Anti-surge method and system for aviation hybrid electric engine

Abstract

The invention relates to the technical field of aero-engines, and discloses an anti-surge method and system for an aero-hybrid electric engine, and the method comprises the steps: setting a value interval of the maximum allowable acceleration rate according to the structural integrity limitation and acceleration performance requirements of the engine; compressor performance data are obtained through a compressor component performance test, and a linear prediction model changing along with time is established based on the performance data of adjacent moments; predicting an engine operation state in a future preset time period according to the linear prediction model acceleration rate; and calculating a surge margin according to the predicted operation state, and when the predicted surge margin is lower than a preset safety threshold, dynamically adjusting the maximum allowable acceleration rate. According to different severe environments and working conditions, the variable acceleration rate limit value is set, the surge margin is strictly controlled, surge can be actively restrained, the surge risk is greatly reduced, full-process closed-loop anti-surge control is formed, the method is suitable for complex working conditions and multi-scene application, an engine is effectively protected, and flight safety is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and particularly relates to an anti-surge method and system for an aero hybrid-electric engine. Background Art

[0002] Compared with traditional aeroengines, hybrid-electric engines have the characteristic of fast acceleration, but this poses higher requirements for anti-surge design. Surge in aero hybrid-electric engines generally occurs during fast acceleration, especially during intake distortion and fast acceleration. As the acceleration rate increases instantaneously, the surge margin decreases instantaneously, approaching the surge line, and the higher the surge risk. The harm of surge is extremely great, which will cause the engine to operate unstably, and even cause serious consequences such as damage to the compressor and engine shutdown.

[0003] To avoid surge, the numerical control system of traditional aeroengines will set the "maximum allowable acceleration rate" limit value during the acceleration process. By restricting the acceleration rate, the rising speed of the engine state is reduced to avoid the surge risk brought by instantaneous fast acceleration. Figure 1 is the characteristic diagram of the compressor component, Figure 1 marking the engine acceleration path under normal conditions. As Figure 1 can be seen, during the process of the engine accelerating from A to B, the acceleration rate gradually increases until it is gradually reduced after receiving the maximum allowable acceleration rate limit at point C. At this time, the surge margin at point C is the lowest. Due to the limitation of the acceleration rate, the engine has completed fast acceleration quickly, safely and reliably.

[0004] The determination of the maximum allowable acceleration rate is often affected by multiple factors. For example, to ensure structural integrity, the highest acceleration rate allowed by the gas generator rotor, and the lowest acceleration rate required to achieve the specified acceleration time. To take into account the above situations, the traditional maximum allowable acceleration rate is often set as a fixed value, and this value is often relatively high. A relatively high acceleration rate limit value can be applied to most aircraft usage scenarios. However, the usage environment of aero hybrid-electric engines is variable, and they often have to be used in high-temperature, low-temperature, and high-altitude environments within the entire envelope, and withstand harsh working conditions such as temperature and pressure distortion. In such harsh situations, the surge margin before the acceleration of the hybrid-electric engine is already low. If fast acceleration operation is still carried out, the surge margin will be reduced to the surge boundary line in advance before reaching the "relatively high" maximum allowable acceleration rate limit, resulting in surge. Therefore, the traditional fixed maximum allowable acceleration rate has certain risks when dealing with extreme working conditions.

[0005] Figure 2 is the characteristic diagram of the compressor component, Figure 2 showing the acceleration process path under temperature distortion conditions. And Figure 1Similarly, when accelerating from A to B, due to the influence of temperature distortion, the converted speed N of the gas generator speed n becomes smaller, and point A moves to the upper left to A*, with a lower surge margin. Since the maximum allowable acceleration rate is a fixed value, during the fast acceleration process, there is a lack of effective acceleration rate limitation, and the engine enters the surge boundary, resulting in surge. Summary of the Invention

[0006] In view of this, the present invention provides an anti-surge method and system for an aviation hybrid-electric engine to solve the problem that the maximum allowable acceleration rate in the prior art can only meet the conventional working conditions. For severe working conditions such as intake distortion and fast acceleration, the surge margin will be reduced to the surge boundary line in advance before reaching the maximum allowable acceleration rate limit, resulting in surge deficiencies.

