Cryogenic fuel supply system for turbine engine combustor

Abstract

The invention relates to a cryogenic fuel supply system (9) for a combustion chamber (5) of an aircraft turbine engine, the cryogenic fuel supply system comprising: a tank for storing liquid cryogenic fuel (90); and a mixing chamber (91) connected to the combustion chamber (5) and receiving different supercritical or gaseous cryogenic fuel flows. The system is characterized in that it comprises: an auxiliary heating device (92, 92') mounted on a pipe connecting the tank (90) to the mixing chamber (91) and enabling the reheating of the cryogenic fuel; a heat exchanger assembly (93, 93') connected to the cryogenic fuel tank (90) and the mixing chamber (91) and mounted in parallel with the auxiliary heating device (92, 92'), the heat exchanger assembly (93, 93') comprising a cryogenic fuel / oil heat exchanger (94, 94') and a cryogenic fuel / air heat exchanger for circulating in the main flow of the turbine engine (95, 95'); a plurality of valves located upstream of the device and the assembly and controlled by a central unit (99).

Description

Technical Field

[0001] The present invention relates to the field of aircraft turbine engines.

[0002] More precisely, the invention relates to a cryogenic fuel supply system for a combustion chamber of an aircraft turbine engine and to an aircraft turbine engine comprising, in sequence, at least one air compressor, a combustion chamber supplied with cryogenic fuel and at least one turbine, the turbine engine being equipped with said cryogenic fuel supply system. Background Art

[0003] Cryogenic fuels are commonly used in space propulsion due to their higher thermodynamic efficiency. However, the transition to cryogenic fuels in aviation and the industrialization of their large-scale use require resolving a number of technical challenges.

[0004] Therefore, the use of liquid hydrogen has been proposed, as the use of liquid hydrogen will enable CO2 emissions to be reduced to zero.

[0005] Another cryogenic fuel that could be used is “liquefied” natural gas (abbreviated to GNL), which has the additional advantage of being able to be used at much higher temperatures than liquid hydrogen, as LNG has a low viscosity at 1 bar (10 5 Pa) is minus 161°C, while for liquid hydrogen it is minus 252°C, which simplifies the use of liquefied natural gas.

[0006] In both cases, these cryogenic fuels still need to be transported in liquid form so that the volume of these cryogenic fuels in the aircraft is acceptable, and then vaporized and thus heated to be able to be used in the combustion chamber.

[0007] It is also desirable that the cryogenic fuel used in the combustion chamber is no longer in a gaseous state but in a supercritical fluid state, which is not provided in the cited prior art. As a reminder, a fuel reaches a supercritical fluid state when it is at a temperature greater than its critical temperature and a pressure greater than its critical pressure.

[0008] Also known from document US 2015 / 000298 is a cryogenic fuel supply system for a combustion chamber of a turbine engine, which also includes a compressor and a turbine. The cryogenic fuel, liquefied natural gas, is stored in tanks.

[0009] The system also has a heat exchanger assembly including an exchanger between the low-temperature fuel and the exhaust gas and an exchanger between the low-temperature fuel and the air circulating in the main duct.

[0010] However, this document does not describe a mixing chamber or a cryogenic fuel / oil heat exchanger or auxiliary heating equipment. Summary of the Invention

[0011] One object of the present invention is therefore to provide a cryogenic fuel supply system for a combustion chamber of a turbine engine of an aircraft, which can vaporize liquid cryogenic fuel or bring it to a supercritical fluid state in an ecologically and energetically advantageous manner.

[0012] To this end, the invention relates to a cryogenic fuel supply system for a combustion chamber of an aircraft turbine engine, comprising, in sequence, at least one air compressor, said combustion chamber and at least one turbine, the supply system comprising:

[0013] - a storage tank for the liquid cryogenic fuel,

[0014] a mixing chamber receiving various flows of cryogenic fuels in a supercritical or gaseous state, the mixing chamber being connected to the combustion chamber in order to supply the combustion chamber with cryogenic fuels in a supercritical or gaseous state.

