CN116756866A - Engine dynamic performance real-time calculation method and system based on vehicle bench test data - Google Patents

Engine dynamic performance real-time calculation method and system based on vehicle bench test data Download PDF

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CN116756866A
CN116756866A CN202310609100.3A CN202310609100A CN116756866A CN 116756866 A CN116756866 A CN 116756866A CN 202310609100 A CN202310609100 A CN 202310609100A CN 116756866 A CN116756866 A CN 116756866A
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value
pressure turbine
air
pressure
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郑华雷
黄兴
苏志敏
李维
成本林
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Hunan Aviation Powerplant Research Institute AECC
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Hunan Aviation Powerplant Research Institute AECC
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Abstract

The invention discloses a real-time calculation method and a real-time calculation system for the dynamic performance of an engine based on vehicle bench test data. The whole calculation process is carried out based on the vehicle test data, simulation expansion is not needed through other methods, the dynamic performance calculation result is closer to the actual measurement result, and the calculation accuracy of the dynamic performance of the engine is greatly improved.

Description

Engine dynamic performance real-time calculation method and system based on vehicle bench test data
Technical Field
The invention relates to the technical field of engine dynamic performance calculation, in particular to an engine dynamic performance real-time calculation method and system based on vehicle test data, electronic equipment and a computer readable storage medium.
Background
The structure of the existing double-rotor turbojet engine is shown in figure 1, a rotating low-pressure turbine and a low-pressure compressor are connected on the same shaft, a rotating high-pressure turbine and a rotating high-pressure compressor are connected on the same shaft, a combustion chamber is arranged between the high-pressure turbine and the high-pressure compressor, air is continuously sucked by the low-pressure compressor through an air inlet device, enters the high-pressure compressor for continuous compression after compression, then enters the combustion chamber for fuel injection and combustion to form high-temperature fuel gas, the high-temperature fuel gas enters the high-pressure turbine from the combustion chamber for expansion work, the high-temperature fuel gas discharged from the high-pressure turbine enters the low-pressure turbine for continuous expansion work, the high-pressure turbine drives the high-pressure compressor through the high-pressure shaft, the low-pressure turbine drives the low-pressure compressor through the low-pressure shaft, and the outlet fuel gas of the low-pressure turbine is discharged into the atmosphere through a tail nozzle. The traditional dynamic performance calculation method is generally to model an engine based on a component method and analyze the dynamic performance of the engine, for example, a DYGEN calculation model based on the component method and a certain volumetric dynamics model published in the U.S. NASA in 1975, and a state space modeling method based on the component method is provided. The component method integrates the advantages of accurate calculation of the component method model and applicability to full flight envelope and the advantages of real-time calculation and wide convergence range of the volumetric dynamics model, and can complete the full-state real-time calculation of various types of gas turbine engines. The specific calculation method is as follows:
Step (1), obtaining low rotation speed characteristics of the compressor and the turbine: the test characteristic data of the impeller mechanical parts such as the compressor, the turbine and the like usually only have the test characteristic above the slow vehicle, but the characteristic data below the slow vehicle, especially close to zero rotation speed, are not at all available, and are difficult to accurately obtain through a test method. The low rotation speed characteristic of the impeller machinery component generally needs to be expanded according to the test characteristic, and common component expansion methods comprise a cascade method, a proportionality coefficient method, a zero rotation speed characteristic line method, a back line method, an exponential extrapolation method, a support vector machine method and the like, and fig. 2 is a schematic diagram of the full state characteristic of the air compressor obtained by expanding the support vector machine.
Step (2), establishing an engine dynamic model: according to the principle of an aeroengine, the dynamic relationship between a high-pressure turbine and a rotor of a high-pressure compressor, the dynamic relationship between a low-pressure turbine and a rotor of a low-pressure compressor and the volumetric dynamic relationship between the high-pressure turbine, the low-pressure turbine and inlet and outlet flow of a spray pipe are satisfied, so that the equation describing the dynamic model of the double-rotor turbojet engine comprises 2 dynamic equations and 3 volumetric dynamic equations of the rotor.
And (3) solving an equation set, so as to obtain the dynamic performance of the engine.
However, due to factors such as actual matching and design differences of engine components, characteristics of the whole machine and dynamic process, and differences in component tests, and incapability of accurately obtaining low-state performance of the components, the calculated result of the dynamic performance of the engine by adopting a conventional method often has larger differences from the performance in actual test runs, and the dynamic performance of the engine cannot be accurately obtained in real time in the test runs of the vehicle platform due to the need of subsequent adjustment according to the test results.
Disclosure of Invention
The invention provides a real-time calculation method and system for dynamic performance of an engine based on test data of a vehicle, electronic equipment and a computer readable storage medium, which are used for solving the technical problem that the existing calculation method for dynamic performance of the engine cannot accurately obtain the dynamic performance of the engine in real time in test of the vehicle.
According to one aspect of the present invention, there is provided a method for calculating dynamic performance of an engine based on test data of a vehicle, for calculating dynamic performance of a dual-rotor turbojet engine in real time, comprising:
taking the measured air inlet channel flow as an initial guess value, and guessing the air system distribution, wherein the air system distribution comprises the air-entraining amount of the outlet of the low-pressure compressor, the air-releasing amount of the middle stage of the high-pressure compressor, the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor and the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor;
Respectively calculating a calculated value of a high-pressure turbine guide vane inlet flow function, a calculated value of a high-pressure turbine outlet temperature, a calculated value of a low-pressure turbine guide vane inlet flow function, a calculated value of a low-pressure turbine outlet temperature, a flow guess value of an exhaust nozzle and an outlet flow based on vehicle table test data, an air inlet flow guess value and an air system distributed guess value;
constructing a first residual equation based on the calculated value of the high-pressure turbine vane inlet flow function and the test value of the high-pressure turbine flow function, constructing a second residual equation based on the calculated value and the actual measured value of the high-pressure turbine outlet temperature, constructing a third residual equation based on the calculated value of the low-pressure turbine vane inlet flow function and the test value of the low-pressure turbine flow function, constructing a fourth residual equation based on the calculated value and the actual measured value of the low-pressure turbine outlet temperature, and constructing a fifth residual equation based on the flow guess value and the outlet flow of the tail nozzle;
constructing a residual equation set based on five residual equations, and iteratively solving the residual equation set by taking a guess value of the flow of the air inlet channel and a guess value distributed by the air system as iteration variables, so that the five residual values all meet the requirements, and further determining the actual values distributed by the flow of the air inlet channel and the air system;
The dynamic performance of the engine is calculated based on the inlet flow and the actual value of the air system distribution.