[0007] In a first aspect, the present invention provides an anti-surge method for an aviation hybrid-electric engine, including:

[0008] Setting a value range of the maximum allowable acceleration rate according to the engine structural integrity limit and acceleration performance requirements;

[0009] Obtaining compressor performance data through compressor component performance tests, and establishing a linear prediction model that changes with time based on the performance data at adjacent times;

[0010] Predicting the engine operating state within a preset future time period according to the linear prediction model;

[0011] Calculating the surge margin according to the predicted operating state;

[0012] When the predicted surge margin is lower than the preset safety threshold, dynamically adjusting the maximum allowable acceleration rate.

[0013] The anti-surge method for an aviation hybrid-electric engine provided by the embodiments of the present invention can balance the engine structural safety and acceleration performance, can capture the trend of working condition changes in real time, improve the prediction accuracy and robustness, can early warn of the surge risk, and can actively suppress the occurrence of surge by multi-dimensionally evaluating the surge risk and dynamically adjusting the maximum allowable acceleration rate, reduce manual operations while taking into account occasional working conditions and normal performance, form a full-process closed-loop anti-surge control, adapt to complex working conditions and multi-scene applications, effectively protect the engine, and ensure flight safety.

[0014] In an optional implementation manner, the value range of the maximum allowable acceleration rate is: between the structural limit acceleration rate and the minimum acceleration rate, and is dynamically adjusted according to a preset margin coefficient.

[0015] In the embodiments of the present invention, the upper limit is the structural limit acceleration rate, which avoids component damage due to overload caused by excessive acceleration, such as preventing the rotor blades from breaking due to excessive centrifugal force. The lower limit is the minimum acceleration rate, which ensures that the engine has the basic acceleration ability under various operating conditions and meets the power requirements for normal flight of the aircraft. By presetting the dynamic adjustment range of the margin coefficient, the safety and efficiency can be flexibly balanced according to different flight stages (such as takeoff, cruise) or engine states, optimizing the operating performance.

[0016] In an alternative embodiment, the formula for calculating the maximum allowable acceleration rate is:

[0017] V = F + (E - F) × k,

[0018] where V is the maximum allowable acceleration rate, E is the structural limit acceleration rate, F is the minimum acceleration rate, and k is the preset margin coefficient.

[0019] In the embodiments of the present invention, the structural limit acceleration rate E, the minimum acceleration rate F, and the margin coefficient k are combined through the formula to accurately calculate the maximum allowable acceleration rate V. On the premise of ensuring the structural safety of the engine, the acceleration performance requirements are maximally met. The formula has a simple form and is convenient for integration and implementation in the engine control system. By adjusting the value of k in real time, the engine can quickly respond to changes in operating conditions and ensure safe and efficient operation under various conditions.

[0020] In an alternative embodiment, the compressor performance data includes the common operating line, the surge margin S corresponding to different gas generator conversion speeds M , the flow rate M at the surge point D , and the pressure ratio π at the surge point D ; the linear prediction model that changes with time established based on the performance data at adjacent times includes:

[0021] Obtain the performance data at the current time t2 and the previous time t1;

[0022] Construct a speed-time function n = f(t) according to the speed parameters (nt1, nt2);

[0023] Construct a flow rate-time function M = f(t) according to the air flow rate parameters (Mt1, Mt2);

[0024] Construct a pressure ratio-time function π = f(t) according to the pressure ratio parameters (πt1, πt2);

[0025] Obtain the acceleration rate at the current time t2 by taking the derivative of the speed function n = f(t).

