CN117782612A - Outdoor crosswind test equipment for aeroengine - Google Patents
Outdoor crosswind test equipment for aeroengine Download PDFInfo
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- CN117782612A CN117782612A CN202311836902.4A CN202311836902A CN117782612A CN 117782612 A CN117782612 A CN 117782612A CN 202311836902 A CN202311836902 A CN 202311836902A CN 117782612 A CN117782612 A CN 117782612A
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- 238000012360 testing method Methods 0.000 title claims abstract description 86
- 238000009792 diffusion process Methods 0.000 claims abstract description 16
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 12
- 239000007921 spray Substances 0.000 claims abstract description 9
- 230000008602 contraction Effects 0.000 claims abstract description 5
- 238000007789 sealing Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 7
- 238000005259 measurement Methods 0.000 description 7
- 238000000926 separation method Methods 0.000 description 4
- 230000000712 assembly Effects 0.000 description 3
- 238000000429 assembly Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000011156 evaluation Methods 0.000 description 2
- 235000004443 Ricinus communis Nutrition 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000002079 cooperative effect Effects 0.000 description 1
- 230000000875 corresponding effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention provides open-air crosswind test equipment for an aeroengine, which relates to the technical field of crosswind tests, and comprises a wind tunnel structure, wherein the wind tunnel structure comprises an air inlet pipe section, a fan pipe section, a diffusion pipe section, a stable pipe section, a contraction pipe section and a spray pipe section which are sequentially communicated along the airflow direction; a fan device is arranged in the fan pipe section; the diameter of the diffuser section is gradually wider along the flow direction of the air flow; a plurality of rectifying nets are sequentially arranged in the stabilizing pipe section along the flowing direction of the air flow; the diameter of the contracted pipe section is gradually reduced along the flowing direction of the air flow, the crosswind test equipment can adapt to the open-air test environment, the on-way resistance loss is reduced through pneumatic and overall layout design, the air outlet flow of the wind tunnel structure is large, the dynamic pressure uniformity is good, and the air outlet flow and the dynamic pressure uniformity of the wind tunnel structure are ensured to meet test requirements.
Description
Technical Field
The invention belongs to the technical field of crosswind tests, and particularly relates to open-air crosswind test equipment for an aeroengine.
Background
The engine is often influenced by side wind during the test run of the ground open-air test bed, so that the engine works unstably, and the thrust measurement and performance evaluation of the engine are influenced. The purpose of the engine crosswind test is to verify the compatibility of the air inlet channel and the engine under the crosswind condition. Strong crosswinds in natural space may cause distortion of the engine intake airflow, resulting in unstable compressor operation and even surge. Therefore, it is necessary to develop a device specially used for testing and researching the outdoor crosswind of the engine so as to obtain the response of the engine and the flow characteristics of the air inlet channel under different wind directions and wind speeds, and determine the ground working crosswind boundary of the engine, so that the compatibility of the air inlet channel and the engine is optimized, and the safety operation of the aircraft under the crosswind condition is ensured.
Disclosure of Invention
The invention aims to provide open-air crosswind test equipment for an aeroengine aiming at the defects of the prior art, so as to solve the problems that the engine provided in the prior art is always influenced by crosswind during the ground open-air test bed test, so that the engine is unstable in operation and the thrust measurement and performance evaluation of the engine are influenced, and the compatibility of an engine inlet channel and the engine is not easy to obtain crosswind meeting test requirements in the prior art.
In order to achieve the above object, the present invention provides an outdoor crosswind test apparatus for an aeroengine, the crosswind test apparatus comprising a wind tunnel structure including an intake pipe section, a fan pipe section, a diffuser pipe section, a stabilizer pipe section, a constrictor pipe section, and a nozzle section which are sequentially communicated in an airflow direction;
a fan device is arranged in the fan pipe section;
the diameter of the diffusion pipe section gradually widens along the flow direction of the airflow;
a plurality of rectifying nets are sequentially arranged in the stable pipe section along the flowing direction of the airflow;
the diameter of the contracted pipe section is tapered along the flow direction of the air flow.
