Dynamic control method, device and equipment for angle of adjustable guide vane of gas compressor

Abstract

The invention relates to the technical field of engines, and discloses a dynamic control method, device and equipment for the angle of an adjustable guide vane of a gas compressor, and the method comprises the steps that when it is detected that an anti-icing valve is opened, the initial anti-icing air entraining amount is obtained, and the anti-icing air entraining amount is continuously obtained; determining a first angle offset based on the initial anti-icing air entrainment amount and the current anti-icing air entrainment amount; surge margin verification is carried out based on a surge margin compensation model, and a second angle offset is obtained; determining a target angle offset based on the first angle offset and the second angle offset; and controlling the angle of the adjustable guide vane of the gas compressor to adjust the target angle offset. According to the method, the target angle offset is obtained from the first angle offset based on the anti-icing air entraining amount and the second angle offset based on the surge margin, the anti-icing requirement and the surge safety are both considered, and accurate dynamic control over the adjustable guide vane of the gas compressor is achieved based on the target angle offset. The power loss caused when the anti-icing valve is opened is effectively compensated, and the power requirement of the helicopter is met.

Description

Technical Field

[0001] The present invention relates to the field of engine technology, and in particular to a method, device and equipment for dynamically controlling the angle of adjustable guide vanes of a compressor. Background Art

[0002] When a turboshaft engine is flying in a low-temperature environment with visible moisture (such as clouds, precipitation, and fog), the anti-icing valve must be actively opened to prevent ice from forming on the air inlet and compressor inlet guide vanes. This process usually draws hot air from the axial compressor outlet to the air inlet and compressor guide vanes, which causes air flow loss at the axial compressor outlet, reducing the gas entering the combustion chamber and turbine to perform work, and thus causing engine power loss, which is generally 3% to 10%. Therefore, how to improve the power utilization efficiency of the turboshaft engine after the anti-icing valve is opened and minimize the power loss caused by anti-icing bleed air to meet the use requirements of helicopters has become a technical problem that needs to be solved urgently.

[0003] The standard guide vane control law is difficult to solve the above problem. Whether the anti-ice valve is open or closed, this standard guide vane control law calculates the converted gas generator speed based on the engine inlet temperature and the gas generator speed. The converted speed is then linearly interpolated to determine a unique guide vane angle, with one guide vane angle corresponding to each converted gas generator speed. This fixed guide vane angle maintains the compressor at its optimal operating point, ensuring the engine output power under different operating conditions to match the helicopter's required power. However, when the anti-ice valve is open, hot air is drawn from the compressor to prevent ice, reducing the amount of air available for turbine work. At this time, the standard guide vane control law still calculates the guide vane angle using conventional methods, failing to increase the compressor inlet air flow. Consequently, it cannot effectively compensate for the power loss caused by anti-ice bleed air, making it difficult to meet the helicopter's power requirements. Summary of the Invention

[0004] In view of this, the present invention provides a method, device and equipment for dynamically controlling the adjustable guide vane angle of a compressor to solve the problem that the existing guide vane control law cannot effectively compensate for power loss and is difficult to meet the power requirements of a helicopter.

[0005] In a first aspect, the present invention provides a method for dynamically controlling the angle of an adjustable guide vane of a compressor, the method comprising:

[0006] When the anti-icing valve is detected to be open, the initial anti-icing air flow rate is obtained and the anti-icing air flow rate is continuously obtained;

[0007] determining a first angle offset based on an initial anti-icing air bleed amount and a current anti-icing air bleed amount;

[0008] Performing surge margin verification based on a surge margin compensation model to obtain a second angle offset;

[0009] determining a target angular offset based on the first angular offset and the second angular offset;

[0010] Control the angle of the compressor's adjustable guide vanes to adjust the target angle offset.

[0011] The present invention can timely grasp the working status of the engine anti-icing system by real-time monitoring of the anti-icing valve status and the change of the bleed air volume, thereby realizing dynamic control of the angle of the adjustable guide vane of the compressor. By comparing the initial and current anti-icing bleed air volumes, the first angle offset is determined based on the change of the bleed air volume, and the second angle offset is derived using the surge margin compensation model, so as to obtain the target angle offset from the first angle offset based on the anti-icing bleed air volume and the second angle offset based on the surge margin, fully taking into account the anti-icing requirements and surge safety, maximizing power compensation within a safe range, and finally realizing precise dynamic control of the adjustable guide vanes of the compressor based on the target angle offset, thereby increasing the air flow at the compressor inlet, effectively compensating for the power loss caused by the opening of the anti-icing valve, significantly improving the power output stability and economic efficiency of the engine in high-altitude and low-temperature environments, and meeting the power requirements of the helicopter at the same time.

