CN108680359B - Airflow impulse gain measurement system and use method and application thereof - Google Patents
Airflow impulse gain measurement system and use method and application thereof Download PDFInfo
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- CN108680359B CN108680359B CN201810649225.8A CN201810649225A CN108680359B CN 108680359 B CN108680359 B CN 108680359B CN 201810649225 A CN201810649225 A CN 201810649225A CN 108680359 B CN108680359 B CN 108680359B
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/042—Testing internal-combustion engines by monitoring a single specific parameter not covered by groups G01M15/06 - G01M15/12
Abstract
The application discloses air current impulse gain measurement system, the system includes pulse laser light source, leaded light arm, beam splitter, front window observation camera, back window observation camera, front window light conversion camera lens, back window light conversion camera lens, combustion chamber and control computer, wherein, pulse laser light source transmission pulse laser, pulse laser is guided by leaded light arm extremely front window light conversion camera lens and back window light conversion camera lens, front window observation camera and back window observation camera set up the horizontal position of combustion chamber is used for shooing respectively the front and back window of combustion chamber, the control computer is gathered and is recorded data and control the operation of system. The application also discloses a method for measuring the airflow impulse gain by using the airflow impulse gain measuring system and application of the system and the measuring method.
Description
Technical Field
The application relates to an airflow impulse gain measurement system and a using method and application thereof, belonging to the field of performance evaluation and test measurement of a ramjet engine.
Background
Ramjets, including sub-combustion ramjets, super-combustion ramjets, and combinations thereof, are one type of air-breathing engine that utilizes atmospheric oxygen as all or part of the oxidant to react with its own entrained fuel. Unlike turbocharged aircraft engines, they utilize the impulse charging principle, relying on fixed structural components to compress and accelerate high velocity gas streams. The basic ramjet consists of an intake port, diffuser section, combustion chamber and tailpipe. The inlet channel captures and compresses air, which is then directed through a diffuser into the combustion chamber. In the combustion chamber, air reacts chemically with the fuel, and the chemical energy is converted into internal energy of gas by combustion. The gas expands and accelerates through the nozzle and finally is discharged into the atmosphere, and the gas velocity at the outlet of the nozzle is higher than that before entering the air inlet channel, so that forward thrust is generated. Thrust is the main performance parameter of a ramjet, which is a parameter that characterizes the magnitude of the operating capacity of the ramjet.
The calculation formula is as follows:
F＝meVe-ma Va+Ae(Pe-Pa)
wherein, F: thrust of engine
Ve: exhaust velocity at the nozzle outlet
Va: engine inlet air velocity
Pe: gas pressure at the outlet of the nozzle
Pa: atmospheric pressure at engine working height
Ae: cross-sectional area of exhaust surface of nozzle
Among the components of the thrust force component,
is the net thrust, which is closely related to the combustor performance and the flow conditions of the nozzle; m isaVaIs the ram resistance, which accounts for a significant proportion of the scramjet; a. thee(Pe-Pa) Is a pressure correction term that is small compared to the first term. As a key index of the engine, the thrust is a key parameter for evaluating the working performance of the engine, and the value of the thrust is mainly determined by the momentum difference of inlet and outlet airflow
Is also referred to as the impulse gain value. This value is the most core index parameter of the engine. In the current engine test, the value is not directly measured, and various measurement results such as internal thrust, bench thrust, thrust gain, cold thrust, hot thrust and the like are comprehensively considered. For the evaluation of the thrust performance of the scramjet, see the detailed description in the Master thesis of national defense science and technology university (research on the scramjet performance evaluation method, author: Wangfang, 2005). Parameters directly measured in the direct connection type engineering test are two macroscopic parameters of thrust and pressure, and the magnitude of the value is indirectly evaluated by acquiring the magnitude of a thrust gain value of a combustion chamber before and after ignition and a wall surface pressure integral value of the combustion chamber. The magnitude of the airflow velocity value is measured by contact methods such as a hot wire instrument and a pitot tube, but the methods are only suitable for low-speed flow. For high velocity ram air flows, the conventional method cannot be used, and in particular in the case of combustion, it is difficult to obtain values of the air flow velocity. The PIV method is a non-invasive flow field measurement method, can obtain the velocity of a two-dimensional flow field, and has larger data information amount compared with single-point data obtained by a Doppler frequency shift method. The PIV is used for measuring the flow direction section velocity value, so that the acceleration condition of the airflow in the combustion flow process can be calculated, and the internal microscopic information of the combustion chamber in the working process can be reflected more clearly. In the process of generating the thrust of the engine, the speed distribution of the spray pipe is interfered by various complex wave systems. Therefore, the acquisition of the plane information data has great significance for the evaluation of the air flow acceleration condition under the condition of uneven flow velocity distribution, particularly for the scramjet engine, the flow structure in the scramjet engine is very complex, and the uneven velocity distribution is more obvious. Obtaining the impulse gain of the airflow requires measuring the speed of the inlet and outlet of the engine at the same time. The existing PIV technology mostly adopts a single sheet light source, is influenced by the irradiation area and the intensity distribution uniformity of the sheet light source, and has limited area of a measuring region. If a plurality of PIV systems are adopted to work simultaneously, the difficulty of synchronous time sequence control and consistency control of the light source intensity is high. Therefore, the application of the PIV technology to the performance evaluation measurement of the engine is limited to the testMeasurement of local flow conditions in some complex flow regions within the combustion chamber at laboratory conditions, without scaling from this to obtain the macroscopic thrust performance of the engine.
