CN114184349B - Method for obtaining supersonic jet static operation pressure matching point of jet wind tunnel - Google Patents
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Abstract
The invention discloses a method for obtaining a static operating pressure matching point of supersonic jet of a jet wind tunnel. The method comprises the steps of firstly, calculating the initial opening degree of a pressure regulating valve at a lower threshold value of initial reference operation total pressure, then, changing the opening degree of an annular gap pressure regulating valve in a stepped mode, obtaining the static pressure of an outlet of a spray pipe, the static pressure of a reference point of a test cabin and the total pressure of a stable section in real time through a pressure acquisition system, then, calculating the Mach number of the outlet of the spray pipe and the Mach number of the reference point of the test cabin, searching the moment when the static pressure of the outlet of the spray pipe is the same as the static pressure of the reference point of the test cabin after the Mach number of the outlet of the spray pipe is stable, and obtaining the total pressure of the stable section corresponding to the moment as the operation total pressure of a matching point; and if the matching point does not appear, adjusting the initial reference operation total pressure and then continuing searching. The method for obtaining the supersonic jet static operation pressure matching point of the jet wind tunnel can quickly determine the optimum supersonic jet operation pressure in a specific test state, and expands the uniform area of the traditional supersonic jet flow field from a diamond area to a jet boundary area.
Description
Technical Field
The invention belongs to the technical field of high-speed free jet wind tunnel tests, and particularly relates to a method for obtaining a supersonic jet static operation pressure matching point of a jet wind tunnel.
Background
When a traditional high-speed free jet wind tunnel is used for supersonic speed tests, the mode of improving the running total pressure is usually adopted for blowing, and the mode can ensure that a rhombic area at the outlet of a spray pipe is uniform airflow. And the gas flow outside the diamond area and inside the jet boundary can carry out repeated expansion acceleration and compression deceleration processes, so that the quality of the flow field outside the diamond area is rapidly deteriorated. The uniform airflow in the rhombic area can be subjected to tests with small requirements on the uniform area range, such as a small attack angle air inlet channel, engine characteristics and the like, and the model scale cannot exceed the rhombic area range. Other blowing tests with low requirements on the quality of the convection field can also be carried out in a larger jet flow range. But the uniform flow field range of the diamond area is too small, so that the high-quality test requirements of a large-attack-angle air inlet channel, air inlet/engine body/engine integration, thrust vector characteristics, a large-scale model and the like are difficult to meet.
The high-speed free jet wind tunnel is developed in the middle of the 20 th century, is not strictly limited by a wallboard in a closed wind tunnel test section, has large allowable model blockage degree and flexible arrangement of supporting and testing equipment, and is important ground simulation equipment for developing special wind tunnel tests such as a propulsion system, dynamic characteristics and the like. A series of free jet test devices are built in aerospace countries such as America and Russia, tests such as air inlet channel and engine characteristics or blow tests are mainly developed, and a plurality of aerodynamic problems in the aircraft development process are solved. At present, the number of low-speed and high-supersonic-speed jet wind tunnels in China is large, and in recent years, the development of high-speed free jet wind tunnels is accelerated.
The high-speed free jet wind tunnel has the obvious advantages that the blockage degree of a model is allowed to be large, but the uniform area of the supersonic jet flow field in the traditional operation mode is small, and the function exertion of the high-speed free jet wind tunnel is limited. The application range of the high-speed free jet wind tunnel is further expanded, the development requirements of a new generation of aircrafts are better met, the uniform area range of the high-speed free jet flow field needs to be improved, and the matching operation pressure of a corresponding test state is rapidly determined. In order to ensure that the supersonic free jet does not generate expansion waves and compression waves at the outlet of the spray pipe, the operating pressure of the supersonic free jet needs to meet the following conditions: at a specific total operating pressure, the static pressure at the outlet of the nozzle is equal to the ambient pressure of the jet (static pressure in the test chamber). When the condition is met, the supersonic jet can flow more uniformly within the jet boundary, so that the range of the jet uniform area breaks through the limitation of a diamond area.
Currently, with the rapid development of aerospace industry in China, the development of advanced aircrafts puts an urgent need on the flow field simulation capability of a large-scale supersonic jet flow uniform area, and a method for rapidly determining matching operation pressure in different test states is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for obtaining a static operating pressure matching point of supersonic jet of a jet wind tunnel.