[0012] In an optional embodiment, determining the first angle offset based on the initial anti-icing air bleed amount and the current anti-icing air bleed amount includes:

[0013] calculating a first difference between the current anti-icing bleed air amount and the initial anti-icing bleed air amount;

[0014] Calculating a quotient of the first difference divided by a preset judgment value;

[0015] The product of the quotient and the preset offset is used as the first angle offset.

[0016] The present invention dynamically tracks the change of the anti-icing air bleed volume, thereby determining the first angle offset based on the change of the air bleed volume. Compared with the standard guide vane control law in the related art, the present invention helps to compensate for power loss.

[0017] In an optional embodiment, performing surge margin verification based on the surge margin compensation model to obtain the second angle offset includes:

[0018] Obtain target surge margin gain, guide vane angle influence coefficient, standard surge margin, and minimum allowable surge margin of the engine;

[0019] Using a surge margin compensation model, calculating a sum of a target surge margin gain and a standard surge margin, and calculating a second difference between a minimum allowable surge margin of the engine and the sum;

[0020] A quotient of the second difference divided by the guide vane angle influence coefficient is calculated as the second angle offset.

[0021] The present invention converts the safety requirement of the surge margin into a specific limit value of the guide vane angle to ensure that the engine still maintains the surge margin safety after the guide vane angle is adjusted.

[0022] In an optional embodiment, determining a target angle offset based on the first angle offset and the second angle offset includes:

[0023] When the first angle offset is greater than the second angle offset, determining the second angle offset as the target angle offset;

[0024] When the second angular offset is greater than the first angular offset, the first angular offset is determined as the target angular offset.

[0025] The present invention uses the smaller value of the two angular offsets as the target angular offset, thereby maximizing the compensation for the power loss caused by the anti-icing bleed air while ensuring the safety of the engine.

[0026] In an optional implementation, before obtaining the target surge margin gain, the method further includes:

[0027] Construct multiple operating conditions based on simulated atmospheric conditions, engine operating status and anti-icing air volume;

[0028] Under each operating condition, the engine is tested with the anti-icing valve open and closed, and the corresponding compressor parameters are collected.

[0029] Based on the compressor parameters corresponding to when the anti-icing valve is opened and when the anti-icing valve is closed, a surge margin change of the operating condition is calculated as a surge margin gain of the operating condition;

[0030] An operating condition corresponding to the current anti-icing bleed air volume, the current atmospheric environment conditions, and the current engine operating state is determined from all operating conditions, and a surge margin gain of the operating condition is used as a target surge margin gain.

[0031] The present invention constructs multiple operating conditions and collects compressor parameters when the anti-icing valve is opened and closed under each operating condition, thereby determining the surge margin gain for each operating condition, ensuring that the surge margin gain matches the actual operating condition in real time, and improving the accuracy of subsequent safety verification.

[0032] In an optional embodiment, before obtaining the guide vane angle influence coefficient, the method further includes:

[0033] Controlling the angle of the compressor's adjustable guide vanes to change according to a preset step size, and testing the compressor performance parameters corresponding to each compressor's adjustable guide vane angle;

[0034] Based on the compressor performance parameters, calculate the surge margin corresponding to the angle of each compressor's adjustable guide vane;

[0035] Based on the fitting of the angle of each compressor adjustable guide vane and its corresponding surge margin, a fitting function relationship is obtained;

[0036] The slope of the fitting function relationship is determined as the guide vane angle influence coefficient.

[0037] The present invention determines the surge margin corresponding to each guide vane angle and performs fitting to quantify the impact of guide vane angle changes on the surge margin, which helps to improve the accuracy of subsequent safety verification.

[0038] In an optional embodiment, the method further includes:

[0039] Calculate the product of the target angle offset and the anti-ice flag, which is used to indicate whether the anti-ice valve is open or closed;

[0040] The sum of the product and the standard adjustable guide vane angle is taken as the anti-icing optimized adjustable guide vane angle.

[0041] The present invention realizes dynamic control of the adjustable guide vanes by determining the anti-icing optimized adjustable guide vane angle.