Further, the process of calculating the high pressure turbine vane inlet flow function based on the bench test data, the guess of the inlet flow and the guess of the air system distribution is specifically as follows:
calculating to obtain the air flow rate of the inlet of the combustion chamber based on the guess value of the air flow rate of the air inlet channel and the guess value distributed by the air system;
calculating to obtain the outlet temperature of the combustion chamber based on the actual measurement value of the fuel flow and the inlet air flow of the combustion chamber;
and calculating to obtain the high-pressure turbine guide vane inlet flow function based on the total pressure recovery coefficient of the combustion chamber, the actual measured value of the fuel flow, the calculated value of the outlet temperature of the combustion chamber and the calculated value of the inlet air flow of the combustion chamber.
Further, the process of calculating the high pressure turbine outlet temperature based on the bench test data, the guess of the inlet flow and the guess of the air system distribution is specifically:
the acceleration rate of the high-pressure compressor is calculated based on the actual measurement value of the rotation speed of the high-pressure compressor, and the acceleration work of the high-pressure rotor is calculated based on the acceleration rate of the high-pressure compressor, the rotational inertia of the high-pressure rotor and the rotation speed of the high-pressure compressor;
interpolating from the air turbine starter characteristic diagram according to the inlet pressure and the rotating speed of the air turbine starter to obtain the power of the air turbine starter;
Calculating to obtain high-pressure compressor work based on the guess value of the flow of the air inlet channel, the calculated value of the flow of the air inlet of the combustion chamber, the actual measured value of the total temperature of the outlet of the low-pressure compressor and the actual measured value of the total temperature of the outlet of the high-pressure compressor;
calculating to obtain high-pressure turbine work based on the calculated value of the high-pressure rotor acceleration work, the interpolation of the air turbine starter power and the calculated value of the high-pressure compressor work;
the high pressure turbine outlet temperature is calculated based on the calculated value of the high pressure turbine work and the calculated value of the combustor outlet temperature.
Further, the process of calculating the low pressure turbine vane inlet flow function based on the bench test data, the guess of the inlet flow and the guess of the air system distribution is specifically as follows:
summing the calculated value of the inlet air flow of the combustion chamber, the actual measured value of the fuel flow and the guess value of the cold air quantity led to the high-pressure turbine rotor by the high-pressure compressor outlet, and calculating to obtain the inlet flow of the high-pressure turbine rotor;
and summing the calculated value of the inlet flow of the high-pressure turbine rotor and the guess value of the cold air quantity led to the high-pressure turbine rotor by the high-pressure compressor outlet, calculating to obtain the inlet flow of the low-pressure turbine guide vane, and further calculating to obtain the inlet flow function of the low-pressure turbine guide vane.
Further, the process of calculating the low pressure turbine outlet temperature based on the bench test data, the guess of the inlet flow and the guess of the air system distribution is specifically:
the acceleration rate of the low-pressure compressor is calculated based on the actual measurement value of the rotation speed of the low-pressure compressor, and the acceleration work of the low-pressure rotor is calculated based on the acceleration rate of the low-pressure compressor, the rotational inertia of the low-pressure compressor and the rotation speed of the low-pressure compressor;
calculating to obtain low-pressure compressor work based on the guess value of the flow of the air inlet channel, the actual measured value of the total temperature of the inlet of the low-pressure compressor and the actual measured value of the total temperature of the outlet of the low-pressure compressor;
summing the low-pressure rotor acceleration power and the low-pressure air compressor power, and calculating to obtain low-pressure turbine power;
the low pressure turbine outlet temperature is calculated based on the calculated value of low pressure turbine work and the actual measured value of high pressure turbine outlet temperature.
Further, the process of calculating the flow guess and the outlet flow of the tail nozzle based on the vehicle bench test data, the guess of the flow of the air inlet channel and the guess of the distribution of the air system is specifically as follows:
calculating to obtain a flow guess value of the tail nozzle based on the air inlet channel flow guess value and the actual measurement value of the fuel flow;
and calculating the outlet flow of the tail pipe based on the actual measured value and the area of the total temperature and the total pressure of the tail pipe.
Further, the expression of the residual equation set is:
wherein ε 1 、ε 2 、ε 3 、ε 4 And epsilon 5 Representing five residual values, W 4, cor, calculation Representing calculated values of high pressure turbine vane inlet flow function, W 4,cor Test values representing high pressure turbine flow function, T 43, calculate And T 43 Representing calculated and actual measured values, W, of the high pressure turbine outlet temperature, respectively 45, cor, calculation Calculated value representing low pressure turbine vane inlet flow function, W 45,cor Test values representing low pressure turbine flow function, T 45, calculating And T 45 Representing calculated and actual measured values, W, of the low pressure turbine outlet temperature, respectively 8, calculating Indicating the flow guess value, W, of the tail nozzle 8 Representing the outlet flow of the tail pipe.
In addition, the invention also provides an engine dynamic performance real-time computing system based on the vehicle test data, which adopts the engine dynamic performance real-time computing method, comprising the following steps:
the iteration variable selection module is used for taking the measured air inlet channel flow as an initial guess value and performing guess value on air system distribution, wherein the air system distribution comprises the air-entraining amount of the outlet of the low-pressure compressor, the air-releasing amount of the middle stage of the high-pressure compressor, the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor and the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor;
The calculation module is used for respectively calculating a calculated value of the high-pressure turbine guide vane inlet flow function, a calculated value of the high-pressure turbine outlet temperature, a calculated value of the low-pressure turbine guide vane inlet flow function, a calculated value of the low-pressure turbine outlet temperature, a flow guess value of the tail nozzle and an outlet flow based on the vehicle bench test data, the air inlet flow guess value and the air system allocated guess value;
the residual equation construction module is used for constructing a first residual equation based on the calculated value of the high-pressure turbine guide vane inlet flow function and the test value of the high-pressure turbine flow function, constructing a second residual equation based on the calculated value and the actual measurement value of the high-pressure turbine outlet temperature, constructing a third residual equation based on the calculated value of the low-pressure turbine guide vane inlet flow function and the test value of the low-pressure turbine flow function, constructing a fourth residual equation based on the calculated value and the actual measurement value of the low-pressure turbine outlet temperature, and constructing a fifth residual equation based on the flow guess value and the outlet flow of the tail nozzle;
the iteration solving module is used for constructing a residual equation set based on five residual equations, and carrying out iteration solving on the residual equation set by taking the guess value of the flow of the air inlet channel and the guess value distributed by the air system as iteration variables, so that the five residual values meet the requirements, and the actual values distributed by the flow of the air inlet channel and the air system are determined;
And the dynamic performance calculation module is used for calculating the dynamic performance of the engine based on the flow of the air inlet channel and the actual value distributed by the air system.
In addition, the invention also provides an electronic device comprising a processor and a memory, wherein the memory stores a computer program, and the processor is used for executing the steps of the method by calling the computer program stored in the memory.
In addition, the present invention also provides a computer-readable storage medium storing a computer program for performing real-time calculation of engine dynamic performance based on vehicle test data, the computer program executing the steps of the method as described above when running on a computer.
