An adjustable angle lead control method and device during the deceleration process of an aeroengine

Abstract

This application belongs to the field of engine control technology, and particularly relates to a method and device for adjustable angle lead control during the deceleration process of an aeroengine. The method includes step S1, determining that the engine enters deceleration control; step S2, determining a first high-pressure conversion speed relative to the total temperature at the fan inlet and a second high-pressure conversion speed relative to the total temperature at the compressor inlet; step S3, determining the original given value of the adjustable vane angle of the compressor according to the lead angle control offset of the adjustable vane angle of the compressor; step S4, interpolating the lead limit value of the adjustable vane angle of the compressor based on the median value of the lead value range of the adjustable vane angle of the compressor; step S5, taking the smaller value of the original given value and the lead limit value as the final lead setting value of the adjustable vane angle of the compressor; step S6, controlling the adjustable vane angle of the compressor to deflect ahead with the lead setting value. This application improves the delivery efficiency of the engine.

Description

Technical Field

[0001] This application belongs to the technical field of engine control, and particularly relates to a method and device for adjustable angle lead control during the deceleration process of an aeroengine. Background Art

[0002] During the factory test run of a certain type of engine, it is required to check the lead angle of the adjustable vane angle α2 of the compressor during the deceleration process. During the test run, problems often occur where the inspection fails multiple times and repeated adjustment and verification are required.

[0003] Currently, in order to ensure the stability and performance of an aeroengine, the control of the adjustable vane angle α2 of the compressor adopts a combined control of α2 = f(n 2r )(n 2r is the converted rotational speed converted according to the total temperature T1 at the fan inlet to ensure stability) and α2 = f(n 2r25 )(n 2r25 is the converted rotational speed converted according to the total temperature T 25 at the compressor inlet to ensure performance). During the deceleration process, the adjustable vane angle α2 of the compressor is controlled with a lead angle. However, due to the large time response constant of the T 25 sensor, the given value of α2 calculated according to α2 = f(n 2r25 ) will be significantly off. After being combined with α2 = f(n 2r ), finally, the engine is controlled according to the off-limit value (generally limited by the backup system) at the current rotational speed. If the off-limit value of the engine is inappropriate (the adjustment accuracy of the backup system is poor), it will lead to the problem that the inspection fails multiple times during the test run. Multiple adjustments and start-up verifications are required, which not only wastes the engine life but also increases the waste of test run resources. Summary of the Invention

[0004] To solve one of the above problems, this application provides a method and device for adjustable angle lead control during the deceleration process of an aeroengine, so as to accurately set the off-limit value, ensure that the lead angle of α2 can quickly meet the requirements during the test run, and save test run resources and adjustment workload.

[0005] The first aspect of this application provides a method for adjustable angle lead control during the deceleration process of an aeroengine, mainly including:

[0006] Step S1, determine that the engine enters deceleration control;

[0007] Step S2, determine the first high-pressure converted rotational speed relative to the total temperature at the fan inlet and the second high-pressure converted rotational speed relative to the total temperature at the compressor inlet;

[0008] Step S3: Determine the original set value of the adjustable vane angle of the compressor according to the lead angle control deviation amount of the adjustable vane angle of the compressor;

[0009] Step S4: Interpolate the lead limit value of the adjustable vane angle of the compressor based on the midline value of the lead value range of the adjustable vane angle of the compressor;

[0010] Step S5: Use the smaller value of the original set value and the lead limit value as the final lead set value of the adjustable vane angle of the compressor;

[0011] Step S6: Control the adjustable vane angle of the compressor to deflect ahead with the lead set value.

[0012] Preferably, in step S1, determining that the engine enters deceleration control includes:

[0013] Step S11: Obtain the set speed value and the measured speed value;

[0014] Step S12: When the difference between the set speed value and the measured speed value is less than the set value, determine that the engine enters deceleration control.

[0015] Preferably, in step S2, determining the first high-pressure corrected speed n 2r includes:

[0016]

[0017] where n2 is the high-pressure physical speed and T1 is the total temperature at the fan inlet;

[0018] Determine the second high-pressure corrected speed n 2r25 includes:

[0019]

[0020] where T 25 is the total temperature at the compressor inlet, and T 25设计点 is the design value of the total temperature at the compressor inlet.

