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CN114687877A - On-line calculation method for flow coefficient of injector nozzle based on injector inlet pressure wave - Google Patents

On-line calculation method for flow coefficient of injector nozzle based on injector inlet pressure wave Download PDF

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Publication number
CN114687877A
CN114687877A CN202011638905.3A CN202011638905A CN114687877A CN 114687877 A CN114687877 A CN 114687877A CN 202011638905 A CN202011638905 A CN 202011638905A CN 114687877 A CN114687877 A CN 114687877A
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pressure
wave
inlet
flow coefficient
fuel
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董全
周谈庆
杨晰宇
王迪
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Harbin Engineering University
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Harbin Engineering University
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1401—Introducing closed-loop corrections characterised by the control or regulation method
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/30—Controlling fuel injection
    • F02D41/38—Controlling fuel injection of the high pressure type
    • F02D41/40—Controlling fuel injection of the high pressure type with means for controlling injection timing or duration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1401—Introducing closed-loop corrections characterised by the control or regulation method
    • F02D2041/1409—Introducing closed-loop corrections characterised by the control or regulation method using at least a proportional, integral or derivative controller
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02D—CONTROLLING COMBUSTION ENGINES
    • F02D41/00—Electrical control of supply of combustible mixture or its constituents
    • F02D41/02—Circuit arrangements for generating control signals
    • F02D41/14—Introducing closed-loop corrections
    • F02D41/1401—Introducing closed-loop corrections characterised by the control or regulation method
    • F02D2041/1413—Controller structures or design
    • F02D2041/1427—Decoupling, i.e. using a feedback such that one output is controlled by only one input

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Abstract

The invention discloses an on-line calculation method for a fuel injector nozzle flow coefficient based on fuel injector inlet pressure waves. Installing a pressure sensor on a high-pressure oil pipe of the oil sprayer, and collecting the pressure at the inlet of the oil sprayer; obtaining a pressure change rate curve of the inlet pressure; obtaining a second derivative curve of the inlet pressure; the characteristic points and the second derivative on the pressure change rate curve are combined to judge the characteristic time when W1, W2 and W3 reach the measuring point; judging whether W3 reaches a pressure measurement point or not by using the obtained characteristic points on the second derivative curve, and decoupling W1 if the W3 does not reach the pressure measurement point to obtain a flow coefficient; and if the pressure test point is reached, decoupling the W1 and the W3 to obtain a flow coefficient. The invention aims to solve the problems of high cost, insufficient model precision and the like of the existing experimental method for measuring the nozzle flow coefficient.

