CN116448374A - Air inlet duct wind tunnel test method for simulating multiple interference - Google Patents
Air inlet duct wind tunnel test method for simulating multiple interference Download PDFInfo
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- 238000012360 testing method Methods 0.000 claims abstract description 38
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- 238000000034 method Methods 0.000 claims description 18
- 238000004088 simulation Methods 0.000 claims description 5
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- 238000012545 processing Methods 0.000 claims description 4
- 238000011084 recovery Methods 0.000 claims description 4
- 238000010079 rubber tapping Methods 0.000 claims description 4
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- G—PHYSICS
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- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
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Abstract
The invention relates to the field of wind tunnel tests, and discloses an air inlet channel wind tunnel test method for simulating multiple interferences, which comprises the following steps: selecting a measuring position of an aircraft model, perforating, and installing a steady-state piezometer tube and a dynamic sensor; installing an aircraft model; installing multiple air inlets, starting vacuum injection, simulating the flying speed flow field of the aircraft, regulating the flow of the air inlets to reach the flow required by respective tests, and after the flow field in the air inlets is stable, carrying out dynamic and steady-state pressure acquisition, wherein one flow point acquisition is completed; repeating the steps of adjusting the flow and collecting the pressure, collecting the next flow point, and closing the flow field of the wind tunnel and vacuum injection after the number of the flow points reaches the test requirement; and (3) exchanging the positions of the multiple air inlets on the aircraft model until all positions required to be tested by the test are tested, and ending the test. The invention solves the problem that the influence of different positions and different flow rates among multiple air inlets on the performance of each air inlet is difficult to obtain.
Description
Technical Field
The invention relates to the field of wind tunnel tests, in particular to an air inlet channel wind tunnel test method for simulating multiple interferences.
Background
The advanced power device with high bypass ratio and high efficiency is a heart of a modern civil large-scale passenger plane, and the nacelle air inlet channel which is an important component of the power device plays an important role in the performance of the whole civil power passenger plane device. The current civil large-scale airliners are generally multiple nacelle air inlets, the distance of the multiple air inlets on one side is relatively short, and if one air inlet is abnormal in operation, for example, the air inlet cannot work normally, can only work at a low speed or is damaged, the peripheral aerodynamic flow field can be influenced to a certain extent, and then the adjacent air inlets and the normal operation of an engine are influenced.
In order to study the influence of different positions and different flow rates of multiple air inlets on the performance of each air inlet, stability and safety of an air inlet system and a power device system of an aviation aircraft are evaluated, and interference tests of the multiple air inlets of the aircraft must be carried out, but no relevant test method exists in the prior art.
Disclosure of Invention
In order to solve the technical problems in the prior art, an air inlet duct wind tunnel test method for simulating multiple interferences comprises the following steps:
firstly, selecting a measuring position of an aircraft model, carrying out model tapping at the position to be measured, and installing a steady-state piezometer tube and a dynamic sensor;
installing an aircraft model to achieve the required aircraft model posture for the test;
step three, installing multiple air inlets, and connecting the multiple air inlets with corresponding measuring sections, pipelines and flow meters;
step four, starting vacuum injection, opening a wind tunnel adjusting valve, starting to simulate the flying speed flow field of the aircraft, adjusting the flow of the air inlet channel to the flow required by respective tests by an air inlet channel flow simulation system consisting of a flowmeter, a pipeline and a vacuum tank connected with each air inlet channel after the wind tunnel flow field is stable, and carrying out dynamic and steady pressure acquisition after the air inlet channel flow field is stable, wherein one flow point acquisition is completed; repeating the steps of adjusting the flow and collecting the pressure, collecting the next flow point, and closing the flow field of the wind tunnel and vacuum injection after the number of the flow points reaches the test requirement;
and fifthly, changing the positions of the multiple air inlets on the aircraft model, and repeating the fourth step until all the positions are tested, and ending the test.
The front end of the pipeline is connected with the measuring section, the rear end of the pipeline is connected with the front end of the flowmeter, and the rear end of the flowmeter is connected with the vacuum tank.
The measuring positions are the wing surface of the inlet of the air inlet of the aircraft model, the inlet of the air inlet, the inner surface of the air inlet and the outlet of the air inlet.
