CN115615653A - Low-speed wind tunnel propeller air inlet channel integrated test method - Google Patents
Low-speed wind tunnel propeller air inlet channel integrated test method Download PDFInfo
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- CN115615653A CN115615653A CN202211256926.8A CN202211256926A CN115615653A CN 115615653 A CN115615653 A CN 115615653A CN 202211256926 A CN202211256926 A CN 202211256926A CN 115615653 A CN115615653 A CN 115615653A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention relates to the technical field of aircraft wind tunnel tests, in particular to a low-speed wind tunnel propeller air inlet channel integrated test method, which comprises the following steps: the propeller model is arranged in the wind tunnel body, and a gas pipeline is connected to the gas inlet channel body of the propeller model; supplying air to a turbine air motor in the propeller model to enable the turbine air motor to start rotating, and further driving the propeller body to rotate; and after the wind tunnel starts to wind and the wind speed is stable, the air supply pressure of the turbine air motor is increased until the rotating speed of the propeller body is increased to a preset rotating speed, and outflow simulation is completed. The propeller, the air inlet channel and the nacelle are integrated into the test piece together, the test piece is arranged in the wind tunnel to be tested, the propeller slipstream test and the air inlet channel test are carried out simultaneously, the rotating effect and the accelerating effect caused by the rotation of the propeller body can be accurately simulated, the performance of the air inlet channel of the propeller aircraft can be accurately estimated, and more reliable test data can be provided for the performance evaluation of the air inlet channel of the turboprop aircraft.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests of aircrafts, in particular to an integrated test method for a low-speed wind tunnel propeller air inlet channel.
Background
The design of the turboprop engine air inlet needs to consider the matching with a speed reducer and a nacelle, and is generally an S-shaped air inlet with large deflection, the flow field of the S-shaped air inlet is complex, the outlet distortion level is high, and the design of a turboprop airplane is a challenge. Furthermore, the inlet of the turboprop inlet is greatly affected by the rotating propeller. The air inlet channel and the propeller of the turboprop engine are generally influenced mutually, the air tunnel test method in the prior art is used for independently carrying out an air inlet channel test and a propeller test, the combined pneumatic performance is simulated by a simulation method, the pneumatic performance obtained after combination is different from the actual pneumatic performance, and the pneumatic performance of the propeller and the air inlet channel in the actual working state of the airplane cannot be accurately evaluated.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that the test data of the aerodynamic performance of the turboprop aircraft in the prior art is different from the actual aerodynamic performance, so that the integrated test method for the propeller and air inlet channel of the low-speed wind tunnel is provided.
In order to solve the technical problem, the invention provides an integrated test method for a low-speed wind tunnel propeller air inlet channel, which comprises the following steps:
mounting a test piece in the wind tunnel body, and connecting a gas transmission pipeline on the gas inlet channel body of the test piece;
supplying air to a turbine air motor in the test piece to enable the turbine air motor to start rotating, and further driving the propeller body to rotate;
and after the wind tunnel starts to wind and the wind speed is stable, the air supply pressure of the turbine air motor is increased until the rotating speed of the propeller body is increased to a preset rotating speed, and outflow simulation is completed.
Optionally, after the outflow simulation is completed, the method further comprises
And controlling the gas transmission pipeline to start gas supply, starting suction of the gas inlet channel body, adjusting the gas flow of the gas inlet channel body to reach a preset flow, and finishing simulation of the internal and external flow integrated flow field of the propeller gas inlet channel.
Optionally, after the flow field simulation is completed, the method further includes: the method comprises the steps of collecting aerodynamic force data and flow field data of the propeller, and collecting flow data in an air inlet channel body.
Optionally, after the flow data in the air inlet channel body is acquired, the turbine air motor is sequentially controlled to stop supplying air, the air delivery pipeline is controlled to stop supplying air, and the wind tunnel is controlled to stop blowing air.
Optionally, a rotating shaft balance is installed in the test piece, the rotating shaft balance is coaxially installed with the propeller body, and the rotating shaft balance is used for collecting propeller aerodynamic force data.
Optionally, a five-hole probe rotary rake is installed in the test piece and used for collecting flow field data.