Description

On-line calculation method for flow coefficient of injector nozzle based on injector inlet pressure wave
Technical Field
The invention belongs to the field of on-line measurement of flow coefficients of a nozzle of an oil sprayer, and particularly relates to an on-line calculation method of the flow coefficients of the nozzle of the oil sprayer based on pressure waves at the inlet of the oil sprayer.
Background
The flow coefficient is one of the most critical parameters of the fuel injection nozzle, and directly influences the spraying and emission characteristics of fuel. The transient flow coefficient of the nozzle can effectively reflect the actual dynamic change in the nozzle. The flow coefficient of the spray hole is measured in real time in the actual running process of the engine, and real-time effective feedback parameters can be provided for fault diagnosis and health evaluation of an oil sprayer in a control system and the control process of the oil spraying quantity under variable working conditions.
Currently, the evaluation of nozzle flow coefficients is usually performed by theoretical estimation or experimental measurement. The theoretical estimation method has low accuracy due to the difficulty in estimating the complex cavitation and pressure fluctuation conditions in the actual operation process of the engine. In addition, the theoretical estimation method can only calculate the average flow coefficient of a single injection and cannot realize transient measurement in the injection process. The time and equipment cost required by experimental measurement are too high, the measurement of the conventional device for measuring the flow coefficient is related to the sprayed fuel, a measuring device needs to be arranged outside a nozzle, the fuel cannot be directly sprayed into a cylinder, and the fuel can only be carried out on an experimental table and cannot be applied in the actual process of an engine, so that accurate basis cannot be provided for fault diagnosis and health assessment of the fuel injector.
With the continuous development of fuel systems, a great deal of information is contained in pressure fluctuation signals in a high-pressure common rail fuel system, and the pressure fluctuation signals become one of hot spots for studying the injection characteristics of the fuel systems for domestic and foreign students, however, the relation between the pressure fluctuation and the fuel injection characteristics in the actual operation process of an engine is still not studied thoroughly. Many studies of nozzle flow rate coefficients based on pressure fluctuations use the pressure fluctuations generated by the injection process directly in the calculation together with the pressure fluctuations generated by the non-injection process, resulting in an algorithm with insufficient accuracy.
At home and abroad, few methods for online measurement and research of the nozzle flow coefficient exist, and the research of the online measurement of the flow coefficient also meets the bottleneck. Therefore, the fuel system internal complex pressure change process is simplified into the Riemann wave evolution and transmission process based on the Riemann invariant theory, the pressure fluctuation generated in the non-injection process is decoupled, and a mathematical model of the inlet pressure and the flow coefficient of the fuel injector in the fuel injection process is provided.
Disclosure of Invention
The invention provides an on-line calculation method of a fuel injector nozzle flow coefficient based on inlet pressure waves of a fuel injector, which aims to solve the problems that the cost for measuring the nozzle flow coefficient by using the existing experimental method is high, the nozzle flow coefficient is required to be directly arranged outside a nozzle, the out-of-cylinder measurement cannot be realized, and the influence of pressure fluctuation caused by a non-injection process is not eliminated by the existing algorithm for calculating the fuel injection quantity and the flow coefficient based on the inlet pressure, so that the model precision is insufficient and the like.
The invention is realized by the following technical scheme:
an on-line calculation method for a fuel injector nozzle flow coefficient based on a fuel injector inlet pressure wave comprises the following steps:
step 1: installing a pressure sensor at a high-pressure oil pipe of the oil sprayer, and collecting the pressure at the inlet of the oil sprayer by using a data acquisition card;
step 2: obtaining a pressure change rate curve by derivation of the inlet pressure collected in the step 1;
and step 3: performing second-order derivation on the inlet pressure acquired in the step 1 to obtain a second-order derivative curve;
and 4, step 4: and (3) combining the characteristic points on the pressure change rate curve in the step (2) with the second derivative of the inlet pressure in the step (3) to judge the characteristic moments t when the left-row expansion waves W1 and W2 and the right-row compression wave W3 reach the measuring points1、t2、t3；
And 5: and obtaining a flow coefficient according to the inlet pressure of the oil injector by utilizing a Riemann invariant theory and a Bernoulli equation.
Step 6: judging whether W3 reaches a pressure measuring point or not according to the characteristic points on the second derivative curve obtained in the step 4, if not, performing the step 7, and if so, performing the step 8;
and 7: according to the characteristic points obtained in the step 4 and the relationship between the inlet pressure and the flow coefficient obtained in the step 5, only the pressure wave P generated by the leftward expansion wave W1 needs to be subjected toW1Decoupling is carried out;
and 8: obtained according to step 4And the relationship between the inlet pressure and the flow coefficient obtained in step 5, except for the pressure wave P generated by the leftward expansion wave W1W1Decoupling also requires a pressure wave P generated by a compression wave W3 traveling to the rightW3Decoupling is carried out;