Preferably, the outdoor crosswind test device for the aero-engine further comprises a vehicle body, wherein a plurality of lifting upright posts are distributed at the bottom of the vehicle body, and the wind tunnel structure is arranged on the vehicle body.
Preferably, the outdoor crosswind test device for an aeroengine further comprises a flow field calibration device, wherein the flow field calibration device can be arranged at a position close to an air outlet of the wind tunnel structure, and the flow field calibration device comprises:
a support frame;
the bent is arranged in the supporting frame;
the anemometers are distributed on the bent frame;
the movable casters are distributed at the bottom of the supporting frame;
the lifting support legs are distributed at the bottom of the supporting frame.
Preferably, the air inlet of the air inlet pipe section is in a horn shape, and a filter screen is arranged in the air inlet pipe section.
Preferably, a collecting port is arranged between the air outlet of the air inlet pipe section and the air inlet of the fan pipe section.
Preferably, the diffuser section is provided with a preset equivalent diffusion angle, and a rectifying net is arranged in the air outlet of the diffuser section.
Preferably, the side wall of the stable pipe section is provided with a plurality of annular openings, the openings are connected with cover plates in a sealing manner, rectifying plates are arranged on two sides of the position, close to the rectifying net, of the inside of each opening, supporting pieces are arranged in the openings, a plurality of tensioning structures are distributed on the supporting pieces in the openings, the tensioning structures are connected with clamping structures, and each rectifying net penetrates through one opening and is connected with the clamping structures in the openings.
Preferably, the tensioning structure comprises:
a sleeve coupled to the support;
the screw rod penetrates through the sleeve and the supporting piece, and the bottom end of the screw rod is connected with the clamping structure;
the spring is sleeved on the screw rod, the bottom end of the spring is connected with the supporting piece, the top end of the spring is connected with a supporting seat, the supporting seat is penetrated at the top end of the screw rod, a tensioning nut is connected with the top end of the screw rod in a threaded manner, and the tensioning nut is in contact with the supporting seat.
Preferably, the clamping structure comprises:
the rectifying net is arranged between the two adjacent clamping plates;
and the bolts penetrate through the at least two clamping plates and are connected with the locking nuts.
Preferably, the inner diameters of the spray pipe sections are the same, and a pitot tube can be connected to the air outlet of the spray pipe sections.
The invention provides outdoor crosswind test equipment for an aeroengine, which has the beneficial effects that: the air inlet pipe section of the side air test equipment provides uniform airflow for the fan equipment of the fan pipe section as much as possible, the air flow loss of an air inlet of a wind tunnel structure is reduced, the fan equipment is arranged in the fan pipe section of the side air test equipment, the energy for maintaining the airflow is maintained when the fan equipment operates, the diameter of the diffusion pipe section of the side air test equipment is gradually widened along the flowing direction of the airflow, the diffusion pipe section is used for reducing the energy loss and the airflow noise, a plurality of rectifying nets are sequentially arranged in the stabilizing pipe section of the side air test equipment along the flowing direction of the airflow, the stabilizing pipe section has the functions of stabilizing the airflow from the outside in a turbulence uneven mode, vortex attenuation is achieved, the speed and the direction of the airflow are distributed more uniformly, better flow field quality is obtained, the diameter of the contraction pipe section of the side air test equipment is gradually reduced along the flowing direction of the airflow, the contraction pipe section is mainly used for enabling the airflow from the stabilizing pipe section to be uniformly accelerated, the flow field quality of a test area for placing test pieces is improved, the side air test equipment can adapt to the test environment, the flow loss along the way is reduced through pneumatic and overall layout design, the dynamic pressure uniformity of an air outlet of the wind tunnel structure is high, and the dynamic pressure uniformity of the air outlet is guaranteed, and the dynamic pressure uniformity of the structure is guaranteed, and the dynamic pressure test requirement of the structure is met.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The foregoing and other objects, features and advantages of the invention will be apparent from the following more particular descriptions of exemplary embodiments of the invention as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the invention.