Optionally, the step of collecting flow field data comprises: and controlling the five-hole probe rotary rake to rotate, and collecting once every time the five-hole probe rotary rake rotates one angle until all the angle collection is finished.
Optionally, a high-speed slip ring is mounted in the test piece for transmitting the operation data in the test piece to an external device.
The technical scheme of the invention has the following advantages:
1. the invention provides a low-speed wind tunnel propeller air inlet channel integrated test method, which comprises the following steps: mounting a test piece in the wind tunnel body, and connecting a gas transmission pipeline on the gas inlet channel body of the test piece; supplying air to a turbine air motor in the test piece to enable the turbine air motor to start rotating, and further driving the propeller body to rotate; and after the wind tunnel starts to wind and the wind speed is stable, the air supply pressure of the turbine air motor is increased until the rotating speed of the propeller body is increased to a preset rotating speed, and outflow simulation is completed. The propeller, the air inlet channel and the nacelle are integrated into the test piece together, the test piece is arranged in the wind tunnel to be tested and communicated with the air inlet channel body through the air conveying pipeline, air supply to the air inlet channel body is achieved, propeller slipstream test and air inlet channel test are conducted simultaneously, rotation effect and acceleration effect and the like caused by rotation of the propeller body can be accurately simulated, propeller aircraft air inlet channel performance can be estimated more accurately, and more reliable test data can be provided for evaluating the performance of the propeller aircraft air inlet channel.
2. The invention provides an integrated test method for a propeller air inlet channel of a low-speed wind tunnel, which is characterized in that after outflow simulation is completed, an air conveying pipeline is controlled to start air supply, an air inlet channel body starts suction, the air flow of the air inlet channel body is adjusted to reach a preset flow, and simulation of an internal and external flow integrated flow field of the propeller air inlet channel is completed. When carrying out the flow field simulation, intake duct body suction, screw rotation and wind tunnel wind-lifting go on simultaneously, can simulate the screw of screw and intake duct under actual operating condition and the pneumatic performance of intake duct more accurately, and test data is more accurate.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a layout diagram of an integrated test system for a low-speed wind tunnel propeller inlet duct according to an embodiment of the present invention.
Fig. 2 is a schematic structural view of a test piece provided in an embodiment of the present invention.
Description of reference numerals: 1. a test piece; 2. a ventilation support rod; 3. a wind tunnel lower bottom plate; 4. a gas transmission pipeline; 5. covering the nacelle with skin; 6. an inlet duct body; 7. rotating the five-hole probe; 8. a propeller body; 9. a rotating shaft balance; 10. a high-speed slip ring; 11. a turbine air motor.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Furthermore, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Examples
The embodiment provides an integrated test method for a propeller air inlet channel of a low-speed wind tunnel, which is carried out in the low-speed wind tunnel, as shown in fig. 1, a test piece 1 is supported and installed on a lower bottom plate 3 of the wind tunnel through a ventilating support rod 2, and the ventilating support rod 2 is used for preventing interference on an inlet flow field of an air inlet channel body 6. The ventilation support rod 2 is obliquely arranged, the propeller body 8 faces the oblique direction of the ventilation support rod 2, and the outlet of the air inlet channel body 6 is back to the oblique direction of the ventilation support rod 2. The outlet of the air inlet channel body 6 is connected with the air delivery pipeline 4 through a flexible rubber pipe, and the air delivery pipeline 4 is used for sucking, controlling and measuring the flow field in the air inlet channel body 6. The aeration support bar 2 is a hollow bar for aerating the turbine air motor 11. Wherein the test piece 1 is a propeller air inlet integrated test piece. The test piece 1 can be manufactured according to the actual size of the aircraft, and can also be a scaled test piece of the actual aircraft.
As shown in fig. 2, all the devices in the test piece 1 are highly integrated within the nacelle skin 5. A turbine air motor 11 is installed in the test piece 1 and used for driving the propeller body 8 to rotate. A rotating shaft balance 9 is installed in the test piece 1, the rotating shaft balance 9 and the propeller body 8 are coaxially installed, and the rotating shaft balance 9 is used for collecting propeller aerodynamic force data. A five-hole probe rotary rake 7 is installed in the test piece 1 and used for collecting flow field data. A high-speed slip ring 10 is installed in the test piece 1 and used for transmitting the operation data in the test piece 1 to external equipment.
