CN219284628U - Aerodynamic force test system for simulating rotating state of propeller - Google Patents

Abstract

The aerodynamic force test system for simulating the rotating state of the propeller comprises a cavity structure (2) which comprises left and right semicircular gyros which are symmetrically arranged; one end of the left semicircular revolving body is used as an air outlet to be connected with an air inlet of the contraction section (3); the contraction section (3) is a hollow cavity with a gradually reduced cross section, and an air outlet of the contraction section (3) is connected with an air inlet at one end of the test section (4); the test section (4) is a hollow cavity; the air outlet at the other end of the test section (4) is connected with the air inlet of the reflux section (6); the test device (5) carries a propeller; one end of the reflux section (6) with a smaller section is connected with the air outlet of the test section (4), and the other end with a larger section is connected with the air inlet of the right semicircular revolving body; the air outlet at the other end of the right semicircular revolving body is connected with the air inlet at one end of the buffer section (7); the other end of the buffer section (7) is used as an air outlet to be connected with an air inlet at the other end of the left semicircular revolving body. The utility model has the advantages of easy realization, low cost, high efficiency and high precision.

Description

Aerodynamic force test system for simulating rotating state of propeller

Technical Field

The utility model belongs to the technical field of wind tunnel tests, and particularly relates to a aerodynamic force test system for simulating the rotating state of a propeller.

Background

The propeller is an important component and a core device of the propeller power aircraft, and the rotating power of the engine is converted into the power for the aircraft to fly by rotating the blades in the air, so that the functions of taking off, cruising, landing and the like in the flight profile process of the aircraft are realized. Compared with a jet power propulsion system, the propeller power propulsion system has the advantages of high efficiency, long voyage, short-distance take-off and landing and low cost. In order to obtain the aerodynamic performance and the propeller-generator matching characteristics of an accurate propeller, it is generally necessary to simulate the actual working state of the propeller and measure the thrust and torque of the propeller under the corresponding working conditions.

The traditional main means for realizing the simulation measurement of the propeller are that the propeller is required to rotate, and then the thrust and the torque of the propeller are measured through a high-precision multi-component force-measuring balance, so that the efficiency of the propeller is calculated. However, the area of the propeller is increased in a rotating state, the wind tunnel required by ensuring the uniformity of the flow field has higher requirement, and most wind tunnels hardly meet the test requirement of the large-size propeller; the shrinkage ratio test can be performed in a small wind tunnel, but geometric similarity, motion similarity and dynamic similarity cannot be ensured at the same time, the influence of Reynolds number and Mach number is ignored, and meanwhile, the deformation similarity criterion cannot be met, so that the accuracy of a measurement result is greatly affected; the flight test not only needs complete machine cooperation, but also needs matched telemetry acquisition equipment, has high test cost and high risk, and is not applicable in the development stage.

According to the experimental hydrodynamic similarity rule, for the propellers with similar geometry, the air flow speed fields of the propellers, which are required to be bypassed by the motion similarity, are similar, namely, the speed and the direction of corresponding points in the bypassing field of the propellers are consistent. In view of this, there is a need for an aerodynamic test system.

Disclosure of Invention

The utility model aims to solve the defects of the conventional propeller wind tunnel test, and provides a aerodynamic force test system for simulating the rotating state of a propeller, which is used for testing based on aerodynamic force for simulating the rotating state of the propeller under the condition of variable-section shear layer incoming flow, solves the technical problem of aerodynamic force test for simulating the rotating state of the propeller under the condition of variable-section shear layer incoming flow, and realizes flow field simulation and aerodynamic force high-precision measurement under the rotating state of the propeller.

