CN113266468B - Method and device for hybrid electric propulsion of three-shaft gas turbine engine - Google Patents

Abstract

The present disclosure relates to the technical field of gas turbine engines, and discloses a hybrid electric propulsion method and device for a three-shaft gas turbine engine. The present disclosure uses a simulation model to determine the corresponding relationship between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine by adjusting the power of the gas generator motor, and then to determine the optimal reduced speed of the gas generator and the gas generator. Optimum power of the motor. The optimal reduced speed of the gas generator determined by the hybrid electric propulsion method of the three-shaft gas turbine engine of the present disclosure can improve the thermal efficiency of the gas turbine engine, break through the current hybrid electric propulsion technology energy-saving effect limited by the battery capacity, and greatly improve the hybrid electric propulsion technology. The power density of the electric propulsion system is reduced, the system cost is reduced, and the non-design point efficiency of the engine is improved while ensuring the balance of power supply and demand.

Description

Method and device for hybrid electric propulsion of three-shaft gas turbine engine

technical field

The present disclosure relates to the technical field of gas turbine engines, in particular to a hybrid electric propulsion method and device for a three-shaft gas turbine engine.

Background technique

Gas turbine engines have excellent performance and have a series of advantages such as high power-to-weight ratio, good acceleration, controllable emission pollution, and good fuel adaptability. They are widely used in ships, vehicles, aviation, gas transportation, thermal power generation and other fields. market prospects. However, gas turbine engines generally have the problem of reduced efficiency at non-design points. The root cause is that the common operating point of each component is highly coupled with the engine load. The aerodynamic and mechanical constraints between the components determine the operating point and output power of each component. correspond. As the load decreases, on the one hand, the operating point of the components deviates from the high-efficiency region, resulting in a decrease in the efficiency of the components; on the other hand, the total pressure ratio of the engine and the initial gas temperature decrease, resulting in a decrease in the efficiency of the Brayton cycle. Reduced component efficiency and engine cycle efficiency are the direct causes of engine off-design point performance degradation.

In order to improve the off-design point performance of gas turbine engines, hybrid electric propulsion technology has been vigorously developed. At present, the currently disclosed hybrid electric propulsion technology mainly adjusts the engine load actively through the power battery to avoid the low and medium load conditions of low engine efficiency, but does not directly solve the problem of performance deterioration of the engine under medium and low load. For scenarios with large power levels, excessive battery capacity is required, which has a large negative impact on the economy and power density of the power system.

SUMMARY OF THE INVENTION

The purpose of the present disclosure is to overcome the above technical deficiencies and provide a hybrid electric propulsion method for a three-shaft gas turbine engine, which realizes the decoupling of the operating point of each component and the engine load, thereby optimizing the non-design point efficiency of the engine.

In order to achieve the above technical purpose, the technical solution of the present disclosure provides a hybrid electric propulsion method for a three-shaft gas turbine engine, the three-shaft gas turbine engine includes a gas generator and a power turbine, and the gas generator includes a high-pressure part and a low-pressure part. , the high-pressure component has a high-pressure turbine, a high-pressure compressor, a high-pressure shaft and a high-pressure shaft motor that controls the rotational speed of the high-pressure shaft, and the low-pressure turbine has a low-pressure turbine, a low-pressure compressor, a low-pressure shaft and a low-pressure shaft motor that controls the rotational speed of the low-pressure shaft, so The hybrid electric propulsion method includes:

obtaining component characteristic parameters of the gas turbine engine;

establishing a simulation model of the gas turbine engine according to the component characteristic parameters, the simulation model including an energy analysis module;

Using the energy module of the simulation model, the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine is determined by adjusting the power of the gas generator motor, where the gas generator motor includes a high-pressure shaft The motor and/or the low-pressure shaft motor, the reduced rotational speed of the gas generator includes the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft;

According to the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine, the optimal reduced rotational speed of the gas generator and the optimal power of the gas generator motor are determined.

Further, the component characteristic parameters of the gas turbine engine include: pressure ratio and efficiency characteristics of the high-pressure compressor, pressure ratio and efficiency characteristics of the low-pressure compressor, expansion ratio and efficiency characteristics of the high-pressure turbine, expansion ratio and efficiency characteristics of the low pressure turbine, expansion ratio and efficiency characteristics of the power turbine.