[0015] According to the present invention, the supply system comprises:

[0016] - an auxiliary heating device installed in the line connecting the tank to the mixing chamber, this auxiliary heating device being able to heat the cryogenic fuel,

[0017] a heat exchanger assembly connected to the cryogenic fuel tank and the mixing chamber and installed in parallel with the auxiliary heating device, comprising a cryogenic fuel / oil heat exchanger and a heat exchanger between the cryogenic fuel and the air circulating in the main duct of the turbine engine,

[0018] - a flow distribution device, which is arranged upstream of the auxiliary heating device, at least one flow distribution device is arranged upstream of the heat exchanger assembly, and the opening and closing of these individual flow distribution devices are controlled by a central control unit.

[0019] These features of the invention, and in particular the presence of the auxiliary heating device, make it possible to have smaller dimensions for the cryogenic fuel / oil heat exchanger and for the exchanger between the cryogenic fuel and the air circulating in the main duct of the turbine engine. The cryogenic fuel / oil heat exchanger and the exchanger are therefore lighter and generate less pressure drop, thus reducing the thrust of the aircraft. The supply system according to the invention is therefore more environmentally friendly and energy-efficient.

[0020] According to other advantageous and non-limiting features of the invention, alone or in combination:

[0021] - the system comprises a pump, which is arranged at the outlet of the liquid cryogenic fuel tank, upstream of the auxiliary heating device, and upstream of the heat exchanger assembly, and the pump is capable of bringing the cryogenic fuel originating from the storage tank to a pressure higher than the critical pressure of the cryogenic fuel;

[0022] the auxiliary heating device, the cryogenic fuel / oil heat exchanger and the heat exchanger between the cryogenic fuel and the air (which circulates in the main duct of the turbine engine) are supercritical exchangers capable of bringing the cryogenic fuel to a temperature above its critical temperature;

[0023] - the system comprises a pump arranged at the outlet of the liquid cryogenic fuel tank, upstream of the auxiliary heating device and upstream of the heat exchanger assembly, the pump being capable of pressurizing the cryogenic fuel leaving the tank so as to render the cryogenic fuel completely liquid;

[0024] The auxiliary heating device, the cryogenic fuel / oil heat exchanger and the heat exchanger between the cryogenic fuel and the air (which circulates in the main duct of the turbine engine) are two-phase exchangers capable of heating the liquid cryogenic fuel in order to convert it into a gaseous state;

[0025] - the turbine engine is a twin-shaft turbine engine, which comprises, in sequence, a low-pressure air compressor, a high-pressure air compressor, the combustion chamber, a high-pressure turbine, and a low-pressure turbine; the heat exchanger between the low-temperature fuel and the air (the air circulates in the main duct of the turbine engine) is an inter-compressor cooling exchanger, which is arranged between the low-pressure air compressor and the high-pressure air compressor and exchanges heat with the air, which comes from the main duct and is downstream of the low-pressure air compressor of the turbine engine;

[0026] - the heat exchanger between the low-temperature fuel and the air circulating in the main duct of the turbine engine is a recuperator which exchanges heat with the air coming from the main duct downstream of the turbine of the turbine engine;

[0027] - The auxiliary heating device is an electrical device or a thermal device.

[0028] According to a first alternative embodiment, the inter-compressor cooling exchanger is installed in series with the cryogenic fuel / oil heat exchanger, preferably upstream of the cryogenic fuel / oil heat exchanger.

[0029] According to a second alternative embodiment, the inter-compressor cooling exchanger is installed in parallel with the low-temperature fuel / oil heat exchanger.

[0030] Preferably, the recuperator and the low-temperature fuel / oil heat exchanger are installed in series, with the recuperator being installed upstream or downstream of the low-temperature fuel / oil heat exchanger.