The utility model provides a aerodynamic force test system for simulating a rotating state of a propeller, which comprises the following components: the device comprises a hole body structure, a contraction section, a test device, a reflux section and a buffer section; wherein, the liquid crystal display device comprises a liquid crystal display device,

the hole body structure comprises a left semicircular revolving body and a right semicircular revolving body which are arranged in a bilateral symmetry manner; one end of the left semicircular revolving body is used as an air outlet to be connected with an air inlet of the contraction section;

the shrinkage section is a hollow cavity with a gradually reduced cross section, one end of the shrinkage section with a larger cross section area is used as an air inlet, and the other end with a smaller cross section area is used as an air outlet; the air outlet of the contraction section is connected with the air inlet at one end of the test section;

the test section is a hollow cavity, and a propeller and a test carrier are arranged in the cavity; the air outlet at the other end of the test section is connected with the air inlet of the reflux section;

the testing device bears the propeller, adjusts the pitch angle of the propeller and measures aerodynamic data of the propeller;

the backflow section is a sealed expansion section body with rectangular interfaces at two ends, and one end of the backflow section with a smaller section is used as an air inlet to be connected with an air outlet of the test section; one end with a larger section of the reflux section is used as an air outlet to be connected with an air inlet of the right semicircular revolving body; the air outlet at the other end of the right semicircular revolving body is connected with the air inlet at one end of the buffer section;

the buffer section is a hollow cuboid, a multilayer damping disturbance flow net is arranged in the buffer section, and the other end of the buffer section is used as an air outlet to be connected with an air inlet at the other end of the left semicircular revolving body.

Further, when the propeller is a single-section airfoil, the test device includes: the device comprises a supporting structure, a pitch angle adjusting device, a force measuring balance and a switching support rod;

the pitch angle adjusting device is arranged on the supporting structure, an extension section of an adjusting end of the pitch angle adjusting device is connected with one end of the force measuring balance, the other end of the force measuring balance is connected with one end of the switching support rod, and the other end of the switching support rod is connected with the single-section wing profile.

Further, when the propeller is a multi-section airfoil, the test device includes: the device comprises a supporting structure, a pitch angle adjusting device, a force measuring balance, a switching support rod, a pitch-changing motor and a cantilever supporting structure; the pitch angle adjusting device is arranged on the supporting structure, a cantilever at the adjusting end of the pitch angle adjusting device penetrates through the cantilever supporting structure and is provided with the variable-pitch motor, an output shaft of the variable-pitch motor enters the inside of the test section, the end part of the output shaft is connected with the multi-section wing profile through a series combination of a force measuring balance and a switching support rod, and a series combination of the force measuring balance and the switching support rod is arranged between each section of wing profile of the multi-section wing profile.

Further, when the propeller is a multi-section airfoil, the contraction section further comprises a plurality of sub-vents formed by dividing a plurality of air guide plates arranged in a comb shape; the number of the sub-vents corresponds to the number of the multi-section airfoils, and each sub-vent corresponds to one section of airfoil.

Further, the cross-sectional width of each sub-vent outlet is the same as the width of the corresponding segmented airfoil; each sectional airfoil is of a hollow structure.

Further, two ends of the buffer section are respectively provided with a connecting section with a gradually-changed cross section rectangle, two ends of the buffer section are respectively connected with two ends of the buffer section at one end with a smaller cross section of the connecting section, one end with a larger cross section of the connecting section is connected with the air outlet of the right semicircular revolving body, and the other end with a larger cross section of the connecting section is connected with the air inlet of the left semicircular revolving body.

Further, the multilayer damping disturbance flow net is 5-10 layers of damping disturbance flow nets, and the thickness of each layer of damping disturbance flow net is at least 10cm.

Furthermore, the interfaces at two ends of the reflux section are rectangular, the outer wall surface of the reflux section is in gradual transition with a conic section, and the outer wall is equal in thickness.

Compared with the prior art, the utility model has the advantages that:

(1) The utility model has the advantages of easy realization, low cost and high efficiency. According to the aerodynamic force test system and equipment for simulating the rotating state of the propeller under the variable-section shear layer incoming flow condition, a large-size wind tunnel is not required to be used for testing the propeller, and the wind tunnel size requirement of the propeller in the rotating state is 50% smaller than that of the propeller in the rotating state. Meanwhile, the utility model does not need a high-power engine/motor to drive the propeller to rotate, only the aerodynamic force subsection measurement is carried out on the single blade in the small-size wind tunnel, and the utility model has the advantages of wide applicable propeller range, relatively simple and convenient test system, low cost, high efficiency and the like, and has more outstanding advantages than flight test, easier realization and higher safety.