流动以及不可逆损失情况。Further, the energy analysis module is configured to calculate the energy flow of the components of the gas turbine engine using the first and second laws of thermodynamics,

flow and irreversible losses.

Further, the hybrid electric propulsion means that when the gas turbine engine is working, the gas generator motor acts as a motor to provide input power to the high pressure shaft and/or the low pressure shaft, or the gas generator motor As a generator, the output power is extracted from the high pressure shaft and/or the low pressure shaft to actively adjust the reduced speed of the gas generator.

Further, according to the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine, determine the optimal reduced rotational speed of the gas generator and the optimal power of the gas generator motor, including:

Under the condition of ensuring that the gas turbine engine does not exceed the rated operating temperature, does not exceed the rated operating speed, and the surge margin is not less than the safe surge margin, the reduced speed of the gas generator corresponding to the optimal thermal efficiency is determined. is the optimal reduced speed of the gas generator; the motor power of the gas generator corresponding to the optimal thermal efficiency is determined as the optimal power

Further, the method also includes:

According to the optimal reduced rotational speed of the gas generator, the optimal power of the motor of the gas generator under different specific atmospheric environments is determined.

Further, the optimal power of the gas generator motor in the specific atmospheric environment needs to meet the following two conditions:

The thermal efficiency of the gas turbine engine is increased by greater than 1% at 30% rated load; and,

Under the specific atmospheric environment, it is satisfied that the gas turbine engine does not exceed the rated operating temperature, does not exceed the rated operating speed, and the surge margin is not lower than the safe surge margin.

The technical solution of the present disclosure also provides a three-shaft gas turbine engine hybrid electric propulsion device, the three-shaft gas turbine engine includes a gas generator and a power turbine, the gas generator includes a high-pressure part and a low-pressure part, the The high-pressure part has a high-pressure turbine, a high-pressure compressor, a high-pressure shaft, and a high-pressure shaft motor that controls the rotational speed of the 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 that controls the rotational speed of the low-pressure shaft. Propulsion controls include:

an acquisition module for acquiring component characteristic parameters of the gas turbine engine;

a modeling module for establishing a simulation model of the gas turbine engine according to the component characteristic parameters, the simulation model including an energy analysis module;

The first determination module is configured to use the energy module of the simulation model to determine the corresponding relationship between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine by adjusting the power of the gas generator motor, the The gas generator motor includes a high pressure shaft motor and/or the low pressure shaft motor, and the reduced rotational speed of the gas generator includes the reduced rotational speed of the high pressure shaft and the reduced rotational speed of the low pressure shaft;

The second determination module is configured to determine the optimal reduced rotational speed of the gas generator and the optimal power of the gas generator motor according to the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine.

Further, the hybrid electric propulsion control device further includes a third determination module for determining the optimal power of the motor of the gas generator under different specific atmospheric environments according to the optimal reduced rotational speed of the gas generator.

Compared with the prior art, the hybrid electric propulsion method of the three-shaft gas turbine engine of the present disclosure has at least one or a part of the following beneficial effects:

(1) The speed of the gas generator (high pressure shaft and low pressure shaft) is decoupled from the engine load. By adjusting the input power or output power of the gas generator motor, it can be ensured that the gas generator (high and low pressure shafts) under the condition that the output power of the gas turbine engine is constant. ) The speed and the common working point are adjusted within a certain range.

(2) The effectiveness of the hybrid electric propulsion scheme can be verified by simulation.

损失，有效缓解发动机中低负荷下的效率恶化问题。(3) The present disclosure can optimize the non-design point operating conditions, especially the gas turbine engine component efficiency and cycle thermal efficiency under medium and low loads, and reduce the reduction of various parts.

It can effectively alleviate the problem of efficiency deterioration under low and medium loads of the engine.

(4) The energy-saving effect of the present disclosure is not limited by the battery capacity, and under the condition of ensuring the balance of power supply and demand, the performance of the engine off-design point is improved, so it is suitable for high-power scenarios such as ships, thermal power generation, trunk line passenger aircraft, etc., effectively reducing hybrid electric propulsion Battery capacity in the system, improving system power density and economy.

