Adjustable guide vane angle control method for gas compressor

Abstract

The invention provides an angle control method for an adjustable guide vane of a gas compressor, which belongs to the technical field of aero-engines and comprises the following steps: calculating the total temperature of an inlet of a high-pressure gas compressor through an engine model; the high-pressure compressor rotation speed is obtained, and the high-pressure compressor conversion rotation speed is obtained through calculation according to the high-pressure compressor inlet total temperature and the high-pressure compressor rotation speed; the change relation between the adjustable guide vane angle and the conversion rotating speed of the high-pressure compressor is obtained, and the adjustable vane angle corresponding to the conversion angle of the high-pressure compressor is obtained according to the conversion rotating speed of the high-pressure compressor and the change relation between the adjustable guide vane angle and the conversion rotating speed of the high-pressure compressor; the engine inlet air inlet distortion intensity is obtained, the adjustable guide vane angle is corrected according to the engine inlet air inlet distortion intensity, and the corrected adjustable vane angle corresponding to the high-pressure compressor conversion rotating speed is obtained; and the upper limit and the lower limit of the adjustable blade angle of the high-pressure compressor of the engine are obtained, the corrected adjustable blade angle is limited according to the upper limit and the lower limit, and therefore the control value of the adjustable blade angle is obtained.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a method for controlling the angle of adjustable guide vanes of a compressor. Background Technology

[0002] In the design of modern advanced gas turbine engines, high-pressure compressors typically have a large number of stages or a high stage load level. To improve compressor performance and aerodynamic stability, the guide vanes of the first few stages are designed to be adjustable, and relatively accurate control of the compressor guide vane adjustment angle is required.

[0003] The current common practice is to use an airborne high-pressure compressor inlet temperature sensor to obtain the total inlet temperature T of the high-pressure compressor. t25 (abbreviated as total temperature T) t25 The measured value is based on the total temperature T. t25 The measured values ​​were used to calculate the rotational speed n of the high-pressure compressor, converted to the compressor inlet section 25. 2r25 However, airborne temperature sensors typically use platinum resistance thermometers for measurement, and their time constants are generally within the range of 4.5s ± 0.5s. When the engine undergoes a transitional test, the total temperature T... t25 The measured values ​​will exhibit a significant lag, meaning they will be lower (or higher) than the actual airflow temperature, thus affecting the calculated compressor inlet speed n. 2r25 Calculated values ​​that are too high (or too low) can cause the compressor's adjustable guide vane angle to open (or close) excessively, potentially leading to compressor surge (or fan surge). To address this issue, the current solution involves setting up separate control schemes for steady-state and transient states, and implementing transient state switching logic: when the engine is operating in steady state, the total temperature To obtained from the compressor inlet engine temperature sensor is used. t25 Calculate the compressor inlet speed n from the measured value 2r25 And by setting the corresponding adjustment rules, the guide vane angle α can be adjusted. c =f(n) 2r25 When the engine is operating in transient mode, the compressor inlet total temperature T is obtained using the compressor inlet airborne temperature sensor. t2 Calculation of the converted speed n of the high-pressure rotor based on the measured value 2r And by setting the corresponding adjustment rules, the guide vane angle α can be adjusted. c =f(n) 2r The switching between the two is generally based on the difference between the given throttle state and the actual state within a specified threshold range.

[0004] Currently, using two sets of control laws to control the adjustable guide vane angle of the compressor has the following main drawbacks:

[0005] 1) Due to the influence of factors such as different throttle trajectories, low Reynolds number at high altitudes, and different adjustment rules for nozzle throat area A8 in different regions within the envelope, the transient state adopts the control law α. c =f(n) 2r When ), the converted speed n of the high-voltage rotor 2r It cannot accurately reflect the compressor inlet converted speed n 2r25 This leads to the adjustable guide vane angle α c Off-center or off-center (increased deviation in angle control) is detrimental to engine performance and stability, and cannot take into account the effects of slip changes caused by related factors.

[0006] 2) A transition is required between the two sets of control laws. Under some operating conditions, there are significant fluctuations when the control laws are switched, resulting in a deterioration in control quality.

[0007] 3) As the engine's service life increases, the engine parameters change, α c =f(n) 2r25 ), α c =f(n) 2r The two sets of rules may not match and often need to be adjusted;

[0008] 4) Under conditions of temperature distortion or engine water ingestion, the total temperature T t25 The measured values ​​may have a large deviation, affecting the adjustable guide vane angle α. c To be slightly off (or slightly closed). Summary of the Invention

[0009] The purpose of this application is to provide a method for controlling the adjustable guide vane angle of a compressor to solve or mitigate at least one of the problems in the prior art.