(2) The utility model has high precision and obvious contrast effect. Compared with the traditional wind tunnel shrinkage ratio test, the test system adopted by the utility model can simultaneously ensure geometric similarity, motion similarity and power similarity, and compared with the full-size wind tunnel test, the test system has the advantages that the influence on the single-blade She Celi test by the wind tunnel wall effect is smaller, and the measurement accuracy is higher. The utility model has more obvious effects of blade optimization, improvement and verification.

Drawings

FIG. 1 is a flow chart of the operation of the system of the present utility model;

FIG. 2 is a schematic diagram of a system and layout of the present utility model;

FIG. 3 is a schematic illustration of a single-stage airfoil test trial arrangement and layout of the present utility model;

FIG. 4 is a schematic diagram of the connection of a single-section airfoil balance and a strut according to the present utility model;

FIG. 5 is a schematic layout of a multi-section airfoil test run arrangement of the present utility model;

FIG. 6 is a schematic diagram of a multi-segment airfoil pitch angle adjustment apparatus and connection of the present utility model;

FIG. 7 is a schematic diagram of the connection of the multi-section airfoil balance and the strut according to the present utility model.

1. The control system comprises a control system, a hole body structure comprising left and right semicircular gyros, a contraction section, a 4 section, a test section, a 5 section, a test device, a 6 section, a reflux section, a 7 section, a buffer section, a 8 section, a support structure, a 9 section, a pitch angle adjusting device, a 10 section, a force measuring balance, a 11 section, a single Duan Yixing section, a 12 section, a switching support rod, a 13 section, a variable section shearing contraction section, a 14 section, a multi-section wing section, a 15 section wing section, a first section wing section, a 16 section wing section, a second section wing section, a 17 section wing section, a third section wing section, a 18 section wing section, a fourth section wing section, a 19 section wing section, a fifth section wing section, a 20 section, a variable-pitch motor and a 21 section support.

Detailed Description

The utility model provides a aerodynamic force test system for simulating a rotating state of a propeller. As shown in fig. 2, the test system includes: control system 1, hole body structure 2, shrink section 3, test section 4, testing arrangement 5, backward flow section 6 and buffer section 7.

The hole body structure 2 comprises a left semicircular revolving body and a right semicircular revolving body which are arranged in a bilateral symmetry manner; the air outlet of the left semicircular revolving body is connected with the air inlet of the contraction section 3, the air outlet of the other end of the contraction section 3 is connected with the air inlet of the test section 4, the air outlet of the other end of the test section 4 is connected with the air inlet of the reflux section 6, the air outlet of the other end of the reflux section 6 is connected with the air inlet of the right semicircular revolving body, the air outlet of the right semicircular revolving body is connected with the air inlet of the buffer section 7, and the air outlet of the other end of the buffer section 7 is connected with the air inlet of the other end of the left semicircular revolving body.

The control system 1 of the aerodynamic force test system is used for adjusting flow field parameters of the cavity structure, the flow field parameters are adjusted by controlling a high-pressure air source, an inlet flow and an ejector which enter the flow field, the flow field parameters comprise total temperature T, total pressure P, flow Q and the like, and the control system 1 generates the flow field in the cavity structure according to the flow field parameters to provide a flow field environment for a test.

The hole body structure 2 is a main body bearing structure for circulating airflow, the sectional structure of the main body bearing structure is a semicircular revolving body which is arranged in a bilateral symmetry manner, an air outlet of the semicircular revolving body at the left side is in sealing connection with an air inlet at the expansion end of a contraction section 3 of a gradual change section structure, the air outlet at the contraction end of the contraction section 3 is directly connected with an air inlet of a test section 4 in a flange sealing mode, the circulating airflow is ensured to flow in a constant pressure sealing state, the contraction section 3 is a gradual change section rectangular continuous structure capable of changing flow field parameters before the test section 4, and the flow field speed of an outlet can be further improved through the contraction of the section area.

The test section 4 is arranged at the tail end of the shrinkage section 3, one end of the test section is in sealing direct connection with the tail end of the shrinkage section 3 of the hole body structure, the air outlet of the other end of the test section is in sealing connection with the air inlet of the reflux section 6, the test section is a long straight rectangular device for placing an object to be tested and a test system, the side wall of the test section 4 is provided with an opening, and the object to be tested is arranged in the center of the test section in a mode of inserting the opening.