Description of drawings

FIG. 1 is a schematic structural diagram of a three-shaft gas turbine engine in an embodiment of the disclosure;

FIG. 2 is a flowchart of a hybrid electric propulsion method for a three-shaft gas turbine engine according to an embodiment of the disclosure;

Figure 3 shows a component-level simulation model and energy analysis module of a triaxial gas turbine established in Simulink;

Figure 4 shows the energy analysis results of the hybrid electric propulsion method applied to a tri-shaft gas turbine in Figure 1 under 40% load condition, simulating the energy flow and irreversible loss of each component;

损失情况。可以看到，在此工况下，本方案有效降低了燃气轮机排气损失，热效率提高2％；Fig. 5 shows the efficiency and each part of the gas turbine before and after using the hybrid electric propulsion method proposed by the present invention under the 40% load condition of a three-shaft gas turbine in Fig. 1

loss situation. It can be seen that under this working condition, this scheme effectively reduces the exhaust gas loss of the gas turbine and increases the thermal efficiency by 2%;

FIG. 6 is a schematic structural diagram of a three-shaft gas turbine engine hybrid electric propulsion device of the disclosure.

Detailed ways

In order to make the objectives, technical solutions and advantages of the present disclosure more clear, the present disclosure will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present disclosure, but not to limit the present disclosure.

Gas turbine engines include gas turbines and aero-engines, split-shaft gas turbines and turboshaft engines generally include gas generators and power turbines, and gas generators include combustors, compressors, and compressor turbines. In operation, the compressor draws air into the interior of the gas turbine engine and compresses it. After that, the compressed air and fuel will be mixed and combusted in the combustion chamber, and then the high-temperature and high-pressure gas generated will drive the turbine blades to rotate. The turbine drives the compressor to rotate. Therefore, the output power of the gas turbine engine and the speed of the compressor are highly coupled, and the aerodynamic and mechanical constraints between the components determine the one-to-one correspondence between the operating points of each component and the output power. The present disclosure realizes the decoupling between the operating point of each component and the engine load through the hybrid electric propulsion method, thereby optimizing the non-design point efficiency of the engine.

FIG. 1 is a schematic structural diagram of a three-shaft gas turbine engine in an embodiment. As shown in FIG. 1 , the gas turbine engine includes a gas generator and a power turbine, and the gas generator includes a combustion chamber, a high-pressure compressor , low pressure compressor, high pressure turbine and low pressure turbine.

The high pressure part has a high pressure compressor, a high pressure turbine, a high pressure shaft and a high pressure shaft motor that controls the rotational speed of the high pressure shaft, and the low pressure part has a low pressure compressor, a low pressure turbine, a low pressure shaft and a low pressure shaft motor that controls the rotational speed of the low pressure shaft. Specifically, the high-pressure turbine drives the high-pressure compressor through the high-pressure shaft, and the low-pressure turbine drives the low-pressure compressor through the low-pressure shaft. A high-voltage shaft motor is installed on the high-voltage shaft, and the rotation speed of the high-voltage shaft can be controlled by controlling the input power or output power of the high-voltage shaft motor. A low-voltage shaft motor is installed on the low-voltage shaft, and the low-voltage shaft can be controlled by controlling the input power or output power of the low-voltage shaft motor. Rotating speed.

FIG. 2 is a flowchart of a hybrid electric propulsion method based on a three-shaft gas turbine engine according to an embodiment of the present disclosure.

As shown in Figure 2, a hybrid electric propulsion method for a three-shaft gas turbine engine includes:

Step S1: obtaining component characteristic parameters of the gas turbine engine;

Step S2: establishing a simulation model of the gas turbine engine according to the component characteristic parameters, where the simulation model includes an energy analysis module;

Step S3: Using the energy module of the simulation model, by adjusting the power of the gas generator motor, determine the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine, and the gas generator motor It includes a high-pressure shaft motor and/or the low-pressure shaft motor, and the reduced rotational speed of the gas generator includes the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft;

Step S4: Determine the optimal reduced rotational speed of the gas generator and the optimal power of the gas generator motor according to the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine.