[0026] Embodiments of the present invention cover data such as the common working line, surge margin, surge point flow rate, and pressure ratio at the surge point, comprehensively characterizing the aerodynamic characteristics of the compressor at different rotational speeds, providing a complete benchmark for surge risk assessment; constructing a linear function based on the rotational speed, flow rate, and pressure ratio parameters at adjacent moments, extrapolating the future state through the two-point equation, with small computational amount and suitable for real-time operation of the controller, meeting the millisecond-level response requirement for surge warning; obtaining the acceleration rate at time t by differentiating the rotational speed function, and combining with the time functions of flow rate and pressure ratio to achieve dynamic correlation analysis of "rotational speed - flow rate - pressure ratio", accurately capturing the change trend of the compressor performance.

[0027] In an alternative embodiment, the calculation of the surge margin is based on the air flow rate M at the prediction moment tx and the corresponding surge point flow rate M Dtx , or the compressor pressure ratio π tx and the corresponding surge point pressure ratio π Dtx The calculation formula is:

[0028]

[0029] Embodiments of the present invention calculate the surge margin based on two parameters, air flow rate or pressure ratio, evaluate the operating state of the compressor from two dimensions of fluid mechanics and thermodynamics, avoid misjudgment by a single parameter, and can dynamically match the surge boundary of the engine at different rotational speeds and loads by combining the parameters at the prediction moment.

[0030] In an alternative embodiment, when the predicted surge margin is lower than the preset safety threshold, the dynamic adjustment of the maximum allowable acceleration rate includes:

[0031] When the predicted surge margin ≤ 5%, adjust the maximum allowable acceleration rate to the current acceleration rate value; after the acceleration process ends, restore the initial preset value of the maximum allowable acceleration rate.

[0032] In embodiments of the present invention, when the surge margin ≤ 5%, immediately lock the maximum allowable acceleration rate to the current acceleration rate, reduce the intake air fluctuation of the compressor by reducing the acceleration rate, quickly move the operating point away from the surge boundary, reduce the probability of surge occurrence, and automatically restore the initial acceleration rate after the acceleration process ends, avoiding long-term restrictions from affecting the power performance. For occasional severe working conditions such as intake air distortion and rapid acceleration, through the "real-time limit + automatic recovery" mechanism, it can not only cope with sudden risks but also does not affect the normal operation efficiency, with strong adaptability.

[0033] In a second aspect, the present invention provides an anti-surge system for an aviation hybrid-electric engine, the system includes: a maximum allowable acceleration rate setting module, configured to set the value range of the maximum allowable acceleration rate according to the engine structural integrity limit and acceleration performance requirements;

[0034] A prediction model construction module, configured to obtain compressor performance data through compressor component performance tests, and establish a linear prediction model that changes over time based on the performance data at adjacent times;

[0035] An operating state prediction module, configured to predict the operating state of the engine within a preset future time period according to the linear prediction model;

[0036] A surge margin calculation module, configured to calculate the surge margin according to the predicted operating state;

[0037] A dynamic control module, configured to dynamically adjust the maximum allowable acceleration rate when the predicted surge margin is lower than a preset safety threshold.

[0038] In a third aspect, the present invention provides a computer device, including: a memory and a processor, which are communicatively connected to each other. The memory stores computer instructions, and the processor executes the computer instructions to execute the aviation hybrid-electric engine anti-surge method according to the first aspect or any corresponding embodiment thereof.

[0039] In a fourth aspect, the present invention provides a computer-readable storage medium, on which computer instructions are stored. The computer instructions are used to cause a computer to execute the aviation hybrid-electric engine anti-surge method according to the first aspect or any corresponding embodiment thereof.

