COMBUSTION SYSTEM WITH A TUBE COMBUSTION CHAMBER AND A RING-SHAPED HEAT EXCHANGER

Description

Technical field

[0001] The present invention relates to the field of combustion systems of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy.

[0002] It concerns more particularly a microturbine with recuperator for the production of electricity from a liquid or gaseous fuel.

[0003] Generally, a microturbine is understood to mean a small power turbine, usually less than 200 kW.

[0004] Microturbine power generation concepts are particularly suited to the compactness requirements found in on-board applications (range extenders, autonomous refrigeration units, tanks and military shelters, etc.). Furthermore, in stationary applications, microturbine systems are attractive alternatives to traditional generator sets based on piston engines, particularly because maintenance requirements can be significantly reduced. Prior art

[0005] There figure 1 schematically and non-limitingly illustrates a conventional microturbine 1, operating from at least one fuel, such as a liquid fuel, for example of the diesel type, or a gaseous fuel, such as natural gas.

[0006] The turbine comprises at least one compression stage 3 with at least one gas compressor, a heat exchanger 4 (or recuperator), a combustion chamber 5 (or burner) supplied with fuel by at least one reservoir or gas supply pipe 8, at least one expansion stage 6 with at least one expansion turbine connected by a shaft 9 to the compressor 3. This turbine also comprises a means of producing energy, here electrical, which comprises an electric generator 7 advantageously placed on the shaft 9 between the compressor 3 and the turbine 6.

[0007] Of course, this generator can be alternatively connected to the expansion turbine or to the compressor by a shaft other than that connecting the turbine and the compressor. Conventionally, the heat exchanger 4 can be a cross-flow exchanger, for example of the shell-and-tube or alternating plate type with two inlets and two outlets.

[0008] The compressor 3 comprises an inlet 2 for fresh gas containing oxygen, generally outside air generally at ambient temperature, and a compressed air outlet leading to a compressed air inlet of the exchanger 4. The hot compressed air outlet of this exchanger is connected by a line to a hot compressed air inlet of the burner 5. The superheated gas outlet of the burner is connected by a line to the inlet of the turbine 6, the outlet of which is connected to another inlet of the heat exchanger 4 by a line of expanded superheated gases. The heat exchanger 4 also comprises a cooled gas outlet 10 to be directed towards any means of evacuation and treatment, such as a chimney (not shown).

[0009] Such a constitution of a microturbine, in particular the design of the combustion chamber is described in patent applications US 2016 / 054003, FR3041742 (WO2017 / 055074), FR3049044 (WO2017 / 157631), FR3084448, FR3084447 (WO2020 / 025233), FR3084450 (WO2020 / 025234).

[0010] Using a heat recuperator - also called a heat exchanger - is the best solution for achieving good energy efficiency in the microturbine system. However, its integration poses problems in terms of space requirements. Depending on the heat exchanger technology, the system volume can increase by a factor of ten. Furthermore, by multiplying the components (exchanger, chamber, turbine, etc.), the interfaces between components are also multiplied, which represent a risk for the reliability (particularly for the management of hot and pressurized seals) and the efficiency of the entire system.

[0011] Taking the example of a conventional microturbine with a maximum electrical power of around 15 kW, the volume distribution of the main components (excluding casing, insulation and ducts) is shown in Table 1 below: [Table 1] Component Approximate occupied volume (in L) Combustion chamber 12 L Interchange 88 L Turbine / Compressor / Electrical machine / Air inlet 16 L Power electronics / Control and cooling 25 L

[0012] This volume distribution can be generalized to on-board applications (excluding traction) whose power is generally less than 30 kW. This table highlights the significant contribution of the heat exchanger, which alone represents almost two-thirds of the total volume of the system. It therefore seems important to find relevant architectures that improve the compactness of the microturbine.

[0013] In order to propose solutions to these problems of compactness and limiting the number of interfaces between components, patent application US2002175522A describes a compact solution, with an annular combustion chamber around the turbine exhaust and with a recuperator around the shaft connecting the turbine and the compressor. This location of the heat exchanger does not allow for optimization of heat exchanges with the combustion chamber. In addition, the annular shape of the combustion chamber requires a specific design and a larger volume.