The invention has the following effects:
according to the engine dynamic performance real-time calculation method based on the vehicle bench test data, the fact that accurate measurement cannot be conducted in the vehicle bench test is considered, so that the air inlet channel flow and the air system distribution flow are used as iteration variables, dynamic performance indexes of a high-pressure turbine, a low-pressure turbine and an exhaust nozzle are calculated respectively by combining the vehicle bench test data, a mathematical model of five residual equations is built based on calculated values and measured values of the dynamic performance indexes, the five residual equations are solved in an iteration mode based on the five iteration variables, and the five residual values meet design requirements until a set of iteration variables are found, and therefore the actual values of the air inlet channel flow and the air system distribution flow in the vehicle bench test are determined, and all section parameters and component performances of an engine can be calculated in real time in the vehicle bench test process. In addition, the whole calculation process is carried out based on the vehicle bench test data, simulation expansion is not needed through other methods, the calculation result of the dynamic performance of the engine is very close to the actual measurement result, and the calculation precision of the dynamic performance of the engine is greatly improved.
In addition, the engine dynamic performance real-time computing system based on the vehicle test data has the advantages.
In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
fig. 1 is a schematic structural view of a conventional twin-rotor turbojet engine.
Fig. 2 is a diagram showing the full state characteristics of a compressor obtained by expanding a support vector machine in the prior art.
Fig. 3 is a flowchart of a method for calculating engine dynamic performance based on vehicle test data in real time according to a preferred embodiment of the present application.
FIG. 4 is a schematic flow chart of calculating the high pressure turbine vane inlet flow function in a preferred embodiment of the application.
FIG. 5 is a schematic flow chart of the calculation of the high pressure turbine outlet temperature in the preferred embodiment of the application.
FIG. 6 is a schematic flow chart of calculating a low pressure turbine vane inlet flow function in a preferred embodiment of the application.
FIG. 7 is a schematic flow chart of the calculation of the low pressure turbine outlet temperature in the preferred embodiment of the invention.
FIG. 8 is a flow chart illustrating calculation of a flow guess for a tail nozzle in a preferred embodiment of the present invention.
Fig. 9 is a schematic block diagram of an engine dynamic performance real-time computing system based on vehicle test data according to another embodiment of the present invention.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
It will be appreciated that as shown in fig. 3, the preferred embodiment of the present invention provides a method for calculating the dynamic performance of a dual-rotor turbojet engine in real time based on vehicle test data, comprising the following steps:
step S1: taking the measured air inlet channel flow as an initial guess value, and guessing the air system distribution, wherein the air system distribution comprises the air-entraining amount of the outlet of the low-pressure compressor, the air-releasing amount of the middle stage of the high-pressure compressor, the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor and the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor;
step S2: respectively calculating a calculated value of a high-pressure turbine guide vane inlet flow function, a calculated value of a high-pressure turbine outlet temperature, a calculated value of a low-pressure turbine guide vane inlet flow function, a calculated value of a low-pressure turbine outlet temperature, a flow guess value of an exhaust nozzle and an outlet flow based on vehicle table test data, an air inlet flow guess value and an air system distributed guess value;
Step S3: constructing a first residual equation based on the calculated value of the high-pressure turbine vane inlet flow function and the test value of the high-pressure turbine flow function, constructing a second residual equation based on the calculated value and the actual measured value of the high-pressure turbine outlet temperature, constructing a third residual equation based on the calculated value of the low-pressure turbine vane inlet flow function and the test value of the low-pressure turbine flow function, constructing a fourth residual equation based on the calculated value and the actual measured value of the low-pressure turbine outlet temperature, and constructing a fifth residual equation based on the flow guess value and the outlet flow of the tail nozzle;
step S4: constructing a residual equation set based on five residual equations, and iteratively solving the residual equation set by taking a guess value of the flow of the air inlet channel and a guess value distributed by the air system as iteration variables, so that the five residual values all meet the requirements, and further determining the actual values distributed by the flow of the air inlet channel and the air system;
step S5: the dynamic performance of the engine is calculated based on the inlet flow and the actual value of the air system distribution.
It can be understood that, according to the engine dynamic performance real-time calculation method based on the vehicle bench test data in this embodiment, considering that the air inlet channel flow and the air system distribution flow cannot be accurately measured in the vehicle bench test, the air inlet channel flow and the air system distribution are used as iteration variables, the vehicle bench test data are combined to calculate the dynamic performance indexes of the high-pressure turbine, the low-pressure turbine and the tail nozzle respectively, a mathematical model of five residual equations is constructed based on the calculated values and the measured values of the dynamic performance indexes, and the five residual equations are iteratively solved based on the five iteration variables until a group of iteration variables are found so that the five residual values all meet the design requirements, thereby determining the actual values of the air inlet channel flow and the air system distribution flow in the vehicle bench test, and further performing real-time calculation on all the section parameters and the component performances of the engine in the vehicle bench test process. In addition, the whole calculation process is carried out based on the vehicle bench test data, simulation expansion is not needed through other methods, the calculation result of the dynamic performance of the engine is very close to the actual measurement result, and the calculation precision of the dynamic performance of the engine is greatly improved.
It will be appreciated that in step S1, since some air inlets are not subjected to the blowing test, there is a large error in the actually measured air inlet flow rate when the bench test is performed, and some air inlets with different shapes are not circular, so that the measured air inlet flow rate deviation is larger. At the same time, the flow distribution of the air system comprises the bleed air quantity B at the outlet of the low-pressure compressor LPC Intermediate stage discharge B of high-pressure compressor HPC Cold air quantity C led to high-pressure turbine rotor by high-pressure compressor outlet HNGV And the cold air quantity C led to the high-pressure turbine rotor by the outlet of the high-pressure compressor HPT These four real-time flow values are also not accurately measured when bench testing is performed. Therefore, the invention adopts the flow W of the air inlet channel 2 Air-entraining quantity B at outlet of low-pressure compressor LPC Intermediate stage discharge B of high-pressure compressor HPC Cold air quantity C led to high-pressure turbine rotor by high-pressure compressor outlet HNGV And the cold air quantity C led to the high-pressure turbine rotor by the outlet of the high-pressure compressor HPT As a guess, namely as an iteration variable, the five iteration variables are transformed in the subsequent calculation process to realize iteration solution.
It will be appreciated that, as shown in fig. 4, in the step S2, the process of calculating the high pressure turbine vane inlet flow function based on the vehicle table test data, the guess of the inlet flow rate and the guess of the air system distribution is specifically:
Step S201: calculating to obtain the air flow rate of the inlet of the combustion chamber based on the guess value of the air flow rate of the air inlet channel and the guess value distributed by the air system;
step S202: calculating to obtain the outlet temperature of the combustion chamber based on the actual measurement value of the fuel flow and the inlet air flow of the combustion chamber;
step S203: and calculating to obtain the high-pressure turbine guide vane inlet flow function based on the total pressure recovery coefficient of the combustion chamber, the actual measured value of the fuel flow, the calculated value of the outlet temperature of the combustion chamber and the calculated value of the inlet air flow of the combustion chamber.
