Oxygen-enriched turbine engine and thermodynamic cycle method of oxygen-enriched turbine engine

Abstract

The invention discloses an oxygen-enriched turbine engine and a thermodynamic cycle method of the oxygen-enriched turbine engine. Comprising an oxygen-enriched gas generator, a turbine, a gas compressor, an oxygen-enriched gas auxiliary atomization injector and an active cooling combustion chamber, the oxygen-enriched gas generator comprises an oxidizing agent inlet, an oxidizing agent liquid collecting cavity, a catalytic bed, a reaction cavity located on the downstream of the catalytic bed, a fuel inlet and an oxygen-enriched gas outlet, and the fuel inlet and the oxygen-enriched gas outlet are located in the side wall face of the reaction cavity. A valve located on a fuel supply pipeline controls on-off of fuel, and two working modes of the oxygen-enriched fuel gas generator can be obtained, namely an oxidizing agent and fuel double-component oxygen-enriched combustion working mode and an oxidizing agent single-component catalytic decomposition working mode. The problems that rich oil circulation combined power is prone to coking and carbon deposition, combustion is not easy to organize, and the power capability of a turbine is limited are solved.

Description

Technical Field

[0001] The present application relates to the technical field of turbine engines, and in particular to an oxygen-enriched turbine engine and a thermodynamic cycle method for an oxygen-enriched turbine engine. Background Art

[0002] From a long-term perspective, near-space combined-power aircraft are the technological highland for the future development of aerospace, and have become strategic and cutting-edge technologies that are of great concern to all countries, while combined cycle engines are the core technology of combined-power aircraft. Hypersonic combined cycle engines are a technical problem of the century, which is specifically manifested in that the most economical turbojet engine at low Mach numbers can only work up to Ma2.5, while the best hypersonic scramjet engine has problems of not starting and insufficient thrust below Ma3.5, resulting in a gap between turbojet and scramjet engines. The reason is that the turbojet engine has a large air intake volume, and the resistance increases sharply with the increase of Mach number, while the scramjet engine has a weak shock wave intensity and a low pressure ratio at low Mach numbers, which limits the heat release of combustion and makes it impossible to add enough energy.

[0003] The current flight envelope of the flight-based space transportation system is wide and the flight mission is complex. It needs to consider both acceleration missions and hovering and cruising missions. It needs to launch at a high frequency, exit missions in real time, and return home safely. To this end, its power system must be able to cruise in the most economical way under high-altitude and high-speed flight conditions, and it must also be able to provide sufficiently large acceleration capabilities and maintain a certain degree of maneuverability. Therefore, the power system is required to be able to achieve wide-range thrust adjustment under high-speed flight conditions, taking into account cruising and maneuverability. The various types of combined power systems currently available, including rocket-based combined engines, turbine combined engines, and air-turbine rocket engines, are difficult to meet the requirements.

[0004] Specifically, the current ATR type combined engines all use rich oil cycles, and the gas temperature changes dramatically with the equivalence ratio, which is prone to local over-temperature ablation. In addition, rich oil combustion is not easy to organize, the combustion efficiency is not high, and coking and carbon deposition often occur, which affects the engine's reusability performance; based on the traditional aircraft engine type combined power, the compressor and turbine work in a coupled manner (that is, the compressor compresses the incoming air, the high-pressure air and fuel are organized to burn in the combustion chamber, the combustion products drive the turbine to work, and the turbine drives the compressor to work), so that the engine thrust is limited by the captured flow, so the thrust adjustment range is narrow. The introduction of the rich oil pre-combustion chamber to drive the turbine (ZL201810529464.X) has achieved the decoupling of the compressor and the turbine, but in order to avoid coking and carbon deposition, the temperature of the rich fuel gas is usually controlled at 800-1000K, resulting in the gas work turbine's ability to be limited, affecting the engine's performance; at high flight altitudes, the existing combined power cannot generate sufficient thrust due to insufficient air capture.

[0005] It should be noted that the above information disclosed in this background technology section is only used to understand the background technology of the present invention concept, and therefore may contain information that does not constitute prior art.