The aircraft model is supported by a support rod, the rear end of the support rod is connected with a variable attack angle bent blade mechanism of the wind tunnel, the front end of the support rod is connected with and supports the air inlet channel model and the measuring section through a variable sideslip angle device, and the air inlet channel test model can be adjusted to the attack angle and sideslip angle required during test through the variable attack angle bent blade mechanism and the variable sideslip angle device.
And firstly, measuring pressure through a scanning valve, converting the pressure load into an electric signal, transmitting the electric signal to a pressure acquisition system, and corresponding each pressure signal to an independent pressure processing channel.
The nacelle rack is arranged on the nacelle rack, the nacelle rack is arranged on the lower surface of the wing, screw holes are formed in the lower surface of the wing according to positions where the nacelle rack is to be arranged, the nacelle rack is arranged at different screw holes through screws, and the position change of the nacelle rack and the nacelle rack can be realized through adjusting the nacelle rack.
The steady-state pressure collection in the step four is the pressure measured at the measuring section, and the pressure is converted into the parameters of the air inlet channel by the method that the total pressure recovery coefficient sigma is equal to the total flattened mean value of the outlet section of the air inlet channelDivided by the mean value of the total free flow flattening +.>；
Total flattening of outlet cross section of air inlet channelThe average value is obtained by adopting a flow averaging method;
；
total pressure measured for each total pressure point;
a dense flow function measured for each total pressure point;
a small area represented for each total pressure point;
the angle mark r represents the number of measuring rakes, and i represents the number of measuring points of each measuring rake;
the measuring section can also calculate a flow coefficient by the total static pressure according to the flow average method, which is recorded as；
；
wherein ,is the mean value of total free flow flattening->For the incoming flow function +.>Is the reference area of the air inlet channel.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses an air inlet channel wind tunnel test method for simulating multiple interference, which is characterized in that a plurality of air inlet channels with adjustable positions are additionally arranged on an aircraft model, the positions of the multiple air inlet channels are changeable, and the front-back and left-right position change can be realized; each air inlet is connected with a corresponding measuring section, a pipeline and a flowmeter, flow regulation can be carried out, the wind tunnel is started to operate, after a stable flow field is formed by the wind tunnel, flow regulation is carried out, the surface of an air inlet wing of a selected aircraft model of the aircraft model, an inlet of the air inlet, the inner surface of the air inlet and an outlet of the air inlet are perforated at the measuring position, a steady-state pressure measuring pipe and a dynamic sensor are installed, the pressure is measured through a scanning valve and the dynamic sensor, the influence of each air inlet on the surface of a peripheral model of other air inlets, the load of the inner surface of the air inlet and the performance of the air inlet is obtained, and the influence of the position and the flow of the air inlet on the interference among multiple air inlets is analyzed. The method can systematically develop the experimental study of the interference influence of the multiple air inlets, further evaluate the stability and safety of the air inlet system and the power device system of the aviation aircraft and prevent accidents.
Drawings
FIG. 1 is a schematic diagram of an air inlet duct wind tunnel test device for simulating multiple disturbances in a wind tunnel according to the present invention;
FIG. 2 is a schematic illustration of a multiple inlet arrangement of the present invention;
FIG. 3 is a top view of FIG. 2;
fig. 4 is a bottom view of fig. 2.