[0010] The technical solution of this application is: a method for controlling the adjustable guide vane angle of a compressor, comprising:

[0011] The total inlet temperature T of the high-pressure compressor was calculated using an engine model. t25 ;

[0012] Obtain the high-pressure compressor speed n2, based on the total inlet temperature T of the high-pressure compressor. t25 The equivalent speed n of the high-pressure compressor is calculated from the high-pressure compressor speed n2. 2r25 ;

[0013] Obtain the relationship α between the adjustable guide vane angle and the equivalent speed of the high-pressure compressor. c =f(n) 2r25 According to the high-pressure compressor, the converted speed n 2r25 The relationship between the adjustable guide vane angle and the equivalent speed of the high-pressure compressor α c =f(n) 2r25The adjustable blade angle α corresponding to the converted angle of the high-pressure compressor is obtained. c (n 2r25 );

[0014] Obtain the engine inlet air distortion intensity W, and adjust the adjustable guide vane angle α based on the engine inlet air distortion intensity W. c Make corrections to obtain the adjustable blade angle α corresponding to the corrected high-pressure compressor converted speed. c (n 2r25 );

[0015] Obtain the upper and lower limits of the adjustable blade angle of the engine's high-pressure compressor, and adjust the adjusted blade angle α according to the upper and lower limits of the adjustable blade angle of the engine's high-pressure compressor. c By imposing restrictions, an adjustable blade angle α can be obtained. c The control value.

[0016] In at least one embodiment of this application, the equivalent speed n of the high-pressure compressor is calculated. 2r25 The method is as follows:

[0017] n 2r25 =n2×(T) t25设计点 / T t25 ) 0.5

[0018] In the formula, T t25设计点 The total inlet temperature of the high-pressure compressor at the design point.

[0019] In at least one embodiment of this application, the relationship α between the adjustable blade angle and the converted speed of the high-pressure compressor is... c =f(n) 2r25 This is obtained through component simulation or testing.

[0020] In at least one embodiment of this application, the adjustable guide vane angle α c The method for making the correction is as follows:

[0021] α c (n 2r25 ) 修正 =α c (n 2r25 )+Δα c (W)

[0022] In the formula, α c (n 2r25 ) 修正 The adjustable blade angle corresponding to the corrected converted speed of the high-pressure compressor; Δα c (W) represents the adjustable blade angle correction amount corresponding to the intake distortion intensity.

[0023] In at least one embodiment of this application, the adjusted blade angle α is modified according to the upper and lower limits of the adjustable blade angle of the high-pressure compressor of the engine. c By imposing restrictions, an adjustable blade angle α can be obtained. c The method for controlling the value is as follows:

[0024] α c控制值 =MIN{α c (n 2r25 ) 上限 MAX[α] c (n 2r25 ) 下限 α c (n 2r25 ) 修正 ]}

[0025] In the formula, α c (n 2r25 ) 修正 The adjustable blade angle corresponding to the corrected converted speed of the high-pressure compressor;

[0026] α c (n 2r25 ) 上限 This is the upper limit of the adjustable blade angle;

[0027] α c (n 2r25 ) 下限 This is the lower limit value for the adjustable blade angle;

[0028] α c控制值 This is the control value for the adjustable blade angle.

[0029] The method in this application calculates the total inlet temperature T of the high-pressure compressor using an airborne engine model. t25 It can accurately characterize the total inlet temperature of the high-pressure compressor under steady-state and transient conditions, without the time lag caused by temperature sensors, and does not undergo drastic changes during distortion or water ingestion. Therefore, only α is needed under steady-state and transient conditions. c =f(n) 2r25 The control principle can be followed; the guide vane angle α can be adjusted. c It is easier to control. Attached Figure Description

[0030] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0031] Figure 1 This is a flowchart of the compressor adjustable guide vane angle control method of this application.

[0032] Figure 2This is a flowchart of the calculation of the total inlet temperature of the high-pressure compressor based on the engine model in this application.