[0031] Advantageously, the system comprises a fuel compressor arranged between the mixing chamber and the combustion chamber.

[0032] Preferably, the cryogenic fuel is liquefied natural gas or liquid hydrogen.

[0033] Preferably, the flow distribution device is a valve.

[0034] The present invention also relates to an aircraft turbine engine, comprising, in order: at least one air compressor; a combustion chamber supplied with cryogenic fuel; and at least one turbine. According to the present invention, as described above, the turbine engine comprises a cryogenic fuel supply system for the combustion chamber.

[0035] Finally, the present invention relates to a method for controlling a cryogenic fuel supply system for a combustion chamber as described above, comprising the following steps:

[0036] - during takeoff of the aircraft, opening the flow distribution device arranged upstream of the auxiliary heating device and the at least one flow distribution device arranged upstream of the heat exchanger assembly, so as to circulate the cryogenic fuel to be heated through the auxiliary heating device and the heat exchanger assembly,

[0037] - and during other flight phases of the aircraft, closing the flow distribution device arranged upstream of the auxiliary heating device and opening the at least one flow distribution device arranged upstream of the heat exchanger assembly so that the low-temperature fuel to be heated circulates only in the heat exchanger assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Other features, objects and advantages of the present invention will appear from the following description, which is given by way of illustration only and not limitation, and which should be read with reference to the accompanying drawings, in which:

[0039] [ Figure 1 ] shows an overview of a turbine engine equipped with a cryogenic fuel supply system for its combustion chambers, only part of which is visible in the figure.

[0040] [ Figure 2 ] is a schematic diagram of a cryogenic fuel supply system for a combustion chamber of a turbine engine for an aircraft according to the present invention.

[0041] In all figures, the same elements have the same reference numerals. DETAILED DESCRIPTION

[0042] The present invention relates to a cryogenic fuel supply system for a combustion chamber of a turbine engine of an aircraft, such as an airplane.

[0043] Figure 1 An example of such a turbine engine is shown. In this example, this is a twin-shaft bypass turbine engine.

[0044] The turbine engine 1 is arranged in the direction of air flow (in other words, from upstream ( Figure 1 in the left) to the downstream ( Figure 1 The right side in the figure) comprises in turn an air inlet 10 in which is located a fan 2 which delivers air on the one hand into a primary duct 11 and on the other hand into a secondary duct 12. The term "duct" shall denote the volume (here in the form of an annular channel) through which the air flow circulates.

[0045] The air flow flowing in the main duct 11 passes through the low-pressure air compressor 3 , the high-pressure air compressor 4 , the combustion chamber 5 , the high-pressure turbine 6 and the low-pressure turbine 7 in sequence before being discharged through the main flow nozzle 8 .

[0046] Without exceeding the scope of the present invention, other types of turbine engines (such as a single-shaft turbine engine comprising: only one air compressor and only one turbine, the air compressor and the turbine being connected together by a shaft; and a combustion chamber inserted between the air compressor and the turbine) may be equipped with a cryogenic fuel supply system according to the present invention.

[0047] Now combine Figure 2 A cryogenic fuel supply system 9 according to the present invention is described.

[0048] The system 9 comprises a tank 90 for storing liquid cryogenic fuel. This cryogenic fuel is intended to be supplied to the combustion chamber 5 via various lines which will be described below.

[0049] The cryogenic fuel is, for example, liquefied natural gas or liquid hydrogen.

[0050] The system 9 also includes a mixing chamber 91 that receives various low-temperature fuel streams in a gaseous or supercritical state, as described below. The mixing chamber 91 is connected to the combustion chamber 5 via at least one pipeline 900. In addition, the fuel is preferably injected into the combustion chamber 5 via at least one injector (not shown).

[0051] Optionally, a fuel compressor 97 may be arranged in one or more lines 900 between the mixing chamber 91 and the combustion chamber 5. The compressor 97 may increase the pressure of the cryogenic fuel injected into the combustion chamber 5.