Symbol description:
1. the device comprises a vacuum tank, a flow meter, a pipeline, a bent cutter mechanism, a supporting rod, a measuring section, an air inlet model, a wind tunnel wall, a multiple air inlet, a wing, a connecting plate and an air inlet bracket, wherein the vacuum tank, the flow meter, the pipeline, the bent cutter mechanism, the supporting rod, the measuring section, the air inlet model, the wind tunnel wall, the multiple air inlet and the wing are arranged in sequence, and the air inlet bracket is arranged in sequence.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The invention discloses an air inlet channel wind tunnel test method for simulating multiple interferences, which is combined with figures 1-4, and comprises the following steps: firstly, selecting a measuring position of an aircraft model, carrying out model tapping at the position to be measured, and installing a steady-state piezometer tube and a dynamic sensor; installing an aircraft model to achieve the required aircraft model posture for the test; step three, installing a multiple air inlet channel 10, and connecting the multiple air inlet channel 10 with a corresponding measuring section 7, a pipeline and a flowmeter 3; step four, starting vacuum injection, opening a wind tunnel adjusting valve, starting to simulate the flying speed flow field of the aircraft, adjusting the flow of the air inlet channel to the flow required by respective tests by an air inlet channel flow simulation system consisting of a flowmeter 3, a pipeline 4 and a vacuum tank 1, wherein the flowmeter is connected with each air inlet channel after the wind tunnel flow field is stable, and performing dynamic and steady pressure acquisition after the air inlet channel flow field is stable, and completing one flow point acquisition; repeating the steps of adjusting the flow and collecting the pressure, collecting the next flow point, and closing the flow field of the wind tunnel and vacuum injection after the number of the flow points reaches the test requirement; and fifthly, exchanging the positions of the multiple air inlets 10 on the aircraft model, and repeating the fourth step until all the positions are tested, and ending the test. After the test is finished, conventional air inlet channel parameter processing is carried out on total static pressure and dynamic test data obtained through air inlet channel measurement, respective air inlet channel performance parameters are obtained, air inlet channel performance comparison among respective different states is carried out, interference influence among multiple air inlet channels can be obtained, and further stability and safety of an air inlet system and a power device system of the aviation aircraft are evaluated, so that accidents are prevented.
The front end of the pipeline 4 is connected with the measuring section 7, the rear end of the pipeline 4 is connected with the front end of the flowmeter 3, and the rear end of the flowmeter 3 is connected with the vacuum tank 1. The flow of the air inlet channel is regulated and measured through a flowmeter 7, and a vacuum air source in the vacuum tank 1 provides a negative pressure suction environment at the rear end for the whole flow simulation system, so that the flow required by a test is achieved.
The measurement positions are the surface of an air inlet wing 11, an air inlet, an air inlet inner surface and an air inlet outlet of the aircraft model. The aircraft model is supported by a supporting rod 6, the rear end of the supporting rod 6 is connected with a variable attack angle bent blade mechanism 5 of the wind tunnel, the front end of the supporting rod is connected with a supporting air inlet channel model 8 and a measuring section 7 through a variable sideslip angle device, and the air inlet channel test model can be adjusted to the attack angle and sideslip angle required in the test through the variable attack angle bent blade mechanism 5 and the variable sideslip angle device.
And firstly, measuring pressure through a scanning valve, converting pressure load of each measuring point into an electric signal, transmitting the electric signal to a pressure acquisition system, and corresponding each pressure signal to an independent voltage signal acquisition channel. The multiple air inlets 10 are arranged on the nacelle hanging frame through the air inlet support 13, the nacelle hanging frame is arranged on the lower surface of the wing 11, screw holes are formed in the lower surface of the wing 11 according to positions where the air inlets are to be arranged, the nacelle hanging frame is arranged at different screw holes through screws, and the position change of the multiple air inlets 10 relative to each other can be realized through adjusting the multiple air inlets 10.
Examples
An air inlet duct wind tunnel test method for simulating multiple interferences, which comprises the following steps:
firstly, selecting an inlet wing surface, an inlet inner surface and an outlet of an inlet of an air inlet of an aircraft model of the aircraft model as positions to be tested, carrying out model tapping at the positions to be tested, and installing a steady-state piezometer tube and a dynamic sensor;
installing an aircraft model to achieve the required aircraft model posture for the test (referring to the attached drawings, the aircraft model posture is an attack angle of 0 degrees and a sideslip angle of 0 degrees);
step three, installing multiple air inlets, and connecting the multiple air inlets with corresponding measuring sections, pipelines and flow meters;
step four, starting vacuum injection, opening a wind tunnel adjusting valve, starting to simulate the flying speed flow field of the aircraft, adjusting the flow of the air inlet channel to the flow required by respective tests by an air inlet channel flow simulation system consisting of a flowmeter, a pipeline and a vacuum tank connected with each air inlet channel after the wind tunnel flow field is stable, collecting dynamic and steady pressure after the air inlet channel flow field is stable,
the collection of one flow point is completed; repeating the steps of adjusting the flow and collecting the pressure, collecting the next flow point, and closing the flow field of the wind tunnel and vacuum injection after the number of the flow points reaches the test requirement;
the pressure measured at the measurement segment for steady state pressure may be converted into an inlet related parameter:
the total pressure recovery coefficient sigma is equal to the total flattening average value of the outlet section of the air inlet channelDivided by the mean value of the total free flow flattening +.>。
；
The total flattening average value of the outlet section of the air inlet channel is obtained by adopting a flow averaging method.