The invention discloses a method for obtaining a static operating pressure matching point of supersonic jet of a jet wind tunnel, which comprises the following steps of:
s01, arranging a spray pipe outlet static pressure measuring point 1 at a spray pipe outlet of the jet flow wind tunnel, and collecting spray pipe outlet static pressure Pout by using the spray pipe outlet static pressure measuring point 1; arranging a test chamber reference point static pressure measuring point 2 on the inner wall of the test chamber, and collecting a test chamber reference point static pressure Psyc by the test chamber reference point static pressure measuring point 2;
s02, determining an initial reference operation total pressure P0 of a jet flow wind tunnel stable section corresponding to the supersonic mach number Ma according to jet flow wind tunnel design indexes;
s03, reducing the initial reference operation total pressure P0 by delta P to serve as an initial starting total pressure P01, namely P01= P0-delta P;
s04, increasing delta P to the initial reference operation total pressure P0 to serve as the wind tunnel closing total pressure P02, namely P02= P0 +/delta P;
s05, calculating the opening k of the annular gap pressure regulating valve of the jet flow wind tunnel by adopting P01, and taking the opening k as the preset opening of the annular gap pressure regulating valve when the wind tunnel is started;
s06, starting the wind tunnel, keeping the opening k of the annular gap pressure regulating valve unchanged until the total pressure P0 of the stable sectioniP01 was reached and remained stable;
s07, according to the step opening k = k + delta k × N and N = 1-N, the opening k of the annular gap pressure regulating valve is increased in a step increasing mode, and N is the total step number of the annular gap pressure regulating valve when the wind tunnel is closed; total pressure P0 in stable sectioniThe total pressure P0 increases along with the step increase of the valve opening when the stable sectioniShutting down the vehicle after reaching P02;
s08. the stable section total pressure array P0 with one-to-one correspondence obtained in the step S07iStatic pressure array Pout of nozzle outletiAnd test chamber reference point static pressure array PsyciAnd calculating the Mach number Ma of the outlet of the spray pipe corresponding to each acquisition timeiMas number of reference point of test chamberiI = 1-M, wherein M is the total point number collected by the collection system;
the calculation formula is as follows:
s09. according to
Finding the Mach number Ma of the nozzle outletiA stable interval and determining a corresponding time interval (T1, T2);
s10, drawing time-total pressure P0 on the same graphiCurve, time-spray pipe outletStatic pressure PoutiCurve, time-test cabin reference point static pressure PsyciA curve;
s11, searching static pressure Pout of the nozzle outlet in the range of time intervals (T1, T2)iStatic pressure Psyc with reference point of test chamberiAt the same time T, i.e. time-nozzle outlet static pressure PoutiCurve and time-test cabin reference point static pressure PsyciThe intersection point of the curves;
s12, finding out the total pressure P03 of the stable section corresponding to the moment T, namely the running pressure matching point P03;
s13, if the operating pressure matching point P03 cannot be found, the method is divided into two conditions: the first condition is that P0 is lower, and Mas is checked after the pressure of the stable section of the step S07 reaches P02 as the reference point Mach number of the test chamberiMach number Ma of spray pipe outletiRelationship if it satisfies
If the P0 is lower, the step S01-the step S12 are repeated after the P0 is increased by 2 delta P on the original basis, and an operation pressure matching point P03 is searched; the second condition is that P0 is higher, and Mas is the reference point Mach number of the test chamber after the pressure of the stable section reaches P01 in the step S06 is checkediMach number Ma of spray pipe outletiRelationship if it satisfies
If the pressure is higher than the reference pressure, P0 is higher, and then P0 is reduced by 2 Δ P on the original basis, and then steps S01 to S12 are repeated to find an operating pressure matching point P03.
Further, the opening k of the annular gap pressure regulating valve in the step S05 satisfies a k = f (γ, Ma) functional relationship, where γ = P01/P0S and P0S is the air source pressure; the k = f (gamma, Ma) function relation curve is obtained through the debugging work of the annular gap pressure regulating valve characteristic.
Further, the total pressure P0 of the stable segment in the step S06iThe stability judgment basis is as follows:
and the value interval of i is the opening of the annular slit valveK is the corresponding interval of each acquisition time.
The method for obtaining the supersonic jet static operation pressure matching point of the jet wind tunnel is suitable for model single-state tests, and attitude angles, position parameters and the like of the test model are not changed during wind tunnel tests.
The invention discloses a method for obtaining a static running pressure matching point of supersonic jet flow of a jet flow wind tunnel, which comprises the steps of firstly calculating initial opening of a ring-shaped gap pressure regulating valve based on initial reference running total pressure according to a given lower threshold of the initial reference running total pressure, then stepwisely changing the opening of the ring-shaped gap pressure regulating valve, obtaining static pressure of a nozzle outlet, static pressure of a test cabin reference point and total pressure of a stable section in real time through a jet flow wind tunnel pressure acquisition system, then calculating the Mach number of the nozzle outlet and the Mach number of the test cabin reference point, searching the moment when the static pressure of the nozzle outlet is the same as the static pressure of the test cabin reference point after the Mach number of the nozzle outlet is stabilized, wherein the total pressure of the stable section corresponding to the moment is the running total pressure of the matching point, and if no matching point exists, continuously searching after the initial reference running total pressure is adjusted.
