CN110895200B - On-site calibration system for test bed of aerospace engine and calibration method for measurement and control unit of on-site calibration system - Google Patents
On-site calibration system for test bed of aerospace engine and calibration method for measurement and control unit of on-site calibration system Download PDFInfo
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Abstract
The invention provides a field calibration system of a test bed of an aerospace engine and a calibration method of a measurement and control unit of the field calibration system, wherein the field calibration system of flow measurement comprises a fuel supply unit, a turbine flowmeter assembly, the test bed of the engine, the measurement and control unit and the field calibration assembly, wherein the field calibration assembly comprises a decompression unit, a degassing unit and a passive volume pipe which are sequentially connected, the decompression unit is used for reducing the fuel pressure in a pipeline, the degassing unit is used for removing gas in fuel in the pipeline, and the passive volume pipe is used for collecting the volume of flow in the pipeline so as to calibrate the turbine flowmeter assembly. The turbine flow meter assembly is connected at one end to a fuel supply unit and at the other end is selectively connectable to a pressure relief unit in an engine test stand or field calibration assembly. By applying the technical scheme of the invention, the technical problem of low accuracy of on-site measurement of the flow of the engine caused by the influence of on-site environmental factors of the engine test bed, such as vibration, pressure, air bubbles and the like, in the prior art is solved.
Description
Technical Field
The invention relates to the technical field of flow measurement, in particular to a field calibration system of a test bed of an aerospace engine and a calibration method of a measurement and control unit of the field calibration system.
Background
The ground simulation test of the test bed of the space engine is an important component of the engineering of a development system of the space engine, wherein the flow is one of important parameters for evaluating the function, the performance and the stability of the space engine. The accurate measurement of the flow is crucial to determining the performance of the space engine, the measured value is directly used for calculating main performance parameters such as thrust, mixing ratio and characteristic speed of the space engine, and is also a main basis for determining parameters such as the missile-borne propellant quantity, the missile storage tank volume and the like, and important indexes such as the working time of the space engine, the flying speed of a missile, the range and the like are determined, so that the flow measurement precision of a test bed of the space engine is higher and higher in recent years, and the requirement of the original common test bed for 1.0% flow precision is improved to 0.5%.
The existing test bed of the aerospace engine comprises a large number of flowmeters, the flowmeters are mainly turbine flowmeters, used media comprise kerosene, lubricating oil and the like, and the media enter a pipeline under the action of a fuel pump and high-pressure gas, so that the media contain a certain amount of impurities such as bubbles and the like, and the pipeline vibration exists during testing, so that the precision of a flow measurement system of the test bed of the aerospace engine is influenced. At present, the calibration work of a flow measurement system of a test bed of an aerospace engine is usually carried out in a laboratory, namely a flowmeter is disassembled and sent to the laboratory, but in the actual use process, the flow measured by the calibrated flowmeter is different from the actual flow, namely, the flowmeter with the accuracy grade of 0.5 is adopted, the error caused in the actual field use can be increased to +/-5% to +/-10%, the overlarge flow measurement error of the test bed of the aerospace engine is caused, the propellant quantity and the storage tank volume of the aerospace engine are influenced, and further the working time of the aerospace engine, the flying speed and the range of a missile are influenced. Meanwhile, the field test conditions are complex, the flowmeter is difficult to disassemble and transport, and the field calibration work of the flow measurement system is not carried out yet.
Disclosure of Invention
The invention provides a field calibration system of a test bed of an aerospace engine and a calibration method of a measurement and control unit of the field calibration system, which can solve the technical problem of low flow measurement accuracy of the aerospace engine caused by the influence of field environment factors of the test bed of the aerospace engine such as vibration, pressure, bubbles and the like in the prior art.
According to an aspect of the invention, an on-site calibration system for flow measurement of an aerospace engine test bed is provided, and comprises: the fuel supply unit is used for supplying fuel to the on-site calibration system for measuring the flow of the test bed of the aerospace engine; the turbine flowmeter assembly is connected with the fuel supply unit pipeline and is used for measuring the flow of the fuel in the pipeline; the system comprises an engine test bed and a measurement and control unit, wherein the engine test bed is connected with the measurement and control unit, and the measurement and control unit is used for acquiring flow data of the engine test bed and a turbine flowmeter assembly; the on-site calibration assembly is connected with the fuel supply unit and comprises a pressure reduction unit, a degassing unit and a passive volume pipe, wherein the pressure reduction unit is used for reducing the pressure of the fuel in the pipeline, the degassing unit is used for removing gas in the fuel in the pipeline, and the passive volume pipe is used for collecting the volume of the fuel in the pipeline so as to calibrate the turbine flowmeter assembly; the turbine flowmeter assembly is selectively connected with a decompression unit in an engine test bed or a field calibration assembly, and when the field calibration system is in a normal test working state, the turbine flowmeter assembly is connected with the engine test bed; when the field calibration system is in a first measurement state, the turbine flowmeter assembly is connected with the pressure relief unit in the field calibration assembly, and the field calibration assembly is used for calibrating the turbine flowmeter assembly.