[0033] Figure 3 For the adjustable guide vane angle α in this application c Provide a diagram illustrating the limitations. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0035] This application provides an adjustable guide vane angle α for a compressor. c The control method obtains the total inlet temperature T of the high-pressure compressor through an airborne model. t25 Calculated value, using total temperature T t25 The calculated value yields the converted speed n of the high-pressure compressor. 2r25 To adjust the guide vane angle α c Control of the total inlet temperature T of the high-pressure compressor t25 The calculated value can characterize the total inlet temperature of the high-pressure compressor under steady-state and transient conditions, thus allowing for the accurate obtained conversion speed n of the high-pressure compressor. 2r25 Using the method of this application, the adjustable guide vane angle α can be adjusted. c More precise control, and no need to use α. c =f(n) 2r The control law simplifies the adjustable guide vane angle α. c The control method avoids the need for two sets of rules to improve control quality. When the engine ingests water, the water interference will not cause a decrease in the total inlet temperature T of the high-pressure compressor. t25 A drastic change occurred, causing the adjustable guide vane angle α to... c Deviations can affect engine stability. Ultimately, it's necessary to balance the differences in low Reynolds number and nozzle area control patterns across different regions within the compressor envelope, which impact the compressor's converted speed and adjustable guide vane angle α. c The impact of control deviation.

[0036] like Figure 1 As shown, the adjustable guide vane angle α of the compressor provided in this application c The control method includes the following steps:

[0037] Step S10: Calculate the total inlet temperature T of the high-pressure compressor using the engine model. t25 .

[0038] An engine model is a collection of mathematical models and computer programs that describe an engine's operating performance, thermodynamic processes, physical characteristics, and control logic. It is built upon physical laws (such as thermodynamics, fluid mechanics, and mechanics) and a large amount of experimental data. Engine models typically include overall performance models and high-fidelity models.

[0039] The engine model has the following uses:

[0040] 1) Performance analysis and optimization: predict thrust and fuel consumption rate, and optimize cycle parameters (such as pressure ratio and bypass ratio).

[0041] 2) Control law design: Design engine control algorithm to ensure stable, efficient and safe operation.

[0042] 3) Structural strength and life analysis: Evaluate the reliability of key components such as blades and rotors under extreme conditions.

[0043] 4) Condition monitoring and fault prediction (PHM): Real-time assessment of engine health status and prediction of remaining life.

[0044] For example, in this embodiment of the application, the engine model includes a fan component pressure ratio model and a fan component temperature ratio model.

[0045] like Figure 2 The figure shown is the total inlet temperature T of the high-pressure compressor calculated based on an engine model in one embodiment of this application. t25 The computational logic diagram shows that the process includes:

[0046] 1) Based on the low-pressure rotor speed n1 and the total inlet temperature T t2 The calculated equivalent speed n of the low-pressure rotor is obtained. 1r According to the total pressure P at the engine inlet t2 Total pressure P at the outer duct inlet t13 The fan external bypass pressure ratio P was calculated. t13 / P t2 ;

[0047] 2) Calculate the speed n based on the low-pressure rotor. 1r Fan external bypass pressure ratio P t13 / P t2 The fan pressure ratio P is obtained from the fan component pressure ratio model. t21 / P t2 ;

[0048] 3) Calculate the speed n based on the low-pressure rotor. 1r Fan pressure ratio P t21 / P t2 The fan temperature ratio T is obtained from the fan component temperature ratio model. t21 / T t2 Combined with the imported total temperature T t2The fan outlet temperature T is then calculated. t21 ;

[0049] 4) Considering Reynolds number, fan clearance variation, etc., the temperature correction Δ is obtained through simulation experiments. Based on the temperature correction Δ, the fan outlet temperature T is adjusted. t21 The corrected fan outlet temperature T is obtained by making corrections. t21 ;

[0050] 5) Considering the difference between the fan outlet temperature and the compressor inlet temperature, based on the modified fan inlet temperature T t21 The total inlet temperature T of the high-pressure compressor was calculated. t25 .

[0051] Step S20: Obtain the high-pressure compressor speed n2, and calculate the total inlet temperature T of the high-pressure compressor obtained in step S10. t25 The equivalent speed n of the high-pressure compressor is calculated from the high-pressure compressor speed n2. 2r25 The specific calculation method is as follows:

[0052] n 2r25 =n2×(T) t25设计点 / T t25 ) 0.5 .

[0053] In the formula, T t25设计点 The total inlet temperature of the high-pressure compressor at the design point.

[0054] Step S30: Obtain the relationship α between the adjustable guide vane angle and the converted speed of the high-pressure compressor. c =f(n) 2r25 Based on the high-pressure compressor converted speed n obtained in step S20, 2r25 The relationship between the adjustable guide vane angle and the equivalent speed of the high-pressure compressor α c =f(n) 2r25 The adjustable blade angle α corresponding to the converted angle of the high-pressure compressor is obtained. c (n 2r25 ).