[0040] In a fifth aspect, the present invention provides a computer program product, including computer instructions, which are used to cause a computer to execute the aviation hybrid-electric engine anti-surge method according to the first aspect or any corresponding embodiment thereof. Description of the Drawings

[0041] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0042] Figure 1 It is a characteristic diagram of the compressor component for the engine acceleration path under normal conditions;

[0043] Figure 2 It is a characteristic diagram of the compressor component for the acceleration process path under temperature distortion conditions;

[0044] Figure 3 A flowchart of the aviation hybrid-electric engine anti-surge method according to an embodiment of the present invention;

[0045] Figure 4It is a schematic diagram of the compressor characteristics according to an embodiment of the present invention;

[0046] Figure 5 It is a structural block diagram of an anti-surge system for an aviation hybrid-electric engine according to an embodiment of the present invention;

[0047] [[ID=1...]]Figure 6 It is a schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. Specific embodiments

[0048] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0049] In the prior art, the maximum allowable acceleration rate during the acceleration process in the numerical control system of an aeroengine is set to a relatively high fixed value. Although it can meet the normal operating conditions, for harsh conditions such as intake distortion and rapid acceleration, the surge margin will be reduced to the surge boundary line in advance before reaching the maximum allowable acceleration rate limit, resulting in surge. It is equivalent to in this case, the "maximum allowable acceleration rate" that should have a limiting effect becomes ineffective.

[0050] Therefore, in this embodiment, an anti-surge method for an aviation hybrid-electric engine is provided. According to the real-time measured parameters, it senses the changes in the engine intake conditions and operating conditions and sets a variable acceleration rate. This method can cope with the situation where the compressor surge margin is reduced under harsh environments such as intake distortion, and can effectively reduce the surge risk and ensure the stable and safe operation of the engine. Figure 3 It is a flowchart of an anti-surge method for an aviation hybrid-electric engine according to an embodiment of the present invention. As Figure 3 shown, this process includes the following steps:

[0051] Step S101, set the value range of the maximum allowable acceleration rate according to the engine structure integrity limit and the acceleration performance requirements.

[0052] Specifically, the aviation hybrid-electric engine in the embodiment of the present invention is composed of components such as an intake duct, a compressor, a combustion chamber, a gas turbine, and a power turbine. The main measured parameters of the engine are: the engine inlet temperature T t1 , the engine inlet pressure P t1 , the engine inlet air flow rate M, the gas generator rotor speed n, the total pressure P at the compressor outlet t3 , and the calculation formula for the compressor pressure ratio π is: P t3 / P t1; The calculation formula for the converted speed N of the gas generator rotor is as follows:

[0053] In the embodiment of the present invention, according to the acceleration rate limit E allowed by the structural integrity of the gas generator rotor and the minimum acceleration rate F allowed to ensure acceleration performance, the value range of the maximum allowed acceleration rate V is F < V < E, and V = F + (E - F) × k, where k is a margin coefficient. For example, k is taken as 0.8. The margin coefficient k can be flexibly adjusted according to factors such as flight conditions (such as takeoff, cruise, landing) and engine status (such as new or old degree), so that V can adapt to different scenarios, avoiding both the structural risks brought by too high acceleration rate and preventing too low acceleration rate from affecting power output.

[0054] Step S102: Obtain the compressor performance data through the compressor component performance test, and establish a linear prediction model that changes with time based on the performance data at adjacent times.

[0055] Specifically, in the embodiment of the present invention, the compressor characteristic map is obtained by performing a performance test on the compressor component. Figure 4 It is a schematic diagram of the compressor characteristics, including the common working line, the surge margin SM corresponding to different converted speeds N of the gas generator, the flow rate M at the surge point D , and the pressure ratio π at the surge point D and other reference data, comprehensively characterizing the aerodynamic characteristics of the compressor at different speeds and providing a complete reference for surge risk assessment.

[0056] Furthermore, a linear function is constructed based on the rotational speed, flow rate, and pressure ratio parameters at adjacent times (t1, t2), and the future state is extrapolated through the two-point equation. The calculation amount is small and suitable for real-time operation of the controller, meeting the millisecond-level response requirement of surge warning.