[0042] In a second aspect, the present invention provides a compressor adjustable guide vane angle dynamic control device, the device comprising:

[0043] An acquisition module is used to detect the opening of the anti-icing valve, obtain the initial anti-icing air flow rate and continuously obtain the anti-icing air flow rate;

[0044] A first determining module is configured to determine a first angle offset based on an initial anti-icing air bleed amount and a current anti-icing air bleed amount;

[0045] A verification module, configured to perform surge margin verification based on a surge margin compensation model to obtain a second angle offset;

[0046] a second determining module, configured to determine a target angular offset based on the first angular offset and the second angular offset;

[0047] The control module is used to control the angle of the adjustable guide vanes of the compressor to adjust the target angle offset.

[0048] In a third aspect, the present invention provides a computer device comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the method for dynamic control of the adjustable guide vane angle of the compressor according to the first aspect or any corresponding embodiment thereof by executing the computer instructions.

[0049] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the method for dynamic control of the adjustable guide vane angle of a compressor according to the first aspect or any corresponding embodiment thereof. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0051] Figure 1 is a flow chart of a method for dynamically controlling an adjustable guide vane angle of a compressor according to an embodiment of the present invention;

[0052] Figure 2 2 is a block diagram of a dynamic control device for an adjustable guide vane angle of a compressor according to an embodiment of the present invention;

[0053] Figure 3 Schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0054] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0055] The standard guide vane control law cannot increase the air flow at the compressor inlet, cannot effectively compensate for the power loss caused by anti-icing bleed air, and is difficult to meet the power requirements of the helicopter. The present invention obtains a target angle offset from a first angle offset based on the anti-icing bleed air amount and a second angle offset based on the surge margin, fully taking into account the anti-icing requirements and surge safety, maximizing power compensation within a safe range, and finally achieving precise dynamic control of the compressor adjustable guide vanes based on the target angle offset. This increases the air flow at the compressor inlet, effectively compensates for the power loss caused by the opening of the anti-icing valve, significantly improves the power output stability and economic efficiency of the engine in high-altitude and low-temperature environments, and simultaneously meets the power requirements of the helicopter.

[0056] According to an embodiment of the present invention, an embodiment of a method for dynamically controlling the angle of adjustable guide vanes of a compressor is provided. It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a set of computer executable instructions, and although a logical order is shown in the flowchart, in some cases, the steps shown or described can be executed in an order different from that shown here.

[0057] In this embodiment, a method for dynamically controlling the angle of adjustable guide vanes of a compressor is provided. Figure 1 FIG. 1 is a flow chart of a method for dynamically controlling an adjustable guide vane angle of a compressor according to an embodiment of the present invention. Figure 1 As shown, the process includes the following steps:

[0058] Step S101: Detecting the opening of the anti-icing valve, obtaining the initial anti-icing air flow and continuously obtaining the anti-icing air flow. Specifically, the helicopter is equipped with an ice detector. When the ambient temperature is between -20°C and 0°C, the ice detector will sound an alarm. If there is also supercooled water in the air (liquid water content ≤ 1g / m 3 ), the anti-ice valve automatically opens. Optionally, if the ice detector fails or the pilot visually determines that anti-ice is necessary, the anti-ice valve can be opened manually. The controller automatically detects whether the anti-ice valve is open or closed. When the anti-ice valve is open, it obtains the initial anti-ice bleed air volume at that time and continuously collects anti-ice bleed air volume while the anti-ice valve is open.

[0059] Step S102 determines a first angle offset based on the initial anti-icing bleed air volume and the current anti-icing bleed air volume. Specifically, fluctuations in the anti-icing bleed air volume directly lead to dynamic changes in engine power loss. However, the standard guide vane control principle employed in related technologies fails to increase compressor inlet air flow as the bleed air volume changes, rendering it ineffective in compensating for power loss. Therefore, embodiments of the present invention dynamically track changes in the anti-icing bleed air volume, directly linking the guide vane angle offset to the degree of power loss. This fundamentally increases air flow to compensate for work gas loss.

[0060] Step S103: Surge margin verification is performed based on the surge margin compensation model to obtain a second angle offset. Specifically, the surge margin compensation model quantitatively analyzes changes in compressor operating conditions. Widening the compressor's adjustable guide vane angle may reduce the surge margin. Therefore, the surge margin compensation effect of anti-icing bleed air on the surge margin must be considered. The second angle offset is calculated using the surge margin compensation model to ensure that after the guide vane angle is adjusted, the surge margin still meets the safety threshold, allowing the engine to maintain stable operation while compensating for power, without the risk of stall or surge.