Further, the field calibration assembly further comprises: the mass flow meter is connected with the passive volume pipe and is used for measuring the mass flow of the fuel in the pipeline of the field calibration assembly; and the electric regulating valve is respectively connected with the passive volume tube and the fuel supply unit and is used for controlling the flow of the fuel in the pipeline.
Furthermore, the field calibration assembly further comprises a numerical control system, the numerical control system is respectively connected with the passive volume pipe and the turbine flowmeter assembly to acquire data of the passive volume pipe and the turbine flowmeter assembly, and the field calibration assembly calibrates the turbine flowmeter assembly according to the acquired data.
Furthermore, the field calibration system also has a second measurement state, and when the field calibration system is in the second measurement state, the field calibration component is connected with the measurement and control unit to calibrate the measurement and control unit.
Furthermore, the numerical control system also comprises a signal sending unit, the signal sending unit is connected with the measurement and control unit, and when the field calibration system is in a second measurement state, the signal sending unit sends a measurement signal to the measurement and control unit so as to calibrate the measurement and control unit.
Furthermore, the pressure reducing unit, the air eliminating unit, the electric switch valve, the mass flow meter, the passive volume pipe and the electric regulating valve are sequentially connected through the metal corrugated hose.
Further, the turbine flowmeter assembly comprises a plurality of turbine flowmeters, a plurality of switch valves and a plurality of regulating valves, the plurality of turbine flowmeters, the plurality of switch valves and the plurality of regulating valves are correspondingly arranged, and the flow ranges of the plurality of turbine flowmeters are different; when the on-site calibration system is in a normal working state, the turbine flowmeter assembly is connected with an engine test bed through a corrugated hose; the turbine flow meter is connected to the field calibration assembly by a bellows when the field calibration system is in a first measurement state.
According to another aspect of the present invention, a calibration method for a test bed measurement and control unit is provided, the calibration method for the test bed measurement and control unit uses an aerospace engine test bed flow measurement field calibration system, the aerospace engine test bed flow measurement field calibration system is the aerospace engine test bed flow measurement field calibration system, and the calibration method for the test bed measurement and control unit includes: firstly, a signal sending unit in a numerical control system sends a standard frequency signal to a measurement and control unit; secondly, the measurement and control unit receives and displays the frequency signal of the signal sending unit; and step three, calibrating the measurement and control unit according to the difference between the signal value displayed by the measurement and control unit and the signal value sent by the signal sending unit.
By applying the technical scheme of the invention, the field calibration of the turbine flowmeter assembly is realized through the field calibration assembly, the influence of pressure on the flow measurement of the test bed of the aerospace engine is effectively reduced or eliminated by arranging the decompression unit in the field calibration system, the influence of bubbles on the flow measurement of the test bed of the aerospace engine is effectively reduced or eliminated by arranging the air elimination unit in the field calibration system, the accuracy of the flow measurement of the test bed of the aerospace engine is improved by arranging the passive volume tube, the passive volume tube has higher flow measurement precision, the performance is more stable when the test is carried out under the environmental conditions of pressure and vibration, and the influence of the pressure and the vibration on the flow measurement of the test bed of the aerospace engine is effectively reduced. Compared with the prior art, the on-site calibration system provided by the invention can effectively reduce or eliminate the influence of environmental factors such as pressure, bubbles and vibration on the flow measurement of the test bed of the aerospace engine, realizes the calibration of a turbine flowmeter and a measurement and control unit in the flow measurement system of the test bed of the aerospace engine, and effectively improves the flow measurement precision of the test bed of the aerospace engine.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 shows a system block diagram of an aerospace engine test bed flow measurement field calibration system provided in accordance with a specific embodiment of the invention;
FIG. 2 is a schematic diagram illustrating two measurement states of an on-site calibration system for flow measurement of an aircraft engine test bed according to an embodiment of the invention;
FIG. 3 is a schematic diagram illustrating a calibration of a measurement and control unit according to an embodiment of the present invention;
FIG. 4 illustrates a schematic structural diagram of a turbine flow meter assembly provided in accordance with a specific embodiment of the present invention;
FIG. 5 illustrates a schematic diagram of a turbine flowmeter in-situ calibration method provided in accordance with a specific embodiment of the invention.