The present disclosure utilizes the energy module of the simulation model to determine the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine by adjusting the power of the gas generator motor, to determine its influence on the performance of the whole machine, and then to determine the gas generator. The optimal reduced speed and the optimal power of the gas generator motor. That is, by inputting or extracting optimal power to the high-pressure shaft and/or the low-pressure shaft, actively adjusting the rotational speed of the high-pressure shaft and/or the low-pressure shaft, optimizing the reduced rotational speed of the high-pressure shaft and the low-pressure shaft, and realizing the solution between the rotational speed and the load of the gas generator of the gas turbine engine. coupled. The optimal reduced rotational speed of the gas generator determined by the hybrid electric propulsion method of the three-shaft gas turbine engine of the present disclosure can improve the thermal efficiency of the gas turbine engine, break through the current hybrid electric propulsion technology's energy saving effect limited by the battery capacity, and greatly improve the hybrid electric propulsion technology. The power density of the propulsion system is reduced, the system cost is reduced, and the non-design point efficiency of the engine is improved while ensuring the balance of power supply and demand.

In some embodiments, a hybrid electric propulsion method for a three-shaft gas turbine engine, comprising:

Step S1: Acquire component characteristic parameters of the gas turbine engine.

Specifically, the component characteristic maps of the high-pressure compressor, the low-pressure compressor, the high-pressure turbine, the low-pressure turbine and the power turbine can be determined through three-dimensional computational fluid simulation or component characteristic experiments. The component characteristic parameters of the gas turbine engine can be determined by means of the component characteristic map. The component characteristic parameters of the gas turbine engine may include: pressure ratio and efficiency characteristics of the high-pressure compressor, pressure ratio and efficiency characteristics of the low-pressure compressor, expansion ratio and efficiency characteristics of the high-pressure turbine, expansion ratio and efficiency characteristics of the low pressure turbine, expansion ratio and efficiency characteristics of the power turbine.

Step S2: establishing a simulation model of the gas turbine engine according to the component characteristic parameters, where the simulation model includes an energy analysis module.

流动以及不可逆损失情况。燃气涡轮发动机的部件可以是高压压气机、低压压气机、高压涡轮、低压涡轮和动力涡轮。图3为在Simulink中建立的某一三轴式燃气轮机部件级仿真模型和能量分析模块。Specifically, based on the component characteristics in step 1, a component-level simulation model is established, and an energy analysis module is added to the simulation model. The energy analysis module is configured to calculate the energy flow of the components of the gas turbine engine using the first and second laws of thermodynamics,

flow and irreversible losses. Components of a gas turbine engine may be a high pressure compressor, a low pressure compressor, a high pressure turbine, a low pressure turbine, and a power turbine. Figure 3 shows the component-level simulation model and energy analysis module of a triaxial gas turbine established in Simulink.

Step S3: Using the energy module of the simulation model, by adjusting the power of the gas generator motor, determine the corresponding relationship between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine. The reduced rotational speed includes the reduced rotational speed of the high pressure shaft and the reduced rotational speed of the low pressure shaft.

Wherein, the gas generator motor includes a high pressure shaft motor and/or the low pressure shaft motor, and the reduced rotational speed of the gas generator includes the reduced rotational speed of the high pressure shaft and/or the reduced rotational speed of the low pressure shaft.

Hybrid electric propulsion means that, when the gas turbine engine is working, the electric motor acts as an electric motor to provide input power to the high-pressure shaft and/or the low-pressure shaft, or the electric motor acts as a generator to provide input power to the high-pressure shaft and/or the low-pressure shaft. The low pressure shaft extracts power to actively adjust the reduced rotational speed of the gas generator, so as to realize decoupling control of the rotational speed of the high pressure shaft and the rotational speed of the low pressure shaft and the engine load.

流动以及不可逆损失情况，进而确定燃气发生器折合转速与所述燃气涡轮发动机热效率的对应关系。During implementation, the energy analysis module of the simulation model constructed in step S3 is used to adjust the input/output power of the high-pressure shaft and/or the low-pressure shaft to change the high-pressure shaft reduced rotational speed NH _cor and the low-pressure shaft reduced rotational speed NL _cor , thereby calculating different high-pressure shafts. The energy flow of the components of the gas _{turbine engine} , the

flow and irreversible losses, and then determine the corresponding relationship between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine.