Specifically, based on the guess value W of the flow of the air inlet channel 2 And the bleed air quantity B at the outlet of the low-pressure compressor LPC Calculating to obtain the inlet flow W of the high-pressure compressor 25 The calculation formula is as follows: w (W) 25 ＝W 2 -B LPC And is based on the inlet flow W of the high-pressure compressor 25 And the intermediate-stage discharge amount B of the high-pressure compressor HPC Calculating to obtain the outlet flow W of the high-pressure compressor 3 The calculation formula is as follows: . While the combustion chamber inlet air flow W 31 The calculation formula of (2) is as follows: w (W) 31 ＝W 3 -C HNGV -C HPT W is then 31 ＝W 2 -B LPC -B HPC -C HNGV -C HPT 。
Then, based on the actual measurement value W of the fuel flow rate f And combustor inlet air flow W 31 Calculating to obtain the outlet temperature T of the combustion chamber 4 The calculation formula can be expressed as: t (T) 4 ＝f 1 (W f ，W 31 ). The outlet temperature of the combustion chamber cannot be directly and accurately measured due to overhigh temperature, so the invention is calculated based on the fuel flow and the inlet air flow of the combustion chamber.
Then, based on the combustion chamber total pressure recovery coefficient delta B Actual measurement W of fuel flow f Calculated value T of combustion chamber outlet temperature 4 And combustor inlet air flow W 31 Calculated value of (2) is calculated to be highPressure turbine vane inlet flow function W 4, cor, calculation The calculation formula can be expressed as: w (W) 4, cor, calculation ＝f 2 (W f ,W 31 ,T 4 ,δ B ). It follows that only W needs to be determined 2 、B LPC 、B HPC 、C HNGV And C HPT The values of the five iteration variables can be calculated to obtain the inlet flow function W of the high-pressure turbine guide vane 4, cor, calculation 。
It will be appreciated that, as shown in fig. 5, in the step S2, the process of calculating the high-pressure turbine outlet temperature based on the vehicle table test data, the guess of the intake passage flow rate and the guess of the air system distribution is specifically:
step S211: the acceleration rate of the high-pressure compressor is calculated based on the actual measurement value of the rotation speed of the high-pressure compressor, and the acceleration work of the high-pressure rotor is calculated based on the acceleration rate of the high-pressure compressor, the rotational inertia of the high-pressure rotor and the rotation speed of the high-pressure compressor;
step S212: interpolating from the air turbine starter characteristic diagram according to the inlet pressure and the rotating speed of the air turbine starter to obtain the power of the air turbine starter;
step S213: calculating to obtain high-pressure compressor work based on the guess value of the flow of the air inlet channel, the calculated value of the flow of the air inlet of the combustion chamber, the actual measured value of the total temperature of the outlet of the low-pressure compressor and the actual measured value of the total temperature of the outlet of the high-pressure compressor;
Step S214: calculating to obtain high-pressure turbine work based on the calculated value of the high-pressure rotor acceleration work, the interpolation of the air turbine starter power and the calculated value of the high-pressure compressor work;
step S215: the high pressure turbine outlet temperature is calculated based on the calculated value of the high pressure turbine work and the calculated value of the combustor outlet temperature.
Specifically, the actual measurement value n of the high-pressure compressor rotation speed is firstly based on H Calculating to obtain the acceleration rate dn of the high-pressure compressor H Dt and then combining the high pressure rotor moment of inertia M H And the rotation speed n of the high-pressure compressor H Calculating to obtain the acceleration power P of the high-pressure rotor H,A The calculation formula is as follows: p (P) H,A ＝M H *n H *dn H /dt。
Then, the air turbine starter power P is interpolated from the air turbine starter characteristic map based on the inlet pressure and rotational speed of the air turbine starter Starting up . Wherein, the characteristic of the air turbine starter is that the rotation speed (abscissa) and the starting power (ordinate) form a curve corresponding to a certain inlet pressure, therefore, after measuring the inlet pressure and the rotation speed of the air turbine starter, the power P of the air turbine starter can be interpolated from the characteristic diagram Starting up 。
Then, based on the guess value W of the flow of the air inlet channel 2 Calculated value W of combustion chamber inlet air flow 31 Actual measurement T of total outlet temperature of low-pressure compressor 24 Actual measurement T of total outlet temperature of high-pressure compressor 3 Calculating to obtain the work P of the high-pressure compressor HPC The calculation formula can be expressed as: p (P) HPC ＝f 3 (W 2 ,W 31 ,T 24 ,T 3 )。
Then, the calculated value P of the acceleration work of the high-pressure rotor can be based H,A Interpolation of air turbine starter power P Starting up And calculated value P of high-pressure compressor work HPC Calculating to obtain high-pressure turbine work P HPT The calculation formula is as follows: p (P) HPT ＝P H,A +P HPC -P Starting up 。
Finally, a calculated value P based on the high-pressure turbine work HPT And a calculated value T of the combustion chamber outlet temperature 4 Calculating to obtain the outlet temperature T of the high-pressure turbine 43, calculate The calculation formula can be expressed as: t (T) 43, calculate ＝f 4 (T 4 ,P HPT ). It follows that only W needs to be determined 2 、B LPC 、B HPC 、C HNGV And C HPT The values of the five iteration variables can be calculated to obtain the outlet temperature T of the high-pressure turbine 43, calculate 。
It will be appreciated that, as shown in fig. 6, in the step S2, the process of calculating the low pressure turbine vane inlet flow function based on the vehicle table test data, the guess of the inlet flow rate and the guess of the air system distribution is specifically:
step S221: summing the calculated value of the inlet air flow of the combustion chamber, the actual measured value of the fuel flow and the guess value of the cold air quantity led to the high-pressure turbine rotor by the high-pressure compressor outlet, and calculating to obtain the inlet flow of the high-pressure turbine rotor;
step S222: and summing the calculated value of the inlet flow of the high-pressure turbine rotor and the guess value of the cold air quantity led to the high-pressure turbine rotor by the high-pressure compressor outlet, calculating to obtain the inlet flow of the low-pressure turbine guide vane, and further calculating to obtain the inlet flow function of the low-pressure turbine guide vane.