Wherein the figures include the following reference numerals:
10. a fuel supply unit; 20. a turbine flow meter assembly; 21. a turbine flow meter; 22. an on-off valve; 23. adjusting a valve; 30. an engine test bed; 40. a measurement and control unit; 50. a field calibration component; 51. a pressure reducing unit; 52. a degassing unit; 53. a passive volume tube; 54. a mass flow meter; 55. an electrically operated on-off valve; 56. an electric control valve; 57. and (4) a numerical control system.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the 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. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As shown in fig. 1 to 5, according to an embodiment of the present invention, there is provided an on-site calibration system for measuring flow rate of an aerospace engine test bed, the on-site calibration system for measuring flow rate of an aerospace engine test bed comprises a fuel supply unit 10, a turbine flowmeter assembly 20, an engine test bed 30, a measurement and control unit 40, and an on-site calibration assembly 50, wherein the fuel supply unit 10 is used for supplying fuel to the on-site calibration system for measuring flow rate of an aerospace engine test bed, the turbine flowmeter assembly 20 is connected to the fuel supply unit 10 in a pipeline, the turbine flowmeter assembly 20 is used for measuring flow rate of fuel in the pipeline, the engine test bed 30 is connected to the measurement and control unit 40, the measurement and control unit 40 is used for collecting flow rate data of the engine test bed 30 and the turbine flowmeter assembly 20, the on-site calibration assembly 50 comprises a decompression unit 51, a degassing unit 52, and a passive volume tube 53 which are connected in sequence, the pressure reducing unit 51 is used to reduce the pressure of the fuel in the pipeline, the degassing unit 52 is used to remove gases from the fuel in the pipeline, and the passive volume tube 53 is used to take the volume of the fuel in the pipeline for calibrating the turbine flow meter assembly 20. The turbine flowmeter assembly 20 is selectively connected with the decompression unit 51 in the engine test bed 30 or the field calibration assembly 50, and when the field calibration system is in a normal test running working state, the turbine flowmeter assembly 20 is connected with the engine test bed 30; when the field calibration system is in the first measurement state, the turbine flow meter assembly 20 is connected to the pressure reduction unit 51 in the field calibration assembly 50, and the field calibration assembly 50 is used to calibrate the turbine flow meter assembly 20.
By applying the configuration mode, the field calibration of the turbine flowmeter assembly 20 is realized through the field calibration assembly 50, the influence of pressure on the flow measurement of the test bed of the aerospace engine is effectively reduced or eliminated by arranging the decompression unit 51 in the field calibration system, the influence of bubbles on the flow measurement of the test bed of the aerospace engine is effectively reduced or eliminated by arranging the air elimination unit 52 in the field calibration system, the flow measurement accuracy of the test bed of the aerospace engine is improved by arranging the passive volume tube 53, the passive volume tube 53 has higher flow measurement precision, the measurement performance is more stable under the environmental conditions of pressure and vibration, and the influence of the pressure and the vibration on the flow measurement of the test bed of the aerospace engine is effectively reduced. Compared with the prior art, the on-site calibration system provided by the invention can effectively reduce or eliminate the influence of environmental factors such as pressure, bubbles and vibration on the flow measurement of the test bed of the aerospace engine, realizes the calibration of the turbine flowmeter and the measurement and control unit 40 in the flow measurement system of the test bed of the aerospace engine, and effectively improves the flow measurement precision of the test bed of the aerospace engine.
As an embodiment of the present invention, the pressure reducing unit 51 is a pressure reducing valve, and the degassing unit 52 is a degassing filter, and when the fuel flows through the pressure reducing valve, the pressure reducing valve reduces the pressure of the high-pressure fuel in the pipeline to below 3MP, and the pressure reduction is favorable for the precipitation of bubbles and the protection of the passive volume pipe 53. The degassing filter separates gas in the medium, thereby achieving the purpose of reducing or eliminating the influence of bubbles on the flow measurement of the test bed of the space engine.
Further, as shown in fig. 1, in order to correct the influence of bubbles and adjust the flow rate in the on-site pipeline of the test bed of the aerospace engine, the on-site calibration assembly 50 further includes a mass flow meter 54, an electric switch valve 55 and an electric regulating valve 56, the electric switch valve 55 is respectively connected with the degassing unit 52 and the mass flow meter 54, the electric switch valve 55 is used for controlling the opening and closing of the fuel in the pipeline of the on-site calibration assembly 50, the mass flow meter 54 is connected with the passive volume pipe 53, and the mass flow meter 54 is used for measuring the mass flow rate of the fuel in the pipeline of the on-site calibration assembly 50. The electric control valve 56 is connected to the passive volume pipe 53 and the fuel supply unit 10, respectively, and the electric control valve 56 is used for controlling the flow rate of the fuel in the pipeline.