流动以及不可逆损失情况。通过调整不同燃气发生器电机功率，计算不同的高压轴折合转速NH_cor和低压轴折合转速NL_cor的组合情况，可以确定在燃气涡轮发动机40％负荷工况下燃气发生器折合转速与所述燃气涡轮发动机热效率的对应关系。Specifically, as shown in FIG. 4 , taking the gas turbine engine at 40% load as an example, the energy flow of the components of the gas turbine engine is calculated under the specific combination of the high-pressure shaft reduced speed NH _cor and the low-pressure shaft reduced speed NL _cor ,

flow and irreversible losses. By adjusting the motor power of different gas generators and calculating the combination of different high-pressure shaft reduced speed NH _cor and low-pressure shaft reduced speed NL _cor , it can be determined that the gas generator reduced speed and the gas turbine engine under 40% load condition of the gas turbine engine Correspondence of the thermal efficiency of a turbine engine.

In some embodiments, the gas turbine engine may also be calculated as 10% load, 20% load, 30% load, 40% load, 50% load, 60% load, 70% load, 80% load, 90% load, respectively and 100% load operation to determine the corresponding relationship between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine under different loads.

Step S4: Determine the optimal reduced rotational speed of the gas generator and the optimal power of the gas generator motor according to the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine.

Specifically, under the condition that the gas turbine engine does not exceed the rated operating temperature, does not exceed the rated operating speed, and the surge margin is not less than the safe surge margin, the optimal thermal efficiency corresponds to the gas generator. The reduced rotational speed is determined as the optimal reduced rotational speed of the gas generator; the motor power of the gas generator corresponding to the optimal thermal efficiency is determined as the optimal power.

During implementation, the target gas generator reduced speed can be achieved by adjusting the power of the gas generator motor, so as to determine the optimal power of the gas generator motor.

Figure 5 shows the energy analysis results of the three-shaft gas turbine hybrid electric propulsion scheme at 40% load. As shown in Figure 5, the left picture is the situation before optimization, and the right picture is the situation after optimization. It can be seen that different high-pressure shaft reduced speed and/or low-pressure shaft reduced speed will lead to different thermal efficiencies of the engine. In the figure on the right, by controlling the high-pressure shaft and low-pressure shaft of the gas generator at the optimal reduced speed, the gas generator motor is adjusted to the optimal power, and the thermal efficiency of the engine is increased by 2%.

In other embodiments, the optimal reduced rotational speed of the gas generator and the optimal power of the motor of the gas generator under different loads can also be determined through the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine under different loads , so that both the high-pressure shaft and the low-pressure shaft are at the optimal reduced speed under different loads, and the optimal reduced speed can ensure that the engine is not over-temperature, over-rev, and sufficient surge margin. The irreversible loss of the turbine engine system under different loads reduces the fuel consumption rate at the non-design point.

The above simulation calculation is carried out in a standard atmospheric environment, the engine load is the converted parameter under standard operating conditions, and the control law optimization results are the corresponding optimal NH _cor and NL _cor values under different loads. When the gas turbine is running, the optimal closed-loop control of NH _cor and NL _cor under different reduced loads is realized by the gas generator motor.

In some embodiments, after determining the optimal power of the gas turbine engine gas generator motor, the hybrid electric propulsion method further includes:

Step S5: Determine the optimal power of the motor of the gas generator under different specific atmospheric environments according to the optimal reduced rotational speed of the gas generator. The atmospheric environment includes, but is not limited to, the total temperature and total pressure of the gas turbine engine inlet.

The optimal power of the gas generator motor in a specific atmospheric environment must meet the following two conditions:

the thermal efficiency of the gas turbine engine is improved by greater than 1% at 30% rated load; and

Under the condition of atmospheric pressure, it is satisfied that the gas turbine engine does not exceed the rated operating temperature, does not exceed the rated operating speed, and the surge margin is not lower than the safe surge margin.

During implementation, input the motor power of the high pressure shaft and/or the low pressure shaft to verify whether the reduced speed of the gas generator meets the optimal reduced speed, the efficiency improvement effect of the gas turbine under this reduced power, whether it is over-temperature and over-rotation, and the surge margin whether the requirements are met.