[0057] Specifically, the linear prediction model of the rotor speed is constructed through the two-point equation. Before solving the equation in the embodiment of the present invention, the parameter measurement period T is obtained. T is generally 0.024 - 0.1 s, and it varies for different engines.

[0058] Assume that the previous moment is t1, and the parameters measured at this moment are (nt1, Mt1, πt1), and the current moment is t2 (t2 = t1 + T), and the parameters measured at this moment are (nt2, Mt2, πt2). According to the three groups of data of (t1, nt1) and (t2, nt2), (t1, Mt1) and (t2, Mt2), (t1, πt1) and (t2, πt2), three groups of linear equations are respectively calculated:

[0059] n = f(t) (1)

[0060] M = f(t) (2)

[0061] π = f(t) (3)

[0062] For example, according to the two-point form linear equation method using two points (t1, nt1) and (t2, nt2), the equation n = f(t) can be obtained, that is:

[0063]

[0064] Derive according to the equation n = f(t) to calculate the acceleration rate ndot2 at time t2.

[0065] Step S103, predict the operating state of the engine within a preset future time period according to the linear prediction model.

[0066] Specifically, for example, if tx is the time at x measurement cycles after t1, substituting tx (tx = t2 + (x - 2)T) into equations (1), (2), and (3), the values of n, M, and π at time tx can be obtained, assumed to be (ntx, Mtx, πtx) respectively. Since surge occurs very rapidly, in order to avoid surge, the risk of surge should be detected as early as possible and discovered and processed in a short time. Therefore, x should be determined according to the length of the measurement cycle T. However, regardless of the value of the measurement cycle T, it should be ensured that tx - t2 ≤ 0.2s, that is, the risk of surge should be predicted 0.2s in advance. x is the maximum value obtained from tx - t2 ≤ 0.2s. Example: If the measurement cycle T is 0.1s, then x is 4; if the measurement cycle is 0.05s, then x is 6.

[0067] Step S104, calculate the surge margin according to the predicted operating state.

[0068] In the embodiment of the present invention, according to n tx and the measured inlet temperature T of the hybrid electric engine t1 , N can be obtained from the formula in the preconditions tx :

[0069]

[0070] According to the above main measurement parameters of the engine, substituting Ntx, the flow rate MDtx at the surge point and the pressure ratio πDtx at the surge point under the condition of Ntx can be obtained. Combining Mtx and πtx measured at time tx, the surge margin at time tx can be obtained:

[0071]

[0072] In the embodiment of the present invention, the surge margin is calculated based on two parameters, namely air flow or pressure ratio, and the operating state of the compressor is evaluated from two dimensions of fluid mechanics and thermodynamics to avoid misjudgment by a single parameter. For example, when the flow rate is normal but the pressure ratio is abnormal, the potential surge risk can still be identified. By combining the parameter calculation at the prediction moment, the surge boundary under different engine speeds and loads can be dynamically matched. For example, at high engine speeds, the pressure ratio margin is mainly considered, and at low engine speeds, the flow rate margin is the core index. The calculation formula is directly related to the compressor characteristic diagram (such as the common operating line and surge boundary), which is convenient for obtaining reference data in advance through bench tests, and the calculation logic is simple, suitable for real-time operation of the embedded controller.

[0073] Step S104: When the predicted surge margin is lower than the preset safety threshold, dynamically adjust the maximum allowable acceleration rate.

[0074] Specifically, if the surge margin at time tx is greater than 5%, it is considered that the current engine speed is safe, the preset maximum allowable acceleration rate is feasible, and the engine continues to execute the fast acceleration program. If the surge margin at time tx is in the range of 4% - 5%, it is considered that the setting of the maximum allowable acceleration rate is unreasonable. If the engine continues to accelerate at the current acceleration rate, the probability of future surge risk is high, and it is necessary to automatically readjust the maximum allowable acceleration rate. The adjustment countermeasures are as follows:

[0075] 1) The numerical control system locks the acceleration rate ndot2 at time t2, and reduces the preset maximum allowable acceleration rate (F+(E - F)*0.8) to ndot2 as the latest maximum allowable acceleration rate.