By applying the configuration mode, the mass flow of the fuel measured by the mass flow meter 54 corrects the measured volume of the passive volume pipe 53 of the on-site calibration system so as to reduce the influence of bubbles, the flow in the on-site calibration system is controlled by the electric switch valve 55 and the electric regulating valve 56 so as to provide back pressure for the on-site calibration assembly 50, thereby being beneficial to the smooth movement of the piston of the passive volume pipe 53, preventing cavitation and further reducing the influence of bubbles on flow measurement. Further, the mass flow meter 54 may estimate the flow in the pipeline prior to the actual flow measurement, so as to select a specific mass flow calibration point for calibrating the turbine flowmeter assembly 20. This approach enables the turbine meter assembly 20 to be calibrated at selected flow calibration points by estimating the fuel flow in the pipeline.
Further, as shown in fig. 1, in order to further improve the accuracy of the on-site calibration system for measuring flow of the test bed of the aerospace engine, the on-site calibration assembly 50 further includes a numerical control system 57, the numerical control system 57 is respectively connected to the passive volume pipe 53 and the turbine flowmeter assembly 20 to acquire data of the passive volume pipe 53 and the turbine flowmeter assembly 20, and the on-site calibration assembly 50 calibrates the turbine flowmeter assembly 20 according to the acquired data.
By adopting the configuration mode, the numerical control system 57 controls the electric switch valve 55 and the electric regulating valve 56 of the calibration system for the flow measurement field of the test bed of the engine, and the calibration system for the flow measurement field of the test bed of the aerospace engine is controlled in an automatic mode. Furthermore, the time corresponding to the standard volume of the fuel flowing through the passive volume pipe 53 is obtained by measuring the photoelectric switch signal of the passive volume pipe 53 through the numerical control system 57, so that the volume flow of the engine test bed is measured, and the flow measured by the passive volume pipe 53 is compared with the flow measured by the turbine flowmeter assembly 20 to calibrate the turbine flowmeter assembly 20. In addition, the numerical control system 57 can measure the pressure and the temperature in the passive volume tube 53, and the measurement state of the calibration system for the flow measurement field of the engine test bed can be monitored in such a way.
Further, as shown in fig. 2, in order to avoid that the field test channel of the flow collection and processing system of the test bed of the aerospace engine is long, and the influence of environmental factors causes drift and error to the flow collection and processing channel, the field calibration system further has a second measurement state, and when the field calibration system is in the second measurement state, the field calibration component 50 is connected with the measurement and control unit 40 to calibrate the measurement and control unit 40.
By applying the configuration mode, the measurement and control unit 40 is calibrated by sending a standard frequency signal by the measurement and control unit 40 of the field calibration assembly 50, so that the problem that the measurement and control unit 40 of the engine test bed cannot be calibrated due to incapability of being detached is solved, and a flow measurement result with higher precision can be obtained by testing and calibrating the rear-end acquisition channel of the turbine flowmeter assembly 20.
Further, as shown in fig. 3, in order to simulate the frequency signal output by the turbine flowmeter assembly 20 to calibrate the measurement and control unit 40, the numerical control system 57 further includes a signal sending unit, the signal sending unit is connected with the measurement and control unit 40, and when the field calibration system is in the second measurement state, the signal sending unit sends a measurement signal to the measurement and control unit 40 to calibrate the measurement and control unit 40.
As a specific embodiment of the present invention, a function generator may be used as the signal sending unit, the measurement and control unit 40 includes a data acquisition system and a computer/secondary meter, during the calibration process of the measurement and control unit 40, the function generator generates a standard frequency signal to simulate a frequency signal output by the turbine flowmeter assembly 20, and the standard frequency signal enters the data acquisition system of the measurement and control unit 40 and displays a flow value through the computer/secondary meter. The method comprises the steps of selecting calibration points for calibration when the turbine flowmeter assembly 20 is calibrated to obtain a relationship between frequency and flow, obtaining a conversion relationship between the frequency and the flow of each calibration point through least square fitting, and comparing the relationship between the frequency and the flow measured by the measurement and control unit 40 with a flow real value corresponding to the frequency sent by the function generator to obtain errors of each measurement channel. Moreover, a sectional calibration compensation mode is adopted to compensate the rear-end processing system of the turbine flowmeter assembly 20, the computer/secondary instrument coefficient of the calibration section calibration measurement and control unit 40 is divided according to requirements, and the compensation calibration is carried out on a flowmeter rear-end channel.
Further, in order to reduce the influence of pressure and vibration on the test bed flow measurement field calibration system, the pressure reduction unit 51, the air elimination unit 52, the electric switch valve 55, the mass flow meter 54, the passive volume tube 53, and the electric control valve 56 are connected in sequence through a metal bellows hose. By applying the configuration mode, the influence of pressure on the test bed flow field calibration system can be reduced by utilizing the pressure resistance of the metal corrugated hose, and the influence of a field vibration environment on the test bed flow measurement accuracy can be prevented by adopting the flexible connection of the metal corrugated hose between any two adjacent parts in the field calibration assembly. Moreover, the corrugated metal hose can prevent the influence of whole pipeline expend with heat and contract with cold deformation to the pipe connection, and this kind of mode can reduce pressure, vibration, temperature effectively to the influence of test bed flow measurement precision.