[0014] Another solution is described in patent application WO2016 / 040964A, which relates to a system with a turbine immediately at the outlet of the combustion chamber and a co-current heat exchanger around the turbine and the combustion chamber. Due to the co-current heat exchange, the heat exchange is not optimal, and does not allow optimal performance of the microturbine to be obtained. Summary of the invention

[0015] The aim of the invention is to enable the construction of a turbine, in particular a microturbine, that is compact and has improved performance. For this purpose, the invention relates to a combustion system with a tubular combustion chamber and a counter-current annular heat exchanger around the combustion chamber. Thus, this combustion system makes it possible to eliminate traditional thermal insulation around the combustion chamber by replacing it with the exchanger. This avoids the heat losses encountered in conventional microturbines while making the most of the volume represented by the exchanger, thus optimizing the compactness of the microturbine.

[0016] The invention relates to a combustion system for a turbine, in particular for a thermodynamic cycle turbine with recuperator, for energy production, comprising a continuous flow tubular combustion chamber and a heat exchanger between the intake gases for said combustion chamber and the burnt gases from said combustion chamber. Said heat exchanger is an annular counter-current heat exchanger arranged around said combustion chamber.

[0017] According to one embodiment, said heat exchanger comprises a plurality of axial channels.

[0018] According to one implementation, said axial channels are concentric.

[0019] According to one aspect, said heat exchanger comprises a central channel for the circulation of said burnt gases.

[0020] According to one embodiment option, at least one of said channels incorporates a microstructure.

[0021] According to one characteristic, said heat exchanger comprises at least two annular collectors for said intake gases and two annular collectors for said burnt gases, preferably said heat exchanger comprises at each axial end an annular collector for said intake gases and an annular collector for said burnt gases.

[0022] Advantageously, each annular collector for said burnt gases comprises a single or a plurality of inlet and / or outlet connections for said burnt gases regularly distributed around the circumference of said annular collector, preferably each annular collector for said burnt gases comprises between two and eight inlet and / or outlet connections.

[0023] Advantageously, the annular manifold located at the same axial end as a fuel injector of said combustion chamber for said intake gases comprises a single or a plurality of inlet connections for said intake gases regularly distributed around the circumference of said annular manifold, preferably between two and eight inlet connections.

[0024] Preferably, the annular manifold for said intake gases located at the opposite axial end of a fuel injector for said combustion chamber is connected to said combustion chamber.

[0025] According to one embodiment, said heat exchanger is made of stainless steel or superalloy.

[0026] According to one implementation, said combustion chamber comprises a flame tube with a radially perforated diffuser for the passage of said intake gases, and an axial fuel injector.

[0027] Furthermore, the invention relates to a turbine for energy production comprising at least one compression stage with at least one gas compressor, a combustion system according to one of the preceding characteristics, a fuel supply, at least one expansion stage with at least one expansion turbine connected by a shaft to a gas compressor, in which said heat exchanger of said combustion system ensures a heat exchange between said intake gases at the outlet of said at least one compression stage, and said burnt gases at the outlet of said at least one expansion stage.

[0028] Other characteristics and advantages of the system according to the invention will appear on reading the following description of non-limiting examples of embodiments, with reference to the figures appended and described below. List of figures

[0029] There figure 1, already described, illustrates a thermodynamic cycle turbine with recuperator according to the prior art. The figure 2 illustrates an axial section of a combustion system according to one embodiment of the invention. The figure 3 illustrates a cross-section of a combustion system according to one embodiment of the invention. The figure 4 illustrates a three-dimensional view of a combustion system according to one embodiment of the invention. The Figure 5 illustrates a three-dimensional view of a combustion system according to a second variant embodiment of the invention. The figure 6 illustrates a three-dimensional view of a combustion system according to one embodiment of the invention. The figure 7 illustrates a three-dimensional view of a combustion system according to a second variant embodiment of the invention. The figure 8 illustrates a sectional view of a combustion system according to one embodiment of the invention. Description of the embodiments

[0030] The present invention relates to a combustion system for a turbine, in particular a thermodynamic cycle turbine with recuperator, in particular a microturbine. This turbine allows the production of energy, in particular electrical energy.

[0031] The combustion system according to the invention comprises: a tubular, continuous-flow combustion chamber in which the combustion of intake gases by means of a fuel takes place continuously, a heat exchanger (also called a recuperator), which allows heat exchange between the intake gases for the combustion chamber, these intake gases can be previously compressed, and the burnt gases from the combustion chamber, the burnt gases can be previously expanded before passing through a heat exchanger.