Disclosure of Invention
According to an aspect of the application, an air current impulse gain measurement system is provided, the system includes pulse laser light source, leaded light arm, beam splitter, front window observation camera, back window observation camera, front window piece light conversion camera lens, back window piece light conversion camera lens, combustion chamber and control computer, wherein, pulse laser light source transmission pulse laser, pulse laser is guided by leaded light arm extremely front window piece light conversion camera lens and back window piece light conversion camera lens, front window observation camera and back window observation camera set up the horizontal position of combustion chamber is used for shooing respectively the front and back window of combustion chamber, the control computer gathers and the record data and control the operation of system.
The observation cameras in the invention are arranged in the direction perpendicular to the plane sheet light and respectively correspond to the front window and the rear window of the combustion chamber.
Preferably, the front window observation camera and the rear window observation camera are CCD cameras.
The CCD camera lens in the invention preferably adopts a macro fixed-focus lens, an optical filter is added in front of the lens to filter the influence of background light, and the environmental light is isolated from the experimental section as much as possible during the test. In a preferred embodiment, the camera shortest frame crossing time is 200 ns.
The camera lens preferably adopts a macro fixed-focus camera lens, an optical filter is added in front of the camera lens to filter the influence of background light, and the ambient light is isolated from the experimental section as much as possible during the test.
Preferably, the laser wavelength generated by the pulse laser light source is 532nm, and the single pulse duration is 6ns of point laser.
The laser light source used by the invention can have various different wavelengths and single pulse time, and the laser with the parameters is selected because the laser is the main selection type parameter of the experiment at present, and has the advantages of low cost, wide source and stable performance.
Preferably, the front window light conversion lens and the rear window light conversion lens are composed of convex lenses and cylindrical lenses, the focal length of the cylindrical lenses is 10-15m, preferably 12.5mm, and the focal length of the convex lenses is 800-1200mm, preferably 1000 mm.
Preferably, the distance between the front window light conversion lens and the rear window light conversion lens is 0.2-2 m.
Preferably, the system further comprises a synchronous controller, wherein the synchronous controller is respectively connected with the pulse laser light source, the front window observation camera, the rear window observation camera and the control computer in the system and used for coordinating synchronous work among all the components.
In a preferred embodiment of the present invention, when the system is in operation, the synchronization controller sends a signal to trigger the camera, and the camera receives the trigger signal and then sends a feedback signal back to the synchronizer, and at the same time, the first frame of the CCD camera starts to be exposed. After the pulse of the laser is delayed, the laser emits a first beam of pulse to illuminate the nano particles in the flow field when the first frame of the camera is exposed, and the capture of a first particle image is completed. Subsequently, a second frame of the CCD is exposed and simultaneously the image of the first frame is stored, during which time interval a second laser pulse is emitted, enabling capture and storage of a second image of the particle during the given time interval. The obtained pairs of particle scatter images are used to calculate the flow field velocity.
Preferably, the system further comprises N film light conversion lenses arranged between the front window film light conversion lens and the rear window film light conversion lens;
and N windows correspondingly arranged on the combustion chamber, wherein each sheet of light conversion lens corresponds to one window;
and N observation cameras which are correspondingly arranged at the horizontal positions of the windows, wherein each observation camera is used for shooting the window at the corresponding position.