The testing device 5 comprises an object to be tested, a supporting mechanism 8, a pitch angle adjusting mechanism 9, a high-precision multi-component force measuring balance 10 and a data acquisition device thereof, and is used for measuring aerodynamic force data of the object to be tested under different working conditions.

The reflux section 6 is a rectangular expansion section body with a gradual change section, the contraction end of the expansion section is connected with the tail end of the test section 4, the expansion end of the expansion section is connected with one end of an air inlet of the right semicircular revolving body, and the air outlet of the other end of the right semicircular revolving body is connected with one end of an air inlet of the buffer section 7 through the gradual change section rectangular contraction section and is used for recovering the deceleration air flow after passing through the model. The reflux section 6 is a sealed expansion section body with rectangular two ends, gradual transition of a secondary curve in the middle and equal-thickness walls, and receives a flow field from the test section 4, and the flow field is slowed down after passing through the reflux section 6;

the buffer section 7 is of a long straight rectangular honeycomb structure, and an air outlet at the other end is connected with an air inlet at the other end of the left semicircular revolving body through a variable cross-section rectangular expansion section, and is used for buffering a turbulence flow field and improving flow field uniformity. The buffer section 7 is a hollow cuboid with rectangular ends, equal size and equal back wall, and is internally provided with 5-10 layers of netlike damping thin layers with the thickness of more than 10mm, and is used for buffering the flow field output by the backflow section 6.

The aerodynamic force test system can test the propeller model to be tested of a single-section airfoil and a multi-section airfoil respectively.

As shown in fig. 3 to 4, when the model to be tested is a single-stage airfoil, the test device 5 includes: a supporting structure 8, a pitch angle adjusting device 9 and a force measuring balance 10. The pitch angle adjusting device 9 is arranged on the supporting structure 8, an extension section of an adjusting end of the pitch angle adjusting device 9 enters the test section through a hole in the test section 4 and is connected with one end of the force measuring balance 10, the other end of the force measuring balance 10 is connected with the test wing section 11, and the force measuring balance 10 is used for measuring aerodynamic data of an object to be measured, such as thrust, torque and the like. Preferably, a high-precision multicomponent force balance 10 is used, which is connected to a single-section airfoil 11 via a transfer strut 12, the transfer strut 12 being used to fix, support and connect the pitch angle adjusting device 9. The pitch angle adjusting device 9 is used for quantitatively adjusting the pitch angle of the airfoil 11 to be measured.

5-6, when the model to be tested is a multi-section airfoil 14, a single-section airfoil conventional contraction section is replaced by a variable-section shear contraction section 13, and a flow field at the front end of the model to be tested is changed into a progressive accelerating simulated rotating flow field under the influence of the variable-section shear contraction section, and a ventilation outlet of the variable-section shear contraction section 13 is divided into a plurality of sub ventilation outlets by a plurality of air guide plates arranged in a comb shape. The inlet area of the vents of the variable cross-section shear constriction can be adjusted. In one embodiment, the multi-section airfoil 14 is divided into five sections of sub-airfoils, and the sub-ventilation outlets of the variable-section shear contraction section 13 correspond to the first section airfoil 15, the second section airfoil 16, the third section airfoil 17, the fourth section airfoil 18, and the fifth section airfoil 19, respectively.

The test device 5 includes: a support structure 8, a pitch angle adjusting device 9 and a force measuring balance 10; the pitch angle adjusting device 9 is arranged on the supporting structure 8, a cantilever at the adjusting end of the pitch angle adjusting device 9 penetrates through the cantilever supporting structure 21 and is provided with the pitch-changing motor 20, the pitch-changing motor 20 is used for driving the connecting strut to change the rotation angle of the whole mechanism so as to realize pitch angle adjustment, an output shaft of the pitch-changing motor 20 enters the inside of the test section 4 through a hole in the test section, and the end part of the output shaft is sequentially connected with a plurality of sections of wing profiles, such as a first section of wing profile 15, a second section of wing profile 16, a third section of wing profile 17, a fourth section of wing profile 18 and a fifth section of wing profile 19, and the pitch angle positions of the wing profiles can be changed through the driving of the pitch-changing motor, so that five sections of wing profiles can be measured simultaneously in one test.

