Continuous steam injection aviation turbine engine configuration and overall parameter design method and system

Abstract

The invention relates to the field of aero-turbine engines, and discloses a steam jet aero-turbine engine configuration and overall parameter design method and system which can be used for subsonic airplanes such as large transport planes and civil airliners. According to the continuous steam injection aviation turbine engine, the steam generator and the condenser are arranged behind the low-pressure turbine, so that the exhaust temperature is reduced to be close to the environment temperature, and steam is recycled through the gas-liquid separator. The condensers are arranged on engine wings and an engine body, and high-altitude environment air is used for cooling fuel gas. In addition, according to the invention, the fuel gas is excessively expanded to be lower than the environmental pressure in the low-pressure turbine, and an exhaust compressor is additionally arranged behind the condenser, so that the exhaust pressure is improved, the exhaust gas is exhausted at a high speed, and the connotation thrust is generated. The exhaust compressor is driven by a motor, and electric energy is extracted from the low-pressure shaft through a generator.

Description

Technical Field

[0001] The present invention belongs to the technical field of steam injection of aviation turbine engines, and in particular relates to a method and device for establishing engine water circulation. The present invention can be used for large transport aircraft and civil passenger aircraft with a heat recovery system. Background Art

[0002] Considering the rising fuel prices and strict civil aviation emission requirements, high thermal efficiency and minimum emission pollution have become increasingly important for aircraft engines. Steam jet gas turbines have been widely used in power plants and ships because of their ability to effectively improve thermal efficiency. Applying this technology to the field of aircraft engines is expected to significantly reduce their fuel consumption. However, the problem of water supply difficulties has always been the main problem faced by the development of water jet aircraft turbine engines, which makes it impossible for the engine to continuously spray water.

[0003] In order to solve the problem that the steam jet turbofan engine cannot work continuously, the engine needs to add water circulation on the basis of the original circulation, that is, to meet the engine's sustainable water injection requirements by recycling the water in the exhaust gas. In addition, after adding the water circulation, the exhaust temperature of the low-pressure turbine of the turbine engine is still very high, and only low-grade heat energy can be recovered through the heat exchanger. Therefore, it is possible to consider increasing the expansion ratio at the low-pressure turbine, further expand and do work, and directly utilize the high-grade energy of the exhaust gas. Summary of the invention

[0004] The purpose of the present invention is to overcome the above problems existing in the prior art and provide a method and device for optimizing the overall parameters of a steam continuous injection aviation turbine engine. Compared with conventional regenerative aircraft engines, the engine condenser proposed by the present invention is designed at the wing and fuselage, and the internal combustion gas is cooled by high-altitude ambient air. Since the air on the wing surface flows at the speed of the flight Mach number, the cooling temperature of the cold source can be almost regarded as constant, and the cooling temperature is lower than that designed inside the engine, thereby significantly reducing the requirements for the heat exchange performance of the condenser. In addition, in order to further utilize the high-grade energy in the low-pressure turbine combustion gas, that is, to allow the low-pressure turbine of the combustion gas to over-expand and do more work, the present invention adds a first-stage exhaust compressor after the condenser, so that the combustion gas is pressurized to a pressure greater than the ambient static pressure before entering the internal nozzle, so that it can be discharged into the atmosphere. Since a large amount of water is recovered and the temperature of the combustion gas at the outlet of the condenser is greatly reduced, compared with the additional expansion work of the low-pressure turbine, the compression work consumed when compressed is also lower, and the exhaust compressor is driven by a motor, and the power it consumes is extracted from the low-pressure shaft. In particular, an adjustable valve is set in front of the exhaust compressor. When using low hydrogen-to-carbon ratio fuel (H2), the valve is adjusted to allow the gas to pass through the exhaust compressor. When using high hydrogen-to-carbon ratio fuel (CH2, CH4), the gas does not pass through the exhaust compressor. An adjustable tail nozzle is used to adapt to different turbine outlet pressures.