[0076] 2) Since severe conditions such as intake distortion and fast acceleration are occasional and have a very short duration, maintaining ndot2 as the maximum allowable acceleration rate for a long time will limit the acceleration performance and maneuverability of the engine. Therefore, after the current acceleration process ends, the lock on ndot2 should be released and restored to the preset maximum allowable acceleration rate.

[0077] In the embodiment of the present invention, when the surge margin ≤ 5%, the maximum allowable acceleration rate is immediately locked to the current acceleration rate. By reducing the acceleration rate, the intake air fluctuation of the compressor is reduced, and the operating point quickly moves away from the surge boundary, which can reduce the probability of surge occurrence. After the acceleration process ends, the initial acceleration rate is automatically restored to avoid long-term limitation affecting the power performance. For occasional severe working conditions such as intake distortion and fast acceleration, through the "real-time limitation + automatic restoration" mechanism, it can not only cope with sudden risks but also not affect the normal operation efficiency, has strong adaptability, can handle complex operations, effectively protect the engine, and ensure flight safety.

[0078] In this embodiment, an anti-surge system for an aviation hybrid-electric engine is also provided. This system is used to implement the above-mentioned embodiments and preferred implementation manners, and those that have been described will not be repeated here. As used hereinafter, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the systems described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware is also possible and contemplated.

[0079] This embodiment provides an anti-surge system for an aviation hybrid-electric engine. As Figure 5 shown, it includes:

[0080] A maximum allowable acceleration rate setting module 501, which is used to set the value range of the maximum allowable acceleration rate according to the engine structure integrity limit and acceleration performance requirements;

[0081] A prediction model construction module 502, which is used to obtain compressor performance data through compressor component performance tests, and establish a linear prediction model that changes with time based on the performance data at adjacent times;

[0082] An operating state prediction module 503, which is used to predict the engine operating state within a preset time period in the future according to the linear prediction model;

[0083] A surge margin calculation module 504, which is used to calculate the surge margin according to the predicted operating state; [[ID=-19]]

[0084] A dynamic control module 505, which is used to dynamically adjust the maximum allowable acceleration rate when the predicted surge margin is lower than a preset safety threshold.

[0085] In some alternative implementation manners, the value range of the maximum allowable acceleration rate is: between the structural limit acceleration rate and the minimum acceleration rate, and it is dynamically adjusted according to a preset margin coefficient.

[0086] In some alternative implementation manners, the calculation formula for the maximum allowable acceleration rate is:

[0087] V = F + (E - F) × k,

[0088] where V is the maximum allowable acceleration rate, E is the structural limit acceleration rate, F is the minimum acceleration rate, and k is the preset margin coefficient.

[0089] In some alternative implementation manners, the compressor performance data includes the common operating line, the surge margin S corresponding to different gas generator conversion speeds M , the flow rate M at the surge point D , and the pressure ratio π at the surge point D ; Based on the performance data at adjacent times, establishing a linear prediction model that changes with time includes:

[0090] Obtain the performance data at the current moment t2 and the previous moment t1;

[0091] Construct a rotational speed - time function n = f(t) according to the rotational speed parameters (nt1, nt2);

[0092] Construct a flow - time function M = f(t) according to the air flow parameters (Mt1, Mt2);

[0093] Construct a pressure ratio - time function π = f(t) according to the pressure ratio parameters (πt1, πt2);

[0094] Obtain the acceleration rate at the current moment t2 by taking the derivative of the rotational speed function n = f(t).