The method for obtaining the matching point of the supersonic jet static operation pressure of the jet wind tunnel can determine the matching point of the static pressure of the nozzle outlet of the supersonic flow field of the high-speed free jet wind tunnel and the static pressure of the reference point of the test chamber and the total operation pressure of the stable section corresponding to the matching point, and is an effective method for rapidly determining the matching operation pressure of the supersonic jet in a specific test state and expanding the uniform area of the traditional supersonic jet flow field from a diamond area to a jet boundary area.
The method for acquiring the supersonic jet static operation pressure matching point of the jet wind tunnel is simple and clear, has sufficient theoretical basis, is beneficial to quickly and accurately acquiring the total operation pressure of the stable section corresponding to the supersonic jet uniform area pressure matching point in a specific test state, gives consideration to the requirements of flow field stability and uniformity, and is actually applied to supersonic flow field operation of a high-speed free jet wind tunnel.
The method for obtaining the jet flow wind tunnel supersonic velocity jet flow static operation pressure matching point can be applied to the debugging and optimization of the jet flow wind tunnel supersonic velocity flow field, can also be applied to conventional and special tests under the specific state of a strange model, and has wide application range and universality.
Drawings
FIG. 1 is a layout diagram of static pressure measuring points in the method for obtaining matching points of supersonic jet static operating pressure of a jet wind tunnel according to the present invention;
FIG. 2 is a graph of time vs. Mach number obtained in example 1;
FIG. 3 is a graph of time vs. total static pressure obtained in example 1.
In the figure, 1, a static pressure measuring point at the outlet of a spray pipe; 2. a test chamber reference point static pressure test point; 3. a nozzle outlet; 4. a test chamber; 5. a collector.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in fig. 1, the jet wind tunnel sequentially comprises a spray pipe, a test chamber 4 and a collector 5 from front to back according to the wind tunnel airflow direction. Arranging a spray pipe outlet static pressure measuring point 1 at a spray pipe outlet 3 of the jet flow wind tunnel, and collecting spray pipe outlet static pressure Pout by the spray pipe outlet static pressure measuring point 1; arranging a test chamber reference point static pressure measuring point 2 on the inner wall of a test chamber 4, and collecting a test chamber reference point static pressure Psycp by the test chamber reference point static pressure measuring point 2;
the method comprises the steps of selecting a supersonic Mach number Ma =2.3, an initial reference operation total pressure P0=364kPa, a delta P =60kPa, an initial starting total pressure P01=304kPa, and a wind tunnel shut-off total pressure P02=424 kPa.
According to the opening function relation k = f (gamma, Ma) of the annular gap pressure regulating valve, gamma = P01/P0s, under the condition of current P01 and gas source P0s, the preset opening k =440mm of the annular gap pressure regulating valve.
Starting the wind tunnel, judging the stability condition of the wind tunnel operation control program according to the total pressure of the stable section
And i = i-M, and the total pressure is judged stably automatically.
When the stable section has total pressure P0iAfter the stability judgment condition is met, the step opening of the annular gap pressure regulating valve is increased progressively according to steps of delta k =20 mm.
When P0i reaches 424kPa, the wind tunnel closes and starts to process data.
Calculating the Mach number Ma of the current blowing nozzle outlet according to a Mach number calculation formulaiMas number of reference point of test chamberiAnd drawing a time-Mach number curve shown in FIG. 2.
Nozzle outlet Mach number array Ma measured according to step opening change of annular gap pressure regulating valveiCalculating satisfy
The time interval of (a) is 25.18 s-64.98 s.
Time-total pressure P0 is plotted in FIG. 3iTime-nozzle outlet static pressure PoutiTime-test cabin reference point static pressure PsyciCurve line.
From FIG. 3, it can be seen that PoutiAnd PsyciAnd (3) finding the total pressure corresponding to T =42.28 seconds as the total pressure P03 of the stable section, wherein the T is 42.28s at the intersection point within the time interval of 25.18 s-64.98 s, and the P is 03=384 kPa.
Finally, when the supersonic mach number Ma =2.3 is determined, the total pressure of the stable section of the supersonic jet static operation pressure matching point of the jet wind tunnel is 384 kPa.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, and it can be fully applied to various fields of high-speed free jet pressure matching pattern methods suitable for the present invention. Additional modifications and refinements of the present invention will readily occur to those skilled in the art without departing from the principles of the present invention, and therefore the present invention is not limited to the specific details and illustrations shown and described herein without departing from the general concept defined by the claims and their equivalents.