[0052] The system 9 also comprises an auxiliary heating device installed in the line 901 connecting the tank 90 to the mixing chamber 91 .

[0053] According to a first embodiment of the present invention, the auxiliary heating device (reference numeral 92) can heat the cryogenic fuel and cause a phase change from a liquid phase to a gas phase. According to a second embodiment of the present invention, the auxiliary heating device (referred to as a "supercritical" type and referenced as 92') can heat the cryogenic fuel and cause the cryogenic fuel to reach a temperature higher than the critical temperature of the cryogenic fuel.

[0054] Preferably, the auxiliary heating devices 92, 92' are electrical or thermal. They can be, for example, coils through which the low-temperature fuel circulates, with the coils disposed in a liquid (e.g., ethanol-based water) heated by burning a small amount of the fuel stream. Alternatively, the auxiliary heating devices can be resistors disposed in the low-temperature fuel stream.

[0055] Preferably, a pump is arranged in the line 901 , at the outlet of the tank 90 and upstream of the auxiliary heating device 92 .

[0056] According to a first embodiment of the invention, this pump (reference numeral 96 ) can pressurize the cryogenic fuel leaving the tank 90 , thus ensuring that it is substantially liquid and does not contain any gas before being introduced into the various exchangers described below.

[0057] According to a second embodiment of the invention, the pump (called “supercritical” type and referenced 96 ′) makes it possible to bring the cryogenic fuel originating from the tank 90 to a pressure higher than the critical pressure of the cryogenic fuel.

[0058] Preferably, a flow distribution device 98a is also arranged in the pipeline 901 upstream of the auxiliary heating device 92, 92' and downstream of the pump 96, 96'. Preferably, this flow distribution device 98a is a valve and will be referred to as a valve in the rest of the description.

[0059] According to a first embodiment of the present invention, a heat exchanger assembly (generally referenced 93) is connected to the storage tank 90 and the mixing chamber 91. The heat exchanger assembly is installed in parallel with the auxiliary heating device 92. The heat exchanger assembly 93 includes a low-temperature fuel / oil heat exchanger 94 and a heat exchanger 95 between the low-temperature fuel and the air circulating in the main duct 11 of the turbine engine 1.

[0060] Cryogenic fuel / oil heat exchanger 94 is, for example, a plate-type heat exchanger to optimize heat transfer between the two flows. The oil used to lubricate and cool the various mechanical components of the aircraft (such as rotors, shafts, bearings, or reduction gears) is hot when it leaves these components and enters exchanger 94, where it transfers heat to the cryogenic fuel circulating therein. This cryogenic fuel heats up and undergoes a phase change, transitioning from a liquid to a gaseous state. Conversely, the cryogenic fuel transfers low temperature to the oil, which, once cooled, can be returned to the various mechanical components to cool them, thereby contributing to their thermodynamic efficiency.

[0061] The heat exchanger 95 may be an inter-compressor cooling exchanger (reference numeral 95a) between the low-temperature fuel and the air circulating in the main duct 11 of the turbine engine. The inter-compressor cooling exchanger is arranged in the main duct 11 between the low-pressure air compressor 3 and the high-pressure air compressor 4 (see FIG. Figure 1 The air circulating in the main duct 11 is heated after passing through the low-pressure air compressor 3 and can transfer heat to the low-temperature fuel to convert the low-temperature fuel into a vapor phase.

[0062] The exchanger 95a is, for example, a plate and / or fin exchanger.

[0063] In the case of a fin exchanger, the fins are located in the main duct 11 and are heated by the air circulating therein. However, these fins constitute contact surfaces which generate a pressure drop in the main duct 11 .

[0064] In the case of a plate exchanger, it is arranged on the wall of the main duct 11 , preferably on one of the inner annular walls of this duct, so as to limit the length of the line connecting this duct to the mixing chamber 91 .