The integrated test method for the low-speed wind tunnel propeller air inlet channel comprises the following steps: the test piece 1 is arranged inside the wind tunnel body, and the air inlet channel body 6 of the test piece 1 is connected with the air transmission pipeline 4. And controlling the air supply of the ventilation support rod 2 to supply air to the turbine air motor 11 in the test piece 1 so as to enable the turbine air motor to start rotating, and further driving the propeller body 8 to rotate. After the wind tunnel is started to reach the stable wind speed, the air supply pressure of the ventilation support rod 2 is increased to reach the preset rotating speed when the rotating speed of the propeller body 8 is increased, and the outflow simulation is completed.
After the outflow simulation is completed, the air inlet ejector inside the air conveying pipeline 4 connected with the air inlet body 6 is controlled to start air supply, the air inlet body 6 starts suction, the air flow of the air inlet body 6 is adjusted to reach the preset flow, and the simulation of the internal and external flow integrated flow field of the propeller air inlet is completed.
After the flow field simulation is completed, the propeller aerodynamic force data and the flow field data are collected, and the flow data in the air inlet duct body 6 are collected at the same time. After the flow data in the air inlet channel body 6 is acquired, the ventilation support rods 2 are sequentially controlled to stop air supply, the air delivery pipelines 4 are controlled to stop air supply, the air tunnel is controlled to stop air supply, and the train number is finished. Wherein the step of collecting flow field data comprises: and controlling the five-hole probe rotary rake 7 to rotate, and collecting once every time the five-hole probe rotary rake 7 rotates for one angle until all the angles are collected.
Specifically, during the experiment, at first through the bracing piece 2 that ventilates for 11 little discharge air supplies of turbine air motor make it begin to rotate, turbine air motor 11 passes through reduction gear connection screw body 8, drives screw body 8 and rotates with a relatively less rotational speed, later the wind-tunnel wind-rise to the wind speed stable, this moment, improve the air feed pressure of bracing piece 2 that ventilates, improve to predetermined rotational speed until 8 rotational speeds of screw body, the simulation of outflowing this moment is accomplished. After the outflow simulation is completed, the ejector connected with the gas transmission pipeline 4 starts gas supply, the gas inlet channel body 6 starts suction, the flow regulating valve of the gas inlet channel body 6 walks to the designated position in a conical manner, the flow of the gas inlet channel is controlled to reach the preset flow, and the simulation of the internal and external flow integrated flow field of the propeller gas inlet channel is completed at the moment. After the flow field simulation is completed, aerodynamic force data of the propeller body 8 are collected through the rotary shaft balance 9, and signals are transmitted out through the high-speed slip ring 10 to be processed, so that the aerodynamic force data of the propeller body 8 are obtained. And then, the five-hole probe rotary rake 7 starts to collect, wherein the five-hole probe rotary rake 7 finishes calibration and data processing before installation and can be directly used for flow field measurement. In the range of 360 degrees, the rotary rake collects every 1 degree of rotation until all the angles are collected, and in the process, the flow meter on the gas transmission pipeline 4 also synchronously collects and measures the flow of the gas inlet channel. After the measurement is finished, the air transmission pipeline 4 stops sucking, the turbine air motor 11 stops supplying air, the wind tunnel stops supplying air, and the train number is finished. During the experiment, by changing the parameters of the test state, the data of the high-density stable dynamic pressure field and speed field in the propeller air inlet passage and the internal and external flow integrated air inlet passage, the propeller tension and the like under different incoming flow wind speeds, different propeller states and different air inlet passage flows can be obtained.