[0032] According to the invention, the heat exchanger is a counter-flow heat exchanger, in other words the intake gases and the burnt gases flow in opposite directions in the heat exchanger. This type of heat exchanger allows for optimal heat exchange, which makes it possible to reduce the dimensions of the heat exchanger. Within the heat exchanger, there is no direct contact between the intake gases and the burnt gases, the circulation of the intake gases is separated from the circulation of the burnt gases by walls.

[0033] In addition, the heat exchanger has an annular shape and is arranged around the combustion chamber. This arrangement around the combustion chamber makes it possible to eliminate the traditional thermal insulation around the combustion chamber and replace it with the heat exchanger. This avoids the thermal losses encountered on the combustion chamber while making the most of the volume represented by the exchanger, thus optimizing the compactness of the combustion system, and a fortiori of the turbine using such a combustion system. The axis of the annular heat exchanger is identical to the axis of the tubular combustion chamber.

[0034] Preferably, the combustion system may include means for circulating the intake gases directly from the heat exchanger to the combustion chamber, without exiting the combustion system.

[0035] Advantageously, the combustion system may comprise a burnt gas outlet at the outlet of the combustion chamber, and a burnt gas inlet at the heat exchanger.

[0036] Preferably, the combustion system may not include any casing between the combustion chamber and the heat exchanger.

[0037] According to one embodiment of the invention, the heat exchanger may comprise a plurality of axial channels along the axial direction of the tubular combustion chamber and the annular heat exchanger. Alternatively, the heat exchanger may comprise a plurality of circumferential channels, or channels having other orientations. Within the channels circulate either the intake gases or the burnt gases. In order to facilitate heat exchange, two consecutive channels are provided for the circulation of different gases. In other words, the heat exchanger is formed by alternating channels for the intake gases and channels for the burnt gases. The axial channels allow good heat exchange.

[0038] According to an implementation of the invention, for which the heat exchanger comprises a plurality of axial channels, the channels may be concentric. In other words, the channels are formed by a set of concentric tubes, the intake gases and the burnt gases circulating between two concentric tubes. This embodiment allows a large heat exchange surface, which increases the heat exchanges, and makes it possible to reduce the dimensions of the heat exchanger. For this embodiment the heat exchanger may comprise between 10 and 1000 concentric channels, the number of channels being able to be determined in particular as a function of the power of the turbine. These value ranges allow a good compromise between the heat exchanges and the dimensions of the heat exchanger.

[0039] Preferably, the central channel (closest to the combustion chamber) may be a channel in which the burnt gases circulate. Thus, these intake gases can be heated before entering the combustion chamber.

[0040] According to one feature, at least one channel, preferably all channels of the heat exchanger may comprise integrated microstructures (from the English "latice"). In other words, at least one channel may comprise elements, such as a grid, a lattice, or a foam or any similar shape that can be produced by means of an additive manufacturing process. The microstructures integrated into the channels make it possible to increase the heat exchange surface, and consequently the heat exchanges, and thus to improve the compactness of the combustion system.

[0041] According to one embodiment of the invention, the heat exchanger may comprise: at least two annular collectors for the intake gases: a first collector for the distribution of the intake gases (in other words at the inlet), and a second collector for the collection of the reheated intake gases (in other words at the outlet), at least two annular collectors for the burnt gases: a first collector for the distribution of the burnt gases (in other words at the inlet), and a second collector for the collection of the cooled burnt gases (in other words at the outlet).

[0042] Preferably, the annular exchanger comprises at each axial end (along the axis of the combustion chamber) a collector for the intake gases and a collector for the burnt gases. Since the heat exchanger is counter-current, the inlet manifold for the intake gases in the heat exchanger is on the same side as the outlet manifold for the burnt gases, and the inlet manifold for the burnt gases in the heat exchanger is on the same side as the outlet manifold for the intake gases. This implementation makes it possible to simplify the inlets and outlets of the heat exchanger.

[0043] Alternatively, the annular exchanger may include headers at each end and in the center, for example intake gas inlet headers at the axial ends, and an outlet header in the center of the heat exchanger, as well as a flue gas inlet header in the center, and outlet headers at each axial end of the heat exchanger.