[0021] Preferably, in step S3, the original set value α 2Dem原 is determined by the following formula:

[0022] α 2Dem原 = k1(f(n 2r ) + Δα 2_n2r ) + k2(f(n 2r25 ) + Δα 2_n2r25 );

[0023] where k1 and k2 are the weighting coefficients of f(n 2r ) and f(n 2r25 ), and Δα2_n2r and Δα 2_n2r25 is the lead angle control deviation amount.

[0024] Preferably, in step S4, the lead limit value α 2限制值 is determined by the following formula:

[0025] α 2限制值 = f(n 2r ) + Δα 2_超前要求值中线 + err(n 2r ) 控制精度 ;

[0026] where, Δα 2_超前要求值中线 is the median value of the lead value range of the required adjustable vane angle α2 of the compressor, and err(n 2r ) 控制精度 is the control accuracy of the adjustable vane angle α2 of the compressor at the high-pressure conversion speed n 2r during the deceleration process.

[0027] The second aspect of the present application provides an adjustable angle lead control device during the deceleration process of an aero-engine, mainly including:

[0028] A state determination module for determining that the engine enters deceleration control;

[0029] A high-pressure conversion speed calculation module for determining a first high-pressure conversion speed relative to the total temperature at the fan inlet and a second high-pressure conversion speed relative to the total temperature at the compressor inlet;

[0030] An original set value determination module for determining the original set value of the adjustable vane angle of the compressor according to the lead angle control deviation amount of the adjustable vane angle of the compressor;

[0031] A lead limit value determination module for interpolating the lead limit value of the adjustable vane angle of the compressor based on the median value of the lead value range of the adjustable vane angle of the compressor;

[0032] A lead set value determination module for using the smaller value of the original set value and the lead limit value as the final lead set value of the adjustable vane angle of the compressor;

[0033] An adjustable vane angle control module of the compressor for controlling the adjustable vane angle of the compressor to deflect forward with the lead set value.

[0034] Preferably, the state determination module includes:

[0035] A rotational speed parameter acquisition unit for acquiring a rotational speed set value and a rotational speed measurement value;

[0036] A deceleration control signal generation unit, configured to determine that the engine enters deceleration control when the difference between the rotational speed set value and the rotational speed measured value is less than a set value.

[0037] Preferably, in the high-pressure conversion rotational speed calculation module, to determine the first high-pressure conversion rotational speed n 2r Including:

[0038]

[0039] wherein, n2 is the high-pressure physical rotational speed, and T1 is the total temperature at the fan inlet;

[0040] To determine the second high-pressure conversion rotational speed n 2r25 Including:

[0041]

[0042] wherein, T 25 is the total temperature at the compressor inlet, and T 25设计点 is the designed value of the total temperature at the compressor inlet.

[0043] Preferably, in the original setting value determination module, the original setting value α 2Dem原 is determined by the following formula:

[0044] α 2Dem原 = k1(f(n 2r ) + Δα 2_n2r ) + k2(f(n 2r25 ) + Δα 2_n2r25 );

[0045] wherein, k1 and k2 are the weighting coefficients of f(n 2r ) and f(n 2r25 ), and Δα 2_n2r and Δα 2_n2r25 are the lead angle control offset amounts.

[0046] Preferably, in the lead limit value determination module, the lead limit value α 2限制值 is determined by the following formula:

[0047] α 2限制值 = f(n 2r ) + Δα 2_超前要求值中线 + err(n 2r ) 控制精度 ;

[0048] wherein, Δα 2_超前要求值中线 is the median value of the lead value range of the required adjustable vane angle α2 of the compressor, and err(n 2r ) 控制精度 is the adjustable vane angle α2 of the compressor during deceleration at the high-pressure conversion rotational speed n2r The control accuracy below.

[0049] The key point of this application lies in how to set reasonable limit values to ensure that the engine lead angle value can quickly meet the requirements.