[0006] Application Contents

[0007] In view of the deficiencies in the prior art, the present application discloses an oxygen-rich turbine engine and a thermodynamic cycle method for an oxygen-rich turbine engine, which solve the problems of easy coking and carbon deposition, difficulty in organizing combustion and limited turbine working capacity of oil-rich cycle combined power.

[0008] To achieve the above objectives, this application is implemented through the following technical solutions:

[0009] An oxygen-enriched turbine combination engine includes an oxygen-enriched gas generator, a turbine, a compressor, an oxygen-enriched gas auxiliary atomizing injector, and an actively cooled combustion chamber, wherein the oxygen-enriched gas generator includes an oxidant inlet, an oxidant collecting chamber, a catalyst bed, a reaction chamber located downstream of the catalyst bed, and a fuel inlet and an oxygen-enriched gas outlet located on the side wall of the reaction chamber. The oxidant supply system supplies the oxidant to the oxidant inlet of the oxygen-enriched gas generator, and the fuel supply system supplies the fuel to the fuel inlet of the oxygen-enriched gas generator and the cooling channel inlet of the actively cooled combustion chamber respectively. The valve located on the fuel supply pipeline controls the fuel on and off, and two working modes of the oxygen-enriched gas generator can be obtained, namely, an oxidant and fuel two-component oxygen-enriched combustion working mode and an oxidant single-component catalytic decomposition working mode. The high temperature and high pressure generated at the oxygen-enriched gas outlet of the oxygen-enriched gas generator The oxygen-enriched fuel gas is introduced into the gas inlet of the turbine, works on the turbine, drives the compressor coaxial with the turbine to rotate, and pressurizes the low-pressure air flowing through the compressor to high-pressure air. The high-pressure air generated by the compressor is mixed with the low-pressure oxygen-enriched fuel gas discharged from the turbine gas outlet after working on the turbine, to form oxygen-enriched air with an oxygen content higher than that of conventional air, and is introduced into the oxidant inlet of the oxygen-enriched gas auxiliary atomizing injector. The fuel is delivered to the actively cooled combustion chamber by the fuel supply system, and after actively cooling the combustion chamber wall, it flows out from the cooling channel outlet and enters the fuel inlet of the oxygen-enriched gas auxiliary atomizing injector. A sonic flowmeter is used to divert part of the high-pressure oxygen-enriched fuel gas as auxiliary atomizing gas, which is introduced into the auxiliary atomizing gas inlet of the oxygen-enriched gas auxiliary atomizing injector. The auxiliary gas atomizing injector injects the fuel and oxygen-enriched air into the actively cooled combustion chamber, where oxygen-enriched combustion occurs and thrust is generated.

[0010] According to a preferred technical solution, the number of the oxygen-enriched fuel gas generators can be one or multiple generators working in parallel.

[0011] According to a preferred technical solution, the gas inlet of the turbine can be a single air intake or multiple air intakes corresponding to multiple gas generators working in parallel.

[0012] According to a preferred technical solution, the oxygen-rich gas-assisted atomizing injector may be an injector having injection, atomization, mixing and flame stabilization functions.

[0013] According to a preferred technical solution, in addition to adopting active cooling for thermal protection, the actively cooled combustion chamber can also adopt a composite cooling method combining active cooling with air film cooling to protect the combustion chamber.

[0014] According to a preferred technical solution, the oxidant supplied by the oxidant may be hydrogen peroxide or nitrous oxide, and the supply mode of the oxidant supply system is extrusion supply or pump pressure supply.

[0015] According to a preferred technical solution, the fuel supplied by the fuel supply system is kerosene, and the supply method is extrusion supply or pump pressure supply.