Specifically, the calculated value W based on the combustor inlet air flow is first calculated 31 Actual measurement W of fuel flow f And guess C of the amount of cold gas directed to the high pressure turbine rotor by the high pressure compressor outlet HNGV Summing, and calculating to obtain the inlet flow W of the high-pressure turbine rotor 41 The calculation formula is as follows: w (W) 41 ＝W 31 +W f +C HNGV 。
Then, based on the calculated value W of the inlet flow rate of the high-pressure turbine rotor 41 And guess C of the amount of cold gas directed to the high pressure turbine rotor by the high pressure compressor outlet HPT Summing to calculate the inlet flow W of the low-pressure turbine guide vane 45 The specific calculation formula is as follows: w (W) 45 ＝W 41 +C HPT Further calculating to obtain a low-pressure turbine guide vane inlet flow function W 45, cor, calculation Wherein the low pressure turbine vane inlet flow function W 45, cor, calculation Is calculated based on the principle of (a) and the high-pressure turbine guide vane inlet flow function W 4, cor, calculation The same is true, and therefore, will not be described in detail herein. It follows that only W needs to be determined 2 、B LPC 、B HPC 、C HNGV And C HPT The values of the five iteration variables can be calculated to obtain the inlet flow function W of the high-pressure turbine guide vane 4, cor, calculation 。
It will be appreciated that, as shown in fig. 7, in the step S2, the process of calculating the low pressure turbine outlet temperature based on the vehicle test data, the guess of the intake passage flow rate and the guess of the air system distribution is specifically:
step S231: the acceleration rate of the low-pressure compressor is calculated based on the actual measurement value of the rotation speed of the low-pressure compressor, and the acceleration work of the low-pressure rotor is calculated based on the acceleration rate of the low-pressure compressor, the rotational inertia of the low-pressure compressor and the rotation speed of the low-pressure compressor;
Step S232: calculating to obtain low-pressure compressor work based on the guess value of the flow of the air inlet channel, the actual measured value of the total temperature of the inlet of the low-pressure compressor and the actual measured value of the total temperature of the outlet of the low-pressure compressor;
step S233: summing the low-pressure rotor acceleration power and the low-pressure air compressor power, and calculating to obtain low-pressure turbine power;
step S234: the low pressure turbine outlet temperature is calculated based on the calculated value of low pressure turbine work and the actual measured value of high pressure turbine outlet temperature.
Specifically, the actual measurement value n of the low-pressure compressor rotation speed is firstly based on L Calculating the acceleration rate dn of the low-pressure compressor L Dt, then based on low pressure compressor acceleration rate dn L Moment of inertia M of dt and low pressure compressor L And the low-pressure compressor speed n L Calculating to obtain the acceleration power P of the low-pressure rotor L,A The calculation formula is as follows: p (P) L,A ＝M L *n L *dn L /dt。
Then, based on the guess value W of the flow of the air inlet channel 2 Actual measurement T of total inlet temperature of low-pressure compressor 2 And an actual measurement T of the total temperature of the outlet of the low-pressure compressor 24 Calculating to obtain the work P of the low-pressure air compressor LPC The calculation formula can be expressed as: p (P) LPC ＝f 5 (W 2 ,T 2 ,T 24 )。
Then, based on the low-pressure rotor acceleration work P L,A And low pressure work P LPC Summing, calculating to obtain low-pressure turbine work P LPT The calculation formula is as follows: p (P) LPT ＝P L,A +P LPC 。
Finally, a calculated value P based on low-pressure turbine work LPT And an actual measurement T of the high-pressure turbine outlet temperature 43 Calculating the outlet temperature T of the low-pressure turbine 45, calculating The calculation formula can be expressed as: t (T) 45, calculating ＝f 6 (T 43 ,P LPT ). It follows that only W needs to be determined 2 、B LPC 、B HPC 、C HNGV And C HPT The values of the five iteration variables can be calculated to obtain the outlet temperature T of the low-pressure turbine 45, calculating 。
It will be appreciated that, as shown in fig. 8, in the step S2, the process of calculating the flow guess value and the outlet flow of the tail pipe based on the vehicle test data, the air inlet flow guess value and the air system distribution guess value is specifically as follows:
step S241: calculating to obtain a flow guess value of the tail nozzle based on the air inlet channel flow guess value and the actual measurement value of the fuel flow;
step S242: and calculating the outlet flow of the tail pipe based on the actual measured value and the area of the total temperature and the total pressure of the tail pipe.
Specifically, based on the inlet flow guess W 2 And an actual measurement W of fuel flow f Calculating to obtain the flow guess W of the tail nozzle 8, calculating ，W 8, calculating ＝W 2 +W f . In addition, based on the total temperature T of the tail nozzle 8 And total pressure P 8 Actual measured value of (a) and area a 8 Calculating to obtain the outlet flow W of the tail nozzle 8 The calculation formula can be expressed as: w (W) 8 ＝f 7 (T 8 ,P 8 ,A 8 ). It can be seen that the outlet flow of the tail pipe is directly calculated based on the vehicle table data, and only W needs to be determined 2 、B LPC 、B HPC 、C HNGV And C HPT The values of the five iteration variables can be calculated to obtain the flow guess W of the tail nozzle 8, calculating 。
It will be appreciated that in said step S3, the test value W of the high pressure turbine flow function may be obtained directly during the bench test 4,cor Actual measurement T of high pressure turbine outlet temperature 43 Test value W of low pressure turbine flow function 45,cor Actual measurement T of low pressure turbine outlet temperature 45 Outlet flow W of tail nozzle 8 Thus, the calculated value W of the high pressure turbine vane inlet flow function may be based on 4, cor, calculation And test value W of high pressure turbine flow function 4,cor Constructing a first residual equation:calculated value T based on high pressure turbine outlet temperature 43, calculate And the actual measurement value T 43 Constructing a second residual equation: />Calculated value W based on low pressure turbine vane inlet flow function 45, cor, calculation And test value of low pressure turbine flow function W 45,cor Constructing a third residual equation: />Calculated value T based on low pressure turbine outlet temperature 45, calculating And the actual measurement value T 45 Constructing a fourth residual equation: />Flow guess W based on tail nozzle 8, calculating And outlet flow W 8 Constructing a fifth residual equation: />
It can be understood that in the step S4, the expression of the constructed residual equation set is:
Wherein ε 1 、ε 2 、ε 3 、ε 4 And epsilon 5 Representing five residual values, W 4, cor, calculation Representing calculated values of high pressure turbine vane inlet flow function, W 4,cor Test values representing high pressure turbine flow function, T 43, calculate And T 43 Representing calculated and actual measured values, W, of the high pressure turbine outlet temperature, respectively 45, cor, calculation Calculated value representing low pressure turbine vane inlet flow function, W 45,cor Test values representing low pressure turbine flow function, T 45, calculating And T 45 Representing calculated and actual measured values, W, of the low pressure turbine outlet temperature, respectively 8, calculating Indicating the flow guess value, W, of the tail nozzle 8 Representing the outlet flow of the tail pipe.
Then, guess value W is used for the flow of the air inlet channel 2 Air-entraining quantity B at outlet of low-pressure compressor LPC Intermediate stage discharge B of high-pressure compressor HPC Cold air quantity C led to high-pressure turbine rotor by high-pressure compressor outlet HNGV And the cold air quantity C led to the high-pressure turbine rotor by the outlet of the high-pressure compressor HPT And the five guesses are used as iteration variables to carry out iterative solution on the equation set until a group of iteration variables are found so that the five residual values all meet the design requirement, and therefore the actual values of the inlet channel flow and the air system distribution flow in the vehicle bench test are determined.