Further, as shown in fig. 4, in order to enable the on-site calibration system for flow measurement of test bed of the aerospace engine to be applicable to calibration of different flow ranges, the turbine flowmeter assembly 20 is configured to include a plurality of turbine flowmeters 21, a plurality of on-off valves 22 and a plurality of regulating valves 23, the plurality of turbine flowmeters, the plurality of on-off valves and the plurality of regulating valves are correspondingly arranged, and the flow ranges of the plurality of turbine flowmeters are different. The turbine flowmeter assembly 20 is connected to the engine test bed 30 via a metal bellows when the field calibration system is in a normal operating condition, and the turbine flowmeter is connected to the field calibration assembly 50 via a metal bellows when the field calibration system is in a first measurement condition.
By adopting the configuration mode, the on-site calibration system for the flow measurement of the test bed of the aerospace engine is suitable for measurement and calibration in a plurality of flow ranges by arranging a plurality of turbine flow meters 21 of different models, a plurality of switch valves 22 and a plurality of regulating valves 23. As a specific embodiment of the present invention, when the working pressure is below 3MPa, the turbine flowmeter assembly 20 is configured with four turbine flowmeters with different flow measurement ranges, the first turbine flowmeter can be selected to achieve flow measurement and calibration within the flow range of 0.95L/min to 100L/min, the second turbine flowmeter can be selected to achieve flow measurement and calibration within the flow range of 100L/min to 250L/min, the third turbine flowmeter can be selected to achieve flow measurement and calibration within the flow range of 250L/min to 400L/min, the fourth turbine flowmeter can be selected to achieve flow measurement and calibration within the flow range of 400L/min to 570L/min, by adopting the mode, the turbine flowmeter 21 with different flow ranges can realize the flow measurement and calibration within the flow range of 0.95L/min to 570L/min.
Furthermore, the two ends of the metal corrugated hose are in threaded connection, so that the corrugated hose connection between the turbine flowmeter assembly 20 and the engine test bed 30 can be disconnected under the condition that an engine test bed test is not carried out, the turbine flowmeter assembly 20 and the field calibration assembly 50 are connected through the corrugated hose, and the mode provides convenience for the access of the field calibration assembly 50, is simple and convenient to operate and is high in efficiency.
According to another aspect of the present invention, as shown in fig. 5, there is provided a turbine flowmeter field calibration method using the field calibration system as described above, the method including: disconnecting a corrugated hose between the turbine flowmeter assembly 20 and the engine test bed 30, and connecting the field calibration assembly 50 with the turbine flowmeter assembly 20 through the corrugated hose; step two, the fuel in the fuel supply unit 10 sequentially passes through the turbine flowmeter assembly 20, the decompression unit 51, the degassing unit 52 and the passive volume pipe 53 in the on-site calibration assembly 50 and returns to the fuel supply unit 10; and step three, the on-site calibration assembly 50 calibrates the turbine flowmeter assembly 20 according to the flow volume measured by the passive volume pipe 53.
By applying the method for calibrating the turbine flowmeter in the field, the turbine flowmeter assembly 20 and the field calibration assembly 50 are connected through the metal corrugated hose, the method can reduce or eliminate the influence of pressure and vibration in the field environment on flow measurement, effectively prevents the whole pipeline from deforming due to expansion caused by heat and contraction caused by cold, and is simple and convenient to operate and high in efficiency. Moreover, the pressure reducing unit 51 in the field calibration assembly 50 reduces the pressure of high-pressure fuel in the pipeline, so that the separation of bubbles is facilitated, the passive volume tube 53 is protected, the air eliminating unit 52 can separate the bubbles in the fuel, and the passive volume tube 53 has the characteristics of high precision and stable performance under the pressure and vibration environment conditions.
Further, in order to further reduce the influence of the bubbles on the flow measurement of the test bed of the space engine, the second step specifically includes: the fuel in the fuel supply unit 10 is returned to the fuel supply unit 10 through the turbine flowmeter assembly 20, the pressure reducing unit 51 in the field calibration assembly 50, the degassing unit 52, the electric switching valve 55, the mass flow meter 54, the passive volume pipe 53, and the electric regulating valve 56 in this order.
By applying the calibration method, the mass flow of the fuel is measured by the mass flow meter 54, the measured volume of the passive volume pipe 53 of the field calibration system is corrected, the electric switch valve 55 and the electric regulating valve 56 control the flow in the field calibration system, back pressure is provided for the field calibration assembly 50, smooth movement of the piston of the passive volume pipe 53 is facilitated, cavitation is prevented, and the influence of bubbles on flow measurement is further reduced. This kind of mode can further revise the bubble to the influence of in-line flow measurement precision, improves the degree of accuracy that on-the-spot calibration subassembly 50 flow measured. Further, the mass flow meter 54 may estimate the flow in the pipeline prior to the actual flow measurement, so as to select a specific mass flow calibration point for calibrating the turbine flowmeter assembly 20. This approach facilitates estimating fuel flow in the pipeline to enable calibration of the turbine meter assembly 20 at selected flow calibration points.