[0005] In addition, in actual operation, conventional aviation turbine engines need to extract cooling air from the compressor to cool the high-temperature turbine, which will cause a partial waste of compression work. In the steam continuous injection aviation turbine engine of the present invention, condensed water can be used directly to cool the turbine, and at the same time, condensed water can be sprayed into the high-pressure compressor to perform intermediate cooling on the high-pressure compressor to reduce compression power consumption. Since water needs to absorb a large amount of latent heat of vaporization when vaporizing, even a small amount of water can achieve a good cooling effect. Compared with the extraction cooling system of conventional aviation turbine engines, the overall efficiency of the steam continuous injection aviation turbine engine can be further improved on the basis of the above-mentioned water spray cycle.

[0006] In order to achieve the above technical objectives and the above technical effects, the present invention is implemented through the following technical solutions:

[0007] Based on the overall parameter optimization method of the continuous steam injection aviation turbine engine, the optimization method includes:

[0008] Step S1: obtaining component characteristic parameters of a steam continuous injection aviation turbine engine;

[0009] Step S2: According to the change of the total efficiency of the continuous steam injection aviation turbine engine at the maximum water injection amount, the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure of the engine under the design point working condition are determined.

[0010] Step S3: using the analysis module of the simulation model, according to the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure, determine the relationship between the total engine efficiency and the water injection amount under the design point working condition, and obtain the optimization of the overall parameters.

[0011] Furthermore, the steam continuous injection aviation turbine engine includes a high-pressure component, a low-pressure component and a heat exchange component. The high-pressure component has a high-pressure turbine, a high-pressure compressor, and a high-pressure shaft. The low-pressure turbine has a low-pressure turbine, a low-pressure compressor, a low-pressure shaft and a low-pressure shaft motor. The heat exchange component includes an evaporator and a condenser.

[0012] Furthermore, the steam continuously injects component characteristic parameters of the aviation turbine engine.

[0013] Furthermore, when the steam continuous injection aviation turbine engine is working, the condensed water first enters the evaporator to be heated into high-temperature steam, and then is sprayed into the combustion chamber to flow with the fuel gas, and finally is re-condensed into liquid water in the condenser to complete the water cycle.

[0014] Furthermore, the step S3 specifically includes:

[0015] When the low-pressure turbine outlet pressure is not lower than 0.5 of the ambient static pressure and the exhaust compressor outlet pressure is not lower than the ambient static pressure, when the exhaust compressor outlet pressure is fixed, the low-pressure turbine outlet pressure of the steam continuous injection aviation turbine engine corresponding to the optimal thermal efficiency at the maximum water injection amount shall be determined as the optimal low-pressure turbine outlet pressure; when the low-pressure turbine outlet pressure is fixed, the exhaust compressor outlet pressure of the steam continuous injection aviation turbine engine corresponding to the optimal thermal efficiency at the maximum water injection amount shall be determined as the optimal exhaust compressor outlet pressure.

[0016] Furthermore, the optimal parameters of the engine at the design point must meet the following conditions:

[0017] Ensure that the fuel is fully burned, that is, the fuel-air equivalence ratio is less than 1.

[0018] The present invention also provides a method for designing a control law of a steam-based continuous injection aviation turbine engine, the control law design method comprising:

[0019] High-pressure components, including high-pressure turbine, high-pressure compressor and high-pressure shaft;

[0020] Low-pressure components, including low-pressure turbine, low-pressure compressor, low-pressure shaft and low-pressure shaft motor;

[0021] Heat exchange components, including evaporators and condensers;

[0022] A control module is used to adjust the amount of water injection based on engine operating data to optimize the outlet pressure of the low-pressure turbine and exhaust compressor.

[0023] Furthermore, the evaporator in the heat exchange component is used to heat the condensed water into high-temperature steam, which enters the combustion chamber and mixes with the fuel gas to improve combustion efficiency. The condenser is used to condense the steam in the exhaust gas into liquid water to achieve water circulation.

[0024] Furthermore, the control module monitors the low-pressure turbine outlet pressure and the exhaust compressor outlet pressure in real time through sensors, and controls the water injection device according to the optimal water injection amount to optimize the engine operating efficiency.

[0025] Furthermore, it also includes an energy analysis module, which analyzes the energy flow of high-pressure components, low-pressure components and heat exchange components based on the first law and the second law of thermodynamics to optimize the energy utilization of steam and gas.

