CN207610835U - Flow resistance force measuring device in a kind of wind tunnel test - Google Patents
Flow resistance force measuring device in a kind of wind tunnel test Download PDFInfo
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Abstract
The utility model is a kind of flow resistance force measuring device in the wind tunnel test for carrying out high-acruracy survey to flow resistance power in aircraft wind-tunnel, belongs to wind-tunnel technique field.It is not solved still with the problems such as pressure measurement errors caused by air-flow drift angle and differentiation of inside and outside outflux boundary accurate since pressure measurement rake number of probes is limited.The utility model proposes flow resistance force measuring devices in a kind of novel high-precision, it include the model support seat on pneumatic tulwar connector, one end that nearly pneumatic tulwar connector is seated against in the model support is equipped with TRAJECTORY CONTROL sliding rail, electric cylinder is fixed on TRAJECTORY CONTROL sliding rail, its telescopic end is connect with pressure measurement rake support arm, the free end that support arm is harrowed in pressure measurement is equipped with total pressure measurement probe array and static pressure measurement probe array, which is also equipped with the laser for getting piece light in the inner flow passage outlet of ventilating model in wind tunnel side wall.More effectively flow resistance power in aircraft can be measured.
Description
Technical Field
The invention relates to a wind tunnel test inflow resistance measuring device suitable for carrying out high-precision measurement on the inflow resistance of an aircraft in a wind tunnel, belonging to the technical field of wind tunnel tests.
Background
The internal flow resistance of the aircraft is closely related to the overall aerodynamic characteristics of the aircraft, and the measurement accuracy directly influences the aerodynamic performance evaluation of the aircraft. Meanwhile, along with the improvement of the flight Mach number (Ma), the size of the engine relative to the engine body is continuously increased, and the proportion of the resistance of the whole inner flow channel in the whole engine is continuously increased, so that how to measure the inner flow resistance with high precision has more and more important significance and value for the development of aircrafts.
The current wind tunnel test internal flow resistance measuring methods mainly comprise three types: firstly, adopt the design philosophy of non-contact in geometry when model and balance design, directly link to each other interior runner with the balance, keep interior runner and other parts that link to each other on the model incomplete contact simultaneously, the intermediate space utilizes sealing material to seal, then utilizes the balance directly to carry out the dynamometry to interior runner to obtain the internal flow resistance. And secondly, the static pressure distribution is obtained directly by arranging pressure measuring points on the pipe wall of the inner flow passage, so that the internal flow resistance of the ventilation model is indirectly calculated and measured. Thirdly, determining the internal flow resistance of the ventilation model according to the change of pipe flow momentum, namely, measuring the momentum and the average pressure of the section by arranging a pressure measuring rake at the position close to the outlet of the internal flow channel, and then converting by using formulas such as the difference of the inlet and the outlet flow quantities to obtain the internal flow resistance.
Among the three types of internal flow resistance measurement methods, the first method can theoretically achieve balance-level error accuracy, but is easily affected by interaction force between the internal flow channel and a model connecting part caused by elastic deformation of the model due to pneumatic load, and particularly has stronger influence on a complex model of an asymmetric internal flow channel, and provides quite high challenges for balance design and an internal and external flow pattern surface isolation technology. In addition, the sealing connection part of the inner flow profile and the outer profile structure always has the problems of slits, smoothness and the like which cannot be eliminated, and the influence on the flow characteristics of the boundary layer near the inlet of the inner flow channel is large. Particularly when the mach number of the incoming flow is high, certain deviation occurs in the flow similarity simulation, the sealing requirement is high, and otherwise, a new pneumatic load error is introduced. The second method is mainly limited by the influence of the arrangement density of the pressure measuring points on the pipe wall of the inner flow passage, and cannot obtain high-precision inner flow resistance, for example, the pressure measuring points cannot be arranged in the areas near the front edge and the like due to the limitation of the wall thickness of the model, and the pressure measuring points cannot be effectively arranged near the complex curved surface of the inner flow passage. The third method can measure the internal flow resistance, can obtain the flow rate flowing into the internal flow channel along the belt, and has higher significance for performance analysis of an aircraft propulsion system and the like. However, the measurement accuracy of the method is severely restricted by the arrangement number of the pressure measuring rakes at the outlet, the definition of the inner/outer flow boundaries and the total/static pressure measurement error caused by the airflow vector direction in front of the pressure measuring probe, and a novel measurement method needs to be explored urgently to meet the engineering application requirements.