[0050] This application can ensure that when the engine is tested before leaving the factory, it can quickly meet the inspection requirements, reduce the number of adjustments and test runs, not only save the test resources and the life of the engine, but also reduce the adjustment workload and improve the delivery efficiency of the engine. Brief Description of the Drawings

[0051] Figure 1 It is a flowchart of a preferred embodiment of the adjustable angle lead control method for the aeroengine deceleration process of this application. Detailed Embodiment

[0052] To make the purpose, technical solutions and advantages of the implementation 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 in the embodiments of this application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements with the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of this application. The embodiments described below by referring to the drawings are exemplary and are intended to explain this application and should not be construed as limiting this application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of this application without creative efforts shall fall within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the drawings.

[0053] The first aspect of this application provides an adjustable angle lead control method for the aeroengine deceleration process, as Figure 1 shown, mainly including:

[0054] Step S1, determining that the engine enters deceleration control;

[0055] Step S2, determining the first high-pressure conversion speed relative to the total temperature at the fan inlet and the second high-pressure conversion speed relative to the total temperature at the compressor inlet;

[0056] Step S3, determining the original given value of the compressor adjustable vane angle according to the lead angle control deviation amount of the compressor adjustable vane angle;

[0057] Step S4, interpolating the lead limit value of the compressor adjustable vane angle based on the midline value of the lead value range of the compressor adjustable vane angle;

[0058] Step S5, taking the smaller value of the original given value and the lead limit value as the final lead setting value of the compressor adjustable vane angle;

[0059] Step S6: Control the adjustable vane angle of the compressor to deflect forward with the forward set value.

[0060] In the prior art, the original given value calculated by the above step S3 is usually used to control the adjustable vane angle of the compressor. As described in the background art, since the value calculated in step S3 is too large, the deflection degree of the adjustable vane angle of the compressor is too large, resulting in an obvious tendency for the adjustable vane of the compressor to close. Therefore, in this application, a forward limit value is calculated through step S4. This forward limit value is smaller than the original given value calculated by the existing step S3. In step S5, this smaller forward limit value is selected as the forward set value, so that the adjustable vane of the compressor will not be overly closed. Thus, the given forward set value can exactly meet the factory inspection requirement value, that is, it can ensure that the inspection requirements are quickly met during the test run.

[0061] In some alternative embodiments, in step S1, determining that the engine enters deceleration control includes:

[0062] Step S11: Obtain the speed given value and the speed measured value;

[0063] Step S12: When the difference between the speed given value and the speed measured value is less than the set value, determine that the engine enters deceleration control.

[0064] In this embodiment, the set value can be determined according to the swing amount of the speed and the deceleration situation.

[0065] In some alternative embodiments, in step S2, determining the first high-pressure converted speed n 2r includes:

[0066]

[0067] where n2 is the high-pressure physical speed and T1 is the total temperature at the fan inlet;

[0068] Determining the second high-pressure converted speed n 2r25 includes:

[0069]

[0070] where T 25 is the total temperature at the compressor inlet, and T 25设计点 is the design value of the total temperature at the compressor inlet.

[0071] In some alternative embodiments, in step S3, the original given value α 2Dem原 is determined by the following formula:

[0072] α 2Dem原 = k1(f(n 2r) + Δα 2_n2r ) + k2(f(n 2r25 ) + Δα 2_n2r25 );

[0073] Among them, k1 and k2 are the weighting coefficients of f(n 2r ) and f(n 2r25 ), and Δα 2_n2r and Δα 2_n2r25 are the advance angle control deviation amounts.

[0074] In some alternative embodiments, in step S4, the advance limit value α 2限制值 is determined by the following formula:

[0075] α 2限制值 = f(n 2r ) + Δα 2_超前要求值中线 + err(n 2r ) 控制精度 ;

[0076] Among them, Δα 2_超前要求值中线 is the median value of the advance value range of the required adjustable vane angle α2 of the compressor, and err(n 2r ) 控制精度 is the control accuracy of the adjustable vane angle α2 of the compressor at the high-pressure corrected speed n 2r during the deceleration process.