[0026] Furthermore, the condenser is installed under the aircraft skin, and the exhaust temperature is reduced by utilizing the cooling effect of the aircraft skin, and condensed water is recovered for recirculation.

[0027] The beneficial effects of the present invention are:

[0028] (1) By placing the condenser outside the wing and fuselage surface, especially the high-speed flow and lower temperature of the air on the wing surface, the engine's heat exchange performance requirements for the condenser can be effectively reduced, while avoiding the pressure loss caused by the condenser design in the external duct.

[0029] (2) The effectiveness of this solution can be verified by performing simulations.

[0030] (3) By adding a compressor after the condenser, the low-pressure turbine can be over-expanded to a lower temperature and pressure, thereby further utilizing the high-grade energy in the fuel gas, relatively reducing the heat exchange in the heat exchanger, and ultimately improving the overall efficiency of the engine.

[0031] (4) By spraying water to cool the high-pressure compressor and the two-stage turbine, the latent heat of vaporization of water is utilized to further improve the efficiency of the engine of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0033] Figure 1 It is a simplified structural diagram of a steam continuous injection aviation turbine engine in an embodiment of the present disclosure;

[0034] Figure 2 A simplified diagram of the arrangement of a condenser for a steam continuous injection aviation turbine engine in an embodiment of the present disclosure;

[0035] Figure 3 It is a flow chart of a method for optimizing parameters of a steam continuous injection aviation turbine engine in an embodiment of the present invention;

[0036] Figure 4 It is a schematic diagram of the analysis results of the total efficiency of the continuous steam injection aviation turbine engine according to the embodiment of the present disclosure as the low-pressure turbine outlet pressure changes;

[0037] Figure 5 It is a schematic diagram of the analysis result of the total efficiency of the continuous steam injection aviation turbine engine according to the exhaust compressor outlet pressure change in the embodiment of the present disclosure;

[0038] Figure 6 It is a schematic diagram showing how the total efficiency of a steam continuous injection aviation turbine engine in an embodiment of the present disclosure varies with the amount of water injection at the optimal exhaust compressor outlet pressure and low-pressure turbine outlet pressure compared to a conventional engine.

[0039] Figure 7It is a schematic diagram showing the fuel consumption rate of a steam continuous injection aviation turbine engine as a function of the injection amount at the optimal exhaust compressor outlet pressure and the low-pressure turbine outlet pressure in an embodiment of the present disclosure compared to a conventional engine. DETAILED DESCRIPTION

[0040] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. It should be noted that although the description object of this embodiment is an aircraft engine, the application object of the present invention is not limited to this. The present invention can be used for engines with heat recovery, including but not limited to turboshaft engines, turbofan engines, and turbojet engines.

[0041] Example 1: Application of continuous steam jet aviation turbine engine in high-altitude long-flight UAV

[0042] A steam continuous injection aviation turbine engine system based on the present invention is used on a high-altitude, long-flight UAV. The steam continuous injection system of the UAV uses a condensed water recovery device and a heat exchange device to re-condense the steam in the exhaust into liquid water using the cooling effect of the aircraft skin to achieve recycling. During the operation of the engine, the evaporator heats the condensed water into high-temperature steam and sprays it into the combustion chamber through water spray, thereby optimizing the combustion efficiency of the gas and increasing the thrust of the engine. Under the action of the control module, the water spray volume is dynamically adjusted based on the needs of different flight stages to ensure that the engine performance and fuel efficiency are optimal in a high-altitude environment. During the long-flight flight of this UAV, the system maintains stable performance by adjusting the outlet pressure of the low-pressure turbine and the exhaust compressor in real time, significantly improving the mission execution capability.

[0043] Example 2: Application of steam continuous jet aviation turbine engine in commercial passenger aircraft

[0044] The steam continuous injection aviation turbine engine system is used on a commercial passenger aircraft. The condenser of the system is installed under the aircraft skin. With the help of air cooling during high-speed flight, the exhaust temperature is effectively reduced and condensed water is recovered. Through an efficient heat exchange device, the condensed water is heated into high-temperature steam and sprayed into the combustion chamber to mix with the fuel gas, which improves the combustion efficiency. The control module obtains flight data and dynamically adjusts the water injection volume and outlet pressure to achieve optimal control of the low-pressure turbine and exhaust compressor. The energy analysis module of the system uses the first and second laws of thermodynamics to monitor the energy utilization of the entire engine, ensuring the optimal configuration of energy flow in different flight stages, ultimately reducing fuel consumption, improving engine efficiency, and significantly improving flight economy.