Since the influence of motor power on the engine performance and the reduced speed of the gas generator is different for different atmospheric temperatures and atmospheric pressures, the reduced power of different atmospheric temperatures and atmospheric pressures can be converted according to the following formula:

Converted power

Among them, p is the output power, and T _in and P _in are the total temperature and total pressure of the gas turbine engine inlet.

FIG. 6 is a schematic structural diagram of a hybrid electric propulsion control device for a three-shaft gas turbine engine. Referring to FIG. 6 , the device includes: an acquisition module 201 , a modeling module 202 , a first determination module 203 , and a second determination module 203 . module 204.

an acquisition module for acquiring component characteristic parameters of the gas turbine engine;

a modeling module for establishing a simulation model of the gas turbine engine according to the component characteristic parameters, the simulation model including an energy analysis module;

The first determination module uses the energy module of the simulation model to determine the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine by adjusting the power of the gas generator motor. The generator motor includes a high-pressure shaft motor and/or the low-pressure shaft motor, and the reduced rotational speed of the gas generator includes the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft;

The second determination module determines the optimal reduced rotational speed of the gas generator and the optimal power of the gas generator motor according to the corresponding relationship between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine.

Further, the hybrid electric propulsion control device also includes:

The third determination module is configured to determine the optimal power of the motor of the gas generator under different specific atmospheric environments according to the optimal reduced rotational speed of the gas generator.

It should be noted that, the hybrid electric propulsion control device provided by the above embodiments only takes the division of the above functional modules as an example for electric propulsion control. 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 hybrid electric propulsion method for the three-shaft gas turbine engine provided by the above embodiments belongs to the same concept, and the specific implementation process is detailed in the method embodiment, which will not be repeated here.

So far, the embodiments of the present disclosure have been described in detail with reference to the accompanying drawings. It should be noted that, in the accompanying drawings or the text of the description, the implementations that are not shown or described are in the form known to those of ordinary skill in the technical field, and are not described in detail. In addition, the above definitions of various elements and methods are not limited to various specific structures, shapes or manners mentioned in the embodiments, and those of ordinary skill in the art can simply modify or replace them.

Based on the above description, those skilled in the art should have a clear understanding of the hybrid electric propulsion solution of the gas turbine engine based on the decoupling of the rotational speed of the gas generator of the present disclosure.

损失的对应关系，确定其对整机性能的影响规律，确定所述燃气涡轮发动机燃气发生器电机的最优功率。即通过向高压轴和/或低压轴输入或提取最优功率，主动调节高压轴和/或低压轴的转速，优化高压轴和低压轴的折合转速，实现燃气涡轮发动机燃气发生器转速与负荷解耦。本公开的三轴式燃气涡轮发动机的混合电推进方法能够突破目前混合电推进技术节能效果受电池容量的限制，大大提高混合电推进系统功率密度、降低系统成本，在保证功率供需平衡的情况下提高发动机非设计点效率。In summary, the present disclosure determines the power of the gas generator motor and the various components of the engine through simulation.

The corresponding relationship of the loss is determined, the influence law on the performance of the whole machine is determined, and the optimal power of the gas generator motor of the gas turbine engine is determined. That is, by inputting or extracting optimal power to the high-pressure shaft and/or the low-pressure shaft, actively adjusting the rotational speed of the high-pressure shaft and/or the low-pressure shaft, optimizing the reduced rotational speed of the high-pressure shaft and the low-pressure shaft, and realizing the solution between the rotational speed and the load of the gas generator of the gas turbine engine. coupled. The hybrid electric propulsion method of the three-shaft gas turbine engine disclosed in the present disclosure can break through the current hybrid electric propulsion technology's energy saving effect limited by the battery capacity, greatly improve the power density of the hybrid electric propulsion system, reduce the system cost, and ensure the balance of power supply and demand under the condition of ensuring the balance of power supply and demand. Improve engine off-design point efficiency.