[0016] In addition, the present application also discloses a thermodynamic cycle method for an oxygen-enriched turbine engine, the specific steps of which are:

[0017] S1. The oxidant supply system and the fuel supply system pressurize the oxidant and the fuel respectively and transport them to the oxygen-enriched fuel gas generator;

[0018] S2. The oxidant and fuel react in the oxygen-enriched gas generator to produce oxygen-enriched gas at 1000-1500K. The oxygen-enriched gas contains residual oxygen that does not participate in the reaction, which can inhibit fuel coking and carbon deposition and avoid local overheating. According to the engine operating requirements, the oxygen-enriched gas generator works in different modes:

[0019] S2-1. When the engine is operating in a long-term cruising state, the valve is closed, the fuel supply is cut off, and the oxygen-enriched gas generator operates in a single-component catalytic decomposition mode. The oxidant flows through the oxidant inlet and the oxidant collecting chamber of the oxygen-enriched gas generator in sequence, and a catalytic decomposition reaction occurs when it reaches the catalyst bed in the oxygen-enriched gas generator, generating oxygen-enriched gas with a temperature of 1000-1100K, which enables the engine to have high specific impulse performance while ensuring that long-term operation does not cause high-temperature ablation of the turbine blades;

[0020] S2-2. When the engine is working in the afterburner state, the valve is opened, and the oxygen-enriched gas generator works in the two-component oxygen-enriched combustion mode. The oxidant decomposition gas decomposed by the catalyst bed and the small amount of fuel injected into the fuel inlet downstream of the catalyst bed undergo oxygen-enriched combustion reaction in the reaction chamber to produce oxygen-enriched gas with a temperature of 1100-1500K, which meets the engine's short-term high power output requirements;

[0021] S3. The high-temperature and high-pressure oxygen-enriched gas generated by the oxygen-enriched gas outlet of the oxygen-enriched gas generator 1 is mainly introduced into the turbine gas inlet, driving the compressor coaxial with the turbine to rotate, and pressurizing the low-pressure air flowing through the compressor to high-pressure air. The oxygen-enriched gas generator decouples the operation of the compressor and the turbine, allowing the turbine to operate within a pressure drop ratio range of 10 to 30 times. The high gas temperature and high pressure drop ratio work together to enhance the turbine's working capacity, allowing the compressor to have a working capacity of 1.1 to 10 times the pressure increase ratio;

[0022] S4. The high-pressure oxygen-enriched gas is expanded into low-pressure oxygen-enriched gas after working the turbine, and the low-pressure oxygen-enriched gas is mixed with high-pressure air to form oxygen-enriched air with an oxygen content of 25-40%;

[0023] S5. Pass the oxygen-enriched air into the oxidant inlet of the oxygen-enriched gas-assisted atomizing injector, pass the fuel after actively cooling the combustion chamber into the fuel inlet of the oxygen-enriched gas-assisted atomizing injector, and pass part of the high-temperature and high-pressure oxygen-enriched fuel gas throttled by the sonic flowmeter as the oxygen-enriched auxiliary atomizing gas into the auxiliary atomizing gas inlet of the oxygen-enriched gas-assisted atomizing injector;

[0024] S6. In the oxygen-rich gas-assisted atomizing injector, the fuel is atomized by high-temperature and high-pressure oxygen-rich combustion gas, fully mixed with oxygen-rich air, and then injected into the actively cooled combustion chamber by the oxygen-rich gas-assisted atomizing injector for oxygen-rich combustion. Oxygen-rich combustion can greatly broaden the flame stabilization range and improve combustion efficiency, thereby realizing efficient conversion of chemical energy into thrust.

[0025] The present application discloses an oxygen-enriched turbine engine and an oxygen-enriched turbine engine thermodynamic cycle method, which have the following advantages:

[0026] 1. Compared with the traditional air turbine rocket (ATR) using an oil-rich gas generator, the core advantages of the oxygen-rich gas generator cycle proposed in this patent are:

[0027] (1) The oxygen-enriched gas generator can achieve a higher gas temperature, and the gas temperature is stable and controllable within the working oxygen-oil ratio range;

[0028] (2) Oxygen-enriched fuel gas contains residual oxygen that does not participate in the reaction, which can inhibit fuel coking and carbon deposition and avoid local overheating, thereby improving engine life and reusability;

[0029] (3) The oxygen content of the mixture of air entering the combustion chamber and turbine exhaust is higher than that of conventional air, which can greatly broaden the flame stability range and improve combustion efficiency, thus realizing efficient conversion of chemical energy into thrust;

[0030] (4) The oxygen-rich gas generator can operate in two modes: oxidant single-component catalytic decomposition and oxidant and fuel dual-component oxygen-rich combustion, thereby improving the engine's wide-range thrust regulation capability.