[0045] like Figure 1 As shown, the steam continuous injection aviation turbine engine in this embodiment is a dual-shaft gas turbine, including a combustion chamber, a high-pressure compressor, a low-pressure compressor, a high-pressure turbine, a low-pressure turbine, an exhaust compressor and a regenerator.

[0046] The high-pressure component has a high-pressure compressor, a high-pressure turbine and a high-pressure shaft, the low-pressure component has a low-pressure compressor, a low-pressure turbine, an exhaust compressor, a water pump and a low-pressure shaft, and the heat exchanger has an evaporator and a condenser. Specifically, the high-pressure turbine drives the high-pressure compressor through the high-pressure shaft, and at the same time, the high-pressure shaft outputs power outward, and the low-pressure turbine drives the low-pressure compressor, the exhaust compressor and the water pump through the low-pressure shaft. A low-pressure shaft motor is installed on the low-pressure shaft, which provides power to the water pump and the exhaust compressor by extracting the work of the low-pressure turbine.

[0047] The steam continuous jet aviation turbine engine of this embodiment is a dual-shaft gas turbine, which uses high-pressure and low-pressure stages to work independently. The high-pressure components include a high-pressure compressor, a high-pressure turbine and a high-pressure shaft, and the low-pressure components include a low-pressure compressor, a low-pressure turbine, an exhaust compressor, a water pump and a low-pressure shaft. During operation, the fuel in the combustion chamber is mixed and burned with the compressed air provided by the high-pressure compressor, and the high-temperature and high-pressure combustion gas generated drives the high-pressure turbine to operate. The high-pressure turbine drives the high-pressure compressor to work through the high-pressure shaft, and transmits the remaining energy to the outside through the high-pressure shaft to provide power output.

[0048] The working principle of the low-pressure part is relatively complex. The low-pressure turbine receives the gas from the high-pressure turbine and drives the low-pressure compressor and exhaust compressor through the low-pressure shaft. The low-pressure compressor further compresses the air and sends it into the combustion chamber, while the exhaust compressor extracts the waste heat from the gas to jointly improve the system efficiency. At the same time, the low-pressure turbine also provides power to the water pump through the low-pressure shaft motor, driving the water pump to send the condensed water in the condenser to the evaporator for heating and generating high-temperature steam.

[0049] The evaporator plays a key role in the entire system. The condenser recovers the steam after combustion and cools it into liquid water, which is then sent to the evaporator to be reheated into high-temperature steam. The evaporator is connected to the high-temperature part of the engine through a heat exchanger, and uses the heat energy generated by combustion to heat water into high-temperature steam. The steam is then sprayed into the combustion chamber and mixed with the gas for further combustion, which improves the combustion efficiency and effectively reduces the exhaust gas temperature. The combination of the steam cycle system and the gas turbine not only improves the energy utilization efficiency, but also further recovers the waste heat through the recuperator, reducing the overall energy consumption.

[0050] The entire system is highly automated and intelligent through the low-pressure shaft motor, control system, sensor and energy management module. During the operation of the system, the energy management module adjusts the working parameters of each part in real time according to the flight conditions and engine status to ensure the stability of combustion and efficient use of energy. Through the coordinated control of the high-pressure and low-pressure turbines, the system can automatically optimize the output power under different working conditions, further improving the efficiency and reliability of the entire aviation turbine engine.

[0051] like Figure 3 As shown, the method for optimizing parameters of a steam continuous injection aviation turbine engine comprises:

[0052] Step S1: obtaining component characteristic parameters of a steam continuous injection aviation turbine engine and establishing a simulation model;

[0053] Step S2: According to the change in total efficiency of the continuous steam injection aviation turbine engine at the maximum water injection amount, determine the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure of the engine under the design point working condition.

[0054] Step S3: using the analysis module of the simulation model, according to the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure, determine the relationship between the total engine efficiency and the water injection amount under the design point working condition, and obtain the optimization of the total engine efficiency.