[0065] Whatever the type of exchanger 95 a , it constitutes an obstacle that impedes the circulation of the air flow in the main duct 11 .

[0066] Therefore, by the presence of the auxiliary heating device 92 , it is possible to use an inter-compressor cooling exchanger 95 a of smaller dimensions, ie lighter and less voluminous, than in the absence of this device 92 .

[0067] Therefore, the inter-compressor cooling exchanger 95a may be sized to provide only the heating of the cryogenic fuel flow required during the cruise flight phase of the aircraft.

[0068] When it is necessary to heat a larger flow of low-temperature fuel, such as during the takeoff phase of the aircraft, during which the engines must deliver more power and consume more fuel, the auxiliary heating device 92 can also be used to heat the additional flow of low-temperature fuel. When the aircraft returns to cruise mode, the auxiliary heating device 92 is deactivated and only the inter-compressor cooling exchanger 95a is used, which has a smaller size and thus generates less pressure drop in the duct 11.

[0069] The heat exchanger 95 can also be a recuperator (reference numeral 95b) between the low-temperature fuel and the air that circulates in the main duct 11 of the turbine engine. The recuperator 95b is arranged in the main duct 11, downstream of the low-pressure turbine 7 (see FIG. Figure 1 ), preferably arranged at the outlet nozzle 8. The air flowing in the main duct 11 downstream of the low-pressure turbine 7, particularly the air flowing at the outlet nozzle 8, is hot and can transfer heat to the low-temperature fuel, thereby converting the low-temperature fuel into a vapor phase. The recuperator 95b is, for example, a plate or fin exchanger.

[0070] Since the hot air leaving the nozzle 8 escapes from the aircraft, this recuperator 95b has the advantage of utilizing heat that would otherwise be lost. The recuperator also has fewer installation constraints in the turbine engine than the exchanger 95a.

[0071] It should be noted that when the turbine engine 1 is single-shaft, the heat exchanger 95 is preferably a recuperator 95b that recovers heat from the air leaving the turbine. Because the low-temperature fuel has a lower temperature than the air entering the duct 11 and can therefore exchange heat, a heat exchanger similar to the aforementioned exchanger 95a can be provided, but positioned upstream of the single air compressor. However, this type of heat exchanger is undoubtedly less efficient.

[0072] According to a first alternative embodiment of the present invention, the heat exchanger 95 and the heat exchanger 94 are installed in parallel with each other. Therefore, they are also installed in parallel with the auxiliary heating device 92.

[0073] In this case, a cryogenic fuel / oil heat exchanger 94 is installed in line 902 connecting the tank 90 (or pump 96, when present) to the mixing chamber 91. Figure 2 As shown, line 902 can also be connected to a branch point 903 located in line 901 downstream of pump 96 and upstream of valve 98a. Preferably, flow distribution device 98b is arranged in line 902 upstream of low-temperature fuel / oil heat exchanger 94 and downstream of pump 96.

[0074] Furthermore, heat exchangers 95, 95a, 95b are installed in line 904, which connects the tank 90 (or the pump 96, when present) to the mixing chamber 91. Figure 2 As shown, it is also possible to connect a pipeline 904 to the branch point 903. Preferably, a flow distribution device 98c is arranged in the pipeline 904, upstream of the heat exchanger 95 and downstream of the pump 96.

[0075] According to a second alternative embodiment of the invention, heat exchanger 95 is installed in series with heat exchanger 94. Thus, heat exchanger 95, 95a, 95b can be upstream or downstream of heat exchanger 94.

[0076] To this end, according to Figure 2 In the first embodiment shown in FIG, a bypass line 905 provided with a flow distribution device 98d connects the outlet of the heat exchanger 94 to the inlet of the heat exchangers 95, 95a, and 95b, and a bypass line 906 provided with a flow distribution device 98e connects the outlet of the heat exchangers 95, 95a, and 95b to the inlet of the heat exchanger 94.