Claims (3)
1. A method for obtaining a static operating pressure matching point of supersonic jet of a jet wind tunnel is characterized by comprising the following steps:
s01, arranging a spray pipe outlet static pressure measuring point (1) at a spray pipe outlet of the jet flow wind tunnel, and collecting spray pipe outlet static pressure Pout by the spray pipe outlet static pressure measuring point (1); arranging a test cabin reference point static pressure measuring point (2) on the inner wall of the test cabin, and collecting a test cabin reference point static pressure Psyc by the test cabin reference point static pressure measuring point (2);
s02, determining an initial reference operation total pressure P0 of a jet flow wind tunnel stable section corresponding to the supersonic mach number Ma according to jet flow wind tunnel design indexes;
s03, reducing the initial reference operation total pressure P0 by delta P to serve as an initial starting total pressure P01, namely P01= P0-delta P;
s04, increasing delta P to the initial reference operation total pressure P0 to serve as the wind tunnel closing total pressure P02, namely P02= P0 +/delta P;
s05, calculating the opening k of the annular gap pressure regulating valve of the jet flow wind tunnel by adopting P01, and taking the opening k as the preset opening of the annular gap pressure regulating valve when the wind tunnel is started;
s06, starting the wind tunnel, keeping the opening k of the annular gap pressure regulating valve unchanged until the total pressure P0 of the stable sectioniP01 was reached and remained stable;
s07, according to the step opening degree delta k, the opening degree k of the annular gap pressure regulating valve is increased in a step increasing mode, so that k = k + delta k x N, N = 1-N, and N is the total step number of the annular gap pressure regulating valve when the wind tunnel is closed; total pressure P0 in stable sectioniThe total pressure P0 increases along with the step increase of the valve opening when the stable sectioniShutting down the vehicle after reaching P02;
s08. the stable section total pressure array P0 with one-to-one correspondence obtained in the step S07iStatic pressure array Pout of nozzle outletiAnd test chamber reference point static pressure array PsyciAnd calculating the Mach number Ma of the outlet of the spray pipe corresponding to each acquisition timeiMas number of reference point of test chamberiI = 1-M, wherein M is the total point number collected by the collection system;
the calculation formula is as follows:
s09. according to
Finding the Mach number Ma of the nozzle outletiA stable interval and determining a corresponding time interval (T1, T2);
s10, drawing time-total pressure P0 on the same graphiCurve, time-spray pipe outlet static pressure PoutiCurve, time-test cabin reference point static pressure PsyciA curve;
s11, searching static pressure Pout of the nozzle outlet in the range of time intervals (T1, T2)iStatic pressure Psyc with reference point of test chamberiAt the same time T, i.e. time-nozzle outlet static pressure PoutiCurve and time-test cabin reference point static pressure PsyciThe intersection point of the curves;
s12, finding out the total pressure P03 of the stable section corresponding to the moment T, namely the running pressure matching point P03;
s13, if the operating pressure matching point P03 cannot be found, the method is divided into two conditions: the first condition is that P0 is lower, and Mas is checked after the pressure of the stable section of the step S07 reaches P02 as the reference point Mach number of the test chamberiMach number Ma of spray pipe outletiRelationship if it satisfies
If the P0 is lower, the step S01-the step S12 are repeated after the P0 is increased by 2 delta P on the original basis, and an operation pressure matching point P03 is searched; the second condition is that P0 is higher, and Mas is the reference point Mach number of the test chamber after the pressure of the stable section reaches P01 in the step S06 is checkediMach number Ma of spray pipe outletiRelationship if it satisfies
If the pressure is higher than the reference pressure, P0 is higher, and then P0 is reduced by 2 Δ P on the original basis, and then steps S01 to S12 are repeated to find an operating pressure matching point P03.
2. The method for obtaining the matching point of the supersonic jet static operation pressure of the jet wind tunnel according to claim 1, wherein the opening k of the annular gap pressure regulating valve in the step S05 satisfies a k = f (γ, Ma) functional relationship, wherein γ = P01/P0S and P0S is an air source pressure; the k = f (gamma, Ma) function relation curve is obtained through the debugging work of the annular gap pressure regulating valve characteristic.
3. The method for obtaining the static operating pressure matching point of the supersonic jet of the jet wind tunnel according to claim 1, wherein the total pressure P0 of the stable section in the step S06iThe stability judgment basis is as follows:
and the value interval of i is an interval corresponding to each acquisition moment when the opening of the annular slit valve is k.
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