It can be understood that in the step S5, after the actual values of the inlet channel flow and the air system distribution flow in the bench test are calculated, all the section parameters and the component performances of the engine can be calculated in real time in the bench test process.
Specifically, during the bench test, for the intake duct, the intake duct flow W 2 Air-entraining quantity B at outlet of low-pressure compressor LPC Intermediate stage discharge B of high-pressure compressor HPC Cold air quantity C led to high-pressure turbine rotor by high-pressure compressor outlet HNGV And the cold air quantity C led to the high-pressure turbine rotor by the outlet of the high-pressure compressor HPT The actual value of (2) can be obtained through iterative solution calculation, so that the section parameter of the air inlet channel can be obtained through real-time calculation.
For low pressure compressors, the total inlet pressure P of the low pressure compressor 2 Total inlet temperature T 2 Total outlet pressure P 24 And the total temperature T of the outlet 24 Can be directly and accurately measured, so that the efficiency eta of the low-pressure compressor is improved LPC ＝f 8 (P 2 ,T 2 ,P 24 ,T 24 ) Can be directly calculated based on vehicle test data, and the work P of the low-pressure air compressor is obtained LPC ＝f 5 (W 2 ,T 2 ,T 24 ) Determination of W in iterative solution 2 And can be calculated later. Because ofThe section parameters and the component performance of the low-pressure compressor can be calculated in real time.
For high pressure compressors, the high pressure compressor inlet flow W 25 ＝W 2 -B LPC Outlet flow W 3 ＝W 25 -B HPC Determination of W in iterative solution 2 、B LPC 、B HPC 、C HNGV And C HPT And can be calculated later. Efficiency eta of high-pressure compressor HPC ＝f 9 (P 24 ,T 24 ,δ 25 ,P 3 ,T 3 ) Wherein the outlet total pressure P of the low-pressure compressor 24 And the total temperature T of the outlet 24 Outlet total pressure P of high-pressure compressor 3 And the total temperature T of the outlet 3 Can be directly and accurately measured, and the total pressure recovery coefficient delta of the transition section of the high-low pressure compressor 25 Is of known quantity, so the efficiency eta of the high-pressure compressor HPC Can be directly calculated based on the vehicle test data. While the high-pressure air compressor work P HPC ＝f 3 (W 2 ,W 31 ,T 24 ,T 3 ) Wherein, the outlet total temperature T of the low-pressure compressor 24 And the total outlet temperature T of the high-pressure compressor 3 Are all measured values, and the W is determined by iterative solution 2 、B LPC 、B HPC 、C HNGV And C HPT After that, W can be calculated 2 And W is 31 Thereby calculating and obtaining the work P of the high-pressure compressor HPC . Therefore, the section parameters and the component performance of the high-pressure compressor can be calculated in real time.
For the combustion chamber, the total outlet pressure P of the combustion chamber 4 Can be directly measured, and the outlet temperature T of the combustion chamber 4 ＝f 1 (W f ，W 31 ) Wherein the fuel flow W f Can be directly measured, and the inlet flow W of the combustion chamber 31 ＝W 2 -B LPC -B HPC -C HNGV -C HPT Determination of W in iterative solution 2 、B LPC 、B HPC 、C HNGV And C HPT The outlet temperature T of the combustion chamber can be calculated 4 . Thus, the cross-sectional parameters of the combustion chamber can be calculated in real timeObtained.
For high pressure turbines, the total outlet pressure P of the high pressure turbine 43 Total outlet temperature T 43 Can be directly measured to obtain the high-pressure turbine work P HPT ＝P H,A +P HPC -P Starting up Wherein the high-pressure rotor accelerates the work P H,A Can be calculated based on the rotation speed measurement result, and the work P of the high-pressure air compressor HPC Determination of W by iterative solution 2 、B LPC 、B HPC 、C HNGV And C HPT The power interpolation P of the air turbine starter can be calculated later Starting up Can be obtained by interpolation, so that the high-pressure aerodynamic work P can be calculated in real time HPC . While high pressure turbine efficiency eta HPT ＝f 10 (P 3 ,δ B ,T 4 ,P 43 ,T 43 ) Wherein, the outlet total pressure P of the high-pressure compressor 3 Total pressure P at high-pressure turbine outlet 43 And the total temperature T of the outlet 43 Can be directly measured to obtain the total pressure recovery coefficient delta of the combustion chamber B Is of known quantity and thus is calculated to obtain the combustion chamber outlet temperature T 4 Then, the high-pressure turbine efficiency eta can be calculated in real time HPT . Thus, the cross-sectional parameters and component performance of the high pressure turbine may be calculated in real time.
For low pressure turbines, the total outlet pressure P of the low pressure turbine 45 Total outlet temperature T 45 Can be directly measured, and the low-pressure turbine work P LPT ＝P L,A +P LPC Wherein the low-pressure rotor accelerates the work P L,A Based on the rotation speed measurement result, the work P of the low-pressure air compressor is calculated LPC ＝f 5 (W 2 ,T 2 ,T 24 )，T 2 And T 24 Are all measured values, and the W is determined by iterative solution 2 Then the low-pressure turbine work P can be calculated LPT . While low pressure turbine efficiency eta LPT ＝f 11 (P 43 ,T 43 ,P 45 ,T 45 ) Wherein the outlet total pressure P of the low-pressure turbine 45 And the total temperature T of the outlet 45 Outlet total pressure P of high-pressure turbine 43 And the total temperature T of the outlet 43 Can be directly measured, thus the low pressureTurbine efficiency eta LPT Can be directly calculated based on the vehicle test data. Thus, the cross-sectional parameters and component performance of the low pressure turbine may be calculated in real time.
For a jet nozzle, the jet nozzle outlet flow W 8 ＝f 7 (T 8 ,P 8 ,A 8 ) Wherein the total temperature T of the tail nozzle 8 And total pressure P 8 Can be directly measured, and the area A of the tail nozzle 8 The outlet flow of the tail pipe can be directly calculated based on the vehicle test data because the outlet flow of the tail pipe is a known quantity. Thus, the cross-sectional parameters and component performance of the tail nozzle can be calculated in real time.
Therefore, the invention takes the air inlet channel flow and the air system distribution flow as iteration variables, constructs five residual equations for iteration solution, and can calculate the full-section parameters and the performances of each part of the engine in real time after determining the actual values of the air inlet channel flow and the air system distribution flow in the vehicle test process. It will be appreciated that the function f in the present invention 1 ()～f 11 () Are well known calculation functions of the double-rotor turbojet engine, so specific expressions are not repeated here.