further, the step 2 is specifically to find a trough of the incident wave or a crest or a trough of the reflected wave corresponding to the crest on the pressure change rate curve, so as to obtain Δ t; combining the propagation path of the pressure wave, obtaining the sound velocity a of the pressure wave propagation:
Figure BDA0002879394130000021
wherein L is the distance from the pressure measuring point to the oil rail end.
Further, t of the step 41The first point of the pressure second derivative curve is changed from 0 to negative;
t2is t1The first extreme point of the second derivative curve of the back pressure;
t3is t2The second derivative of the back pressure has a first zero point with a constant peak to valley at 0, changing from 0 to positive.
Further, the step 5 is to obtain a partial differential equation set according to a riemann invariant theory, a sound velocity equation and a conservation equation; according to a hyperbolic partial differential equation theory, simplifying a partial differential equation set into an ordinary differential characteristic line equation; in one-dimensional pipe flow, according to the Riemann wave invariant theory, a direct relation between the mass flow rate change rate dG and the pressure change rate dP is obtained as follows:
Figure BDA0002879394130000031
combining the definition of the flow coefficient and the Bernoulli equation to obtain the flow coefficient equation based on the pressure wave at the inlet of the oil injector as follows:
Figure BDA0002879394130000032
in the formula, PtestTo test the inlet pressure, CdIs the flow coefficient, ρ is the fuel density, AgeoIs the total area of the nozzle, A is the cross-sectional area of the high pressure oil pipe, PbAnd a is the fuel oil back pressure and the fuel oil sound velocity.
Further, the step 7 is specifically to utilize a flow coefficient equation based on the pressure wave at the inlet of the fuel injector,
Figure BDA0002879394130000033
in the formula, dPW1The calculation method of (2) is as follows:
Figure BDA0002879394130000034
in the formula, A1The inlet area for high-pressure oil into the control chamber, A2To control the outlet area of the chamber to air pressure, QcinFuel flow into the control chamber, QcoutTo the fuel flow out of the control chamber, PinjInlet pressure, P, for admission to the control chamber0At atmospheric pressure, PcFor controlling the pressure in the chamber, VcFor controlling the volume of the chamber, B is the modulus of elasticity of the fuel, Pinj0Is the initial pressure of the test site.
Further, step 8 is specifically to use a flow coefficient equation based on the pressure wave at the inlet of the injector:
Figure BDA0002879394130000035
in which dP is determined according to Riemann's invariant theory and the theory of total negative reflection of pressure wavesW3The calculation method of (2) is as follows:
Figure BDA0002879394130000041
wherein v is the fuel flow rate.
The invention has the beneficial effects that:
the invention can play a guiding role in the nozzle design stage, provides important basis for fault detection and health evaluation of the fuel injector in actual operation, reduces the complexity of an experimental device, improves the accuracy of flow coefficient measurement, and can be widely applied to the industry.
Compared with a theoretical estimation mode, the method provided by the invention not only considers the influence of the structural parameters of the oil injector on the flow coefficient, but also can predict the transient flow coefficient of the oil injector nozzle of the oil injector according to the real-time inlet pressure.
Compared with the existing flow coefficient measurement experiment device, the invention does not need to destroy the integral structure of the engine fuel injector and the combustion chamber, only needs to additionally arrange a rail pressure sensor on the high-pressure fuel pipe, has simple equipment, can realize measurement outside a cylinder, greatly reduces the cost for measuring the transient flow coefficient and breaks through the condition restriction that the measurement can only be carried out on an experiment table.
Compared with the existing mode of calculating the flow coefficient through inlet pressure fluctuation information, the method is based on the all-negative reflection theory of pressure waves, corrects the sound velocity of the fuel under different injection pressures by using the characteristic point on the pressure change rate derivative, and improves the accuracy of the algorithm.
Compared with the existing mode of calculating the flow coefficient through inlet pressure fluctuation information, the method is based on the Riemann invariant theory, and is used for decoupling pressure fluctuation components W1 and W3 generated by non-fuel injection in inlet pressure waves, so that the accuracy of the algorithm is further improved.
Drawings
FIG. 1 is a flow chart of the method of the present invention.
FIG. 2 is a model diagram of an on-line testing apparatus for nozzle flow coefficient according to the present invention.
FIG. 3 is a graph of the fuel sound speed correction of the present invention.
Fig. 4 is a pressure wave arrival measurement diagram of the present invention, in which (a) is a diagram of the decoupling process of W3 of the present invention, and (b) is a diagram of the effect of W3 of the present invention after decoupling.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
An on-line calculation method for a fuel injector nozzle flow coefficient based on a fuel injector inlet pressure wave comprises the following steps:
step 1: installing a pressure sensor at a high-pressure oil pipe of the oil sprayer, and collecting the pressure at the inlet of the oil sprayer by using a data acquisition card;
and 2, step: obtaining a pressure change rate curve by derivation of the inlet pressure collected in the step 1;
and step 3: performing second-order derivation on the inlet pressure acquired in the step 1 to obtain a second-order derivative curve;