[0061] Step S104 determines a target angle offset based on the first angle offset and the second angle offset. Specifically, to achieve a dynamic balance between power compensation requirements and a safety margin, the target angle offset is determined from the first angle offset calculated based on the anti-icing air flow and the second angle offset calculated based on the surge margin compensation model to maximize power compensation within a safe range.

[0062] Step S105 controls the angle of the compressor's adjustable guide vanes to adjust the target angle offset. Specifically, based on the determined target angle offset, the controller outputs a guide vane angle control command, driving the compressor's adjustable guide vanes to adjust according to the target angle offset. By precisely adjusting the compressor throat area, the gas generator air flow is effectively increased to compensate for power losses while ensuring safe engine operation, thereby meeting the helicopter's power requirements.

[0063] The present invention can timely grasp the working status of the engine anti-icing system by real-time monitoring of the anti-icing valve status and the change of the bleed air volume, thereby realizing dynamic control of the angle of the adjustable guide vane of the compressor. By comparing the initial and current anti-icing bleed air volumes, the first angle offset is determined based on the change of the bleed air volume, and the second angle offset is derived using the surge margin compensation model, so as to obtain the target angle offset from the first angle offset based on the anti-icing bleed air volume and the second angle offset based on the surge margin, fully taking into account the anti-icing requirements and surge safety, maximizing power compensation within a safe range, and finally realizing precise dynamic control of the adjustable guide vanes of the compressor based on the target angle offset, thereby increasing the air flow at the compressor inlet, effectively compensating for the power loss caused by the opening of the anti-icing valve, significantly improving the power output stability and economic efficiency of the engine in high-altitude and low-temperature environments, and meeting the power requirements of the helicopter at the same time.

[0064] In this embodiment, a method for dynamically controlling the angle of an adjustable guide vane of a compressor is provided. The method specifically includes the following steps:

[0065] Step S201: Detecting the opening of the anti-icing valve, obtaining the initial anti-icing air flow rate and continuously obtaining the anti-icing air flow rate. Figure 1 Step S101 of the illustrated embodiment will not be described in detail here.

[0066] Step S202 : determining a first angle offset based on the initial anti-icing air flow rate and the current anti-icing air flow rate.

[0067] Specifically, the above step S202 includes:

[0068] Step S2021: Calculate a first difference between the current anti-icing air flow rate and the initial anti-icing air flow rate.

[0069] Step S2022: Calculate the quotient of the first difference divided by the preset judgment value.

[0070] Step S2023: multiplying the quotient by the preset offset value to obtain the first angle offset value.

[0071] Specifically, after the anti-icing valve is opened, the anti-icing air flow rate changes dynamically with the working conditions. The first difference between the current anti-icing air flow rate and the initial anti-icing air flow rate is calculated. There is a preset functional relationship between the anti-icing air flow rate and the guide vane offset. For example, the anti-icing air flow rate increases by a preset judgment value ΔW. b (ΔW b The range of values ​​is 10% to 20%), the guide vane offset is increased by a preset offset Δβ (the range of Δβ is -0.2° to -0.3°), and the first difference represents the change in the initial anti-icing air flow. By dividing the change by the preset judgment value and then multiplying it by the preset offset, the first angle offset can be obtained. From the above ΔW b The value range of Δβ and Δβ indicates that the value range of the first angle offset is -2° to -5°.

[0072] In some optional embodiments, assuming that the preset judgment amount is 10% and the preset offset is -0.2°, that is, for every 10% increase in the anti-icing air flow, the guide vane offset increases by -0.2°. If the initial anti-icing air flow is 100 g / s and the current anti-icing air flow is 120 g / s, then the first angle offset can be obtained through the above step S202:

[0073] Step S203 constructs various operating conditions based on simulated atmospheric conditions, engine operating states, and anti-icing air volumes. Specifically, the simulated atmospheric conditions include varying atmospheric temperatures, pressures, and humidity. Engine operating states include idling, 50% maximum continuous, 75% maximum continuous, maximum continuous, intermediate, maximum, and emergency. By combining these simulated atmospheric conditions, engine operating states, and varying anti-icing air volumes, the operating conditions that may occur during actual engine operation are constructed.

[0074] In step S204, under each operating condition, the engine operating conditions are tested with the anti-icing valve open and closed, and corresponding compressor parameters are collected. Specifically, under each operating condition, compressor parameters such as compressor inlet flow rate, pressure ratio, outlet pressure, efficiency, and airflow angle are tested with the anti-icing valve open and closed.