According to another aspect of the present invention, as shown in fig. 3, there is provided a calibration method of a test bed measurement and control unit, the calibration method of the test bed measurement and control unit uses the on-site calibration system, the method includes: firstly, a signal sending unit in the numerical control system 57 sends a standard frequency signal to the measurement and control unit 40; secondly, the measurement and control unit 40 receives and displays the frequency signal of the signal sending unit; and step three, calibrating the measurement and control unit 40 according to the difference between the signal value displayed by the measurement and control unit 40 and the signal value sent by the signal sending unit.
By applying the calibration method of the test bed measurement and control unit, the signal transmission unit of the numerical control system 57 transmits a standard frequency signal to the measurement and control unit 40 to calibrate the measurement and control unit 40, so that the problem that the measurement and control unit 40 of the engine test bed cannot be calibrated because the measurement and control unit cannot be disassembled is solved, and a more high-precision flow measurement result can be obtained by testing and calibrating a rear-end acquisition channel of the turbine flowmeter assembly 20.
As a specific embodiment of the present invention, the signal sending unit is configured as a function generator, the measurement and control unit 40 includes a data acquisition system and a computer/secondary meter, during the calibration process of the measurement and control unit 40, the function generator generates a standard frequency signal to simulate a frequency signal output by the turbine flowmeter assembly 20, and the standard quasi-frequency signal enters the data acquisition system of the measurement and control unit 40 and displays a flow value through the computer/secondary meter. The method comprises the steps of selecting calibration points for calibration when the turbine flowmeter assembly 20 is calibrated to obtain a relationship between frequency and flow, obtaining a conversion relationship between the frequency and the flow of each calibration point through least square fitting, and comparing the relationship between the frequency and the flow measured by the measurement and control unit 40 with a flow real value corresponding to the frequency sent by the function generator to obtain errors of each measurement channel. Moreover, a sectional calibration compensation mode is adopted to compensate the rear-end processing system of the turbine flowmeter assembly 20, the computer/secondary instrument coefficient of the calibration section calibration measurement and control unit 40 is divided according to requirements, the compensation calibration is carried out on the rear-end channel of the flowmeter, and the accuracy of the calibration system on the flow measurement site of the test bed of the space engine is improved.
In order to further understand the present invention, the on-site calibration system for measuring flow of the test bed of the aerospace engine, the on-site calibration method for the turbine flowmeter, and the calibration method for the test bed measurement and control unit of the aerospace engine of the present invention are described in detail below with reference to fig. 1 to 5.
As shown in fig. 1 to 5, the flow measurement field calibration system includes a fuel supply unit 10, a turbine flowmeter assembly 20, an engine test bed 30, a measurement and control unit 40, and a field calibration assembly 50, wherein the fuel power station serves as the fuel supply unit 10, the fuel power station delivers fuel to each pipeline during operation, the fuel is fuel oil, the turbine flowmeter assembly 20 includes a plurality of turbine flowmeters 21, a plurality of on-off valves 22, and a plurality of regulating valves 23, the turbine flowmeter assembly 20 can realize flow measurement in a range of 0.95L/min to 570L/min by providing the plurality of turbine flowmeters 21, the plurality of on-off valves 22, and the plurality of regulating valves 23, the engine test bed 30 is connected to the measurement and control unit 40, the measurement and control unit 40 includes a data acquisition system and a computer/secondary meter, wherein the data acquisition system is used for acquiring flow data of the engine test bed 30 and the turbine flowmeter assembly 20, a computer/secondary meter is used to display the measured flow.
The field calibration assembly 50 comprises a pressure reducing unit 51, an air elimination unit 52, an electric switch valve 55, a mass flow meter 54, a passive volume pipe 53 and an electric regulating valve 56 which are sequentially connected by a corrugated metal hose, wherein a pressure reducing valve can be used as the pressure reducing unit 51, an air elimination filter is used as the air elimination unit 52, the pressure reducing valve can reduce the pressure of high-pressure fuel oil in a pipeline to be below 3MPa, the reduction of the pressure is favorable for the precipitation of bubbles, and meanwhile, the passive volume pipe 53 is protected. The degassing filter is used for separating gas in fuel oil, the electric switch valve 55 is used for controlling the opening and closing of the fuel oil in the pipeline of the field calibration assembly 50, and the mass flow meter 54 is used for measuring the mass flow of the fuel in the pipeline of the field calibration assembly 50 so as to further correct the influence of bubbles on the test bed flow measurement field calibration system and estimate the test bed flow before calibration test.