The number of the sub-air outlets corresponds to the number of the multi-section wing profiles, and the position of each air outlet corresponds to one section of corresponding rotating paddle profile for testing.

As shown in fig. 7, a load cell 10 may be provided between each of the sections of the multi-section airfoil.

As shown in fig. 2, a symmetrical semicircular revolving body is provided between the return section 6 and the buffer section 7 for connecting the return section 6 and the buffer section 7. The two ends of the buffer section 7 are also respectively provided with a variable-cross-section rectangular connecting section, the expansion end of the variable-cross-section rectangular is connected with one end of the symmetrical semicircular revolving body, and the variable-cross-section rectangular contraction section is connected with the two ends of the buffer section 7.

Based on the utility model, a aerodynamic force test method for simulating the rotating state of a propeller can be implemented, as shown in fig. 1, and the method comprises the following steps:

(1) The test system shown in fig. 2 is built, the flow field parameters are controlled by the control system, and the flow field parameters are calibrated on the premise that the uniformity and the tightness of the flow field meet the requirements.

(2) When the airfoil to be tested is a single section airfoil, the model is subjected to a mounting test as shown in fig. 3 and 4. The single-section airfoil profile characterizes the average morphology and the flow field of the corresponding section position of the propeller, the initial installation angle and the incoming flow speed are determined by decomposing according to a speed triangle, a high-precision multi-component force balance with the range coverage is selected according to the result of numerical calculation, aerodynamic tests are carried out on the single-section airfoil profiles under different incoming flow speeds, different pressures and different pitch angles, and experimental data are recorded for analysis and calculation efficiency.

(3) When the airfoil to be tested is a full-sized multi-section airfoil, an installation test is performed on the model as in fig. 5. The conventional contraction section is replaced by a variable cross-section shear type contraction section, the cross section of the sectional contraction section is designed according to the sum speed of the sectional anisotropic center line speed and the incoming flow speed, the inlet area of the cross section of the corresponding contraction section is identical to the product of the inlet area and the speed, the outlet area is consistent, the outlet parameters of the corresponding different contraction sections are different, and the adjacent contraction section cross section is utilized to mix shear flow to form a gradual change incoming flow field, so that the nozzle with the variable incoming flow speed is realized.

(4) And (3) replacing the debugged variable cross-section contracted section in the step (3) in the figure 5, connecting a debugging simulation test system, and sequentially installing and debugging a first section of wing profile, a second section of wing profile, a third section of wing profile, a fourth section of wing profile, a fifth section of wing profile, a pitch-variable motor, a cantilever support and a pitch angle adjusting mechanism according to the figure 6, and driving the pitch-variable motor to adjust the pitch angles of the plurality of sections of wing profiles through the pitch angle adjusting mechanism.

(5) Decomposing the test system and the multi-section airfoils which are installed and debugged in the step (4) according to a speed triangle, determining an initial installation angle and an incoming flow speed, selecting a high-precision multi-component force measuring balance covered by a measuring range according to a numerical calculation result, arranging balances of different measuring ranges between adjacent airfoils, simultaneously carrying out aerodynamic force tests on the first section airfoil to the fifth section airfoil under different incoming flow speeds, different pressures and different pitch angles, and recording experimental data for analyzing and calculating efficiency.

(6) And (3) adjusting the incoming flow wind speed, the total pressure and the variable cross-section inlet area of the contraction section, ensuring that the similarity conditions of the simulated three-dimensional surface elements meet the geometric similarity and motion similarity criteria, sequentially adjusting the pitch angle position, the incoming flow wind speed and the total pressure according to the pitch angle information determined in the numerical calculation result, repeating the step (5), and completing multiple tests to obtain aerodynamic results of the multi-section airfoil propeller under different pitch angles and working conditions.

(7) After the test model making, connection and simulation test of the steps are completed, data acquisition and processing work is completed, aerodynamic data of each segmented airfoil corresponding to different pitch angles are summed up, and corresponding propeller thrust, torque and efficiency information under different working conditions are finally obtained.

What is not described in detail of the present utility model is common knowledge of a person skilled in the art.