[0031] 2. The oxygen-rich gas generator drives the turbine to work through the catalytic decomposition or oxygen-rich combustion reaction of its own oxygen-rich working fluid, decoupling the work of the compressor and the turbine, so that the turbine end can work at a higher pressure drop ratio. Under the combined effect of the high pressure drop ratio and high gas temperature, the turbine's work capacity is greatly improved.

[0032] 3. As it carries part of the oxidant, it has a higher ceiling at the same flight speed. At the same time, reducing the compressor intake volume and capture area helps reduce compressor power consumption and intake resistance. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below.

[0034] Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0035] Figure 1 It is the schematic diagram of the composition of the oxygen-rich turbine engine;

[0036] Figure 2 It is the pv diagram of the thermodynamic cycle process of the oxygen-rich turbine combination engine;

[0037] Figure 3 It is the hs diagram of the thermodynamic cycle process of the oxygen-rich turbine combination engine;

[0038] Figure 4 It is the phenomenon of coking and carbon deposition when the temperature of the rich fuel gas generator is higher than 1000K (oxidant: oxygen; fuel: kerosene);

[0039] Figure 5 The gas temperature changes with the oxygen-oil ratio. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments.

[0041] Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making any creative work shall fall within the scope of protection of this application.

[0042] An oxygen-enriched turbine combination engine includes an oxygen-enriched gas generator, a turbine, a compressor, an oxygen-enriched gas auxiliary atomizing injector, and an actively cooled combustion chamber. Figure 1 shown.

[0043] The oxygen-enriched gas generator uses the aircraft's own oxidant, which is decomposed through a catalytic bed to form high-temperature and high-pressure oxygen-enriched gas. It can also burn with fuel at a low equivalence ratio to further increase the gas temperature. The oxygen-enriched gas generator includes an oxidant inlet, an oxidant collecting chamber, a catalytic bed, a reaction chamber downstream of the catalytic bed, and a fuel inlet and an oxygen-enriched gas outlet located on the side wall of the reaction chamber. The oxidant and fuel are supplied by the oxidant supply system and the fuel supply system, respectively. The oxidant supplied by the oxidant can be hydrogen peroxide or nitrous oxide, and the supply method of the oxidant supply system is extrusion supply or pump pressure supply. The fuel supplied by the fuel supply system is kerosene, and the supply method is extrusion supply or pump pressure supply. The fuel is controlled on and off by the valve on the fuel supply pipeline, so that the gas generator can work in different modes according to the working conditions:

[0044] ① When the engine is operating in a long-term cruise state, the valve is closed to cut off the fuel supply, and the oxygen-enriched gas generator operates in a single-component catalytic decomposition mode. The oxidant flows through the oxidant inlet and oxidant liquid collecting chamber of the oxygen-enriched gas generator in sequence, and reaches the catalyst bed in the oxygen-enriched gas generator, where a catalytic decomposition reaction occurs to produce oxygen-enriched gas with a temperature of 1000-1100K, which enables the engine to have high specific impulse performance while ensuring that long-term operation does not cause high-temperature ablation of the turbine blades;

[0045] ② When the engine is working in the afterburner state, the valve is opened and the oxygen-enriched gas generator works in the dual-component oxygen-enriched combustion mode. The oxidant decomposition gas decomposed by the catalytic bed and the small amount of fuel injected into the fuel inlet downstream of the catalytic bed undergo an oxygen-enriched combustion reaction in the reaction chamber. By controlling the fuel injection amount, oxygen-enriched gas with a temperature range of 1100-1500K can be generated to meet the engine's short-term high power output requirements;

[0046] The high-temperature and high-pressure oxygen-rich gas generated at the outlet of the oxygen-rich gas generator enters the turbine gas inlet through the pipeline, works on the turbine, drives the compressor coaxial with the turbine to rotate, and pressurizes the low-pressure air flowing through the compressor to high-pressure air. Since the oxygen-rich gas generator is introduced to drive the turbine independently, the operation of the compressor end and the turbine end is decoupled, achieving a working performance of 10 to 30 times the pressure drop ratio at the turbine end. According to the turbine power expression where π t Turbine end pressure ratio, T t is the gas temperature, η tis the total efficiency of the turbine, and the oxygen-rich gas flow rate is m'2. The oxygen-rich gas generator can generate oxygen-rich gas with a temperature of 1000-1600K, and at the same time obtain a working range of 10-30 times high pressure drop ratio. Compared with the gas temperature range of 800-1000K of the rich gas generator, the turbine's working capacity can be improved, so that the compressor has a working performance of 1.1-10 times the pressure ratio, ensuring that the engine has the ability to adjust the thrust in a wide range.