FIG. 1 shows a schematic side view of an open air crosswind test device for an aircraft engine according to one embodiment of the invention;
FIG. 2 shows a schematic body construction of an open air crosswind test device for an aircraft engine according to an embodiment of the invention;
FIG. 3 shows a flow field calibration device configuration schematic for an open air crosswind test apparatus for an aircraft engine, according to one embodiment of the invention;
FIG. 4 shows an enlarged schematic view of the structure shown in FIG. 3A;
FIG. 5 shows a schematic cross-sectional view of a tensioning and clamping arrangement for an open air crosswind test device for an aircraft engine, according to an embodiment of the invention;
fig. 6 shows a schematic cross-sectional view of a tensioning arrangement of an open air crosswind-test device for an aircraft engine according to an embodiment of the invention.
1. An air inlet pipe section; 2. a fan pipe section; 3. a diffuser section; 4. stabilizing the pipe section; 5. shrinking the pipe section; 6. a spray pipe section; 7. a rectifying net; 8. a vehicle body; 9. a lock nut; 10. a flow field calibration device; 11. a support frame; 12. a bent frame; 13. an anemometer; 14. moving casters; 15. lifting the supporting leg; 16. an opening; 17. a cover plate; 18. a rectifying plate; 19. a support; 20. a tensioning structure; 21. a clamping structure; 22. a sleeve; 23. a screw; 24. a spring; 25. a support base; 26. tensioning the nut; 27. a clamping plate; 28. and (5) a bolt.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the preferred embodiments of the present invention are described below, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
As shown in fig. 1, the invention provides an outdoor crosswind test device for an aeroengine, which comprises a wind tunnel structure, wherein the wind tunnel structure comprises an air inlet pipe section 1, a fan pipe section 2, a diffusion pipe section 3, a stable pipe section 4, a contraction pipe section 5 and a spray pipe section 6 which are sequentially communicated along the airflow direction;
a fan device is arranged in the fan pipe section 2;
the diameter of the diffuser section 3 gradually widens in the flow direction of the air flow;
a plurality of rectifying nets 7 are sequentially arranged in the stabilizing pipe section 4 along the flowing direction of the air flow;
the diameter of the convergent section 5 tapers in the direction of flow of the air flow.
Specifically, in order to solve the problem that the prior art is not easy to obtain the crosswind meeting the test requirement to optimize the compatibility of an engine air inlet channel and an engine, the invention provides an open-air crosswind test device for an aeroengine, an air inlet pipe section 1 of the crosswind test device provides uniform airflow for fan devices of a fan pipe section 2 as much as possible to reduce the air inlet airflow loss of a wind tunnel structure, the fan devices are arranged in the fan pipe section 2 of the crosswind test device, the energy for maintaining the airflow is used for maintaining the energy of the airflow when the fan devices are operated, the diameter of a diffusion pipe section 3 of the crosswind test device is gradually widened along the airflow flowing direction, the diffusion pipe section 3 is used for reducing the energy loss and the airflow noise, a plurality of rectifying nets 7 are sequentially arranged in the stabilizing pipe section 4 of the crosswind test device along the airflow flowing direction, the function of the stable tube section 4 is to stabilize the turbulence uneven air flow from the outside, attenuate the vortex, make the speed and direction distribution of the air flow more uniform, obtain better flow field quality, the diameter of the contracted tube section 5 of the crosswind test device is gradually reduced along the flow direction of the air flow, the contracted tube section 5 mainly accelerates the air flow from the stable tube section 4 uniformly, and promote the flow field quality of the test area for placing test pieces, has higher fluency index, the crosswind test device can adapt to the open-air test environment, reduces the along-path resistance loss through pneumatic and overall layout design, has high air outlet flow and good dynamic pressure uniformity of the wind tunnel structure, and ensures that the air outlet flow and dynamic pressure uniformity of the wind tunnel structure meet the test requirement.