In addition, as shown in fig. 9, another embodiment of the present invention further provides a real-time calculation system for engine dynamic performance based on vehicle test data, preferably adopting the method for calculating engine dynamic performance in real time as described above, including:
The iteration variable selection module is used for taking the measured air inlet channel flow as an initial guess value and performing guess value on air system distribution, wherein the air system distribution comprises the air-entraining amount of the outlet of the low-pressure compressor, the air-releasing amount of the middle stage of the high-pressure compressor, the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor and the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor;
the calculation module is used for respectively calculating a calculated value of the high-pressure turbine guide vane inlet flow function, a calculated value of the high-pressure turbine outlet temperature, a calculated value of the low-pressure turbine guide vane inlet flow function, a calculated value of the low-pressure turbine outlet temperature, a flow guess value of the tail nozzle and an outlet flow based on the vehicle bench test data, the air inlet flow guess value and the air system allocated guess value;
the residual equation construction module is used for constructing a first residual equation based on the calculated value of the high-pressure turbine guide vane inlet flow function and the test value of the high-pressure turbine flow function, constructing a second residual equation based on the calculated value and the actual measurement value of the high-pressure turbine outlet temperature, constructing a third residual equation based on the calculated value of the low-pressure turbine guide vane inlet flow function and the test value of the low-pressure turbine flow function, constructing a fourth residual equation based on the calculated value and the actual measurement value of the low-pressure turbine outlet temperature, and constructing a fifth residual equation based on the flow guess value and the outlet flow of the tail nozzle;
The iteration solving module is used for constructing a residual equation set based on five residual equations, and carrying out iteration solving on the residual equation set by taking the guess value of the flow of the air inlet channel and the guess value distributed by the air system as iteration variables, so that the five residual values meet the requirements, and the actual values distributed by the flow of the air inlet channel and the air system are determined;
and the dynamic performance calculation module is used for calculating the dynamic performance of the engine based on the flow of the air inlet channel and the actual value distributed by the air system.
It can be understood that, in the engine dynamic performance real-time computing system based on the vehicle bench test data of the embodiment, considering that the air inlet channel flow and the air system distribution flow cannot be accurately measured in the vehicle bench test, the air inlet channel flow and the air system distribution are used as iteration variables, the vehicle bench test data are combined to respectively calculate the dynamic performance indexes of the high-pressure turbine, the low-pressure turbine and the tail nozzle, a mathematical model of five residual equations is constructed based on the calculated values and the measured values of the dynamic performance indexes, and the five residual equations are iteratively solved based on the five iteration variables until a group of iteration variables are found so that the five residual values all meet the design requirement, thereby determining the actual values of the air inlet channel flow and the air system distribution flow in the vehicle bench test, and further carrying out real-time calculation on all the section parameters and the component performances of the engine in the vehicle bench test process. In addition, the whole calculation process is carried out based on the vehicle bench test data, simulation expansion is not needed through other methods, the calculation result of the dynamic performance of the engine is very close to the actual measurement result, and the calculation precision of the dynamic performance of the engine is greatly improved.
In addition, another embodiment of the present invention also provides an electronic device, including a processor and a memory, where the memory stores a computer program, and the processor is configured to execute the steps of the method described above by calling the computer program stored in the memory.
In addition, another embodiment of the present invention also provides a computer-readable storage medium storing a computer program for performing real-time calculation of engine dynamic performance based on vehicle test data, the computer program executing the steps of the method as described above when running on a computer.
Forms of general computer-readable storage media include: a floppy disk (floppy disk), a flexible disk (flexible disk), hard disk, magnetic tape, any other magnetic medium, a CD-ROM, any other optical medium, punch cards, paper tape, any other physical medium with patterns of holes, a Random Access Memory (RAM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), a FLASH erasable programmable read-only memory (FLASH-EPROM), any other memory chip or cartridge, or any other medium from which a computer can read. The instructions may further be transmitted or received over a transmission medium. The term transmission medium may include any tangible or intangible medium that may be used to store, encode, or carry instructions for execution by a machine, and includes digital or analog communications signals or their communications with intangible medium that facilitate communication of such instructions. Transmission media includes coaxial cables, copper wire and fiber optics, including the wires that comprise a bus for transmitting a computer data signal.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
It will be appreciated by those skilled in the art that embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein. The scheme in the embodiment of the application can be realized by adopting various computer languages, such as object-oriented programming language Java, an transliteration script language JavaScript and the like.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. It is therefore intended that the following claims be interpreted as including the preferred embodiments and all such alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.

Claims (10)

1. The real-time calculation method for the dynamic performance of the engine based on the vehicle test data is used for calculating the dynamic performance of the double-rotor turbojet engine in real time and is characterized by comprising the following steps:
taking the measured air inlet channel flow as an initial guess value, and guessing the air system distribution, wherein the air system distribution comprises the air-entraining amount of the outlet of the low-pressure compressor, the air-releasing amount of the middle stage of the high-pressure compressor, the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor and the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor;
respectively calculating a calculated value of a high-pressure turbine guide vane inlet flow function, a calculated value of a high-pressure turbine outlet temperature, a calculated value of a low-pressure turbine guide vane inlet flow function, a calculated value of a low-pressure turbine outlet temperature, a flow guess value of an exhaust nozzle and an outlet flow based on vehicle table test data, an air inlet flow guess value and an air system distributed guess value;
Constructing a first residual equation based on the calculated value of the high-pressure turbine vane inlet flow function and the test value of the high-pressure turbine flow function, constructing a second residual equation based on the calculated value and the actual measured value of the high-pressure turbine outlet temperature, constructing a third residual equation based on the calculated value of the low-pressure turbine vane inlet flow function and the test value of the low-pressure turbine flow function, constructing a fourth residual equation based on the calculated value and the actual measured value of the low-pressure turbine outlet temperature, and constructing a fifth residual equation based on the flow guess value and the outlet flow of the tail nozzle;
constructing a residual equation set based on five residual equations, and iteratively solving the residual equation set by taking a guess value of the flow of the air inlet channel and a guess value distributed by the air system as iteration variables, so that the five residual values all meet the requirements, and further determining the actual values distributed by the flow of the air inlet channel and the air system;
the dynamic performance of the engine is calculated based on the inlet flow and the actual value of the air system distribution.
2. The method for calculating the dynamic performance of the engine based on the vehicle test data in real time according to claim 1, wherein the process for calculating the inlet flow function of the high-pressure turbine guide vane based on the vehicle test data, the guess of the flow rate of the air inlet passage and the guess of the distribution of the air system is specifically as follows:
Calculating to obtain the air flow rate of the inlet of the combustion chamber based on the guess value of the air flow rate of the air inlet channel and the guess value distributed by the air system;
calculating to obtain the outlet temperature of the combustion chamber based on the actual measurement value of the fuel flow and the inlet air flow of the combustion chamber;
and calculating to obtain the high-pressure turbine guide vane inlet flow function based on the total pressure recovery coefficient of the combustion chamber, the actual measured value of the fuel flow, the calculated value of the outlet temperature of the combustion chamber and the calculated value of the inlet air flow of the combustion chamber.