[0055] The total inlet temperature T of the high-pressure compressor was calculated using an engine model. t25 It can accurately characterize the total inlet temperature of the high-pressure compressor in both steady-state and transient states, and therefore the calculated equivalent speed n of the high-pressure compressor can be obtained through it. 2r25 It can also accurately characterize the converted speed of the high-pressure compressor, therefore the converted speed n of the high-pressure compressor can be used for both the steady-state and transient states of the engine. 2r25 and the control law of adjustable blade angle α c =f(n) 2r25 To control.

[0056] Adjustable blade angle αc The conversion speed n of the high-pressure compressor 2r25 The relationship of change α c =f(n) 2r25 The results were obtained through component simulation or testing. Table 1 shows the relationship points between the five adjustable blade angles and the converted speed of the high-pressure compressor obtained through component simulation or testing in this embodiment of the application. Based on the adjustable blade angle α... c The conversion speed n of the high-pressure compressor 2r25 The relationship between the changes and the converted speed n of the high-pressure compressor calculated by the above process 2r25 The corresponding adjustable blade angle α can be obtained. c (n 2r25 It is understood that Table 1 in this embodiment of the present application lists a limited number of adjustable blade angles α. c The conversion speed n of the high-pressure compressor 2r25 The relationship between the changes, when the calculated equivalent speed n of the high-pressure compressor is obtained. 2r25 There is no direct correspondence to the adjustable blade angle α c (n 2r25 When ), it can be calculated using interpolation.

[0057] Table 1 α c With n 2r25 Change relationship

[0058] <![CDATA[n 2r25 (%)]]> 55 79 91 98 100 <![CDATA[α c ]]> 28 9 3 0 0

[0059] Step S40: Obtain the engine inlet air distortion intensity W, and adjust the adjustable guide vane angle α according to the engine inlet air distortion intensity W. c Make corrections to obtain the adjustable blade angle α corresponding to the corrected high-pressure compressor converted speed. c (n 2r25 ).

[0060] When there is significant intake air distortion at the engine inlet, the adjustable guide vane angle α of the compressor needs to be adjusted to protect the compressor's stability. c Based on design principles or design points, off-center control is implemented to increase the compressor's remaining surge margin and prevent engine surge.

[0061] The engine inlet air distortion intensity W can be obtained through parametric calculation based on experimental data or through CFD simulation.

[0062] For adjustable guide vane angle α c The method for making the correction is as follows:

[0063] α c (n 2r25 ) 修正 =α c (n2r25 )+Δα c (W)

[0064] In the formula, α c (n 2r25 ) 修正 The adjustable blade angle corresponding to the corrected converted speed of the high-pressure compressor; Δα c (W) represents the adjustable blade angle correction amount corresponding to the intake distortion intensity.

[0065] In this application, the adjustable blade angle correction amount Δα corresponding to the engine intake distortion intensity W is... c (W) Values ​​are taken according to Table 2. It is understood that the adjustable blade angle correction amount Δα, which is not provided in Table 2, is not included. c (W) can be obtained through interpolation.

[0066] Table 2 Adjustable blade angle correction amount Δα c Relationship between intake distortion intensity W and other factors

[0067] W(％) 0 4 8 12 <![CDATA[Δα c ]]> 0 0 1 2

[0068] Step S50: Obtain the upper and lower limits of the adjustable blade angle of the engine's high-pressure compressor, and adjust the adjusted blade angle α according to the upper and lower limits of the adjustable blade angle of the engine's high-pressure compressor. c By imposing restrictions, an adjustable blade angle α can be obtained. c The control value.

[0069] To prevent the adjustable blade angle α c Beyond the limitations of adjustable guide vanes, this application obtains the adjustable blade angle α based on compressor component test or simulation results. c The upper and lower limits, and the adjustable blade angle α is adjusted according to the upper and lower limits. c The correction value is limited to obtain the adjustable blade angle control value, such as... Figure 3 As shown):

[0070] α c控制值 =MIN{α c (n 2r25 ) 上限 MAX[α] c (n 2r25 ) 下限 α c (n 2r25 ) 修正 ]}

[0071] In the formula, α c (n 2r25 ) 修正 The adjustable blade angle corresponding to the corrected converted speed of the high-pressure compressor;

[0072] α c (n 2r25 ) 上限 This is the upper limit of the adjustable blade angle;

[0073] α c (n 2r25 ) 下限 This is the lower limit value for the adjustable blade angle;

[0074] α c控制值 This is the control value for the adjustable blade angle.