；
Total pressure measured for each total pressure point;
a dense flow function measured for each total pressure point;
a small area represented for each total pressure point;
the angle mark r represents the number of measuring rakes, and i represents the number of measuring points of each measuring rake;
the measuring section can also calculate a flow coefficient by the total static pressure according to the flow average method, which is recorded as。
；
wherein ,is the mean value of total free flow flattening->For the incoming flow function +.>Is the reference area of the air inlet channel.
For example, 8 dynamic sensors are arranged at the position of the measuring section, dynamic distortion Tu of the air inlet channel can be obtained through data processing of dynamic acquisition data, namely, the air flow nonuniformity of the flow field of the outlet of the air inlet channel of the engine, which changes with time, is more unfavorable to the engine operation as the dynamic distortion is higher.
；
The total pressure value is dynamically acquired;
the average value of the total pressure values acquired dynamically is used;
pulsating pressure acquired for the kth channel;
is the root mean square of the pulsating pressure.
The performance of the air inlet channel can be evaluated through total pressure recovery, flow coefficient and dynamic distortion.
Step five, changing the positions of multiple air inlets (the distance between one air inlet and the joint of the wing and the fuselage is 20cm, which is fixed close to one air inlet in the wing, moving the other air inlet to the tip of the wing until the distance between the other air inlet and the one air inlet is 25cm, 30cm and 35cm respectively), repeating the step four until all the positions are tested, and ending the test.
In the invention, a plurality of air inlets with adjustable positions are additionally arranged on the aircraft model. The positions of the multiple air inlets are changeable, and the front and back, left and right position changes can be realized. Each air inlet is connected with a corresponding measuring section, a corresponding pipeline and a corresponding flowmeter, so that flow regulation can be performed, and an influence rule of interference between different positions of multiple air inlets is obtained (the closer the distance between the air inlets is, the more serious the mutual interference is, the performance of the air inlets is reduced, and the distortion of the air inlets is improved). Different inlet locations can result in different internal and external flow fields of multiple inlets and aerodynamic characteristics of the inlets.
Under the condition that the aircraft achieves the required flight speed and flight attitude in the wind tunnel, the flow of each multiple air inlet channel is changed, the influence of each air inlet channel on the peripheral model surface of other air inlet channels, the load of the inner surface of the air inlet channel, the performance and distortion of the air inlet channel is obtained, and the influence rule of interference among different flows of the multiple air inlet channels is obtained. The method comprises the steps of measuring respective flow changes of multiple air inlets, obtaining influences of the multiple air inlets on the peripheral model surfaces of other air inlets, the internal surface load of the air inlets and the performance of the air inlets, obtaining influence rules of interference among different positions of the multiple air inlets, obtaining positions with smaller interference among multiple engines (meeting the working requirements of the engines) and relatively reasonable layout (meeting the thrust and strength requirements of an airplane), and further evaluating the stability and safety of an air inlet system and a power device system of an aviation aircraft.
The foregoing drawings and description are only one embodiment of the present invention, but the specific scope of the present invention is not limited to the above description, and any simple replacement or modification within the scope of the technical idea disclosed in the present invention and according to the technical scheme of the present invention should be within the scope of the present invention.
Claims (7)
1. The method for simulating the multi-interference wind tunnel test of the air inlet channel is characterized by comprising the following steps of:
firstly, selecting a measuring position of an aircraft model, carrying out model tapping at the position to be measured, and installing a steady-state piezometer tube and a dynamic sensor;
installing an aircraft model to achieve the required aircraft model posture for the test;
step three, installing multiple air inlets, and connecting the multiple air inlets with corresponding measuring sections, pipelines and flow meters;
step four, starting vacuum injection, opening a wind tunnel adjusting valve, starting to simulate the flying speed flow field of the aircraft, adjusting the flow of the air inlet channel to the flow required by respective tests by an air inlet channel flow simulation system consisting of a flowmeter, a pipeline and a vacuum tank connected with each air inlet channel after the wind tunnel flow field is stable, and carrying out dynamic and steady pressure acquisition after the air inlet channel flow field is stable, wherein one flow point acquisition is completed; repeating the steps of adjusting the flow and collecting the pressure, collecting the next flow point, and closing the flow field of the wind tunnel and vacuum injection after the number of the flow points reaches the test requirement;
and fifthly, changing the positions of the multiple air inlets on the aircraft model, and repeating the fourth step until all the positions are tested, and ending the test.