[0075] In step S205, based on the compressor parameters corresponding to the open and closed anti-icing valves, a surge margin change is calculated for the operating condition, serving as the surge margin gain for the operating condition. Specifically, the surge margins for the two conditions are calculated, and the difference between the two is the surge margin change for the operating condition, i.e., the surge margin gain.

[0076] Step S206 determines, from among all operating conditions, an operating condition corresponding to the current anti-icing bleed air volume, the current atmospheric environmental conditions, and the current engine operating state, and uses the surge margin gain for that operating condition as a target surge margin gain. Specifically, based on the current atmospheric environmental conditions, the current engine operating state, and the current anti-icing bleed air volume, an identical or similar operating condition is selected from the aforementioned multiple operating conditions, and the surge margin gain for that operating condition is used as the current target surge margin gain. This ensures that the surge margin gain matches the actual operating condition in real time, thereby improving the accuracy of subsequent safety verification.

[0077] Step S207 controls the angle of the compressor's adjustable guide vanes to vary according to a preset step size, and tests the compressor performance parameters corresponding to each adjustable guide vane angle. Specifically, the angle of the compressor's adjustable guide vanes is controlled to vary according to a preset step size (e.g., 0.2°), and compressor performance parameters, including flow rate, pressure ratio, efficiency, and outlet pressure, are tested at each angle to establish a mapping relationship between the guide vane angle and compressor performance.

[0078] Step S208: Calculate the surge margin corresponding to the angle of each adjustable guide vane of the compressor based on the compressor performance parameters. Specifically, calculate the surge margin corresponding to each guide vane angle based on the collected compressor performance parameters.

[0079] Step S209 is to perform a fitting function relationship based on the angle of each compressor adjustable guide vane and its corresponding surge margin. Specifically, a curve fitting (such as linear fitting, polynomial fitting, etc.) is performed on each guide vane angle and its corresponding surge margin to obtain a fitting function relationship between the two.

[0080] In step S210 , the slope of the fitted function relationship is determined as the guide vane angle influence coefficient. Specifically, the slope of the fitted function relationship between the guide vane angle and the surge margin is used as the guide vane angle influence coefficient to quantify the influence of the guide vane angle change on the surge margin.

[0081] Step S211 : performing surge margin verification based on the surge margin compensation model to obtain a second angle offset.

[0082] Specifically, the above step S211 includes:

[0083] Step S2111 : obtaining a target surge margin gain, a guide vane angle influence coefficient, a standard surge margin, and a minimum allowable surge margin of the engine.

[0084] Step S2112 uses a surge margin compensation model to calculate the sum of the target surge margin gain and the standard surge margin, and then calculates a second difference between the minimum allowable engine surge margin and the sum. Specifically, this second difference represents the allowable surge margin reduction margin due to guide vane offset after the anti-icing bleed air increases the surge margin.

[0085] Step S2113, calculate the quotient of the second difference and the guide vane angle influence coefficient as the second angle offset. Specifically, the surge margin compensation model is shown in the following formula (1):

[0086] SM new =SM std +ΔSM bleed +θ*K vane (1)

[0087] Among them, SM new Indicates the surge margin after anti-icing optimization; SM std Indicates the standard surge margin; ΔSM bleed represents the target surge margin gain; θ represents the angular offset of the compressor adjustable guide vane; K vane Represents the guide vane angle influence coefficient.

[0088] To ensure the stability and safety of the engine, SM new It needs to be greater than or equal to the minimum allowable surge margin of the engine. Therefore, the maximum allowable offset of the adjustable guide vane, that is, the second angle offset, can be calculated by the following formula (2). The safety requirement of the surge margin is converted into a specific limit value of the guide vane angle to ensure that the engine still maintains surge margin safety after the guide vane angle is adjusted.

[0089]

[0090] Where Δθ max Indicates the second angle offset; SM min Indicates the minimum allowable surge margin of the engine; SM std Indicates the standard surge margin; ΔSM bleed represents the target surge margin gain; K vane Represents the guide vane angle influence coefficient.

[0091] Step S212: determining a target angle offset based on the first angle offset and the second angle offset.

[0092] Specifically, the above step S212 includes:

[0093] In step S2121, when the first angle offset is greater than the second angle offset, the second angle offset is determined as the target angle offset. Specifically, if the first angle offset calculated based on the anti-icing bleed air volume is greater than the second angle offset obtained through surge margin verification, this indicates that using the first angle offset may result in excessive guide vane opening, causing the surge margin to fall below the minimum allowable value for the engine, posing a surge risk. In this case, the second angle offset is determined as the target angle offset to ensure the engine maintains the minimum surge margin and prevent compressor stall caused by excessive guide vane opening.