[0077] The second aspect of this application provides an adjustable angle advance control device corresponding to the above method for an aero-engine deceleration process, mainly including:

[0078] A state determination module for determining that the engine enters deceleration control;

[0079] A high-pressure corrected speed calculation module for determining a first high-pressure corrected speed relative to the total temperature at the fan inlet and a second high-pressure corrected speed relative to the total temperature at the compressor inlet;

[0080] An original set value determination module for determining the original set value of the adjustable vane angle of the compressor according to the advance angle control deviation amount of the adjustable vane angle of the compressor;

[0081] An advance limit value determination module for interpolating the advance limit value of the adjustable vane angle of the compressor based on the median value of the advance value range of the adjustable vane angle of the compressor;

[0082] An advance set value determination module for using the smaller value of the original set value and the advance limit value as the final advance set value of the adjustable vane angle of the compressor;

[0083] The compressor adjustable vane angle control module is used to control the compressor adjustable vane angle to deflect in advance with the advance set value.

[0084] In some alternative embodiments, the state determination module includes:

[0085] A rotational speed parameter acquisition unit for acquiring a rotational speed set value and a rotational speed measured value;

[0086] A deceleration control signal generation unit for determining that the engine enters deceleration control when the difference between the rotational speed set value and the rotational speed measured value is less than a set value.

[0087] In some alternative embodiments, in the high-pressure converted rotational speed calculation module, the first high-pressure converted rotational speed n 2r includes:

[0088]

[0089] where n2 is the high-pressure physical rotational speed and T1 is the total temperature at the fan inlet;

[0090] Determine the second high-pressure converted rotational speed n 2r25 includes:

[0091]

[0092] where T 25 is the total temperature at the compressor inlet, and T 25设计点 is the design value of the total temperature at the compressor inlet.

[0093] In some alternative embodiments, in the original command set value determination module, the original command set value α 2Dem原 is determined by the following formula:

[0094] α 2Dem原 = k1(f(n 2r ) + Δα 2_n2r ) + k2(f(n 2r25 ) + Δα 2_n2r25 );

[0095] where k1 and k2 are the weighting coefficients of f(n 2r ) and f(n 2r25 ), and Δα 2_n2r and Δα 2_n2r25 are the advance angle control offset amounts.

[0096] In some alternative embodiments, in the advance limit value determination module, the advance limit value α 2限制值 is determined by the following formula:

[0097] α 2限制值 = f(n2r ) + Δα 2_超前要求值中线 + err(n 2r ) 控制精度 ;

[0098] where Δα 2_超前要求值中线 is the median value of the leading value range of the required adjustable vane angle α2 of the compressor, and err(n 2r ) 控制精度 is the control accuracy of the adjustable vane angle α2 of the compressor at the high-pressure corrected speed n 2r during the deceleration process.

[0099] This application can ensure that when the engine leaves the factory for a test run, it can quickly meet the inspection requirements, reduce the number of adjustments and test runs, not only saving the test run resources and the life of the engine, but also reducing the adjustment workload and improving the delivery efficiency of the engine.

[0100] Although the present application has been described in detail above with general descriptions and specific implementation manners, based on the present application, some modifications or improvements can be made, which are obvious to those skilled in the art. Therefore, these modifications or improvements made without departing from the spirit of the present application all fall within the scope claimed by the present application.