[0075] The compressor adjustable guide vane angle control method provided in this application has the following main advantages compared with the existing adjustable blade angle αc control method:

[0076] 1) The method of this application calculates the total inlet temperature T of the high-pressure compressor using an airborne engine model. t25 It can accurately characterize the total inlet temperature of the high-pressure compressor under steady-state and transient conditions, without the time lag caused by temperature sensors, and does not undergo drastic changes during distortion or water ingestion. Therefore, only α is needed under steady-state and transient conditions. c =f(n) 2r25 The control principle can be followed; the guide vane angle α can be adjusted. c It is easier to control;

[0077] 2) The transition between two sets of rules is not required, which improves the quality of control;

[0078] 3) α does not need to be adjusted based on changes in slip. c =f(n) 2r25 ) and α c =f(n) 2r Control patterns facilitate engine operation;

[0079] 4) No need to measure the total inlet temperature T of the high-pressure compressor. t25 The measurement of the total inlet temperature Tt25 of the high-pressure compressor can be eliminated, thereby reducing the delivery weight of the engine and saving costs.

[0080] 5) It can take into account factors such as differences in low Reynolds number and nozzle area control patterns in different regions within the compressor envelope, affecting the compressor's converted speed and adjustable guide vane angle α. c The impact of control deviation.

[0081] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for controlling the angle of adjustable guide vanes in a compressor, characterized in that, include: The total inlet temperature T of the high-pressure compressor was calculated using an engine model. t25 ; Obtain the high-pressure compressor speed n2, based on the total inlet temperature T of the high-pressure compressor. t25 The equivalent speed n of the high-pressure compressor is calculated from the high-pressure compressor speed n2. 2r25 ; Obtain the relationship α between the adjustable guide vane angle and the equivalent speed of the high-pressure compressor. c =f(n) 2r25 According to the high-pressure compressor, the converted speed n 2r25 The relationship between the adjustable guide vane angle and the equivalent speed of the high-pressure compressor α c =f(n) 2r25 The adjustable blade angle α corresponding to the converted angle of the high-pressure compressor is obtained. c (n 2r25 ); Obtain the engine inlet air distortion intensity W, and adjust the adjustable guide vane angle α based on the engine inlet air distortion intensity W. c Make corrections to obtain the adjustable blade angle α corresponding to the corrected high-pressure compressor converted speed. c (n 2r25 ); Obtain the upper and lower limits of the adjustable blade angle of the engine's high-pressure compressor, and adjust the adjusted blade angle α according to the upper and lower limits of the adjustable blade angle of the engine's high-pressure compressor. c By imposing restrictions, an adjustable blade angle α can be obtained. c The control value.

2. The compressor adjustable guide vane angle control method as described in claim 1, characterized in that, Calculate the equivalent speed n of the high-pressure compressor. 2r25 The method is as follows: n 2r25 =n2×(T t25设计点 / T t25 ) 0.5 In the formula, T t25设计点 The total inlet temperature of the high-pressure compressor at the design point.

3. The compressor adjustable guide vane angle control method as described in claim 1, characterized in that, The relationship α between the adjustable blade angle and the converted speed of the high-pressure compressor c =f(n) 2r25 This is obtained through component simulation or testing.

4. The compressor adjustable guide vane angle control method as described in claim 3, characterized in that, For adjustable guide vane angle α c The method for making the correction is as follows: a c (n 2r25 ) 修正 =a c (n 2r25 )+Da c (W) In the formula, α c (n 2r25 ) 修正 The adjustable blade angle corresponding to the corrected converted speed of the high-pressure compressor; Δα c (W) represents the adjustable blade angle correction amount corresponding to the intake distortion intensity.

5. The compressor adjustable guide vane angle control method as described in claim 4, characterized in that, The adjusted blade angle α is modified based on the upper and lower limits of the adjustable blade angle of the high-pressure compressor of the engine. c By imposing restrictions, an adjustable blade angle α can be obtained. c The method for controlling the value is as follows: a c控制值 =MIN{a c (n 2r25 ) 上限 ,MAX[a c (n 2r25 ) 下限 ,a c (n 2r25 ) 修正 ]} In the formula, α c (n 2r25 ) 修正 The adjustable blade angle corresponding to the corrected converted speed of the high-pressure compressor; α c (n 2r25 ) 上限 This is the upper limit of the adjustable blade angle; α c (n 2r25 ) 下限 This is the lower limit value for the adjustable blade angle; α c控制值 This is the control value for the adjustable blade angle.

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