[0047] Based on the turbine power expression, by adjusting the oxygen-enriched gas flow m′2 generated by the gas generator, the engine thrust can be adjusted by adjusting the turbine output power, so that the engine has the ability to adjust the thrust over a wide range. Therefore, according to the thrust performance requirements of the oxygen-enriched turbine engine, the number of oxygen-enriched gas generators can be set to one or multiple in parallel. Correspondingly, the turbine gas inlet can be a single air intake or multiple air intakes corresponding to multiple gas generators working in parallel.

[0048] The low-pressure oxygen-enriched gas after the turbine works and the high-pressure air boosted by the compressor are mixed in the turbine casing to form oxygen-enriched air, which is then introduced into the oxidant inlet of the oxygen-enriched gas auxiliary atomizing injector. Since the oxygen-enriched gas contains residual oxygen, the oxygen content of the mixed oxygen-enriched air can reach 25-40%.

[0049] The fuel delivered to the actively cooled combustion chamber by the fuel supply system actively cools the combustion chamber wall, flows out from the cooling channel outlet, and enters the fuel inlet of the oxygen-rich gas assisted atomizing injector.

[0050] The high-temperature, high-pressure, oxygen-rich gas at the outlet of the gas generator mainly drives the turbine, and a small part is diverted through the sonic flowmeter as auxiliary atomizing gas and introduced into the auxiliary atomizing gas inlet of the oxygen-rich gas auxiliary atomizing injector for gas-assisted atomization of the liquid fuel in the injector. The flow rate of the auxiliary atomizing gas is proportional to the area of ​​the sonic flowmeter.

[0051] In the oxygen-enriched gas-assisted atomizing injector, the fuel is atomized by high-temperature and high-pressure oxygen-enriched fuel gas and then injected horizontally into the oxygen-enriched air to form an atomized oxygen-containing jet. After being fully mixed with the oxygen-enriched air, the fuel is injected into the actively cooled combustion chamber by the oxygen-enriched gas-assisted atomizing injector for oxygen-enriched combustion. A flame stabilizing structure is set at the tail of the injector to achieve flame stabilization. Gas-assisted atomization helps to achieve liquid fuel atomization and penetration depth control in the lateral airflow, and can also improve the local equivalence ratio to a certain extent. Oxygen-enriched combustion can greatly broaden the flame stabilization range and improve combustion efficiency, thereby achieving efficient conversion of chemical energy into thrust.

[0052] In order to achieve long-term stable operation of the engine, the actively cooled combustion chamber can also adopt a composite cooling method that combines air film cooling with active fuel cooling. The heat flow is isolated by multiple air films inside the combustion chamber, and the heat absorption of the fuel in the cooling channel is used to reduce the temperature of the combustion chamber wall, thereby improving the thermal protection capability of the combustion chamber.

[0053] Figure 2 and Figure 3 They are the pv diagram and hs diagram of the thermodynamic cycle process of the oxygen-rich turbine combination engine respectively. The changes in physical parameters they represent are consistent with the thermodynamic cycle process based on the structure of the oxygen-rich turbine combination engine, and are used to gain a deeper understanding of the thermodynamic cycle method of the oxygen-rich turbine combination engine from a physical perspective.

[0054] In the figure, (0) is the atmospheric environment at infinity; (1) is the compressor inlet cross section; (2) is the compressor outlet cross section; (3) is the gas generator inlet cross section; (4) is the gas generator outlet cross section, which is also the turbine inlet cross section and the kerosene injection gas atomization bleed air inlet cross section; (5) is the turbine outlet cross section; (6) is the section where the oxygen-rich gas after the turbine works and the high-pressure air after the compressor supercharge are mixed into the injector cross section; (7) is the section where the gas generator outlet bleed air and kerosene are mixed for gas atomization injection; (8) is the combustion chamber straight section outlet cross section; (9) is the combustion chamber tail nozzle outlet cross section.