[0055] The method for optimizing parameters of a steam continuous injection aviation turbine engine of the present invention optimizes the performance of the engine through several steps, especially improving the overall efficiency at the maximum water injection amount. First, in step S1, obtaining the component characteristic parameters of the engine is a key link, mainly including the working characteristics of the turbine, compressor and other core components. Based on these data, a simulation model is established to simulate the influence of steam injection on the thermodynamic and aerodynamic processes inside the engine. The model can accurately reflect the effect of steam injection on the power output and efficiency of the engine.

[0056] Next, in step S2, the optimal low-pressure turbine outlet pressure and exhaust compressor outlet pressure are determined by adjusting the operating conditions of the engine at the maximum water injection amount. The optimization of these pressure parameters is crucial to the steam injection process, especially when maintaining high efficiency and stable working conditions, ensuring that the airflow inside the engine maintains appropriate flow characteristics and thermodynamic balance under steam injection.

[0057] Step S3 further analyzes the trend of the change of the engine's total efficiency under the design point condition with the change of the water injection amount through the analysis module of the simulation model. Through this analysis, it is possible to intuitively see how steam injection affects the efficiency, and by adjusting the water injection amount, find an optimal water injection amount that can maximize the total efficiency.

[0058] Ultimately, this optimization method can provide a complete efficiency optimization strategy that maximizes the positive effects of steam injection by properly regulating the amount of water injection, turbine and compressor pressures, while avoiding the efficiency drop caused by excessive water injection. This method not only improves the fuel economy of the engine, but also improves the overall performance.

[0059] The disclosed invention utilizes the analysis module of the simulation model, and by adjusting the outlet pressure of the low-pressure turbine and the outlet pressure of the exhaust compressor, determines the corresponding relationship between the amount of water sprayed in the steam continuous jet aviation turbine engine and the total efficiency of the gas turbine engine, determines the influence rule on the performance of the whole machine, and finally determines the optimal outlet pressure of the high and low pressure turbines, the optimal outlet pressure of the exhaust compressor and the optimal amount of water sprayed. That is, by giving the maximum amount of water sprayed, the optimal outlet pressure of the low-pressure turbine and the exhaust compressor is gradually determined, and then the optimal amount of water sprayed for the engine operation is determined by the two optimal outlet pressures, so as to obtain the optimal total efficiency of the engine. The steam continuous jet aviation turbine engine and the overall parameter design method disclosed by the present invention can improve the efficiency of the steam continuous jet aviation turbine engine by adding an exhaust compressor and designing the condenser outside the engine, more efficiently recover the waste heat of the fuel gas, and obtain the optimization of the overall parameters of the engine.

[0060] In this embodiment, a steam continuous injection aviation turbine engine and an overall parameter design method include:

[0061] Step S1: Obtaining component characteristic parameters of a steam continuous injection aviation turbine engine.

[0062] Specifically, the component characteristic diagrams of the high-pressure compressor, low-pressure compressor, high-pressure turbine and low-pressure turbine can be determined by three-dimensional computational fluid simulation or component characteristic experiments. Among them, the component characteristics of the steam continuous injection aviation turbine engine include: the pressure ratio and efficiency characteristics of the high-pressure compressor, the pressure ratio and efficiency characteristics of the low-pressure compressor, and the expansion ratio and efficiency characteristics of the high-pressure and low-pressure counter-rotating turbines.

[0063] Step S2: According to the change of the total efficiency of the continuous steam injection aviation turbine engine at the maximum water injection amount, the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure of the engine under the design point working condition are determined.

[0064] Among them, the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure of the engine under the design point conditions are determined separately, that is, the low-pressure turbine outlet pressure is given first, and then the optimal exhaust compressor outlet pressure is determined according to the change in the total efficiency of the continuous steam injection aviation turbine engine; then the above-mentioned optimal low-pressure turbine outlet pressure is re-given, and then the optimal exhaust compressor outlet pressure is determined according to the change in the total efficiency of the continuous steam injection aviation turbine engine.