Claims (8)

1. A aerodynamic force test system for simulating a rotation state of a propeller, comprising: the device comprises a hole body structure (2), a contraction section (3), a test section (4), a test device (5), a reflux section (6) and a buffer section (7); wherein, the liquid crystal display device comprises a liquid crystal display device,

the hole body structure (2) comprises a left semicircular revolving body and a right semicircular revolving body which are symmetrically arranged left and right; one end of the left semicircular revolving body is used as an air outlet to be connected with an air inlet of the contraction section (3);

the shrinkage section (3) is a hollow cavity with a gradually reduced cross section, one end of the shrinkage section (3) with a larger cross section area is used as an air inlet, and the other end with a smaller cross section area is used as an air outlet; the air outlet of the contraction section (3) is connected with the air inlet at one end of the test section (4);

the test section (4) is a hollow cavity, and a propeller and a test carrier are arranged in the cavity; the air outlet at the other end of the test section (4) is connected with the air inlet of the reflux section (6);

the testing device (5) is used for bearing the propeller, adjusting the pitch angle of the propeller and measuring aerodynamic force data of the propeller;

the backflow section (6) is a sealed expansion section body with rectangular interfaces at two ends, and one end of the backflow section (6) with a smaller section is used as an air outlet of the air inlet connection test section (4); one end of the reflux section (6) with a larger section is used as an air outlet to be connected with an air inlet of the right semicircular revolving body; the air outlet at the other end of the right semicircular revolving body is connected with the air inlet at one end of the buffer section (7);

the buffer section (7) is a hollow cuboid, a multilayer damping disturbance flow net is arranged in the buffer section (7), and the other end of the buffer section (7) is used as an air outlet to be connected with an air inlet at the other end of the left semicircular revolving body.

2. The system according to claim 1, wherein the testing device (5) comprises, when the propeller is a single-section airfoil: the device comprises a supporting structure (8), a pitch angle adjusting device (9), a force measuring balance (10) and a switching support rod (12);

the pitch angle adjusting device (9) is arranged on the supporting structure (8), an extension section of an adjusting end of the pitch angle adjusting device (9) is connected with one end of the force measuring balance (10), the other end of the force measuring balance (10) is connected with one end of the switching support rod (12), and the other end of the switching support rod (12) is connected with a single-section airfoil.

3. The system according to claim 1, wherein the testing device (5) comprises, when the propeller is a multi-section airfoil: the device comprises a supporting structure (8), a pitch angle adjusting device (9), a force measuring balance (10), a switching support rod (12), a pitch-changing motor (20) and a cantilever supporting structure (21); the device is characterized in that the pitch angle adjusting device (9) is arranged on the supporting structure (8), a cantilever at the adjusting end of the pitch angle adjusting device (9) penetrates through the cantilever supporting structure (21) and is provided with the variable-pitch motor (20), an output shaft of the variable-pitch motor (20) enters the inside of the test section (4), the end part of the output shaft is connected with the multi-section airfoil through a series combination of the force measuring balance (10) and the switching support rod (12), and the series combination of the force measuring balance (10) and the switching support rod (12) is arranged between each section airfoil of the multi-section airfoil.

4. A system according to claim 3, wherein when the propeller is of multi-section airfoil type, the constriction section (3) further comprises a plurality of sub-vents divided by a plurality of comb-arranged air guide plates; the number of sub-vents corresponds to the number of sections of airfoils (14), one section of airfoil for each sub-vent.

5. The system of claim 4, wherein a cross-sectional width of each of the sub-vent outlets is the same as a width of a respective segmented airfoil; each sectional airfoil is of a hollow structure.

6. The system according to claim 1, wherein the two ends of the buffer section (7) are respectively provided with a connecting section with a gradually-changed cross section rectangle, two ends with smaller cross sections of the connecting sections are respectively connected with the two ends of the buffer section (7), one end with larger cross section of the connecting section is connected with the air outlet of the right semicircular revolving body, and the other end with larger cross section of the connecting section is connected with the air inlet of the left semicircular revolving body.

7. The system of claim 1, wherein the multi-layer damping disturbance network is 5-10 layers of damping disturbance networks, each layer of damping disturbance network having a thickness of at least 10cm.

8. The system according to claim 1, wherein the interfaces at two ends of the backflow section (6) are rectangular, and the outer wall surface of the backflow section (6) is in gradual transition with a conic section, and the outer wall is equal in thickness.

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