[0044] According to an implementation of this embodiment, each annular collector for the flue gases may comprise a single or a plurality, preferably between 2 and 8, and very preferably between 3 and 6, of inlet connections and / or outlet connections. This plurality of inlet and outlet connections are regularly distributed around the circumference of the annular collector. The regular distribution around the circumference allows for a homogeneous distribution of the flue gases in the heat exchanger, and consequently an optimization of the heat exchange, allowing the dimensions of the heat exchanger to be reduced. This regular distribution is particularly suitable for the embodiment for which the heat exchanger comprises axial channels, in particular concentric axial channels. The flue gas inlets and outlets of the heat exchanger are respectively called inlet connections and outlet connections.

[0045] According to an embodiment option of this embodiment, the annular manifold for intake gas located at the same end of a fuel injector of the combustion chamber may comprise a single or a plurality, preferably between 2 and 8, and very preferably between 3 and 6, inlet connections. This plurality of inlet connections is regularly distributed over the circumference of the annular manifold. The regular distribution over the circumference allows a homogeneous distribution of the intake gases in the heat exchanger, and consequently an optimization of the heat exchanges, allowing the compactness of the heat exchanger. This regular distribution is particularly suitable for the embodiment for which the heat exchanger comprises axial channels, in particular concentric axial channels. The intake gas inlets in the heat exchanger are called inlet connections.

[0046] In one aspect of this embodiment, the annular exhaust manifold located at the opposite end of the combustion chamber fuel injector is connected directly to the combustion chamber. For example, this exhaust manifold may be connected to an annular volume of the combustion chamber, which serves to feed the interior of a flame tube by means of radial orifices within the flame tube. This embodiment allows for complete integration of the heat exchanger with the combustion chamber, thereby achieving greater compactness.

[0047] According to one embodiment of the invention, the input connections and / or the output connections may have the shape of an annular sector (ring portion), so as to simplify their production. Alternatively, the input connections and / or the output connections may have a rectangular shape, or any other shape.

[0048] According to one embodiment, the heat exchanger may be made of stainless steel or a superalloy, such as the Inconel™ superalloy (Special Metals Corporation, USA) or any similar material, in order to take into account the thermomechanical resistance constraints of the heat exchanger at high temperature.

[0049] In addition, the heat exchanger can be manufactured by any manufacturing process, including stacking, welding, casting, additive manufacturing, etc.

[0050] According to one implementation of the invention, the combustion chamber may comprise a flame tube within which combustion takes place, and an axial fuel injector for injecting fuel axially into the flame tube. The flame tube may comprise a radially perforated diffuser for the passage of intake gases from outside the flame tube to inside the flame tube. The fuel injector is located at one end of the combustion chamber. The other end of the combustion chamber allows the exhaust of burnt gases. The radial perforations of the flame tube may be located over at least one diameter of the flame tube, for example substantially halfway down the flame tube.

[0051] In addition, the combustion chamber may include at least one of the following equipment: a flame stabilizer, a spark plug, means for generating aerodynamic movement of the intake gases in the combustion chamber, asymmetry of the diffuser perforations, narrowing of the diffuser, etc.

[0052] For example, the combustion chamber may conform to one of the combustion chambers described in one of the following patent applications: FR3041742 (WO2017 / 055074), FR3049044 (WO2017 / 157631), FR3084448, FR3084447 (WO2020 / 025233), FR3084450 (WO2020 / 025234).

[0053] Furthermore, the invention relates to a turbine for the production of energy, in particular electrical energy, which comprises: at least one compression stage with at least one compressor, for compressing intake gases, a combustion system according to one of the variants or combinations of variants described above, with a combustion chamber and a heat exchanger, a fuel supply for supplying the combustion chamber with fuel, the fuel may be a liquid fuel, for example of the diesel type, or a gaseous fuel, such as natural gas, or any other equivalent fuel, at least one expansion stage with at least one expansion turbine, for expanding burnt gases from the combustion chamber, and for producing energy, at least one expansion turbine being connected by a shaft to at least one compressor.

[0054] The combustion system heat exchanger allows heat exchange between the intake gases leaving at least one compression stage and the burnt gases leaving at least one expansion stage. Thanks to the combustion system, the turbine is more compact.

[0055] The turbine also includes pipes for conveying the gases (intake gas and burnt gas): in particular a pipe between a compression stage and the heat exchanger, a pipe between the combustion chamber and an expansion stage, a pipe between the expansion stage and the heat exchanger, and an exhaust pipe for the burnt gases leaving the heat exchanger.

[0056] The turbine may be as shown in figure 1 , except for recuperator 4 (heat exchanger) which is placed around the combustion chamber.