Specifically, the shrinkage tube section 5 is mainly used for uniformly accelerating the air flow from the stable tube section 4 and improving the quality of a flow field of a test area for placing a test piece, the test piece can be an aeroengine, the unevenness and the turbulence of a jet air outlet flow field of a wind tunnel structure of the side wind test equipment are inversely proportional to the square of a shrinkage ratio, the uniformity of the flow field of the test area can be obviously improved by increasing the shrinkage ratio, the turbulence is reduced, and a curve of the shrinkage tube section 5 of the side wind test equipment adopts a hyperbolic curve design;
wherein R is 1 -a convergent section inlet cross-sectional radius (m);
R 2 -a convergent section outlet cross-section radius (m);
the R-axial distance is the cross-sectional radius (m) at x;
l-constriction length (m);
x m -front and back of two curvesThe connection point.
As shown in fig. 1 and 2, the outdoor crosswind test device for an aeroengine preferably further comprises a vehicle body 8, wherein a plurality of lifting columns are distributed at the bottom of the vehicle body 8, and a wind tunnel structure is arranged on the vehicle body 8.
Specifically, the position of the wind tunnel structure of the crosswind test equipment can be adjusted in direction and position through the vehicle body 8, the stepless adjustable capacity is realized, the device can be parked at any position of 0-180 degrees, the movement in each direction is realized, the requirements of different wind directions are met, the central height can be adjusted through the lifting upright post 9, the lifting stroke is ensured to be at least +/-350 mm, the position adjustment of the central height of the wind tunnel structure is realized, and the test requirements of development of relevant models are fully met.
The vehicle body 8 is in the form of a loading flat transport vehicle, the movement of the whole equipment in all directions is realized, a driving device of the vehicle body 8 can be set to be driven in a distributed mode, a group of driving wheel assemblies are respectively arranged at the front part and the rear part of the equipment, the power module provides power for driving the vehicle body 8 forwards, the rest wheels of the vehicle body 8 are all set to be driven wheel assemblies, a steering mechanism is arranged on each group of driving wheel assemblies, the wheels are driven by a hydraulic rod to realize independent steering of the vehicle body 8, and the cooperative action in the steering process of the wheels is realized by cooperation between an electric control system and the hydraulic system.
As shown in fig. 3 and 4, the outdoor crosswind test apparatus for an aeroengine preferably further includes a flow field calibration device 10, where the flow field calibration device 10 can be disposed near an air outlet of the wind tunnel structure, and the flow field calibration device includes:
a support frame 11;
a bent 12, the bent 12 being disposed within the support frame 11;
a plurality of anemometers 13, the plurality of anemometers 13 being distributed on the bent 12;
a plurality of moving casters 14, the plurality of moving casters 14 being distributed at the bottom of the supporting frame 11;
a plurality of lifting legs 15, the plurality of lifting legs 15 being distributed at the bottom of the support frame 11.
Specifically, the flow field measurement of the air outlet section of the wind tunnel structure of the crosswind test equipment can share a set of flow field calibration device 10 with the flow field measurement of the air inlet and outlet section of the test piece, a plurality of anemometers 13 are used for measuring the air outlet uniformity of the wind tunnel structure, the bent frame 12 is a cross measurement bent frame, and in order to reduce the influence of the flow field calibration device on the air inlet flow field of the test piece as much as possible, the cross measurement bent frame for installing the anemometers adopts a flange plate type design mode in design;
the movable castor 14 and the lifting supporting leg 15 of the crosswind test equipment can be respectively guaranteed to be adjustable in position and height, and the gravity center position of the wind tunnel structure can be effectively reduced in the adjusting process, so that the wind tunnel structure is prevented from overturning.