The principle of PIV particle image velocity measurement is that firstly, the displacement of particles in each interrogation zone is calculated by adopting a cross-correlation algorithm, then the velocity in each interrogation zone is calculated according to the frame crossing time, and the calculated velocity field can be used for calculating the flow field parameters such as vorticity, flow lines and the like. The core of the PIV velocity field calculation is the calculation of the displacement vector. When the PIV calculates a velocity field, the whole image is divided into a plurality of inquiry areas, each inquiry area of the second image is traversed for a given inquiry area point in the first image, when the multiplication of the gray values in the two images is maximum, the connecting line between the two inquiry areas is the direction of a displacement vector, the velocity of the inquiry area can be calculated according to the frame crossing time, and by analogy, the velocity of the whole flow field can be calculated.
Therefore, in a preferred embodiment of the present invention, a multi-light PIV light source can be further developed from a dual-light source to form a plurality of interrogation zones, so as to obtain more abundant parameters. However, in the prior art, the flow field region adopting the single-sheet light PIV system is limited by the size of the irradiation area of the sheet light, and only the velocity field of a certain local region of the flow field can be obtained. The local information does not allow for thrust macro-performance of the engine.
According to another aspect of the present invention, there is provided a method of making an airflow impulse gain measurement using the airflow impulse gain measurement system, the method comprising:
1) introducing high-speed airflow containing tracer particles into a combustion chamber, and carrying out injection and combustion processes in the combustion chamber;
2) splitting a single beam of laser of a pulse laser light source, and obtaining a sheet light source through a conversion lens;
3) simultaneously acquiring velocity field distribution of flow direction cross sections near the inlet and outlet areas of the combustion chamber by using a front window observation camera and a rear window observation camera;
4) and obtaining an airflow impulse gain value by extracting the inlet and outlet speed difference value of the relevant position and multiplying the airflow impulse gain value by the mass flow.
Preferably, the gain value of the airflow impulse is calculated by the following formula:
I＝me Ve-ma Va
wherein I is the gain value of the airflow impulse,
Veis the exhaust velocity at the outlet of the combustion chamber,
Vais the velocity of the air at the inlet of the combustion chamber,
According to another aspect of the invention, the application of the airflow impulse gain measuring system and the airflow impulse gain measuring method in measuring the airflow impulse gain value at the inlet and the outlet of the engine is provided.
The beneficial effects that this application can produce include:
1) the impulse gain value of the air flow acceleration process is directly measured, and the generation process of the net thrust of the engine can be directly evaluated;
2) the thrust forming process of the airflow accelerated in the engine combustion chamber is directly measured, the heat-work conversion process of the combustion chamber and the spray pipe can be visually reproduced, and various thrust data information in the test is enriched;
3) two-dimensional velocity field information of the flow direction section of the engine is measured by adopting an optical method, so that direct flow interference cannot be generated on the internal flow field of the engine;
4) under the condition of uneven air flow speed at the inlet/outlet, compared with a one-dimensional speed measuring method, the method can improve the measuring precision of speed impulse, and particularly the condition that the speed distribution of the outlet of the spray pipe and the scramjet combustion chamber is uneven due to interference of various wave systems;
5) two or more light beams are from the same pulse laser, so that the problems of intensity distribution and time synchronism among the light sources are solved, the test error caused by the difficulty is avoided, and the optical path structure of the system is simpler.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate an exemplary embodiment of the invention and, together with the description, serve to explain the invention without unduly limiting the invention. In the drawings:
FIG. 1 is a system schematic of a monolithic optical PIV system;
FIG. 2 is a schematic diagram of an airflow impulse gain measurement system based on a dual-sheet optical PIV;
FIG. 3 is a calculation result of PIV images of front and rear observation windows obtained by the measurement of the biplate optical PIV system shown in FIG. 2;
FIG. 4 is a schematic illustration of an airflow momentum gain measurement method applied to a sub-combustion ramjet;
FIG. 5 is a schematic diagram of an airflow momentum gain measurement method applied to a scramjet engine.
The reference numerals in the figures denote the following meanings:
1 is a pulse laser light source, 2 is a laser light guide arm, 3 is the interval distance of double lights, 4 is a front window observation camera, 5 is a rear window observation camera, 6 is a front window light, 7 is a rear window light, 8 is a front window light conversion lens, 9 is a rear window light conversion lens, 10 is a combustion chamber with front and rear windows, 11 is a beam splitter of the light guide arm, 12 is a data acquisition and control computer, 13 is a synchronous controller, and 14 is an ICCD camera.