[0065] When the steam continuous jet aviation turbine engine is working, the driving power of the exhaust compressor is extracted from the low-pressure shaft, using an axial flow compressor driven by an electric motor;

[0066] During implementation, the analysis module of the simulation model constructed in step S1 is used to change the low-pressure turbine outlet pressure and the exhaust compressor outlet pressure while ensuring the maximum water injection volume, so as to calculate the corresponding relationship between the low-pressure turbine outlet pressure and the exhaust compressor outlet pressure and the efficiency of the steam continuous injection aviation turbine engine under different combinations of low-pressure turbine outlet pressure and exhaust compressor outlet pressure.

[0067] Specifically, when the water injection amount of the steam continuous jet aviation turbine engine is a water-to-air ratio of 0.54, by giving the low-pressure turbine outlet pressure of 44.87 kPa, the exhaust compressor outlet pressure is calculated to change from 1 atmospheric static pressure to 2 ambient static pressures, and the changes in the total efficiency and other overall parameters of the steam continuous jet aviation turbine engine are obtained, and the optimal exhaust compressor outlet pressure of the steam continuous jet aviation turbine engine can be determined; then, by giving the optimal exhaust compressor outlet pressure and the optimal low-pressure turbine outlet pressure combination, the exhaust compressor outlet pressure is calculated to change from 13 kPa to 30 kPa, and the changes in the total efficiency and other overall parameters of the steam continuous jet aviation turbine engine are obtained, thereby determining the optimal exhaust compressor outlet pressure.

[0068] Figure 3 It shows that the total efficiency of the continuous steam injection aviation turbine engine has a global optimal value when the exhaust compressor outlet pressure changes from 1 atmospheric static pressure to 2 ambient static pressures. Considering all factors, the optimal exhaust compressor outlet pressure is 35kPa.

[0069] Figure 4It shows that the total efficiency of the engine decreases monotonically as the exhaust compressor outlet pressure changes from 13 kPa to 30 kPa. However, when the exhaust compressor outlet pressure is below 19 kPa, the fuel-air equivalence ratio of the combustion chamber exceeds 1, and considering the subsequent problem of excessive pressure ratio, the optimal exhaust compressor outlet pressure is determined to be 20 kPa.

[0070] Step S3: using the analysis module of the simulation model, according to the optimal low-pressure turbine outlet pressure and the optimal exhaust compressor outlet pressure, determine the relationship between the total engine efficiency and the water injection amount under the design point working condition, and obtain the optimization of the total efficiency.

[0071] Specifically, under the condition that the gas-air equivalence ratio is not greater than 1, given the optimal low-pressure turbine outlet pressure and exhaust compressor outlet pressure obtained in step S2, the overall parameters under the water injection amount with a water-vapor ratio of 0-0.54 are calculated. Figure 5 It shows that with the increase of water injection amount, the total efficiency of the engine increases significantly and monotonically. Compared with the condition without water injection, the total efficiency of the engine increases by 10.1% when the maximum water injection amount is used.

[0072] Figure 6 It shows that compared with conventional turbofan engines, the fuel consumption rate of the steam continuous injection aviation turbine engine proposed in the present invention is reduced, and as the water injection amount increases, the fuel consumption rate of the engine decreases monotonically. When the maximum water injection amount is reached, the fuel consumption rate of the steam continuous injection aviation turbine engine can be reduced by 27.8% compared with the conventional turbofan engine.

[0073] In summary, the disclosed invention proposes a steam continuous injection aviation turbine engine device, and optimizes the parameters such as the outlet pressure of the low-pressure turbine and the exhaust compressor through the energy management module of the simulation model, so as to obtain the efficiency optimization effect and overall parameters of the engine. That is, by giving a maximum water injection amount, the optimal outlet pressures of the low-pressure turbine and the exhaust compressor are gradually determined, and then the optimal water injection amount for the engine operation is determined through the two optimal outlet pressures. By adopting a steam continuous injection aviation turbine engine and an overall parameter design method disclosed in the present invention, by adding an exhaust compressor and designing the condenser outside the wing and the fuselage, the efficiency of the steam continuous injection aviation turbine engine can be improved, the waste heat of the fuel gas can be recovered more efficiently, the efficiency of the engine design point can be greatly improved, and the optimization of the overall parameters of the engine can be obtained.