Claims

1. An adjustable angle lead control method during the deceleration process of an aeroengine, characterized in that, Including: Step S1: Determine that the engine enters deceleration control; Step S2: Determine the first high-pressure corrected speed relative to the total temperature at the fan inlet and the second high-pressure corrected speed relative to the total temperature at the compressor inlet; Step S3: Determine the original given value of the adjustable vane angle of the compressor according to the advance angle control offset of the adjustable vane angle of the compressor; Step S4: Interpolate the advance limit value of the adjustable vane angle of the compressor based on the midline value of the advance value range of the adjustable vane angle of the compressor; Step S5: Use the smaller value of the original given value and the advance limit value as the final advance setting value of the adjustable vane angle of the compressor; Step S6: Control the adjustable vane angle of the compressor to deflect in advance with the advance setting value; Among them, in step S2, determining the first high-pressure conversion speed n 2r includes: Wherein, n2 is the high-pressure physical speed and T1 is the total temperature at the fan inlet; Determine the second high-pressure conversion speed n 2r25 Including: Among them, T 25 is the total inlet temperature of the compressor, and T 25设计点 is the designed value of the total inlet temperature of the compressor; In step S3, the original given value α 2Dem原 is determined by the following formula: α 2Dem原 = k1(f(n 2r ) + Δα 2_n2r ) + k2(f(n 2r25 ) + Δα 2_n2r25 ); Among them, k1 and k2 are the weighting coefficients of f(n 2r ) and f(n 2r25 ), △α 2_n2r and △α 2_n2r25 are the lead angle control deviation amounts; In step S4, the leading limit value α 2限制值 is determined by the following formula: α 2限制值 = f(n 2r ) + △α 2_超前要求值中线 + err(n 2r ) 控制精度 ; Among them, △α 2_超前要求值中线 is the median value of the leading value range of the required adjustable vane angle α2 of the compressor, and err(n 2r ) 控制精度 is the control accuracy of the adjustable vane angle α2 of the compressor during the deceleration process at the high-pressure corrected speed n 2r .

2. The adjustable angle lead control method during the deceleration process of an aeroengine according to claim 1, characterized in that In step S1, determining that the engine enters deceleration control includes: Step S11: Obtain the speed given value and the speed measured value; Step S12: When the difference between the speed given value and the speed measured value is less than the set value, determine that the engine enters deceleration control.

3. An adjustable angle lead control device during the deceleration process of an aeroengine, characterized in that, Including: A state determination module for determining that the engine enters deceleration control; A high-pressure corrected speed calculation module for determining the first high-pressure corrected speed relative to the total temperature at the fan inlet and the second high-pressure corrected speed relative to the total temperature at the compressor inlet; An original given value determination module for determining the original given value of the adjustable vane angle of the compressor according to the advance angle control offset of the adjustable vane angle of the compressor; An advance limit value determination module for interpolating the advance limit value of the adjustable vane angle of the compressor based on the midline value of the advance value range of the adjustable vane angle of the compressor; An advance setting value determination module for using the smaller value of the original given value and the advance limit value as the final advance setting value of the adjustable vane angle of the compressor; An adjustable vane angle control module of the compressor for controlling the adjustable vane angle of the compressor to deflect in advance with the advance setting value; Among them, in the high-pressure conversion speed calculation module, to determine the first high-pressure conversion speed n 2r includes: Wherein, n2 is the high-pressure physical speed and T1 is the total temperature at the fan inlet; Determine the second high-pressure conversion speed n 2r25 including: Among them, T 25 is the total inlet temperature of the compressor, and T 25设计点 is the designed value of the total inlet temperature of the compressor; In the original given value determination module, the original given value α 2Dem原 is determined by the following formula: α 2Dem原 = k1(f(n 2r ) + Δα 2_n2r ) + k2(f(n 2r25 ) + Δα 2_n2r25 ); Among them, k1 and k2 are the weighting coefficients of f(n 2r ) and f(n 2r25 ), △α 2_n2r and △α 2_n2r25 are the leading angle control deviation quantities; In the aforementioned leading limit value determination module, the leading limit value α 2限制值 is determined by the following formula: α 2限制值 = f(n 2r ) + △α 2_超前要求值中线 + err(n 2r ) 控制精度 ; Among them, △α 2_超前要求值中线 is the median value of the leading value range of the required adjustable vane angle α2 of the compressor, and err(n 2r ) 控制精度 is the control accuracy of the adjustable vane angle α2 of the compressor during the deceleration process at the high-pressure corrected speed n 2r .

4. The adjustable angle lead control device during the deceleration process of an aeroengine according to claim 3, characterized in that The state determination module includes: A speed parameter acquisition unit for acquiring the speed given value and the speed measured value; A deceleration control signal generation unit for determining that the engine enters deceleration control when the difference between the speed given value and the speed measured value is less than the set value.

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