[0094] In step S2122, when the second angle offset is greater than the first angle offset, the first angle offset is determined as the target angle offset. Specifically, when the second angle offset is greater than the first angle offset, it indicates that the maximum allowable offset based on surge margin verification is greater than the offset calculated based on the bleed air volume. In this case, using the first angle offset can both ensure that the engine surge margin is above the safety threshold and effectively increase the gas generator air flow by increasing the guide vane angle, thereby maximizing compensation for power loss caused by anti-icing bleed air.

[0095] Step S213: Control the angle of the compressor adjustable guide vanes to adjust the target angle offset. Figure 1 Step S105 of the illustrated embodiment will not be described in detail here.

[0096] Step S214 calculates the product of the target angle offset and the anti-icing flag. The anti-icing flag indicates whether the anti-icing valve is open or closed. Specifically, steps S214 and S215 allow the angle of the adjustable guide vanes to be calculated after dynamic control of the guide vanes. When the anti-icing valve is open, the anti-icing flag is 1; when the anti-icing valve is closed, the anti-icing flag is 0.

[0097] In step S215, the sum of the product and the standard adjustable guide vane angle is used as the anti-icing optimized adjustable guide vane angle. Specifically, the anti-icing optimized adjustable guide vane angle is determined by the following formula (3).

[0098] θ new =θ std +Δθ*S anti-ice (3)

[0099] Among them, θ new represents the adjustable guide vane angle after anti-icing optimization; θ std represents the standard adjustable guide vane angle; Δθ represents the target angle offset; S anti-ice Indicates anti-icing sign.

[0100] The present invention can timely grasp the working status of the engine anti-icing system by real-time monitoring of the anti-icing valve status and the change of the bleed air volume, thereby realizing dynamic control of the angle of the adjustable guide vane of the compressor. By comparing the initial and current anti-icing bleed air volumes, the first angle offset is determined based on the change of the bleed air volume, and the second angle offset is derived using the surge margin compensation model, so as to obtain the target angle offset from the first angle offset based on the anti-icing bleed air volume and the second angle offset based on the surge margin, fully taking into account the anti-icing requirements and surge safety, maximizing power compensation within a safe range, and finally realizing precise dynamic control of the adjustable guide vanes of the compressor based on the target angle offset, thereby increasing the air flow at the compressor inlet, effectively compensating for the power loss caused by the opening of the anti-icing valve, significantly improving the power output stability and economic efficiency of the engine in high-altitude and low-temperature environments, and meeting the power requirements of the helicopter at the same time.

[0101] This embodiment also provides a compressor adjustable guide vane angle dynamic control device, which is used to implement the above-mentioned embodiments and preferred implementations. Details already described will not be repeated here. As used below, the term "module" may refer to a combination of software and / or hardware that implements a predetermined function. Although the devices 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.

[0102] This embodiment provides a compressor adjustable guide vane angle dynamic control device, such as Figure 2 Shown, including:

[0103] The acquisition module 201 is used to detect that the anti-icing valve is opened, obtain the initial anti-icing air flow rate and continuously obtain the anti-icing air flow rate.

[0104] The first determining module 202 is configured to determine a first angle offset based on an initial anti-icing air bleed volume and a current anti-icing air bleed volume.

[0105] The verification module 203 is configured to perform surge margin verification based on the surge margin compensation model to obtain a second angle offset.

[0106] The second determining module 204 is configured to determine a target angle offset based on the first angle offset and the second angle offset.

[0107] The control module 205 is used to control the angle of the adjustable guide vanes of the compressor to adjust the target angle offset.

[0108] In some optional implementations, the first determining module 202 includes:

[0109] The first calculation unit is configured to calculate a first difference between a current anti-icing air bleed volume and an initial anti-icing air bleed volume.

[0110] The second calculation unit is used to calculate a quotient of the first difference divided by a preset judgment value.

[0111] The first determining unit is configured to multiply the quotient by a preset offset as a first angle offset.

[0112] In some optional implementations, the verification module 203 includes:

[0113] The acquisition unit is used to obtain the target surge margin gain, the guide vane angle influence coefficient, the standard surge margin and the minimum allowable surge margin of the engine.