[0074] It should be noted that the parameter method provided in the above embodiment is only illustrated by the division of the above functional modules. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device is divided into different functional modules to complete all or part of the above functions. In addition, the control method provided in the above embodiment belongs to the same concept, and its specific implementation process is detailed in the method embodiment, which will not be repeated here.

[0075] So far, the embodiments of the present disclosure have been described in detail in conjunction with the accompanying drawings. It should be noted that the implementation methods not shown or described in the drawings or the body of the specification are all forms known to ordinary technicians in the relevant technical field and are not described in detail. In addition, the above definitions of each element and method are not limited to the various specific structures, shapes or methods mentioned in the embodiments, and ordinary technicians in the field can simply change or replace them.

Claims

1. A steam continuous injection aviation turbine engine configuration and overall parameter design method, characterized in that: The following steps are involved: Establish a simulation model of a steam-injection continuous aviation turbine engine; Through the gas turbine engine simulation model, the corresponding relationship between the overall engine parameters and the water injection amount under different water injection amounts is obtained; The optimum water injection amount is obtained based on the corresponding relationship, and the outlet pressures of the low-pressure turbine and the exhaust compressor are controlled, thereby optimizing the operating performance of the engine.

2. The method for designing the configuration and overall parameters of a continuous steam injection aviation turbine engine according to claim 1, characterized in that: The simulation model includes: The high-pressure components, low-pressure components and heat exchange components of a steam continuous injection aviation turbine engine. The high-pressure components include a high-pressure turbine, a high-pressure compressor and a high-pressure shaft. The low-pressure components include a low-pressure turbine, a low-pressure compressor, a low-pressure shaft and a low-pressure shaft motor. The heat exchange components include an evaporator and a condenser.

3. The method for designing the configuration and overall parameters of a continuous steam injection aviation turbine engine according to claim 2, characterized in that: The energy analysis module calculates the energy flow of the engine through the first and second laws of thermodynamics. flow and irreversible losses, thereby optimizing the energy efficiency and efficiency.

4. The method for designing the configuration and overall parameters of a continuous steam injection aviation turbine engine according to claim 2, characterized in that: The condensed water first enters the evaporator and is heated into high-temperature steam. The steam is then sprayed into the combustion chamber to participate in the combustion, and is finally condensed and recovered into liquid water through the condenser, thus realizing water circulation.

5. The method for designing the configuration and overall parameters of a continuous steam injection aviation turbine engine according to claim 1, characterized in that: The condenser of the steam continuous injection aircraft turbine engine is arranged under the aircraft skin, using the aircraft skin for cooling and recycling condensed water to improve the circulation efficiency.

6. A steam continuous injection aviation turbine engine system, characterized in that: include: High-pressure components, including high-pressure turbine, high-pressure compressor and high-pressure shaft; Low-pressure components, including low-pressure turbine, low-pressure compressor, low-pressure shaft and low-pressure shaft motor; Heat exchange components, including evaporators and condensers.

7. The steam continuous injection aviation turbine engine system according to claim 1, characterized in that: The evaporator in the heat exchange component is used to heat the condensed water into high-temperature steam, which enters the combustion chamber and mixes with the fuel gas to improve the combustion efficiency. The condenser is used to condense the steam in the exhaust gas into liquid water to achieve water circulation.

8. The steam continuous injection aviation turbine engine system according to claim 1, characterized in that: The control module monitors the low-pressure turbine outlet pressure and the exhaust compressor outlet pressure in real time through sensors, and controls the water injection device according to the optimal water injection amount to optimize the engine operating efficiency.

9. The steam continuous injection aviation turbine engine system according to claim 1, characterized in that: It also includes an energy analysis module, which analyzes the energy flow of high-pressure components, low-pressure components and heat exchange components based on the first and second laws of thermodynamics to optimize the energy utilization of steam and gas.

10. The steam continuous injection aviation turbine engine system according to claim 1, characterized in that: The condenser is installed under the aircraft skin, and reduces the exhaust temperature by utilizing the cooling effect of the aircraft skin, and recovers condensed water for recirculation.

11. The steam continuous injection aviation turbine engine system according to claim 1, characterized in that: The conventional exhaust cooling system is replaced with one that uses condensed water to cool the high-temperature turbine. In addition, part of the condensed water is sprayed into the high-pressure compressor for intermediate cooling to reduce compression work.

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