and 4, step 4: and (4) combining the characteristic point on the pressure change rate curve in the step (2) with the second derivative of the inlet pressure in the step (3) to judge the characteristic time t of the left-going expansion waves W1 and W2 and the right-going compression wave W3 reaching the measuring point1、t2、t3；
And 5: obtaining a flow coefficient according to the inlet pressure of the oil injector by utilizing a Riemann invariant theory and a Bernoulli equation;
step 6: judging whether W3 reaches a pressure measuring point or not according to the characteristic points on the second derivative curve obtained in the step 4, if not, performing the step 7, and if so, performing the step 8;
and 7: according to the characteristic points obtained in the step 4 and the relationship between the inlet pressure and the flow coefficient obtained in the step 5, only the pressure wave P generated by the leftward expansion wave W1 needs to be subjected toW1Decoupling is carried out; since the left compression wave W1 is generated by control chamber venting when the needle valve is not open, W1 is not caused by the injection event, W1 is decoupled, and the inlet pressure wave rate of change dP from step 2 is usedinjSubtracting dPW1。
And 8: according to the characteristic points obtained in the step 4 and the relationship between the inlet pressure and the flow coefficient obtained in the step 5, except for the pressure wave P generated by the left-going expansion wave W1W1Decoupling also requires a pressure wave P generated by a compression wave W3 traveling to the rightW3The decoupling is performed.
Further, in the step 2, specifically, the left end is closed, the high-pressure common rail end is regarded as an isobaric reflection end, and after the pressure change at the measurement point caused by the incident wave is within the time of delta t, the action of the reflected wave on the pressure at the measurement point is the same in magnitude and opposite in direction; therefore, searching the wave trough or wave crest of the incident wave corresponding to the wave crest or wave trough of the reflected wave on the pressure change rate curve to obtain delta t; combining the propagation path of the pressure wave, obtaining the sound velocity a of the pressure wave propagation:
Figure BDA0002879394130000051
wherein L is the distance (unit: m) from the pressure measuring point to the oil rail end.
Further, t of the step 41The first point of the pressure second derivative curve is changed from 0 to negative;
t2is t1The first extreme point of the second derivative curve of the back pressure;
t3is t2The second derivative of the back pressure has a first zero point with a constant peak to valley at 0, changing from 0 to positive.
Further, step 5 is specifically to regard the high-pressure common rail end as an isobaric reflection end according to the riemann constancy theory, regard pressure fluctuation in the fuel system as one-dimensional unsteady pipe flow, ignore friction force and viscous influence of fluid, and obtain a partial differential equation set by a sound velocity equation and a conservation equation:
Figure BDA0002879394130000061
wherein, P is inlet pressure (unit: MPa), u is fuel flow speed (unit: m/s), and a is fuel sound speed (unit: m/s);
according to the hyperbolic partial differential equation theory, the partial differential equation set is simplified into an ordinary differential characteristic line equation:
Figure BDA0002879394130000062
Figure BDA0002879394130000063
in a one-dimensional pipe flow, if the propagation direction of the pressure wave coincides with the pipe flow direction, the pressure wave follows a characteristic line ΓRIf the propagation direction of the pressure wave is opposite to the direction of the pipe flow, the pressure wave follows a characteristic line ΓLThe above step (1); according to Riemann wave invariant theory, characteristic line gammaRAnd characteristic line gammaLUpper Riemann invariant dRRAnd dRLAre both 0; a direct relationship between the rate of change of mass flow dG and the rate of change of pressure dP is obtained as follows:
Figure BDA0002879394130000064
combining the definition of the flow coefficient and the Bernoulli equation to obtain the flow coefficient equation based on the pressure wave at the inlet of the oil injector as follows:
Figure BDA0002879394130000065
in the formula, PtestTo test the inlet pressure (in MPa), CdIs a flow coefficient, and rho is the fuel density (unit: g/mm)3)，AgeoIs the total area of the nozzle (unit: mm)2) And a is a cross-sectional area of the high-pressure oil pipe (unit: mm is2),PbIs the back pressure (unit: MPa) of the fuel injector, and a is the sound velocity (unit: m/s) of the fuel.
Further, the step 7 is specifically to utilize a flow coefficient equation based on the pressure wave at the inlet of the fuel injector,
Figure BDA0002879394130000071
in the formula, dPW1The calculation method of (2) is as follows:
Figure BDA0002879394130000072
in the formula, A1The inlet area (unit: mm) of high-pressure oil entering the control chamber2)，A2For controlling the area (unit: mm) of the outlet for the air pressure from the chamber2)，QcinFor the fuel flow into the control chamber (unit: mm)3)，QcoutFor the fuel flow out of the control chamber (unit: mm)3)，PinjThe inlet pressure (unit: MPa), P, into the control chamber0Is the atmospheric pressure (unit: MPa), PcFor controlling the pressure in the chamber (in MPa), VcTo control the volume of the chamber (unit: mm)3) B is the modulus of elasticity, P, of the fuel oilinj0The initial pressure (unit: MPa) of the test point.
Further, step 8 is specifically to use a flow coefficient equation based on the pressure wave at the inlet of the injector:
Figure BDA0002879394130000073
in which dP is determined according to Riemann's invariant theory and the theory of total negative reflection of pressure wavesW3The calculation method of (2) is as follows:
Figure BDA0002879394130000074
wherein v is the fuel flow rate (in m/s).
The W3 decoupling process and the waveform after decoupling are shown in fig. 4.