The turbine flowmeter assembly 20 is selectively connected to the decompression unit 51 in the engine test bed 30 or the field calibration assembly 50, and the turbine flowmeter assembly 20 is connected to the engine test bed 30 through a metal bellows when the field calibration system is in a normal test operation state. When the field calibration system is in the first measurement state, the turbine flowmeter assembly 20 is connected to the pressure reduction unit 51 in the field calibration assembly 50 through a metal bellows, and the field calibration assembly 50 is used to calibrate the turbine flowmeter assembly 20. The field calibration system also has a second measurement state, and when the field calibration system is in the second measurement state, the field calibration component 50 is connected to the measurement and control unit 40 to calibrate the measurement and control unit 40.
As shown in fig. 1 and fig. 3, the field calibration assembly 50 further includes a numerical control system 57, wherein the numerical control system 57 includes a signal transmission unit, a function generator can be used as the signal transmission unit, the function generator generates a standard frequency signal to simulate a frequency signal output by the turbine flowmeter assembly 20, and the standard frequency signal enters a data acquisition system of the measurement and control unit 40 and displays a flow value through a computer/secondary meter. The method comprises the steps of selecting calibration points for calibration when the turbine flowmeter assembly 20 is calibrated to obtain a relationship between frequency and flow, obtaining a conversion relationship between the frequency and the flow of each calibration point through least square fitting, and comparing the relationship between the frequency and the flow measured by the measurement and control unit 40 with a flow real value corresponding to the frequency sent by the function generator to obtain errors of each measurement channel. Moreover, a sectional calibration compensation mode is adopted to compensate the rear-end processing system of the turbine flowmeter assembly 20, the computer/secondary instrument coefficient of the calibration section calibration measurement and control unit 40 is divided according to requirements, the compensation calibration is carried out on the rear-end channel of the flowmeter, and the accuracy of the calibration system on the flow measurement site of the test bed of the space engine is improved.
The method for field calibrating a turbine meter using the field calibration system of the present invention is described in detail below. Firstly, disconnecting a corrugated hose connection between the turbine flowmeter assembly 20 and the engine test bed 30, and connecting the field calibration assembly 50 with the turbine flowmeter assembly 20 through the corrugated hose; secondly, the fuel in the fuel power station sequentially passes through the switch valve 22, the turbine flowmeter 21 and the regulating valve 23 in the turbine flowmeter assembly 20, the pressure reducing valve, the degassing filter, the electric switch valve 55, the mass flowmeter 54, the passive volume pipe 53 and the electric regulating valve 56 in the field calibration assembly 50 to return to the fuel power station, the numerical control system 57 controls the electric switch valve 55 and the electric regulating valve 56 to regulate the fuel flow in the pipeline, when the mass flow displayed by the mass flowmeter 54 is a calibration point, the passive volume pipe 53 is started, and the field calibration assembly 50 measures the flow of the flow measurement field calibration system; third, the numerical control system of the in situ calibration assembly 50 calibrates the turbine meter assembly 20 based on the measured flow volume of the passive volume tube 53.
The following describes a method for performing field calibration on a test bed measurement and control unit by using the field calibration system of the present invention in detail. Firstly, a function generator in the numerical control system 57 sends a standard frequency signal to the measurement and control unit 40; secondly, the data acquisition system of the measurement and control unit 40 receives the frequency signal of the function generator and displays the flow corresponding to the frequency signal through a computer/secondary instrument; thirdly, selecting different calibration points for calibration to obtain the relationship between the frequency and the flow, fitting according to a least square method to obtain the conversion relationship between the frequency and the flow of each calibration point, and comparing the relationship between the frequency and the flow measured by the measurement and control unit 40 with the real flow value corresponding to the frequency sent by the function generator to obtain the error of each measurement channel.