Detailed Description
The system and method of the present application are further described below in conjunction with the appended figures.
Fig. 1 is a system schematic of a monolithic optical PIV system. The PIV system is composed of a computer (12), a synchronous controller (13), a CCD camera (14) and a pulse laser light source 1. The computer is used for controlling the time sequence, collecting and storing pictures of the PIV system. The synchronous controller is controlled by a computer to send instructions to a laser and a CCD camera which generate a pulse laser light source; the exposure time of the CCD camera and the frame crossing time of the pulse laser can be adjusted by computer software. YAG laser generates point laser with wavelength of 532nm, the single pulse duration is as short as 6ns, the maximum energy of the single pulse can reach 500mJ, and the laser energy can be adjusted at about 200mJ during experiment. The point laser is changed into plane sheet light through the convex lens and the cylindrical lens. According to the test conditions of a laboratory, the focal length of the cylindrical lens used in the preferred embodiment is 12.5mm, the focal length of the convex lens is 1000mm, and the thickness of the sheet light obtained by verification is 0.5 mm. And (3) acquiring a particle scattering image by using an interline transmission CCD (charge coupled device), wherein the shortest frame spanning time of a camera is 200 ns. The CCD camera is placed in the direction perpendicular to the plane sheet light, the lens is preferably a macro fixed-focus lens, an optical filter is additionally arranged in front of the lens to filter the influence of background light, and the environment light is isolated from the experiment section as much as possible during the experiment. During operation, the synchronous controller sends a signal to trigger the camera, the camera receives the trigger signal and then sends a feedback signal back to the synchronizer, and meanwhile, the first frame of the CCD camera starts exposure. After the pulse of the laser is delayed, the laser emits a first beam of pulse to illuminate the nano particles in the flow field when the first frame of the camera is exposed, and the capture of a first particle image is completed. Subsequently, a second frame of the CCD is exposed and simultaneously the image of the first frame is stored, during which time interval a second laser pulse is emitted, enabling capture and storage of a second image of the particle during the given time interval. The obtained pairs of particle scatter images are used to calculate the flow field velocity. The principle of PIV particle image velocity measurement is that firstly, the displacement of particles in each interrogation zone is calculated by adopting a cross-correlation algorithm, then the velocity in each interrogation zone is calculated according to the frame crossing time, and the calculated velocity field can be used for calculating the flow field parameters such as vorticity, flow lines and the like. The core of the PIV velocity field calculation is the calculation of the displacement vector. When the PIV calculates a velocity field, the whole image is divided into a plurality of inquiry areas, each inquiry area of the second image is traversed for a given inquiry area point in the first image, when the multiplication of the gray values in the two images is maximum, the connecting line between the two inquiry areas is the direction of a displacement vector, the velocity of the inquiry area can be calculated according to the frame crossing time, and by analogy, the velocity of the whole flow field can be calculated. The flow field area of the single-chip light PIV system is limited by the irradiation area of the chip light, and only the velocity field of a certain local area of the flow field can be obtained. The local information does not allow for thrust macro-performance of the engine.
On the basis that a single-chip light PIV system obtains the numerical value of the flow direction section velocity field of a flow field, the invention provides a PIV system based on double-chip light or multi-chip light, and the velocity field information of a plurality of flow field section positions can be obtained under the condition of a single laser light source. Fig. 2 is a schematic diagram of a two-piece optical PIV system. The chosen example is a direct-coupled test situation, where a high-velocity gas stream containing tracer particles enters a front and rear windowed combustion chamber (10). And carrying out fuel injection and combustion processes in the combustion chamber to complete the heat-work conversion process. After the pulse laser light source (1) is generated, the pulse laser light source is transmitted through the laser light guide arm (2). When the light beam passes through the beam splitter of the light guide arm, the light beam is uniformly divided into two light beams with consistent intensity, and each light speed is continuously transmitted along the respective light guide arm. Then the linear laser is converted into a sheet light source by a front window light conversion lens (8) and a rear window light conversion lens (9) respectively, so that two beam light sources with a certain interval are formed. The spacing distance (3) of the double-plate light can be adjusted according to the requirements of a test field. A scattered image generated by the irradiation of the front window sheet light (6) on the flow field is recorded by the front window observation camera (4); the scattered image generated by the irradiation of the rear window sheet light (7) on the flow field is recorded by the rear window observation camera (5). The synchronous controller (13) is used for coordinating synchronous work among all parts.