[0057] According to one embodiment, the turbine may further comprise an electrical generator for recovering energy from the turbine. The electrical generator may be placed on the compression shaft that connects a turbine and a compressor. For compactness, the electrical generator may be placed between a compressor and an expansion turbine. Alternatively, the electrical generator may be arranged at another location, or on an expansion turbine shaft or on a compressor shaft.

[0058] In order to control the electrical machine, and to recover electrical energy, the electrical generator can be controlled by an electrical inverter, which can be connected to a network inverter which is connected to an electrical distribution network and / or to electrical energy storage means, for example at least one electric battery or any similar system.

[0059] According to one embodiment, the turbine can be mounted on a vehicle. In this case, the energy generation is used to move the vehicle.

[0060] According to one feature, the turbine may comprise a plurality of turbines.

[0061] THE figures 2 And 3 illustrate, schematically and in a non-limiting manner, a combustion system according to one embodiment of the invention. The figure 2 is an axial section of the combustion system (along the X axis of the combustion chamber and the heat exchanger), and the figure 3 is a cross-section of the combustion system at the heat exchanger channels.

[0062] The combustion system comprises a tubular combustion chamber 5 and a heat exchanger 4. The tubular combustion chamber 5 comprises a flame tube 23 provided with orifices 21 for the passage of intake gases. In addition, the tubular combustion chamber 5 comprises a fuel injector 22, and optionally a spark plug 24. The gases burned during combustion exit the combustion chamber 5 on the side opposite that of the fuel injector 22. Furthermore, the tubular combustion chamber 5 may optionally comprise a flame holder 25.

[0063] The annular heat exchanger 4 comprises a plurality of concentric axial channels (13, 18). In the axial channels 13 circulate the burnt gases, and in the axial channels 18 circulate the intake gases. The heat exchanger 4 comprises an alternation in the radial direction of the axial channels 13 and the axial channels 18. On the figure 2, the intake gases flow from left to right in the heat exchanger 4, and the flue gases flow from right to left in the heat exchanger 4, thus forming a counterflow heat exchanger.

[0064] For the intake gases, the heat exchanger 4 comprises: at least one inlet connection 16 (only one is shown, but several are distributed around the circumference of the heat exchanger 4), an annular intake gas collector 17, which collects the intake gases coming from the inlet connections 16 and distributing the intake gases into the channels 18, the intake gas channels 18, an annular intake gas collector 19, which collects the heated intake gases coming out of the intake gas channels 18, the intake manifold is connected to a volume 20 around the flame tube 23 to supply the combustion chamber 5 with the heated intake gases.

[0065] For the flue gases, heat exchanger 4 comprises: a plurality of inlet connections 11 (only one is shown, but several are distributed around the circumference of the heat exchanger 4), an annular flue gas collector 12, which collects the flue gases coming from the inlet connections 11 and distributing the flue gases into the channels 13, the flue gas channels 13, an annular flue gas collector 14, which collects the cooled flue gases coming from the channels 13, at least one outlet connection 15 (only one is shown, but several are distributed around the circumference of the heat exchanger 4), which allows the exit of the cooled flue gases coming from the annular flue gas collector 14.

[0066] There figure 4 illustrates, schematically and in a non-limiting manner, a three-dimensional view of a combustion system according to one embodiment of the invention. The figure 4shows the combustion system from the injector 22 side. On this side, the heat exchanger 4 has an inlet connection 16 for the intake gases having the shape of an annular portion, and an outlet connection 15 for the burnt gases having the shape of an annular portion.

[0067] There Figure 5 illustrates, schematically and in a non-limiting manner, a three-dimensional view of a combustion system according to an alternative embodiment of the invention. The Figure 5 shows the combustion system from the injector 22 side. On this side, the heat exchanger 4 has an inlet connection 16 for the intake gases having the shape of an annular portion, and three outlet connections 15 for the burnt gases having the shape of an annular portion.

[0068] There figure 6 illustrates, schematically and in a non-limiting manner, a three-dimensional view of a combustion system according to one embodiment of the invention. The Figure 5 shows the combustion system from the exhaust side, with the flame tube of the combustion chamber 5 opening on this side. On this side, the heat exchanger 4 has an inlet connection 11 for the burnt gases having the shape of an annular portion.