[0114] The third calculation unit is configured to calculate a sum of the target surge margin gain and the standard surge margin using the surge margin compensation model, and calculate a second difference between the minimum allowable surge margin of the engine and the sum.

[0115] The fourth calculation unit is used to calculate a quotient of the second difference divided by the guide vane angle influence coefficient as the second angle offset.

[0116] In some optional implementations, the second determining module 204 includes:

[0117] The second determining unit is configured to determine the second angular offset as a target angular offset when the first angular offset is greater than the second angular offset.

[0118] The third determining unit is configured to determine the first angular offset as a target angular offset when the second angular offset is greater than the first angular offset.

[0119] In some optional embodiments, before the acquiring unit, the apparatus further includes:

[0120] Building blocks for creating multiple operating conditions based on simulated atmospheric conditions, engine operating status, and anti-icing air flow.

[0121] The first acquisition module is used to test the working state of the engine when the anti-icing valve is opened and closed under each working condition, and collect corresponding compressor parameters.

[0122] The first calculation module is configured to calculate a surge margin change of an operating condition based on compressor parameters corresponding to when the anti-icing valve is opened and when the anti-icing valve is closed, as a surge margin gain of the operating condition.

[0123] The third determination module is used to determine the operating condition corresponding to the current anti-icing air flow rate, the current atmospheric environment conditions and the current engine operating state from all operating conditions, and use the surge margin gain of the operating condition as the target surge margin gain.

[0124] In some optional embodiments, before the acquiring unit, the apparatus further includes:

[0125] The test module is used to control the angle of the compressor adjustable guide vanes to change according to a preset step size, and test the compressor performance parameters corresponding to each compressor adjustable guide vane angle.

[0126] The second calculation module is used to calculate the surge margin corresponding to the angle of each compressor adjustable guide vane based on the compressor performance parameters.

[0127] The fitting module is used to fit the angle of each compressor adjustable guide vane and its corresponding surge margin to obtain a fitting function relationship.

[0128] The fourth determination module is used to determine the slope of the fitting function relationship as the guide vane angle influence coefficient.

[0129] In some optional embodiments, the device further comprises:

[0130] The third calculation module is used to calculate the product of the target angle offset and the anti-icing flag, where the anti-icing flag is used to indicate whether the anti-icing valve is in an open state or a closed state.

[0131] The fifth determination module is configured to use the sum of the product and the standard adjustable guide vane angle as the anti-icing optimized adjustable guide vane angle.

[0132] The further functional description of each of the above modules and units is the same as that of the above corresponding embodiments and will not be repeated here.

[0133] The compressor adjustable guide vane angle dynamic control device in this embodiment is presented in the form of a functional unit, where the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and memory that executes one or more software or fixed programs, and / or other devices that can provide the above functions.

[0134] The embodiment of the present invention also provides a computer device having the above Figure 2 The compressor adjustable guide vane angle dynamic control device is shown.

[0135] See also Figure 3 , Figure 3 is a structural diagram of a computer device provided by an optional embodiment of the present invention, such as Figure 3As shown, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components utilize different buses to communicate with each other and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in the memory or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Equally, multiple computer devices can be connected, and each device provides part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 3 A processor 10 is taken as an example.

[0136] The processor 10 may be a central processing unit, a network processor, or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic, or any combination thereof.

[0137] The memory 20 stores instructions that can be executed by at least one processor 10, so as to enable at least one processor 10 to execute the method shown in the above embodiment.

[0138] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created based on the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0139] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0140] The computer device also includes an input device 30 and an output device 40. The processor 10, the memory 20, the input device 30 and the output device 40 can be connected via a bus or other means. Figure 3 The bus connection is taken as an example.

[0141] The input device 30 can receive input digital or character information and generate key signal input related to user settings and function control of the computer device, such as a touch screen, a keypad, a mouse, a trackpad, a touch pad, an indicator stick, one or more mouse buttons, a trackball, a joystick, etc. The output device 40 can include a display device, an auxiliary lighting device (e.g., an LED), and a tactile feedback device (e.g., a vibration motor). The above-mentioned display device includes but is not limited to a liquid crystal display, a light emitting diode, a display, and a plasma display. In some optional embodiments, the display device can be a touch screen.

[0142] The embodiment of the present invention also provides a computer-readable storage medium. The above-mentioned method according to the embodiment of the present invention can be implemented in hardware, firmware, or implemented as a computer code that can be recorded in a storage medium, or implemented as a computer code that is originally stored in a remote storage medium or a non-temporary 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 in 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 storage 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 memory. 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 a computer, a processor or hardware, the method shown in the above embodiment is implemented.