[0077] Preferably, these flow distribution devices 98b, 98c, 98d and 98e are valves and will be referred to as valves in the remainder of the description.

[0078] The opening and closing of each valve 98a, 98b, 98c, 98d and 98e is controlled by a central control unit 99. The central unit may be a computing device such as a computer or a programmable logic controller.

[0079] The computing device comprises a memory in which a program (computer program) is stored, the program comprising code instructions for implementing the control method of the supply system 9 , in particular for the opening and closing of the various valves 98 a to 98 e .

[0080] With this arrangement, it is possible to install exchangers 94 and 95 in parallel by opening valves 98b and 98c and closing valves 98d and 98e. It is possible to install exchangers 94 and 95 in series by opening valves 98b and 98d and closing valves 98c and 98e, with exchanger 94 upstream of exchanger 95 relative to the flow direction of the cryogenic fuel in these exchangers. Conversely, it is possible to install exchangers 94 and 95 in series by opening valves 98c and 98e and closing valves 98b and 98d, but this time with exchanger 95 upstream relative to exchanger 94.

[0081] Although not shown in the drawings, according to the second embodiment, it is also possible to have a single line connecting the pump 96 to the mixing chamber 91 and wherein the exchangers 94 and 95 are installed in series according to a predetermined order and without the bypass lines 905 and 906.

[0082] Whichever solution is chosen, when the exchangers 94 and 95 are connected in series, the line in which they are installed is parallel to the line 901. Thus, if at any time the flow rate of the cryogenic fuel heated in the heat exchanger assembly 93 is insufficient, a portion of the cryogenic fuel can be heated by using the auxiliary heating device 92.

[0083] Another embodiment is also possible. The difference from the previous embodiment is that the heat exchanger assembly 93 is replaced by a heat exchanger assembly 93', which includes: a cryogenic fuel / oil heat exchanger 94' (referred to as "supercritical"); and a heat exchanger 95' (referred to as "supercritical") between the cryogenic fuel and the air circulating in the main duct 11 of the turbine engine 1, either an inter-compressor cooling exchanger type 95'a or a recuperator type 95'b.

[0084] Heat exchanger 94' and heat exchangers 95', 95'a, 95'b are referred to as "supercritical" because they can bring the cryogenic fuel to a temperature above the critical temperature of the cryogenic fuel.

[0085] As a reminder, the critical temperature of hydrogen is 32K (minus 241.15°C) and the critical pressure is 12.8 bar (12.8×10 5 Pa), the critical temperature of natural gas is 190K (minus 83.15℃), and the critical pressure is 46.8 bar (46.8×10 5 Pa).

[0086] Preferably, when the above-described supercritical exchangers 94', 95', 95'a and 95'b and supercritical auxiliary heating device 92' are used, a supercritical pump 96' will be used upstream.

[0087] Therefore, the low-temperature fuel is delivered to the mixing chamber 91 in a supercritical fluid state and then delivered to the combustion chamber 5 .

[0088] The rest of the system, parallel or series connections and valves remain the same as already described previously.

[0089] A method for controlling the system 9 will now be described.

[0090] The central control unit 99 receives information relating to the flight mode (take-off, climb, cruise, etc.) and the flow rate of supercritical or gaseous cryogenic fuel to be fed to the combustion chamber 5 .

[0091] The heating requirement of the cryogenic fuel is proportional to the flow rate of the supercritical or gaseous fuel to be delivered to the combustion chamber 5. However, this flow rate is much greater during take-off than during any other flight phase.

[0092] The central unit 99 controls the opening and closing of valves 98b, 98c, 98d and 98e so that during the climb or cruise flight phase, the cryogenic fuel is heated by passing through the heat exchanger assembly 93' or 93 and is converted into a supercritical or gaseous phase, and valve 98a is closed.