Claims (6)

1. An on-line calculation method for a fuel injector nozzle flow coefficient based on a fuel injector inlet pressure wave is characterized by comprising the following steps of:
step 1: installing a pressure sensor at a high-pressure oil pipe of the oil sprayer, and collecting the pressure at the inlet of the oil sprayer by using a data acquisition card;
step 2: the inlet pressure collected in the step 1 is derived to obtain a pressure change rate curve;
and 3, step 3: performing second-order derivation on the inlet pressure acquired in the step 1 to obtain a second-order derivative curve;
and 4, step 4: and (3) combining the characteristic points on the pressure change rate curve in the step (2) with the second derivative of the inlet pressure in the step (3) to judge the characteristic moments t when the left-row expansion waves W1 and W2 and the right-row compression wave W3 reach the measuring points1、t2、t3；
And 5: and obtaining a flow coefficient according to the inlet pressure of the oil injector by utilizing a Riemann invariant theory and a Bernoulli equation.
Step 6: judging whether W3 reaches a pressure measuring point or not according to the characteristic points on the second derivative curve obtained in the step 4, if not, performing the step 7, and if so, performing the step 8;
and 7: according to the characteristic points obtained in the step 4 and the relation between the inlet pressure and the flow coefficient obtained in the step 5, only the pressure wave P generated by the leftward expansion wave W1 is neededW1Decoupling is carried out;
and 8: according to the characteristic points obtained in the step 4 and the relationship between the inlet pressure and the flow coefficient obtained in the step 5, except for the pressure wave P generated by the leftward expansion wave W1W1Decoupling also requires a pressure wave P generated by a right-hand compression wave W3W3Decoupling is performed.
2. The on-line calculation method according to claim 1, wherein the step 2 is to find the trough of the incident wave or the peak of the reflected wave or the trough of the reflected wave corresponding to the trough of the incident wave on the pressure change rate curve, i.e. to obtain Δ t; combining the propagation path of the pressure wave, obtaining the sound velocity a of the pressure wave propagation:
Figure FDA0002879394120000011
wherein L is the distance from the pressure measuring point to the oil rail end.
3. The on-line computing method according to claim 1, wherein t of the step 4 is t1The first point of the pressure second derivative curve is changed from 0 to negative;
t2is t1The first extreme point of the second derivative curve of the back pressure;
t3is t2The second derivative of the back pressure has a first zero point with a constant peak to valley at 0, changing from 0 to positive.
4. The on-line calculation method according to claim 1, wherein the step 5 is specifically to obtain a partial differential equation set according to a Riemann invariant theory, a sound velocity equation and a conservation equation; according to a hyperbolic partial differential equation theory, simplifying a partial differential equation set into an ordinary differential characteristic line equation; in one-dimensional pipe flow, according to the Riemann wave invariant theory, a direct relationship between the rate of change of mass flow dG and the rate of change of pressure dP is obtained as follows:
Figure FDA0002879394120000021
combining the definition of the flow coefficient and the Bernoulli equation to obtain the flow coefficient equation based on the pressure wave at the inlet of the oil injector as follows:
Figure FDA0002879394120000022
in the formula, PtestTo test the inlet pressure, CdIs the flow coefficient, ρ is the fuel density, AgeoIs the total area of the nozzle, A is the cross-sectional area of the high pressure oil pipe, PbAnd a is the fuel oil back pressure and the fuel oil sound velocity.
5. The on-line calculation method according to claim 1, wherein the step 7 is implemented by using a flow coefficient equation based on a pressure wave at an inlet of the fuel injector,
Figure FDA0002879394120000023
in the formula, PbFor back pressure of fuel injector, dPW1The calculation method of (2) is as follows:
Figure FDA0002879394120000024
in the formula, A1The inlet area for high-pressure oil into the control chamber, A2To control the outlet area of the chamber to air pressure, QcinFuel flow into the control chamber, QcoutTo the fuel flow out of the control chamber, PinjInlet pressure, P, for admission to the control chamber0At atmospheric pressure, PcFor controlling the pressure in the chamber, VcFor controlling the volume of the chamber, B is the modulus of elasticity of the fuel, Pinj0Is the initial pressure of the test site.
6. The on-line calculation method according to claim 1, wherein the step 8 is specifically to use a flow coefficient equation based on a pressure wave at an inlet of the fuel injector:
Figure FDA0002879394120000031
in which dP is determined according to Riemann's invariant theory and the theory of total negative reflection of pressure wavesW3The calculation method of (2) is as follows:
Figure FDA0002879394120000032
wherein v is the fuel flow rate.
CN202011638905.3A 2020-12-31 2020-12-31 On-line calculation method for flow coefficient of injector nozzle based on injector inlet pressure wave Pending CN114687877A (en)

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