Fig. 3 is a calculation result of the front and rear observation window PIV images obtained by the measurement of the biplate optical PIV system described in fig. 2. According to the PIV calculation result, the velocity integral value u on different flow direction cross sections can be obtained respectively1、u2、u3、u4。
Velocity gain value u on the same cross section2–u1，u4–u3The method can be used for evaluating local airflow gain, and the difference value of different cross sections can be used for evaluating the speed difference value of the inlet and converting the speed difference value into an airflow impulse gain value.
FIG. 4 is a schematic view of an airflow momentum gain measurement method applied to a sub-combustion ramjet engine. The double light sheets are respectively arranged at the inlet of the air inlet channel and the outlet of the spray pipe to obtain the gain value of the air flow impulse.
FIG. 5 is a schematic view of an airflow momentum gain measurement method applied to a scramjet engine. The double light sheets are respectively arranged at the inlet of the air inlet channel and the outlet of the spray pipe to obtain the gain value of the air flow impulse. Or a plurality of lights are positioned in the super-combustion chamber, and the airflow impulse gain increasing process is obtained.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modification, equivalent replacement, improvement, reduction or enlargement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A method of measuring an air flow momentum gain for a ramjet engine, the method comprising:
1) introducing high-speed airflow containing tracer particles into a combustion chamber, and carrying out injection and combustion processes in the combustion chamber;
2) splitting a single beam of laser of a pulse laser light source, and obtaining a sheet light source through a conversion lens;
3) simultaneously obtaining the velocity field distribution of the flow direction section near the inlet and outlet area of the combustion chamber by using a front window observation camera and a rear window observation camera which are arranged outside the combustion chamber;
4) obtaining an airflow impulse gain value by extracting an inlet-outlet speed difference value of a relevant position and multiplying the airflow impulse gain value by mass flow;
the airflow impulse gain measurement system correspondingly used in the method comprises a pulse laser light source, a light guide arm, a beam splitter, a front window observation camera, a rear window observation camera, a front window light conversion lens, a rear window light conversion lens, a combustion chamber and a control computer;
the pulse laser light source emits pulse laser, the pulse laser is guided to the front window light conversion lens and the rear window light conversion lens by the light guide arm, the front window light conversion lens and the rear window light conversion lens are arranged outside the combustion chamber, the front window observation camera and the rear window observation camera are located at the horizontal position of the combustion chamber and used for respectively shooting the front window and the rear window of the combustion chamber, and the control computer collects and records data and controls the operation of the system.
2. The method of measuring airflow momentum gain for a ramjet engine according to claim 1, wherein the front window viewing camera and rear window viewing camera are CCD cameras;
the CCD camera lens adopts a micro-distance fixed focus lens, and an optical filter is arranged in front of the micro-distance fixed focus lens.
3. The method of measuring airflow momentum gain for a ramjet according to claim 1, wherein the system further comprises N number of sheet light conversion lenses disposed between the front and rear sheet light conversion lenses;
and N windows correspondingly arranged on the combustion chamber, wherein each sheet of light conversion lens corresponds to one window;
and N observation cameras which are correspondingly arranged at the horizontal positions of the windows, wherein each observation camera is used for shooting the window at the corresponding position.
4. The method of measuring airflow momentum gain for a ramjet according to claim 1, wherein the pulsed laser light source generates a spot laser having a laser wavelength of 532nm and a single pulse duration of 6 ns.
5. The method as claimed in claim 1, wherein the front and rear window light conversion lenses are composed of convex lenses and cylindrical lenses, the focal length of the cylindrical lenses is 10-15mm, and the focal length of the convex lenses is 800-1200 mm.
6. The method of measuring airflow momentum gain for a ramjet according to claim 1, wherein the distance between the front and rear louver optical conversion lenses is 0.2-2 m.
7. The method as claimed in claim 1, wherein the system further comprises a synchronous controller, and the synchronous controller is respectively connected to the pulsed laser light source, the front window observation camera, the rear window observation camera and the control computer in the system, and is used for coordinating synchronous operation of all components.
8. The method of claim 1, wherein the gain value for the airflow impulse is calculated by the equation:
wherein I is the gain value of the airflow impulse,
Veis the exhaust velocity at the outlet of the combustion chamber,
Vais the velocity of the air at the inlet of the combustion chamber,
9. Use of the method of measuring an airflow impulse gain for a ramjet engine according to any of claims 1-8 for measuring an engine inlet outlet airflow impulse gain value.
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