[0093] Furthermore, during takeoff or when an additional cryogenic fuel flow is required, valve 98a is also opened so that an additional volume of cryogenic fuel can be heated and vaporized or converted to a supercritical phase in auxiliary heating devices 92 or 92', respectively. This vaporized or supercritical fuel is then mixed in compartment 91 with the other gaseous or supercritical fuel flows from exchangers 94 and 95 or 94' and 95', respectively.

[0094] Furthermore, within assemblies 93, 93', the liquid cryogenic fuel is primarily directed to cryogenic fuel / oil exchangers 94, 94' to ensure cooling of the engine oil. However, to maintain low viscosity, the oil must not fall below a certain temperature. To this end, a temperature sensor determines the oil cooling requirement and transmits a cryogenic fuel flow rate corresponding to this requirement. The remaining fuel flow enters exchangers 95, 95'.

Claims

1. A cryogenic fuel supply system (9), said cryogenic fuel supply system being used in a combustion chamber (5) of an aircraft turbine engine (1), said turbine engine (1) comprising, in sequence, at least one air compressor (3, 4), said combustion chamber (5) and at least one turbine (6, 7), said cryogenic fuel supply system comprising: - a storage tank (90) for liquid cryogenic fuel, a mixing chamber (91) receiving various low-temperature fuel flows in a supercritical state or a gaseous state, the mixing chamber being connected to the combustion chamber (5) to supply the combustion chamber with the low-temperature fuel in a supercritical state or a gaseous state, The cryogenic fuel supply system (9) is characterized in that the cryogenic fuel supply system comprises: - an auxiliary heating device (92, 92') installed in a pipeline connecting the storage tank (90) to the mixing chamber (91), the auxiliary heating device (92, 92') being capable of heating the cryogenic fuel, a heat exchanger assembly (93, 93') connected to the storage tank (90) and the mixing chamber (91) and installed in parallel with the auxiliary heating device (92, 92'), the heat exchanger assembly (93, 93') comprising a low-temperature fuel / oil heat exchanger (94, 94') and a heat exchanger (95, 95') between the low-temperature fuel and air circulating in the main duct of the turbine engine, - flow distribution devices, said flow distribution devices being arranged upstream of said auxiliary heating devices (92, 92'), at least one flow distribution device being arranged upstream of said heat exchanger assembly (93, 93'), and the opening and closing of these individual flow distribution devices being controlled by a central control unit (99).

2. The cryogenic fuel supply system according to claim 1, characterized in that: The cryogenic fuel supply system includes a pump (96') arranged at the outlet of the storage tank (90), upstream of the auxiliary heating device (92), and upstream of the heat exchanger assembly (93), and the pump (96') is capable of bringing the cryogenic fuel from the storage tank (90) to a pressure higher than the critical pressure of the cryogenic fuel.

3. The cryogenic fuel supply system according to claim 2, characterized in that: The auxiliary heating device (92'), the cryogenic fuel / oil heat exchanger (94') and the heat exchanger (95') between the cryogenic fuel and the air circulating in the main duct of the turbine engine are supercritical exchangers, which are capable of bringing the cryogenic fuel to a temperature higher than the critical temperature of the cryogenic fuel.

4. The cryogenic fuel supply system according to claim 1, characterized in that: The cryogenic fuel supply system includes a pump (96) arranged at the outlet of the storage tank (90), upstream of the auxiliary heating device (92), and upstream of the heat exchanger assembly (93), and the pump (96) is capable of pressurizing the cryogenic fuel leaving the storage tank (90) so that the cryogenic fuel is completely liquid.

5. The cryogenic fuel supply system according to claim 1 or 4, characterized in that: The auxiliary heating device (92), the cryogenic fuel / oil heat exchanger (94) and the heat exchanger (95) between the cryogenic fuel and the air circulating in the main duct of the turbine engine are two-phase exchangers, which are capable of heating the liquid cryogenic fuel so as to convert the liquid cryogenic fuel into a gaseous state.