Preferably, the air inlet of the air inlet pipe section 1 is in a horn shape, and a filter screen is arranged in the air inlet pipe section 1.
Specifically, the air inlet pipe section 1 is the forefront part of the wind tunnel structure of the crosswind test device, and mainly aims to provide uniform airflow as much as possible for fan equipment of the fan pipe section 2 and reduce air flow loss of an air inlet of the wind tunnel structure, and the air inlet pipe section 1 adopts a horn mouth form and is internally provided with a filter screen so as to prevent sundries and the like from entering the wind tunnel structure.
Preferably, a collecting port is arranged between the air outlet of the air inlet pipe section 1 and the air inlet of the fan pipe section 2.
Specifically, when the crosswind test equipment runs, energy for maintaining gas flow is provided by rotation of the fan equipment, and because the crosswind test equipment is of a direct current down-blowing structure, in order to ensure the air inlet airflow angle of the fan pipe section 2 and avoid overlarge separation on the wall surface, a corresponding collecting port is arranged at an air inlet of the fan pipe section 2, the air inlet airflow speed direction of the fan pipe section 2 is ensured to be parallel to the axial direction of a wind tunnel structure as much as possible, the fan pipe section 2 is positioned behind the collecting port, the cross section of the fan pipe section 2 is circular, the fan equipment comprises fan blades, a fairing, a driving motor, a rotation stopping sheet and a supporting sheet, and the fan blades are designed according to the fairing size and the driving motor size, and the driving motor can be placed in the fairing.
Preferably, the diffuser section 3 is provided with a set equivalent diffusion angle, and the inside of the air outlet of the diffuser section 3 is provided with a rectifying net 7.
Specifically, in order to reduce energy loss and airflow noise, the diffuser section 3 is arranged behind the fan section 2, the equivalent diffusion angle is about 16.37 degrees, and due to the fact that the equivalent diffusion angle is larger, a layer of rectifying net 7 is arranged in the air outlet of the diffuser section 3, airflow separation can be effectively reduced, and the purposes of reducing resistance loss and improving dynamic pressure uniformity of the air outlet of the wind tunnel structure are achieved.
When the equivalent diffusion angle of the diffuser section 3 is smaller than 45 °, a layer of rectifying net 7 is arranged in the diffuser section 3, and no obvious separation will occur when the air flow passes through the diffuser section 3 with a large angle.
As shown in fig. 5 and 6, preferably, the side wall of the stable pipe section 4 is provided with a plurality of annular openings 16, the openings are connected with cover plates 17 in a sealing manner, rectifying plates 18 are arranged on two sides of the position, close to the rectifying net 7, inside the openings 16, supporting pieces 19 are arranged inside the openings 16, a plurality of tensioning structures 20 are distributed on the supporting pieces 19 inside the openings 16, the tensioning structures 20 are connected with clamping structures 21, and each rectifying net 7 penetrates through one opening 16 and is connected with the plurality of clamping structures 21 inside the openings 16.
Specifically, the function of the stabilizing tube section 4 is to stabilize the turbulence uneven airflow from the outside, attenuate the vortex, make the speed and direction distribution more uniform, in order to obtain better flow field quality, install the three-layer rectifying net 7 in the stabilizing tube section 4, keep and increase the opening of the fourth layer rectifying net 7 at the same time, in order to ensure the uniformity of the airflow, facilitate the installation and maintenance of the rectifying net 7, the rectifying net 7 adopts the integral structural design, the rectifying net 7 adopts the special tensioning structure 20 to tension, ensure the tensioning degree of each rectifying net 7, so as to improve the rectifying effect.