[0143] A portion of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the form in which the computer program instruction exists in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc. Accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium that can be accessed by the computer.

[0144] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A method for dynamically controlling the angle of an adjustable guide vane of a compressor, characterized in that: The method comprises: When the anti-icing valve is detected to be open, the initial anti-icing air flow rate is obtained and the anti-icing air flow rate is continuously obtained; determining a first angle offset based on the initial anti-icing air bleed amount and the current anti-icing air bleed amount; Performing surge margin verification based on a surge margin compensation model to obtain a second angle offset; determining a target angular offset based on the first angular offset and the second angular offset; The target angle offset is adjusted by controlling the angle of the adjustable guide vanes of the compressor.

2. The method according to claim 1, characterized in that The determining of the first angle offset based on the initial anti-icing air bleed amount and the current anti-icing air bleed amount includes: Calculating a first difference between a current anti-icing air bleed amount and the initial anti-icing air bleed amount; Calculating a quotient of the first difference divided by a preset judgment value; The product of the quotient and the preset offset is used as the first angle offset.

3. The method according to claim 1, characterized in that The surge margin verification based on the surge margin compensation model to obtain the second angle offset includes: Obtain target surge margin gain, guide vane angle influence coefficient, standard surge margin, and minimum allowable surge margin of the engine; Using a surge margin compensation model, calculating a sum of the target surge margin gain and the standard surge margin, and calculating a second difference between the minimum allowable surge margin of the engine and the sum; A quotient of the second difference divided by the guide vane angle influence coefficient is calculated as the second angle offset.

4. The method according to claim 1, wherein The determining a target angle offset based on the first angle offset and the second angle offset includes: When the first angle offset is greater than the second angle offset, determining the second angle offset as the target angle offset; When the second angle offset is greater than the first angle offset, the first angle offset is determined as the target angle offset.

5. The method according to claim 3, characterized in that Before obtaining the target surge margin gain, the method further includes: Construct multiple operating conditions based on simulated atmospheric conditions, engine operating status and anti-icing air volume; Under each operating condition, the engine is tested with the anti-icing valve open and closed, and the corresponding compressor parameters are collected. calculating a surge margin change under the operating condition based on compressor parameters corresponding to when the anti-icing valve is opened and when the anti-icing valve is closed, as a surge margin gain under the operating condition; An operating condition corresponding to the current anti-icing bleed air volume, the current atmospheric environment condition, and the current engine operating state is determined from all operating conditions, and a surge margin gain of the operating condition is used as a target surge margin gain.

6. The method according to claim 3, characterized in that Before obtaining the guide vane angle influence coefficient, the method further includes: Controlling the angle of the adjustable guide vanes of the compressor to change according to a preset step size, and testing the compressor performance parameters corresponding to each angle of the adjustable guide vanes of the compressor; Calculating a surge margin corresponding to an angle of an adjustable guide vane of each compressor based on the compressor performance parameters; Based on the fitting of the angle of each compressor adjustable guide vane and its corresponding surge margin, a fitting function relationship is obtained; The slope of the fitting function relationship is determined as the guide vane angle influence coefficient.

7. The method according to claim 1, characterized in that The method further comprises: calculating a product of the target angle offset and an anti-icing flag, the anti-icing flag being used to indicate whether the anti-icing valve is in an open state or a closed state; The sum of the product and the standard adjustable guide vane angle is used as the anti-icing optimized adjustable guide vane angle.

8. A compressor adjustable guide vane angle dynamic control device, characterized in that: The device comprises: An acquisition module is used to detect the opening of the anti-icing valve, obtain the initial anti-icing air flow rate and continuously obtain the anti-icing air flow rate; A first determining module is configured to determine a first angle offset based on the initial anti-icing air bleed amount and the current anti-icing air bleed amount; A verification module, configured to perform surge margin verification based on a surge margin compensation model to obtain a second angle offset; a second determining module, configured to determine a target angular offset based on the first angular offset and the second angular offset; A control module is used to control the angle of the adjustable guide vanes of the compressor to adjust the target angle offset.

9. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the compressor adjustable guide vane angle dynamic control method according to any one of claims 1 to 7 by executing the computer instructions.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, and the computer instructions are used to enable a computer to execute the compressor adjustable guide vane angle dynamic control method according to any one of claims 1 to 7.

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