2. The method for simulating multiple interference in an air inlet duct wind tunnel test according to claim 1, wherein the front end of the pipeline is connected with the measuring section, the rear end of the pipeline is connected with the front end of the flowmeter, and the rear end of the flowmeter is connected with the vacuum tank.
3. The method of claim 2, wherein the measurement locations are an inlet airfoil surface, an inlet, an inlet interior surface, and an outlet.
4. The method for simulating multi-interference wind tunnel test of an air inlet channel according to claim 3, wherein the aircraft model is supported by a supporting rod, the rear end of the supporting rod is connected with a variable attack angle curved knife mechanism of the wind tunnel, the front end of the supporting rod is connected with the air inlet channel model and a measuring section through a variable sideslip angle device, and the air inlet channel test model can be adjusted to an attack angle and a sideslip angle required in the test through the variable attack angle curved knife mechanism and the variable sideslip angle device.
5. The method for simulating multiple interference according to claim 4, wherein the first step is to measure the pressure by a scan valve, convert the pressure load into an electrical signal, transmit the electrical signal to a pressure acquisition system, and correspond to an independent pressure processing channel for each pressure signal.
6. The method for testing the wind tunnel of the air inlet channel simulating the multiple interferences according to any one of claims 1 to 5, wherein the multiple air inlet channels are installed on a nacelle hanger, the nacelle hanger is installed on the lower surface of a wing, screw holes are formed on the lower surface of the wing according to positions where the air inlet channels are to be installed, the nacelle hanger is installed at different screw holes through screws, and the position change of the multiple air inlet channels relative to each other can be realized by adjusting the multiple air inlet channels.
7. The method for testing the air inlet channel by simulating multiple interferences according to any one of the claims 1 to 5, wherein the steady-state pressure acquisition in the fourth step is the pressure measured at the measuring section, and the method for converting the pressure into the air inlet channel parameter is that the total pressure recovery coefficient sigma is equal to the total average value of the outlet section of the air inlet channelDivided by the mean value of the total free flow flattening +.>；
The total flattening average value of the outlet section of the air inlet channel is obtained by adopting a flow averaging method;
；
total pressure measured for each total pressure point;
a dense flow function measured for each total pressure point;
a small area represented for each total pressure point;
the angle mark r represents the number of measuring rakes, and i represents the number of measuring points of each measuring rake;
the measuring section can also calculate a flow coefficient by the total static pressure according to the flow average method, which is recorded as；
；
wherein ,is the mean value of total free flow flattening->For the incoming flow function +.>Is the reference plane of the air inlet channelAnd (3) accumulation.
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| CN116973065A (en) * | 2023-09-22 | 2023-10-31 | 中国航空工业集团公司沈阳空气动力研究所 | Device and method for simulating impact of shock waves on aircraft |
| CN117054037A (en) * | 2023-10-12 | 2023-11-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Boundary layer suction wind tunnel test device for aircraft with mixed wing body layout |
| CN117890069A (en) * | 2024-03-15 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Compatibility evaluation test method for high-speed wind tunnel air inlet channel and engine |
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| CN116973065A (en) * | 2023-09-22 | 2023-10-31 | 中国航空工业集团公司沈阳空气动力研究所 | Device and method for simulating impact of shock waves on aircraft |
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| CN117054037B (en) * | 2023-10-12 | 2023-12-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Boundary layer suction wind tunnel test device for aircraft with mixed wing body layout |
| CN117890069A (en) * | 2024-03-15 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Compatibility evaluation test method for high-speed wind tunnel air inlet channel and engine |
| CN117890069B (en) * | 2024-03-15 | 2024-05-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Compatibility evaluation test method for high-speed wind tunnel air inlet channel and engine |
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