[0095] In some alternative embodiments, the calculation of the surge margin is based on the air flow M at the prediction moment tx and the corresponding surge point flow M Dtx , or the compressor pressure ratio π tx and the corresponding surge point pressure ratio π Dtx and is calculated by the formula:

[0096]

[0097] In some alternative embodiments, the dynamic control module 505 includes:

[0098] A dynamic adjustment unit, configured to adjust the maximum allowable acceleration rate to the current acceleration rate value when the predicted surge margin ≤ 5%;

[0099] An acceleration - after recovery control unit, which restores the initial preset value of the maximum allowable acceleration rate after the acceleration process ends.

[0100] The further function descriptions of the above - mentioned various modules and units are the same as those in the corresponding above - mentioned embodiments, and will not be elaborated here.

[0101] The anti - surge system of the aviation hybrid - electric engine in this embodiment is presented in the form of functional units. Here, the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and a memory that execute one or more software or fixed programs, and / or other devices that can provide the above - mentioned functions.

[0102] This embodiment of the present invention also provides a computer device having the above - mentioned Figure 5 shown anti - surge system of the aviation hybrid - electric engine.

[0103] Please refer to Figure 6 , Figure 6 which is a schematic structural diagram of the computer device provided by an alternative embodiment of the present invention, as shown in Figure 6As shown, the computer device includes: one or more processors 10, a memory 20, and interfaces for connecting the components, including a high-speed interface and a low-speed interface. Each component communicates with each other using different buses and can be installed on a common motherboard or installed in other ways as needed. The processor can process instructions executed within the computer device, including instructions stored in the memory or on the memory to display graphical information of the GUI on an external input / output device (such as a display device coupled to the interface). In some alternative embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories. Similarly, multiple computer devices can be connected, and each device provides some necessary operations (such as an array of servers, a set of blade servers, or a multi-processor system). Figure 6 Taking one processor 10 as an example in

[0104] The processor 10 can be a central processing unit, a network processor, or a combination thereof. Among them, the processor 10 can further include a hardware chip. The above hardware chip can be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The above programmable logic device can be a complex programmable logic device, a field programmable gate array, a generic array logic, or any combination thereof.

[0105] Among them, the memory 20 stores instructions executable by at least one processor 10, so that at least one processor 10 executes the method shown in the above embodiments.

[0106] The memory 20 can include a program storage area and a data storage area. Among them, the program storage area can store an operating system and application programs required for at least one function; the data storage area can store data created according to the use of the computer device, etc. In addition, the memory 20 can include a high-speed random access memory, and can also include a non-transitory memory, such as at least one disk storage device, a flash memory device, or other non-transitory solid-state storage devices. In some alternative embodiments, the memory 20 can optionally include a memory remotely set relative to the processor 10, and these remote memories can be connected to the computer device through a network. Examples of the above network include but are not limited to the Internet, an enterprise intranet, a local area network, a mobile communication network, and combinations thereof.

[0107] The memory 20 can include a volatile memory, such as a random access memory; the memory can also include a non-volatile memory, such as a flash memory, a hard disk, or a solid-state drive; the memory 20 can also include a combination of the above types of memories.

[0108] The computer device further includes a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0109] Embodiments of the present invention also provide a computer-readable storage medium. The method according to the embodiments of the present invention can be implemented in hardware, firmware, or be implemented as computer code that can be recorded on a storage medium, or be implemented as computer code that is originally stored in a remote storage medium or a non-transitory machine-readable storage medium and downloaded through a network and will be stored in a local storage medium, so that the method described herein can be stored as such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only memory, a random access memory, a flash memory, a hard disk, or a solid-state drive, etc.; further, the storage medium can also include a combination of the above-mentioned types of memories. It can be understood that a computer, a processor, a microprocessor controller, or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by the computer, the processor, or the hardware, the method shown in the above embodiments is implemented.