6. The cryogenic fuel supply system according to any one of claims 1 to 4, characterized in that: The turbine engine (1) is a twin-shaft turbine engine, which comprises a low-pressure air compressor (3), a high-pressure air compressor (4), the combustion chamber (5), a high-pressure turbine (6) and a low-pressure turbine (7) in sequence. The heat exchanger between the low-temperature fuel and the air flowing in the main duct of the turbine engine is an inter-compressor cooling exchanger (95a, 95'a). The inter-compressor cooling exchanger is arranged between the low-pressure air compressor (3) and the high-pressure air compressor (4) and performs heat exchange with the air, which comes from the main duct and is downstream of the low-pressure air compressor (3) of the turbine engine (1).

7. The cryogenic fuel supply system according to any one of claims 1 to 4, characterized in that: The heat exchanger between the low-temperature fuel and the air circulating in the main duct of the turbine engine is a recuperator (95b, 95'b), which exchanges heat with the air coming from the main duct downstream of the turbine (6, 7) of the turbine engine (1).

8. The cryogenic fuel supply system according to any one of claims 1 to 4, characterized in that: The auxiliary heating device (92, 92') is an electric device or a thermal device.

9. The cryogenic fuel supply system according to claim 6, characterized in that: The inter-compressor cooling exchanger (95a, 95'a) is installed in series with the low-temperature fuel / oil heat exchanger (94, 94').

10. The cryogenic fuel supply system according to claim 9, characterized in that: The inter-compressor cooling exchanger (95a, 95'a) is installed upstream of the low-temperature fuel / oil heat exchanger (94, 94').

11. The cryogenic fuel supply system according to claim 6, characterized in that: The inter-compressor cooling exchanger (95a, 95'a) is installed in parallel with the low-temperature fuel / oil heat exchanger (94, 94').

12. The cryogenic fuel supply system according to claim 7, characterized in that: The recuperator (95b, 95'b) and the low-temperature fuel / oil heat exchanger (94, 94') are installed in series.

13. The cryogenic fuel supply system according to claim 12, characterized in that: The recuperator (95b, 95'b) is installed upstream of the low-temperature fuel / oil heat exchanger (94, 94').

14. The cryogenic fuel supply system according to claim 12, wherein: The recuperator (95b, 95'b) is installed downstream of the low-temperature fuel / oil heat exchanger (94, 94').

15. The cryogenic fuel supply system according to any one of claims 1 to 4, characterized in that: The cryogenic fuel supply system includes a fuel compressor (97) disposed between the mixing chamber (91) and the combustion chamber (5).

16. The cryogenic fuel supply system according to any one of claims 1 to 4, characterized in that: The cryogenic fuel is liquefied natural gas or liquid hydrogen.

17. The cryogenic fuel supply system according to any one of claims 1 to 4, characterized in that: The flow distribution device is a valve.

18. A turbine engine (1) for an aircraft, comprising: at least one air compressor (3, 4); a combustion chamber (5) supplied with cryogenic fuel; and at least one turbine (6, 7), characterized in that the turbine engine comprises a cryogenic fuel supply system (9) according to any one of claims 1 to 17, for the combustion chamber.

19. A method for controlling a cryogenic fuel supply system (9) for a combustion chamber according to any one of claims 1 to 16, characterized in that The method comprises the following steps: - during the take-off phase of the aircraft, opening the flow distribution device arranged upstream of the auxiliary heating device (92, 92') and the at least one flow distribution device arranged upstream of the heat exchanger assembly (93, 93') to allow the low-temperature fuel to be heated to circulate through the auxiliary heating device (92, 92') and the heat exchanger assembly (93, 93'), - and during other flight phases of the aircraft, closing the flow distribution device arranged upstream of the auxiliary heating device (92, 92') and opening the at least one flow distribution device arranged upstream of the heat exchanger assembly (93, 93') so that the low-temperature fuel to be heated circulates only in the heat exchanger assembly (93, 93').

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