Preferably, the tensioning structure 20 comprises:
a sleeve 22, the sleeve 22 being connected to the support 19;
the screw 23, the screw 23 wears the sleeve 22 and the supporting piece 19, the bottom of the screw 23 connects with the clamping structure 21;
the spring 24, spring 24 cup joints on screw rod 23, and the bottom and the support piece 19 of spring 24 are connected, and the top of spring 24 is connected with supporting seat 25, and supporting seat 25 is worn to establish on the top of screw rod 23, and the top threaded connection of screw rod 23 has tensioning nut 26, tensioning nut 26 and supporting seat 25 contact.
Specifically, in the tensioning process, the tensioning nut 26 is screwed, the screw 23 moves outwards, and the tensioning of the tensioning net 7 can be achieved by pulling the tensioning net 7 on the clamping structure 21.
Preferably, the clamping structure 21 comprises:
at least two clamping plates 27, the rectifying net 18 being arranged between two adjacent clamping plates 27;
a bolt 28, the bolt 28 passing through at least two clamping plates 27 and being connected with the lock nut 9.
Specifically, when the lock nut 9 is locked, the two clamping plates 27 can clamp the rectifying net 7.
Preferably, the inner diameters of the nozzle segments 6 are identical, and a pitot tube can be connected to the air outlet of the nozzle segments 6.
Specifically, when the wind speed is marked, the pitot tube is utilized to monitor the air outlet of the spray pipe section 6, and the dynamic pressure field of the air outlet is measured, so that the relation curve of the wind speed of the air outlet of the spray pipe section 6 and the power of fan equipment can be given, the air outlet flow rate of the wind tunnel structure is not higher than 1500kg/s, and the dynamic pressure uniformity is not higher than 5%.
In summary, when the outdoor crosswind test equipment of the aeroengine is implemented, before the wind tunnel structure operates, the wind speed calibration work is required to be carried out on the section of the air inlet and the section of the air outlet of the test piece, and the flow field calibration device is used for carrying out wind speed measurement on the section of the inlet and the outlet of the test piece, so that the relation between the power of the rotating speed of the fan equipment and the wind speed of the section of the inlet and the outlet of the test piece is obtained;
conveying the wind tunnel structure from the storage area to the test area by using the vehicle body 8 according to the operation rules, and pre-positioning, connecting and fixing the vehicle body 8 according to the angle and the position parameters of the test working condition;
according to the central height parameter of the test working condition, the vehicle body 8 is adjusted to enable the position and the central height of the wind tunnel structure to meet the test requirement, the vehicle body 8 ensures that the lifting travel is at least +/-350 mm, and the vehicle body is parked at any position in the direction of 0-180 degrees;
confirming whether the starting condition parameters of the fan equipment, such as bearing temperature, vibration signals and the like are normal or not, setting the operation parameters of the fan equipment according to the wind speed calibration result, and starting the fan equipment;
because the back pressure of the air inlet of the fan device is low, the ambient atmosphere is subjected to preliminary rectification through the air inlet pipe section 1 and then is subjected to supercharging through the fan device, the ambient atmosphere enters the diffusion pipe section 3 to be subjected to decelerating and supercharging, the resistance loss is reduced, the rectifying net 7 of the diffusion pipe section 3 effectively inhibits the air flow separation, the air flow quality of the air outlet is improved, the turbulence degree is further reduced after the air flow is subjected to rectification through the three-layer rectifying net 7 of the stabilizing pipe section 4 once, and after the air flow is subjected to shrinkage acceleration through the shrinkage pipe section 5, the dynamic pressure uniformity and the flow field with the flow meeting test requirements are generated on the air outlet section of the spray pipe section 6, so that the compatibility of the air inlet and the engine is optimized, and the guarantee is provided for the safe operation of the aircraft under the side wind condition.
The foregoing description of embodiments of the invention has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described.
Claims (10)
1. The outdoor crosswind test equipment for the aeroengine is characterized by comprising a wind tunnel structure, wherein the wind tunnel structure comprises an air inlet pipe section, a fan pipe section, a diffusion pipe section, a stabilizing pipe section, a contraction pipe section and a spray pipe section which are sequentially communicated in the airflow direction;
a fan device is arranged in the fan pipe section;
the diameter of the diffusion pipe section gradually widens along the flow direction of the airflow;
a plurality of rectifying nets are sequentially arranged in the stable pipe section along the flowing direction of the airflow;
the diameter of the contracted pipe section is tapered along the flow direction of the air flow.