[0110] A part of the present invention can be applied as a computer program product, such as computer program instructions. When executed by a computer, through the operation of the computer, the methods and / or technical solutions according to the present invention can be invoked or provided. Those skilled in the art should understand that the forms in which computer program instructions exist in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways in which computer program instructions are executed by a computer include, but are not limited to: the computer directly executes the instructions, or the computer compiles the instructions and then executes the corresponding compiled program, or the computer reads and executes the instructions, or the computer reads and installs the instructions and then executes the corresponding installed program. Herein, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible to the computer.

[0111] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A method for preventing surge in an aviation hybrid-electric engine, characterized in that, Including: Set the value range of the maximum allowable acceleration rate according to the engine structure integrity limit and acceleration performance requirements; Obtain the compressor performance data through the compressor component performance test, and establish a linear prediction model that changes with time based on the performance data at adjacent times; Predict the engine operating state within a preset future time period according to the linear prediction model; Calculate the surge margin according to the predicted operating state; When the predicted surge margin is lower than the preset safety threshold, dynamically adjust the maximum allowable acceleration rate.

2. The method according to claim 1, characterized in that The value range of the maximum allowable acceleration rate is: between the structural limit acceleration rate and the minimum acceleration rate, and is dynamically adjusted according to a preset margin coefficient.

3. The method according to claim 2, wherein The calculation formula for the maximum allowable acceleration rate is: V = F + (E - F) × k, where V is the maximum allowable acceleration rate, E is the structural limit acceleration rate, F is the minimum acceleration rate, and k is the preset margin coefficient.

4. The method according to claim 1, characterized in that, The compressor performance data includes the common operating line, the surge margin S corresponding to different converted speeds of the gas generator M , the flow rate M at the surge point D , the pressure ratio π at the surge point D ; Establishing a linear prediction model that changes with time based on the performance data at adjacent times, including: Obtain the performance data at the current time t2 and the previous time t1; Construct a speed-time function n = f(t) according to the speed parameters (nt1, nt2); Construct a flow-time function M = f(t) according to the air flow parameters (Mt1, Mt2); Construct a pressure ratio-time function π = f(t) according to the pressure ratio parameters (πt1, πt2); Obtain the acceleration rate at the current time t2 by taking the derivative of the speed function n = f(t).

5. The method according to claim 4, wherein The calculation of the surge margin is based on the air flow rate M at the prediction moment tx and the corresponding surge point flow rate M Dtx , or the compressor pressure ratio π tx and the corresponding surge point pressure ratio π Dtx which is calculated by the formula:

6. The method according to claim 1, characterized in that, When the predicted surge margin is lower than the preset safety threshold, the dynamic adjustment of the maximum allowable acceleration rate includes: When the predicted surge margin ≤ 5%, adjust the maximum allowable acceleration rate to the current acceleration rate value; after the acceleration process ends, restore the initial preset value of the maximum allowable acceleration rate.

7. An anti-surge system for an aviation hybrid electric engine, characterized in that, Including: A maximum allowable acceleration rate setting module for setting the value range of the maximum allowable acceleration rate according to the engine structure integrity limit and acceleration performance requirements; A prediction model construction module for obtaining the compressor performance data through the compressor component performance test and establishing a linear prediction model that changes with time based on the performance data at adjacent times; An operating state prediction module for predicting the engine operating state within a preset future time period according to the linear prediction model; A surge margin calculation module for calculating the surge margin according to the predicted operating state; A dynamic control module for dynamically adjusting the maximum allowable acceleration rate when the predicted surge margin is lower than the preset safety threshold.

8. A computer device, characterized in that, Including: A memory and a processor, which are communicatively connected to each other. The memory stores computer instructions, and the processor executes the computer instructions to execute the anti-surge method for an aviation hybrid electric engine according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, Computer instructions are stored on the computer-readable storage medium, and the computer instructions are used to cause a computer to execute the anti-surge method for an aviation hybrid electric engine according to any one of claims 1 to 6.

10. A computer program product, characterized in that, Including computer instructions, which are used to cause a computer to execute the anti-surge method for an aviation hybrid electric engine according to any one of claims 1 to 6.

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