3. The method for calculating the engine dynamic performance based on the vehicle test data in real time according to claim 2, wherein the process for calculating the high-pressure turbine outlet temperature based on the vehicle test data, the guess of the inlet flow rate and the guess of the air system distribution is specifically as follows:
the acceleration rate of the high-pressure compressor is calculated based on the actual measurement value of the rotation speed of the high-pressure compressor, and the acceleration work of the high-pressure rotor is calculated based on the acceleration rate of the high-pressure compressor, the rotational inertia of the high-pressure rotor and the rotation speed of the high-pressure compressor;
interpolating from the air turbine starter characteristic diagram according to the inlet pressure and the rotating speed of the air turbine starter to obtain the power of the air turbine starter;
calculating to obtain high-pressure compressor work based on the guess value of the flow of the air inlet channel, the calculated value of the flow of the air inlet of the combustion chamber, the actual measured value of the total temperature of the outlet of the low-pressure compressor and the actual measured value of the total temperature of the outlet of the high-pressure compressor;
Calculating to obtain high-pressure turbine work based on the calculated value of the high-pressure rotor acceleration work, the interpolation of the air turbine starter power and the calculated value of the high-pressure compressor work;
the high pressure turbine outlet temperature is calculated based on the calculated value of the high pressure turbine work and the calculated value of the combustor outlet temperature.
4. The method for calculating the dynamic performance of the engine based on the vehicle test data in real time according to claim 3, wherein the process for calculating the inlet flow function of the low-pressure turbine guide vane based on the vehicle test data, the guess of the flow rate of the air inlet passage and the guess of the distribution of the air system is specifically as follows:
summing the calculated value of the inlet air flow of the combustion chamber, the actual measured value of the fuel flow and the guess value of the cold air quantity led to the high-pressure turbine rotor by the high-pressure compressor outlet, and calculating to obtain the inlet flow of the high-pressure turbine rotor;
and summing the calculated value of the inlet flow of the high-pressure turbine rotor and the guess value of the cold air quantity led to the high-pressure turbine rotor by the high-pressure compressor outlet, calculating to obtain the inlet flow of the low-pressure turbine guide vane, and further calculating to obtain the inlet flow function of the low-pressure turbine guide vane.
5. The method for calculating engine dynamic performance based on vehicle test data in real time according to claim 4, wherein the process for calculating the low pressure turbine outlet temperature based on vehicle test data, the guess of the inlet flow rate and the guess of the air system distribution is specifically as follows:
The acceleration rate of the low-pressure compressor is calculated based on the actual measurement value of the rotation speed of the low-pressure compressor, and the acceleration work of the low-pressure rotor is calculated based on the acceleration rate of the low-pressure compressor, the rotational inertia of the low-pressure compressor and the rotation speed of the low-pressure compressor;
calculating to obtain low-pressure compressor work based on the guess value of the flow of the air inlet channel, the actual measured value of the total temperature of the inlet of the low-pressure compressor and the actual measured value of the total temperature of the outlet of the low-pressure compressor;
summing the low-pressure rotor acceleration power and the low-pressure air compressor power, and calculating to obtain low-pressure turbine power;
the low pressure turbine outlet temperature is calculated based on the calculated value of low pressure turbine work and the actual measured value of high pressure turbine outlet temperature.
6. The method for calculating the dynamic performance of the engine based on the vehicle test data in real time according to claim 5, wherein the process for calculating the flow guess and the outlet flow of the tail pipe based on the vehicle test data, the air inlet flow guess and the air system assigned guess is specifically as follows:
calculating to obtain a flow guess value of the tail nozzle based on the air inlet channel flow guess value and the actual measurement value of the fuel flow;
and calculating the outlet flow of the tail pipe based on the actual measured value and the area of the total temperature and the total pressure of the tail pipe.
7. The method for calculating engine dynamic performance based on vehicle test data in real time according to claim 6, wherein the expression of the residual equation set is:
wherein ε 1 、ε 2 、ε 3 、ε 4 And epsilon 5 Representing five residual values, W 4, cor, calculation Representing calculated values of high pressure turbine vane inlet flow function, W 4,cor Test values representing high pressure turbine flow function, T 43, calculate And T 43 Representing calculated and actual measured values, W, of the high pressure turbine outlet temperature, respectively 45, cor, calculation Indicating lowCalculated value of pressure turbine vane inlet flow function, W 45,cor Test values representing low pressure turbine flow function, T 45, calculating And T 45 Representing calculated and actual measured values, W, of the low pressure turbine outlet temperature, respectively 8, calculating Indicating the flow guess value, W, of the tail nozzle 8 Representing the outlet flow of the tail pipe.
8. A real-time calculation system for engine dynamic performance based on vehicle test data, which adopts the real-time calculation method for engine dynamic performance according to any one of claims 1 to 7, and is characterized by comprising:
the iteration variable selection module is used for taking the measured air inlet channel flow as an initial guess value and performing guess value on air system distribution, wherein the air system distribution comprises the air-entraining amount of the outlet of the low-pressure compressor, the air-releasing amount of the middle stage of the high-pressure compressor, the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor and the air-cooling amount of the outlet of the high-pressure compressor led to the high-pressure turbine rotor;
The calculation module is used for respectively calculating a calculated value of the high-pressure turbine guide vane inlet flow function, a calculated value of the high-pressure turbine outlet temperature, a calculated value of the low-pressure turbine guide vane inlet flow function, a calculated value of the low-pressure turbine outlet temperature, a flow guess value of the tail nozzle and an outlet flow based on the vehicle bench test data, the air inlet flow guess value and the air system allocated guess value;
the residual equation construction module is used for constructing a first residual equation based on the calculated value of the high-pressure turbine guide vane inlet flow function and the test value of the high-pressure turbine flow function, constructing a second residual equation based on the calculated value and the actual measurement value of the high-pressure turbine outlet temperature, constructing a third residual equation based on the calculated value of the low-pressure turbine guide vane inlet flow function and the test value of the low-pressure turbine flow function, constructing a fourth residual equation based on the calculated value and the actual measurement value of the low-pressure turbine outlet temperature, and constructing a fifth residual equation based on the flow guess value and the outlet flow of the tail nozzle;
the iteration solving module is used for constructing a residual equation set based on five residual equations, and carrying out iteration solving on the residual equation set by taking the guess value of the flow of the air inlet channel and the guess value distributed by the air system as iteration variables, so that the five residual values meet the requirements, and the actual values distributed by the flow of the air inlet channel and the air system are determined;
And the dynamic performance calculation module is used for calculating the dynamic performance of the engine based on the flow of the air inlet channel and the actual value distributed by the air system.
9. An electronic device comprising a processor and a memory, the memory having stored therein a computer program for executing the steps of the method according to any of claims 1-7 by invoking the computer program stored in the memory.
10. A computer readable storage medium storing a computer program for real-time calculation of engine dynamics based on vehicle test data, characterized in that the computer program when run on a computer performs the steps of the method according to any one of claims 1 to 7.
CN202310609100.3A 2023-05-26 2023-05-26 Engine dynamic performance real-time calculation method and system based on vehicle bench test data Pending CN116756866A (en)

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