustoconical bowl-shaped part (19'), the frustoconical bowl-shaped part flaring downstream and comprising an air passage orifice (190), the annular combustion chamber (1) further comprising an annular deflector (14), the annular deflector being arranged downstream of the annular bottom wall (10) and parallel to the annular bottom wall, Among them, the air injection system (16), the annular bottom wall (10), the deflector (14) and the frustoconical bowl-shaped part (19') being integral, - the deflector (14) comprising an annular part (142) parallel to the annular bottom wall (10) and separated from the annular bottom wall (10) by a first space (140), the annular part (142) comprising an inner end (148) relative to the axis (X), the inner end being connected to the frustoconical bowl-shaped part (19') and the annular bottom wall (10), - the frustoconical bowl-shaped part (19') comprising a first frustoconical wall (192) and a second frustoconical wall (194), the first frustoconical wall and the second frustoconical wall being parallel to each other and separated from each other by a second space (198), the annular bottom wall (10) comprising a first air passage hole (20), the first frustoconical wall (192) of the frustoconical bowl-shaped part (19') comprising a second air passage hole (20') leading to the opposite second frustoconical wall (194), the air passage orifice (190) of the frustoconical bowl-shaped part (19') extending through the first frustoconical wall (192) and the second frustoconical wall (194) until the air passage orifice opens into the annular combustion chamber (1), the outlet of the air passage orifice (190) of the frustoconical bowl-shaped part (19') being located at the junction between the wall of the annular part (142) of the deflector (14) and the second frustoconical wall (194) of the frustoconical bowl-shaped part (19').

2. The annular combustor according to claim 1, wherein Each air injection system (16) comprises a main swirler (181), the main swirler being integral with the annular bottom wall (10), the frustoconical bowl-shaped part (19') and the deflector (14).

3. The annular combustion chamber according to claim 2, characterized in that, Each air injection system (16) includes a secondary swirler (182) and a Venturi tube (183), the secondary swirler and the Venturi tube being integral with the annular bottom wall (10), the frustoconical bowl portion (19'), and the deflector (14), and the Venturi tube (183) being disposed between the primary swirler (181) and the secondary swirler (182).

4. The annular combustor according to any one of claims 1 to 3, characterized in that, The deflector (14) includes, at its outer peripheral edge, an annular edge (144) extending parallel to and spaced apart from the outer annular wall (12), and, at its inner peripheral edge, an annular edge extending parallel to and spaced apart from the inner annular wall (11).

5. The annular combustion chamber according to any one of claims 1 to 3, characterized in that The air passage orifice (190) of the frustoconical bowl portion (19') is inclined at an angle between 15° and 75°, the angle being measured with respect to the axis (X) of the injection device (13).

6. A turbine (3) comprising the annular combustion chamber (1) according to any one of claims 1 to 5.

7. The turbine according to claim 6, characterized in that, The turbine is a turbine of an aircraft.

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