[0055] The PV diagram and HS diagram of the thermodynamic cycle of the oxygen-rich turbine combination engine are as follows Figure 2 , Figure 3 As shown, the process is as follows:

[0056] 0′-3 Constant volume and pressurization process of liquid oxygen-rich energetic working fluid storage tank;

[0057] 3-4 Isobaric catalytic decomposition process of oxygen-rich energetic working fluid in gas generator;

[0058] 4-5 Expansion process of oxygen-rich gas in turbine;

[0059] 5-6 Isobaric heat release process of oxygen-enriched fuel gas;

[0060] 4-7 The process of regulating the pressure reduction of the bleed air between the gas generator outlet and the kerosene nozzle;

[0061] 1-2 Air compression process in compressor;

[0062] 2-6 Isobaric heat absorption process of air;

[0063] 6-8 Medium-pressure combustion process in combustion chamber;

[0064] 8-9 Expansion process in the combustion chamber tail nozzle;

[0065] 9-0 Isobaric exothermic process in atmospheric environment.

[0066] Existing ATR type combined engines all adopt rich oil cycle. The core component of the rich oil cycle is the rich fuel gas generator, whose function is to mix and burn the oxidant and fuel introduced into the rich fuel gas generator at a certain oxygen-oil ratio to produce rich fuel gas with excess fuel, which is used to drive the turbine to do work. Compared with the oxygen-rich fuel gas generator based on two working modes proposed in the present invention, the rich fuel gas generator has the following shortcomings:

[0067] ① Experiments show that when the temperature of the rich-burning generator is higher than 1000K, coking and carbon deposition are likely to occur (such as Figure 4 As shown in the figure, the higher the temperature, the greater the soot concentration. During the combustion process, the soot generates extremely strong heat radiation, which will bring a great load to the engine thermal protection and may even cause ablation of the engine wall. On the other hand, the carbon deposits in the engine are difficult to clean and may even block the fuel delivery pipeline, affecting the engine life and reusability.

[0068] ② In order to suppress the formation of soot, the operating temperature of the rich fuel gas generator is generally lower than 1000K, usually selected to be 800~1000K. Figure 5 From the curve of gas temperature changing with oxygen-oil ratio, we can see that the gas temperature on the fuel-rich side changes dramatically with the oxygen-oil ratio. Due to the uneven distribution of fuel space in the gas generator, local over-temperature ablation is very likely to occur.

[0069] ③ Due to the temperature of rich fuel gas, the ability of the gas turbine to work is limited, affecting the engine's performance;

[0070] ④ There is excess fuel in the rich fuel gas, and the rich fuel combustion is difficult to organize, and the combustion efficiency is not high. Under the same output power, the rich fuel gas cannot increase the thrust.

[0071] Compared with the above shortcomings of the fuel-rich gas cycle, the oxygen-rich gas cycle has the following advantages:

[0072] ① The oxygen-enriched fuel gas generator is equipped with a catalytic bed, which can work in both the oxidant single-component catalytic decomposition mode and the oxidant and fuel dual-component oxygen-enriched combustion mode. By adjusting the fuel flow rate, the oxygen-enriched fuel gas temperature range of 1000-1500K can be obtained. Since the oxygen-enriched fuel gas contains residual oxygen, it can inhibit fuel coking and carbon deposition and avoid local overheating;

[0073] ② From Figure 5 It can be seen that within the oxygen-oil ratio selection range of the oxygen-enriched gas generator, the gas temperature changes slowly with the oxygen-oil ratio, and the gas temperature is stable and controllable;

[0074] ③ Compared with the rich fuel gas of 800-1000K, the oxygen-rich fuel gas has a higher temperature range, so the turbine capacity is stronger;

[0075] ④ In the oxygen-enriched gas cycle, the oxygen-enriched gas is finally sprayed into the combustion chamber to carry out oxygen-enriched combustion with the fuel, which can greatly broaden the flame stabilization range and improve the combustion efficiency, and realize the efficient conversion of chemical energy into thrust. When the flight altitude is high and the intake air volume is insufficient, the oxygen-enriched gas can also provide an additional part of the oxidant to meet the thrust requirements of the aircraft.