2. An outdoor crosswind testing device for an aircraft engine according to claim 1, further comprising a vehicle body, wherein a plurality of lifting columns are distributed at the bottom of the vehicle body, and wherein the wind tunnel structure is disposed on the vehicle body.
3. An open air crosswind testing apparatus for an aircraft engine according to claim 1, further comprising a flow field calibration device positionable adjacent an air outlet of the wind tunnel structure, the flow field calibration device comprising:
a support frame;
the bent is arranged in the supporting frame;
the anemometers are distributed on the bent frame;
the movable casters are distributed at the bottom of the supporting frame;
the lifting support legs are distributed at the bottom of the supporting frame.
4. An outdoor crosswind testing device for an aircraft engine according to claim 1, wherein the inlet of the inlet pipe section is trumpet-shaped, and a filter screen is provided inside the inlet pipe section.
5. An outdoor crosswind testing device for an aircraft engine according to claim 1, wherein a collection port is provided between the air outlet of the air inlet pipe section and the air inlet of the fan pipe section.
6. An outdoor crosswind testing device for an aircraft engine according to claim 1, wherein the diffuser section is provided with a set equivalent diffuser angle and the inside of the air outlet of the diffuser section is provided with a rectifying net.
7. An outdoor crosswind test device for an aeroengine according to claim 1, wherein the side wall of the stable tube section is provided with a plurality of annular openings, the openings are connected with cover plates in a sealing manner, rectifying plates are arranged on two sides of the position, close to the rectifying net, of the inside of the openings, supporting pieces are arranged in the openings, a plurality of tensioning structures are distributed on the supporting pieces in the openings, the tensioning structures are connected with clamping structures, and each rectifying net penetrates through one opening and is connected with the clamping structures in the opening.
8. An open air crosswind testing device for an aircraft engine as claimed in claim 7, wherein said tensioning structure comprises:
a sleeve coupled to the support;
the screw rod penetrates through the sleeve and the supporting piece, and the bottom end of the screw rod is connected with the clamping structure;
the spring is sleeved on the screw rod, the bottom end of the spring is connected with the supporting piece, the top end of the spring is connected with a supporting seat, the supporting seat is penetrated at the top end of the screw rod, a tensioning nut is connected with the top end of the screw rod in a threaded manner, and the tensioning nut is in contact with the supporting seat.
9. An open air crosswind testing device for an aircraft engine as claimed in claim 7, wherein said clamping structure comprises:
the rectifying net is arranged between the two adjacent clamping plates;
and the bolts penetrate through the at least two clamping plates and are connected with the locking nuts.
10. An open air crosswind testing device for an aircraft engine according to claim 8, wherein the nozzle segments have the same internal diameter, and the nozzle segments have pitot tubes connected to their air outlets.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311836902.4A CN117782612A (en) | 2023-12-28 | 2023-12-28 | Outdoor crosswind test equipment for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311836902.4A CN117782612A (en) | 2023-12-28 | 2023-12-28 | Outdoor crosswind test equipment for aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117782612A true CN117782612A (en) | 2024-03-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311836902.4A Pending CN117782612A (en) | 2023-12-28 | 2023-12-28 | Outdoor crosswind test equipment for aeroengine |
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| Country | Link |
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| CN (1) | CN117782612A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118010295A (en) * | 2024-04-09 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Engine bench for supersonic concurrent direct connection wind tunnel test and design method |
-
2023
- 2023-12-28 CN CN202311836902.4A patent/CN117782612A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118010295A (en) * | 2024-04-09 | 2024-05-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Engine bench for supersonic concurrent direct connection wind tunnel test and design method |
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