The propeller, the air inlet channel and the nacelle are integrated into a test piece together, the test piece is placed in a wind tunnel for testing, and in the wind tunnel test, incoming flow, a propeller of a turboprop aircraft and air inlet channel suction are simulated simultaneously to obtain air inlet channel inlet flow field conditions under the influence of the propeller. The turbine air motor 11 is used as a propeller driving device, the rotating shaft balance 9 is used for measuring the aerodynamic force of the propeller and used as a basis for controlling the state of the propeller, a high-pressure injection mode is used for simulating a flow field in an air inlet channel, the performance of the air inlet channel is measured by the five-hole probe rotary harrow 7, the propeller is enabled to reach a preset working state under a certain wind tunnel incoming flow wind speed, the air inlet channel is controlled to reach a specified flow, and finally data acquisition equipment starts to acquire to obtain test data. The propeller slipstream test and the air inlet channel test are carried out simultaneously, the rotating effect, the accelerating effect and the like caused by the rotation of the propeller can be accurately simulated, the performance of the propeller aircraft air inlet channel can be estimated more accurately, more reliable test data can be provided for evaluating the performance of the turboprop aircraft air inlet channel, and the defects of the conventional turboprop aircraft air inlet channel wind tunnel test method are overcome.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. This need not be, nor should it be exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (8)
1. An integrated test method for a low-speed wind tunnel propeller air inlet channel is characterized by comprising the following steps:
the test piece (1) is arranged in the wind tunnel body, and a gas transmission pipeline (4) is connected to the gas inlet channel body (6) of the test piece (1);
supplying air to a turbine air motor (11) in the test piece (1) to enable the turbine air motor to start rotating, and further driving a propeller body (8) to rotate;
after the wind tunnel starts to wind and the wind speed is stable, the air supply pressure of the turbine air motor (11) is increased until the rotating speed of the propeller body (8) is increased to a preset rotating speed, and outflow simulation is completed.
2. The integrated test method for the low-speed wind tunnel propeller air inlet channel according to claim 1, wherein after the outflow simulation is completed, the method further comprises
The air transmission pipeline (4) is controlled to start air supply, the air inlet channel body (6) starts suction, the air flow of the air inlet channel body (6) is adjusted to reach the preset flow, and the simulation of the internal and external flow integrated flow field of the propeller air inlet channel is completed.
3. The integrated test method for the low-speed wind tunnel propeller inlet channel according to claim 2 is characterized by further comprising the following steps after the flow field simulation is completed: the method comprises the steps of collecting propeller aerodynamic force data and flow field data, and collecting flow data in the air inlet channel body (6) at the same time.
4. The integrated test method for the low-speed wind tunnel propeller air inlet channel according to claim 3 is characterized in that after the flow data in the air inlet channel body (6) is acquired, the turbine air motor (11) is sequentially controlled to stop supplying air, the air transmission pipeline (4) is controlled to stop supplying air, and the wind tunnel is controlled to stop supplying air.
5. The integrated test method for the low-speed wind tunnel propeller inlet according to any one of claims 1 to 4, wherein a rotating shaft balance (9) is installed in the test piece (1), the rotating shaft balance (9) is coaxially installed with the propeller body (8), and the rotating shaft balance (9) is used for collecting propeller aerodynamic force data.
6. The integrated test method for the low-speed wind tunnel propeller air inlet channel according to any one of claims 1 to 4, characterized in that a five-hole probe rotary rake (7) is installed in the test piece (1) and used for collecting flow field data.
7. The integrated test method for the low-speed wind tunnel propeller inlet channel according to claim 6, wherein the step of collecting flow field data comprises the following steps: and controlling the five-hole probe rotary rake (7) to rotate, and collecting once every time the five-hole probe rotary rake (7) rotates one angle until all the angles are collected.
8. The integrated test method for the low-speed wind tunnel propeller inlet according to any one of claims 1 to 4, characterized in that a high-speed slip ring (10) is installed in the test piece (1) and used for transmitting the operation data in the test piece (1) to external equipment.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211256926.8A CN115615653A (en) | 2022-10-13 | 2022-10-13 | Low-speed wind tunnel propeller air inlet channel integrated test method |
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| CN202211256926.8A CN115615653A (en) | 2022-10-13 | 2022-10-13 | Low-speed wind tunnel propeller air inlet channel integrated test method |
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| CN115615653A true CN115615653A (en) | 2023-01-17 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115855514A (en) * | 2023-03-02 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Double-bending special-shaped variable cross-section air inlet test device for turboprop power high-altitude platform test |
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2022
- 2022-10-13 CN CN202211256926.8A patent/CN115615653A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115855514A (en) * | 2023-03-02 | 2023-03-28 | 中国航发四川燃气涡轮研究院 | Double-bending special-shaped variable cross-section air inlet test device for turboprop power high-altitude platform test |
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