With the emergence and continuous progress of various new technologies in the fields of materials, electronics, optics and the like, the flow display technology in the wind tunnel test is gradually developed. The Particle Image Velocimetry (PIV) technology can utilize a tracer to move along with a fluid, analyze a flow field structure according to the light scattering or excitation characteristics of the tracer, and obtain quantitative multi-parameter flow field information, such as full-field measurement of density, temperature, pressure, components and speed. Meanwhile, the nano-particle-based planar laser scattering system (NPLS) can well solve the problems of poor particle following performance and low signal-to-noise ratio in the existing high-Ma-number flow imaging technology, the technology is mature, and the engineering applicability is strong. The system can be considered to be used in the wind tunnel to improve the internal flow resistance measurement technology, so that a higher-precision internal flow resistance measurement method can be obtained. In recent years, preliminary research has been carried out and certain results are obtained, but mainly a two-dimensional PIV technology is adopted to measure the velocity fields of the longitudinal sections of the outlets of different inner flow channels, a large number of total pressure probe measurement rakes are arranged at the outlets, and the problems of pressure measurement errors caused by the limited number of probes of the pressure measurement rake and the deflection angle of the air flow, accurate separation of the boundaries of the inner and outer outlets and the like are still solved, and a new test method needs to be explored for research.
Disclosure of Invention
The invention aims to provide a novel high-precision internal flow resistance measuring device aiming at the technical precision defect of the traditional internal flow resistance measurement by utilizing pipe flow momentum change, and the novel high-precision internal flow resistance measuring device can be used for more effectively measuring the internal flow resistance of an aircraft.
The utility model provides a wind-tunnel test internal flow resistance measuring device, the device is including installing the model supporting seat on pnematic tulwar connecting piece, install the orbit control slide rail at this model supporting seat one end near pnematic tulwar connecting piece, electronic jar is fixed on the orbit control slide rail, its flexible end is connected with pressure measurement harrow support arm, install total pressure measurement probe array and static pressure measurement probe array at the free end of pressure measurement harrow support arm, the device still installs the laser instrument that is used for beating out the piece light at the interior runner export of the model of ventilating on the wind-tunnel lateral wall.
And the total pressure measurement probe array and the static pressure measurement probe array are connected with a pressure measurement rake support arm through a pressure measurement rake.
The total pressure measurement probe array and the static pressure measurement probe array are in parallel linear distribution.
The device is installed in a wind tunnel. And a nano particle scattering mechanism is arranged at the upstream of the wind tunnel test section.
The invention has the advantages that:
1) the three-dimensional velocity vector field of the cross section area of the inner runner outlet is accurately obtained by adopting a PIV measuring technology, the boundary boundaries of inner and outer flows can be accurately distinguished, the measured value of the total pressure/static pressure probe is corrected by utilizing a three-dimensional velocity vector angle, and the data accuracy is greatly improved;
2) the controllable pressure-measuring rake mechanism is moved to carry out carpet type scanning pressure measurement, so that the total pressure and the data acquisition density of static pressure measurement points in the area of the section of the outlet of the inner runner are greatly improved, and the pneumatic data of any position point of the section of the outlet can be acquired in the same train number theoretically;
3) a mass flow weighted average method is adopted to obtain more accurate parameters such as outlet flow, momentum and the like;
4) the accuracy of the whole internal flow resistance measuring method is comprehensively improved in the aspects of test data information quantity and data correction.
Drawings
FIG. 1 is a schematic diagram of the whole scheme of the wind tunnel test for accurately measuring the momentum of the inflow port of the invention,
FIG. 2 is a schematic diagram of an accurate measurement of static/total pressure distribution at the exit cross section.