[0069] There figure 7 illustrates, schematically and in a non-limiting manner, a three-dimensional view of a combustion system according to one embodiment of the invention. The figure 6 shows the combustion system from the exhaust side, with the flame tube of the combustion chamber 5 opening on this side. On this side, the heat exchanger 4 has three inlet connections 11 for the burnt gases having the shape of an annular portion.

[0070] There figure 8illustrates, schematically and in a non-limiting manner, a combustion system according to one embodiment in a sectional plane at the level of the collectors. This figure illustrates a part of the channels 13, 18 of the heat exchanger 4, and the combustion chamber 5. In addition, within the collectors, plates 25, 26 are provided in the form of annular portions, these plates guide the passage of gases into or from one of the two collectors: either the intake gas collector or the burnt gas collector. The plates 25 are placed on annular sectors different from the annular sectors of the plates 26. Comparative example:

[0071] For this example, we compare: the volume of the microturbine of the prior art with a maximum electrical power of approximately 15 kW, the volume distribution of the main components (excluding cowling / insulation and conduits) of which is indicated in Table 1 previously described, with the volume of the microturbine according to an embodiment of the invention corresponding to that of the figures 2 And 3 , the volume distribution of the main components (excluding cover / insulation and conduits) is shown in Table 2 below: [Table 1] Component Approximate occupied volume (in L) Combustion system (combustion chamber and exchanger) 25 L Turbine / Compressor / Electrical machine / Air inlet 16 L Power electronics / Control and cooling 25 L

[0072] Thus, the microturbine according to this embodiment of the invention allows a volume gain of approximately 74 L. Consequently, the combustion system according to the invention allows for better compactness of such a microturbine.

Claims

1. Combustion system for a turbine, notably for a turbine having a thermodynamic cycle with a recuperator, for the production of energy, comprising a continuous-flow tubular combustion chamber (5) and a heat exchanger (4) for the exchange of heat between the intake gases for said combustion chamber and the burnt gases coming from said combustion chamber, characterized in that said heat exchanger (4) is an annular counter-current heat exchanger arranged around said combustion chamber (5).

2. Combustion system according to Claim 1, wherein said heat exchanger (4) comprises a plurality of axial channels (13, 18).

3. Combustion system according to Claim 2, wherein said axial channels (13, 18) are concentric.

4. Combustion system according to either of Claims 2 and 3, wherein said heat exchanger (4) comprises a central channel for the circulation of said burnt gases.

5. Combustion system according to one of Claims 2 to 4, wherein at least one of said channels (13, 18) has an integrated microstructure.

6. Combustion system according to one of the preceding claims, wherein said heat exchanger (4) has at least two annular manifolds (17, 19) for said intake gases and two annular manifolds (12, 14) for said burnt gases, preferably said heat exchanger (4) has, at each axial end, an annular manifold for said intake gases and an annular manifold for said burnt gases.

7. Combustion system according to Claim 6, wherein each annular manifold for said burnt gases (12, 14) has a single inlet and / or outlet connection (11, 15) or a plurality of inlet and / or outlet connections for said burnt gases evenly distributed around the circumference of said annular manifold, preferably each annular manifold for said burnt gases (12, 14) has between two and eight inlet and / or outlet connections (11, 15).

8. Combustion system according to either of Claims 6 and 7, wherein the annular manifold (17) situated at the same axial end as a fuel injector (22) of said combustion chamber for said intake gases has a single inlet connection (16) or a plurality of inlet connections for said intake gases evenly distributed around the circumference of said annular manifold (17), preferably between two and eight inlet connections (16).

9. Combustion system according to one of Claims 6 to 8, wherein the annular manifold (19) for said intake gases that is situated at the axial end opposite a fuel injector (22) for said combustion chamber is connected to said combustion chamber (5).

10. Combustion system according to one of the preceding claims, wherein said heat exchanger is made of stainless steel or a superalloy.

11. Combustion system according to one of the preceding claims, wherein said combustion chamber comprises a flame tube with a radially perforated diffuser (21) for the passage of said intake gases, and an axial fuel injector (22).

12. Turbine for the production of energy, comprising at least one compression stage with at least one gas compressor (3), a combustion system according to one of the preceding claims, a fuel supply (8), at least one expansion stage (6) with at least one expansion turbine connected to a gas compressor by a shaft (9), wherein said heat exchanger (4) of said combustion system exchanges heat between said intake gases at the outlet of said at least one compression stage (3), and said burnt gases at the outlet of said at least one expansion stage (6).