[0076] It should be noted that, in this article, relational terms are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0077] Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not expressly listed, or also includes elements inherent to such process, method, article, or apparatus.

[0078] Without more constraints, an element defined by the phrase "comprising a..." does not exclude the existence of other identical elements in the process, method, article or apparatus comprising the element.

[0079] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. An oxygen-enriched turbine combination engine, comprising an oxygen-enriched gas generator (1), a turbine (2), a compressor (3), an oxygen-enriched gas auxiliary atomizing injector (4), and an actively cooled combustion chamber (5), wherein: The oxygen-enriched fuel gas generator comprises an oxidant inlet (1-1), an oxidant collecting chamber (1-2), a catalyst bed (1-3), a reaction chamber (1-4) located downstream of the catalyst bed, and a fuel inlet (1-5) and an oxygen-enriched fuel gas outlet (1-6) located on the side wall of the reaction chamber. An oxidant supply system (6) supplies oxidant to the oxidant inlet (1-1) of the oxygen-enriched fuel gas generator (1). A fuel supply system (7) supplies fuel to the fuel inlet of the oxygen-enriched fuel gas generator (1) and a cooling channel inlet (5-1) of an active cooling combustion chamber. A valve (8) located on the fuel supply pipeline controls the on-off of the fuel. Two working modes of the oxygen-enriched fuel gas generator (1) can be obtained, namely, an oxidant and fuel two-component oxygen-enriched combustion working mode and an oxidant single-component catalytic decomposition working mode. The high-temperature and high-pressure oxygen-enriched fuel gas generated at the oxygen-enriched fuel gas outlet (1-6) of the oxygen-enriched fuel gas generator (1) is introduced into the fuel inlet (2-1) of the turbine (2) to control the turbine. (2) performs work, drives the compressor (3) coaxial with the turbine (2) to rotate, pressurizes the low-pressure air flowing through the compressor (3) to high-pressure air, and the high-pressure air generated by the compressor (3) is mixed with the low-pressure oxygen-enriched gas discharged from the turbine gas outlet (2-2) after the turbine performs work, to form oxygen-enriched air with an oxygen content higher than that of conventional air, which is passed into the oxidant inlet (4-1) of the oxygen-enriched gas auxiliary atomizing injector, and the fuel is delivered to the fuel supply system (7) to the actively cooled combustion chamber (5). After actively cooling the combustion chamber wall, the fuel flows out from the cooling channel outlet (5-2) and enters the fuel inlet (4-2) of the oxygen-enriched gas auxiliary atomizing injector (4). A part of the high-pressure oxygen-enriched fuel gas is diverted by a sonic flowmeter (9) as auxiliary atomizing gas and passed into the auxiliary atomizing gas inlet (4-3) of the oxygen-enriched gas auxiliary atomizing injector (4). The auxiliary gas atomizing injector 4 injects the fuel and oxygen-enriched air into the actively cooled combustion chamber, causing oxygen-enriched combustion and generating thrust.

2. The oxygen-rich turbine engine according to claim 1, wherein the number of the oxygen-rich gas generators (1) can be one or multiple working in parallel.

3. The oxygen-enriched turbine engine as claimed in claim 1, wherein the gas inlet (2-1) of the turbine (2) can be a single air intake or multiple air intakes corresponding to multiple gas generators working in parallel.

4. The oxygen-rich turbine engine according to claim 1, wherein the oxygen-rich gas auxiliary atomizing injector (4) can be an injector having injection, atomization, mixing and flame stabilization functions at the same time.

5. The oxygen-rich turbine engine as claimed in claim 1, wherein the actively cooled combustion chamber (5) can protect the combustion chamber by a composite cooling method combining active cooling with film cooling in addition to thermal protection by active cooling.

6. The oxygen-rich turbine engine according to claim 1, wherein the oxidant supplied by the oxidant 6 can be hydrogen peroxide or nitrous oxide, and the supply method of the oxidant supply system (6) is extrusion supply or pump pressure supply.