1-Ventilation model
2-side wall polishing area
3-inner flow passage outlet
4-Total pressure measurement Probe array
5-track control slide rail
6-static pressure measuring probe array
7-pressure measuring rake support arm
8-electric cylinder
9-model supporting seat
10-wind tunnel curved knife connecting piece
11-coordinate system of measuring points
12-measurement Point velocity vector
Detailed Description
The measuring method mainly comprises three steps of PIV measurement of an outlet section three-dimensional velocity vector field, static pressure-total pressure carpet measurement of a movable pressure measuring rake and data post-processing, and specifically comprises the following steps:
firstly, accurately measuring the speed of the outlet section of an outlet of an internal flow channel by adopting an outflow PIV (particle image velocimetry) measuring method for a ventilation model for measuring the internal flow resistance in a wind tunnel test to obtain three-dimensional speed vector field data of the outlet section
And then, carpet type measurement is carried out on the outlet section by utilizing a movable pressure measuring rake mechanism controlled by an electric cylinder to obtain the static pressure and the total pressure of each measuring point, so that the data acquisition density of the outlet section is greatly improved. Meanwhile, the total pressure and static pressure measurement values of each measurement point are corrected by combining the airflow vector angle of each measurement point, and higher-precision outlet section pressure value distribution is obtained;
finally, the obtained data of the outlet section velocity, the static pressure, the total pressure and the like are processed by adopting a mass flow averaging-based method, and the internal flow resistance D is calculated according to a typical internal flow resistance calculation formulanThe specific derivation and calculation process is as follows:
resistance of vent pattern outlet upstream relative to inner flow channel inlet:
D∞＝qm,∞v∞-qm,2v2+P∞A∞-P2A2(1)
resistance of vent pattern outlet to inner flow channel inlet:
D1＝qm,1v1-qm,2v2+P1A1-P2A2(2)
wherein, the corner mark infinity indicates the far front of the upstream of the inlet of the inner runner, the corner mark 1 indicates the inlet position of the inner runner, the corner mark 2 indicates the outlet position of the inner runner, qm,∞Is the mass flow, v, far forward of the upstream of the inlet of the inner flow channel∞Is the air flow velocity far forward of the upstream of the inner flow passage inlet, qm,2Is the mass flow, v, of the inner flow passage outlet2Is the velocity of the gas flow at the outlet of the inner flow channel, P∞Is the pressure far forward of the upstream of the inlet of the inner flow channel, A∞Is the cross-sectional area, P, of the flow tube far ahead of the upstream of the inlet of the inner flow passage2Is the pressure at the outlet of the inner flow channel, A2Is the cross-sectional area of the inner runner outlet, qm,1Is the mass flow at the inlet of the inner flow channel, v1Is the velocity of the gas flow at the inlet of the inner flow channel, P1Is the pressure at the inlet of the inner flow channel, A1Is the cross-sectional area of the inner runner inlet.
Q is known from conservation of mass flow without regard to overflowm,∞＝qm,1＝qm,2In addition, the far front and inlet airflows are generally uniform and the same as the wind tunnel test section environment, and can be directly obtained from wind tunnel operation parameters.
Defining a coordinate system, and according to the total number ns (variable i) of the measuring points transversely arranged on the measuring rake and the total number nt (variable j) of the moving positions along the movable direction of the outlet section, the mass flow q at the outletm,2Can be dispersed as:
the average density, area and axial velocity along the drag direction are respectively for the adjacent region of each measurement point (i, j).
According to velocity vectorFor shortAxial velocity value in the direction of drag
WhereinFor the velocity space vector angle at each measurement point position of the exit cross-section,the air flow vector of the measuring point (i, j) is converted into resistanceThe included angle of the direction;
according to a typical pneumatic theoretical formula:
wherein, the constant R is 287.053N ∙ m/(Kg ∙ K)
Wherein, T0The total temperature of the wind tunnel is known during operation, gamma is the specific heat ratio of 1.4,for the Mach number of each measurement point (i, j),
wherein the total pressure at the point (i, j) is measuredAnd static pressureThe actual measured value needs to be combined with the included angle between the airflow vector of the measuring point and the pressure measuring probe and the front speedAndand (6) correcting. Total and static pressure correction factorsAndthe method is obtained by performing fitting interpolation on early test data, namely:
finishing to obtain:
in addition, according to a theoretical formula, since the total temperature is constant, the relationship between the pneumatic parameters of static pressure and density and the total pressure and absolute speed values can be further derived as follows:
comparing the equations (11) and (13) and the equations (12) and (14), which are two expressions of static pressure and density of any measuring point (i, j) on the outlet section, respectively, can be mutually verified.
Since the total pressure measurement is less sensitive to the flow angle, the error is relatively low, and the corrected value is more accurate, the local static pressure and density values will be dominated by equations (13) and (14), and equations (13) and (14) are merely used as comparison values. At this time, according to the formula (3), the total momentum over the entire inner flow passage outlet section can be expressed as:
in addition, the average value of each pneumatic parameter of the outlet section of the flow passage in the ventilation model has the following results:
v2weighted average velocity (direction of resistance) for mass flow at the outlet:
P2weighted average static pressure for mass flow at outlet:
ρ2weighted average density for mass flow at outlet:
combining the above formulas, the resistance D of the vent model outlet relative to the upstream of the inner flow passage inlet is adjusted∞Is defined as wind tunnel test internal flow resistance DnAccording to the internal flow resistance formula (1), the resistance of the vent model outlet relative to the far front can be obtained as follows:
from the above formula, each item for carrying out detailed calculation of the internal flow resistance is a known parameter of wind tunnel operation or can be calculated according to the formula (3) to (18) through the measured values of static temperature, static pressure and three-dimensional velocity vector.
Because each measured data has higher precision, the error magnitude of each data acquisition system can be reached, and meanwhile, the PIV technology can be used for accurately measuring the boundary of the inner and outer flow boundaries, so that a quite high-precision measured value of the internal flow resistance can be obtained.