Claims (7)

1. A hybrid electric propulsion method for a three-shaft gas turbine engine, the three-shaft gas turbine engine including a gas generator and a power turbine, the gas generator including a high pressure part having a high pressure turbine, a high pressure compressor, a high pressure shaft, and a high pressure shaft motor for controlling a rotation speed of the high pressure shaft, and a low pressure part having a low pressure turbine, a low pressure compressor, a low pressure shaft, and a low pressure shaft motor for controlling a rotation speed of the low pressure shaft, the hybrid electric propulsion method comprising:

obtaining component characteristic parameters of the gas turbine engine;

establishing a simulation model of the gas turbine engine based on the component characteristic parameters, the simulation model including an energy analysis module;

determining a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor comprising a high pressure shaft motor and/or a low pressure shaft motor, the reduced rotational speed of the gas generator comprising a reduced rotational speed of the high pressure shaft and a reduced rotational speed of the low pressure shaft, using the energy module of the simulation model;

determining an optimal reduced rotation speed of the gas generator and an optimal power of a motor of the gas generator according to a corresponding relation between the reduced rotation speed of the gas generator and the thermal efficiency of the gas turbine engine;

and determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator.

2. The hybrid electric propulsion method of claim 1, wherein the gas turbine engine component characteristic parameters include: pressure ratio and efficiency characteristics of the high pressure compressor, pressure ratio and efficiency characteristics of the low pressure compressor, expansion ratio and efficiency characteristics of the high pressure turbine, expansion ratio and efficiency characteristics of the low pressure turbine, and expansion ratio and efficiency characteristics of the power turbine.

3. The hybrid electric propulsion method of claim 1, wherein an energy analysis module is configured to calculate an energy flow, a thrust force, and a thrust force of a component of the gas turbine engine using a first law and a second law of thermodynamics,

Flow and irreversible loss conditions.

4. The hybrid electric propulsion method of claim 1, wherein the hybrid electric propulsion is such that, when the gas turbine engine is operating, the gas generator motor acts as a motor to provide input power to the high pressure shaft and/or the low pressure shaft, or the gas generator motor acts as a generator to extract output power from the high pressure shaft and/or the low pressure shaft to actively adjust the folded rotation speed of the gas generator.

5. The hybrid electric propulsion method of any one of claims 1 to 4, wherein determining the optimum reduced speed of the gas generator and the optimum power of the gas generator motor based on the correspondence between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine comprises:

determining the reduced rotating speed of the gas generator corresponding to the optimal thermal efficiency as the optimal reduced rotating speed of the gas generator under the condition that the gas turbine engine is guaranteed not to exceed the rated working temperature, not to exceed the rated working rotating speed and the surge margin is not lower than the safety surge margin; and determining the power of the generator motor corresponding to the optimal thermal efficiency as the optimal power.

6. Hybrid electric propulsion method according to any of claims 1 to 4, characterized in that the optimal power of the gas generator motor in said specific atmospheric environment is such as to satisfy the following two conditions:

when the gas turbine engine is at 30% rated load, the thermal efficiency of the gas turbine engine is improved by more than 1%; and

and under the specific atmospheric environment, the gas turbine engine does not exceed the rated working temperature, does not exceed the rated working rotating speed, and has a surge margin not lower than a safety surge margin.

7. A hybrid electric propulsion device of a three-shaft gas turbine engine, characterized in that the three-shaft gas turbine engine comprises a gas generator and a power turbine, the gas generator comprises a high-pressure part and a low-pressure part, the high-pressure part comprises a high-pressure turbine, a high-pressure compressor, a high-pressure shaft and a high-pressure shaft motor for controlling the rotation speed of the high-pressure shaft, the low-pressure part comprises a low-pressure turbine, a low-pressure compressor, a low-pressure shaft and a low-pressure shaft motor for controlling the rotation speed of the low-pressure shaft, and the hybrid electric propulsion control device comprises:

an acquisition module for acquiring component characteristic parameters of the gas turbine engine;

a modeling module for building a simulation model of the gas turbine engine based on the component property parameters, the simulation model including an energy analysis module;

a first determining module, configured to determine a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor including a high-pressure shaft motor and/or a low-pressure shaft motor, the reduced rotational speed of the gas generator including the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft, using the energy module of the simulation model;

a second determining module for determining an optimal reduced rotational speed of the gas generator and an optimal power of the gas generator motor according to a correspondence between the reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine;

and the third determining module is used for determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator.

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