7. The oxygen-rich turbine engine according to claim 1, wherein the fuel supplied by the fuel supply system (7) is kerosene, and the supply method is extrusion supply or pump pressure supply.

8. A thermodynamic cycle method for an oxygen-enriched turbine engine, the specific steps of which are: S1. The oxidant supply system (6) and the fuel supply system (7) respectively pressurize the oxidant and the fuel and deliver them to the oxygen-enriched fuel gas generator (1); S2. The oxidant and the fuel react in the oxygen-enriched gas generator (1) to generate an oxygen-enriched gas at 1000-1500K. The oxygen-enriched gas contains residual oxygen that does not participate in the reaction, which can inhibit fuel coking and carbon deposition and avoid local overheating. According to the engine operating requirements, the oxygen-enriched gas generator (1) operates in different modes: S(2-1). When the engine is operating in a long-term cruising state, the valve (8) is closed to cut off the fuel supply, and the oxygen-enriched gas generator (1) operates in a single-component catalytic decomposition mode. The oxidant flows through the oxidant inlet (1-1) and the oxidant collecting chamber (1-2) of the oxygen-enriched gas generator (1) in sequence, and a catalytic decomposition reaction occurs when the oxidant reaches the catalyst bed (1-3) in the oxygen-enriched gas generator (1), generating oxygen-enriched gas with a temperature of 1000 to 1100K, so that the engine has a high specific impulse performance while ensuring that long-term operation does not cause high-temperature ablation of the turbine blades; S(2-2). When the engine is operating in the boost state, the valve (8) is opened, and the oxygen-enriched gas generator (1) operates in the dual-component oxygen-enriched combustion mode. The oxidant decomposition gas decomposed by the catalyst bed (1-3) and the small amount of fuel injected from the fuel inlet (1-5) downstream of the catalyst bed (1-3) undergo an oxygen-enriched combustion reaction in the reaction chamber (1-4), generating oxygen-enriched gas with a temperature of 1100 to 1500K, which meets the engine's short-term high power output requirements; S3. The high-temperature and high-pressure oxygen-enriched gas generated by the oxygen-enriched gas outlet (1-6) of the oxygen-enriched gas generator (1) is mainly introduced into the gas inlet (2-1) of the turbine (2), driving the compressor (3) coaxial with the turbine (2) to rotate, thereby increasing the pressure of low-pressure air flowing through the compressor to high-pressure air. The oxygen-enriched gas generator decouples the operation of the compressor (3) and the turbine (2), so that the turbine (2) operates within a range of 10 to 30 times the pressure drop ratio. The high gas temperature and the high pressure drop ratio work together to enhance the working capacity of the turbine (2), so that the compressor (3) has the working capacity of 1.1 to 10 times the pressure increase ratio; S4. After the high-pressure oxygen-enriched gas is expanded into a low-pressure oxygen-enriched gas after working the turbine (2), the low-pressure oxygen-enriched gas is mixed with high-pressure air to form an oxygen-enriched air with an oxygen content of 25-40%; S5. The oxygen-enriched air is introduced into the oxidant inlet (4-1) of the oxygen-enriched gas-assisted atomizing injector (4), the fuel after actively cooling the combustion chamber is introduced into the fuel inlet (4-2) of the oxygen-enriched gas-assisted atomizing injector (4), and part of the high-temperature and high-pressure oxygen-enriched fuel gas throttled by the sonic flowmeter is used as the oxygen-enriched auxiliary atomizing gas and introduced into the auxiliary atomizing gas inlet (4-3) of the oxygen-enriched gas-assisted atomizing injector (4); S6. In the oxygen-enriched gas-assisted atomizing injector (4), the fuel is atomized by the high-temperature and high-pressure oxygen-enriched fuel gas and fully mixed with the oxygen-enriched air. The fuel is then injected by the oxygen-enriched gas-assisted atomizing injector (4) into the actively cooled combustion chamber (5) for oxygen-enriched combustion. The oxygen-enriched combustion can greatly broaden the flame stabilization range and improve the combustion efficiency, thereby realizing efficient conversion of chemical energy into thrust.

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