The following examples are given in conjunction with fig. 1 and 2 to further illustrate the technical embodiments of the present invention.
The ventilation model 1 for measuring the typical internal flow resistance is installed in a wind tunnel, the ventilation model 1 is installed on a model supporting seat 9, and the model supporting seat 9 is connected with a wind tunnel bent blade connecting piece 10. The track control slide rail 5 is fixedly arranged on the model supporting seat 9, and the pressure measuring rake supporting arm 7 can move in the track control slide rail 5 through the driving of an electric cylinder 8. The free end of the pressure measuring rake support arm 7 is provided with a pressure measuring rake, and the pressure measuring rake is provided with a pressure measuring rake total pressure measuring probe array 4 and a pressure measuring rake static pressure measuring probe array 6.
(1) And (3) polishing the side wall polishing area 2 of the wind tunnel by a laser to form sheet light which is tightly attached to the tangent plane of the inner runner outlet 3 as much as possible so as to ensure that the pneumatic parameters tightly attached to the inner runner outlet 3 are obtained. When the wind tunnel is operated, after a flow field is stable, continuously scattering nano particles on the upstream of a wind tunnel test section, carrying out PIV measurement, and shooting the motion trail of the nano particles near an inner runner outlet 3 by using a camera, wherein the laser sheet has a certain thickness (more than 1mm), so that a three-dimensional velocity vector field (error is less than 0.5%) of all the particles in the inner runner outlet 3 can be accurately obtained;
(2) after the velocity vector field PIV of the inner runner outlet 3 is measured, the electric cylinder 8 is controlled, the slide rail 5 is controlled along the track to enable the pressure measuring rake to move in a carpet mode on the plane of the light path, and the total pressure and static pressure distribution in the inner runner outlet 3 are measured. The data acquisition density can be given according to the wind tunnel running time and the outlet cross section size. During wind tunnel start-upAnd the pressure measuring rake is moved to a position far away from the inner flow channel outlet 3, so that the pressure measuring rake is prevented from being damaged due to model shaking, and after the wind tunnel starting flow field is stable, the pressure measuring rake is controlled by the electric cylinder 8 to measure the total pressure and static pressure distribution of the inner flow channel outlet 3. In fig. 1, the pressure measuring rake is given as two rows of pressure measuring probes, the first row is a total pressure measuring probe array 4, the second row is a static pressure measuring probe array 6, and the arrangement distance is related to the outlet plane angle of the inner flow channel spray pipe 3, the diameter of the probe and the interference of the static pressure probe on the air flow in front of the total pressure probe. In addition, the total pressure at each measurement point (i, j)And static pressureThe actual measurement total pressure is measured through the air flow speed at the position and the included angle between the air flow vector and the pressure measuring probeAnd actually measuring the static pressureMaking a correction, specifically a correction factorAndhas been obtained by fitting interpolation of previous individual experimental data.
(3) The mass flow averaging-based method is adopted to process the obtained data of the outlet section velocity, the total pressure, the static pressure and the like, and the data are obtained by calculating according to the following formulas:
wherein,
andthe three main polynomials can be calculated from the data measured by the PIV and the pressure measuring rake, and the restP∞，ρ∞，v∞The equal parameters are the geometric dimension of the distance between the pressure measuring rake probes and the pneumatic parameters in the test section in the running process of the wind tunnel, and are known.
Claims (5)
1. The utility model provides a wind tunnel test internal flow resistance measuring device which characterized in that: the device is including installing model supporting seat (9) on pnematic tulwar connecting piece (10), install orbit control slide rail (5) near the one end of pnematic tulwar connecting piece (10) in this model supporting seat (9), electronic jar (8) are fixed on orbit control slide rail (5), its flexible end is connected with pressure measurement harrow support arm (7), install total pressure measurement probe array (4) and static pressure measurement probe array (6) at the free end of pressure measurement harrow support arm (7), the device still installs the laser instrument that is used for beating out the piece light in interior runner export (3) of model (1) of ventilating on the wind-tunnel lateral wall.
2. The wind tunnel test internal flow resistance measurement device according to claim 1, characterized in that: the total pressure measurement probe array (4) and the static pressure measurement probe array (6) are connected with a pressure measurement rake support arm (7) through a pressure measurement rake.
3. The wind tunnel test internal flow resistance measurement device according to claim 2, characterized in that: the total pressure measuring probe array (4) and the static pressure measuring probe array (6) are in parallel linear distribution.
4. The wind tunnel test internal flow resistance measurement device according to claim 3, characterized in that: the device is installed in a wind tunnel.
5. The wind tunnel test internal flow resistance measurement device according to claim 4, characterized in that: and a nano particle scattering mechanism is arranged at the upstream of the wind tunnel test section.
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