In conclusion, compared with the prior art, the on-site calibration system for the flow measurement of the test bed of the aerospace engine, the on-site calibration method for the turbine flowmeter and the calibration method for the test bed measurement and control unit of the aerospace engine can reduce the influence of on-site measurement accuracy of the flow of the aerospace engine caused by on-site environmental factors of the test bed of the engine such as vibration, pressure, bubbles and the like, realize on-site calibration for the flow measurement of the test bed of the aerospace engine, and solve the problems of additional measurement errors, unchanged disassembly and transportation of the flow measurement system and the like caused by different on-site actual use and laboratory calibration conditions of the measurement system.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides an on-spot calbiration system of space engine test run platform flow measurement which characterized in that, the on-spot calbiration system of space engine test run platform flow measurement includes:
a fuel supply unit (10), wherein the fuel supply unit (10) is used for supplying fuel for the on-site calibration system for measuring flow of the test bed of the aerospace engine;
a turbine flow meter assembly (20), the turbine flow meter assembly (20) being in line connection with the fuel supply unit (10), the turbine flow meter assembly (20) being for measuring the flow of fuel in the line;
the system comprises an engine test bed (30) and a measurement and control unit (40), wherein the engine test bed (30) is connected with the measurement and control unit (40), and the measurement and control unit (40) is used for collecting flow data of the engine test bed (30) and the turbine flowmeter assembly (20);
an on-site calibration assembly (50), wherein the on-site calibration assembly (50) is connected with the fuel supply unit (10), the on-site calibration assembly (50) comprises a pressure reduction unit (51), a degassing unit (52) and a passive volume pipe (53) which are connected in sequence, the pressure reduction unit (51) is used for reducing the pressure of the fuel in the pipeline, the degassing unit (52) is used for removing gas in the fuel in the pipeline, and the passive volume pipe (53) is used for collecting the volume of the fuel in the pipeline for calibrating the turbine flowmeter assembly (20);
wherein the turbine flowmeter assembly (20) is selectively connectable to the decompression unit (51) in the engine test stand (30) or the field calibration assembly (50), the turbine flowmeter assembly (20) being connected to the engine test stand (30) when the field calibration system is in a normal test run mode of operation; when the on-site calibration system is in a first measurement state, the turbine flowmeter assembly (20) is connected with the decompression unit (51) in the on-site calibration assembly (50), the on-site calibration assembly (50) is used for calibrating the turbine flowmeter assembly (20), the on-site calibration system further has a second measurement state, and when the on-site calibration system is in the second measurement state, the on-site calibration assembly (50) is connected with the measurement and control unit (40) so as to calibrate the measurement and control unit (40).
2. The on-site calibration system for flow measurement of an aerospace engine test bed according to claim 1, wherein the on-site calibration assembly (50) further comprises:
a mass flow meter (54) and an electric switch valve (55), wherein the electric switch valve (55) is respectively connected with the degassing unit (52) and the mass flow meter (54), the electric switch valve (55) is used for controlling the opening and closing of the fuel in the pipeline of the on-site calibration assembly (50), the mass flow meter (54) is connected with the passive volume pipe (53), and the mass flow meter (54) is used for measuring the mass flow of the fuel in the pipeline of the on-site calibration assembly (50);
and the electric regulating valve (56), the electric regulating valve (56) is respectively connected with the passive volume pipe (53) and the fuel supply unit (10), and the electric regulating valve (56) is used for controlling the flow of the fuel in the pipeline.
3. The on-site calibration system for flow measurement of an aerospace engine test bed according to claim 2, wherein the on-site calibration assembly (50) further comprises a numerical control system (57), the numerical control system (57) being connected to the passive volume tube (53) and the turbine flow meter assembly (20) respectively to acquire data of the passive volume tube (53) and the turbine flow meter assembly (20), the on-site calibration assembly (50) calibrating the turbine flow meter assembly (20) according to the acquired data.
4. The on-site calibration system for flow measurement of test beds of aerospace engines according to claim 3, wherein the numerical control system (57) further comprises a signal transmitting unit connected to the measurement and control unit (40), the signal transmitting unit transmitting a measurement signal to the measurement and control unit (40) for calibrating the measurement and control unit (40) when the on-site calibration system is in a second measurement state.
5. The on-site calibration system for flow measurement of a test bed of an aerospace engine according to claim 2, wherein the decompression unit (51), the air release unit (52), the electric on-off valve (55), the mass flow meter (54), the passive volume tube (53) and the electric regulating valve (56) are connected in sequence by a metal bellows.
6. The on-site calibration system for flow measurement of the test bed of the aerospace engine as claimed in claim 5, wherein the turbine flow meter assembly (20) comprises a plurality of turbine flow meters (21), a plurality of on-off valves (22) and a plurality of regulating valves (23), the plurality of turbine flow meters (21), the plurality of on-off valves (22) and the plurality of regulating valves (23) are correspondingly arranged, and the flow ranges of the plurality of turbine flow meters (21) are different; when the on-site calibration system is in a normal working state, the turbine flowmeter assembly (20) is connected with the engine test bed (30) through a metal corrugated hose; when the field calibration system is in a first measurement state, the turbine flowmeter assembly (20) is connected to the field calibration assembly (50) through a metal bellows.
7. A method for calibrating a test bed instrumentation unit, the method using the field calibration system of claim 4, the method comprising:
firstly, the signal sending unit in the numerical control system (57) sends a standard frequency signal to the measurement and control unit (40);
secondly, the measurement and control unit (40) receives and displays the frequency signal of the signal sending unit;
and thirdly, calibrating the measurement and control unit (40) according to the difference between the signal value displayed by the measurement and control unit (40) and the signal value sent by the signal sending unit.
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