CN114199497A - Wind field environment simulation wind tunnel structure for engine bench test - Google Patents
Wind field environment simulation wind tunnel structure for engine bench test Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 47
- 238000004088 simulation Methods 0.000 title claims abstract description 23
- 238000013016 damping Methods 0.000 claims abstract description 116
- 230000008602 contraction Effects 0.000 claims abstract description 14
- 230000006641 stabilisation Effects 0.000 claims abstract description 7
- 238000011105 stabilization Methods 0.000 claims abstract description 7
- 238000005507 spraying Methods 0.000 claims description 27
- 238000010438 heat treatment Methods 0.000 claims description 10
- 230000007613 environmental effect Effects 0.000 claims description 9
- 241000264877 Hippospongia communis Species 0.000 description 139
- 239000007789 gas Substances 0.000 description 44
- 238000001816 cooling Methods 0.000 description 9
- 238000001914 filtration Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 239000003595 mist Substances 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000002918 waste heat Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005094 computer simulation Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
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- 230000002123 temporal effect Effects 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to an engine bench test wind field environment simulation wind tunnel structure which comprises a power section, a contraction section, a steady flow section, a gradually expanding section and a honeycomb damping section which are sequentially arranged, wherein a wind source generated by the power section passes through the contraction section, the density of airflow is increased to form a gas mixed flow, the gas mixed flow enters the steady flow section, the uniformity of the airflow is improved, the speed of the airflow entering the gradually expanding section is reduced, and the airflow further enters the honeycomb damping section for stabilization. Through designing two-stage honeycomb structure wind tunnel device, through the broken vortex of two-stage honeycomb, lead in the same direction as and draw equal air current to through adjusting the distance between two honeycomb, find the optimum position, through the honeycomb stationary flow of two-stage different structures, realize the adjustment to wind field homogeneity and flow field quality, satisfy under the finite space condition of laboratory, simulate out the wind field that is fit for the experimental needs of multiple model, wind speed and environment. The wind tunnel structure integrally adopts a sectional combination and integral connection mode, so that the wind tunnel structure is convenient to combine and move in a limited space of a laboratory.
Description
Technical Field
The invention relates to the technical field of engine test, in particular to an engine bench test wind field environment simulation wind tunnel structure.
Background
As the power of the developed engine is increased, the heat load is increased. The heat radiation of a heat exchange system and high-temperature components directly causes the thermal environment of an engine compartment to be deteriorated, and the power and the performance of the whole vehicle are influenced. The test period of the development of a loading cooling system and the matching test of the whole vehicle is shortened, and the performance of the cooling system is improved. By simulating the state of a cooling system of a finished automobile on an engine rack and simulating the performance of the cooling system of an engine in the use environment of the finished automobile, a cooling test simulation test device needs to be established under the condition that an engine laboratory simulates the finished automobile.
The patent (CN101750204B) discloses an engine simulator for high-speed wind tunnel dynamic simulation experiments, wherein an air inlet is positioned on an outer shell, the lower end of the air inlet is communicated with a gas collecting ring, a plurality of spray pipes are uniformly distributed on the inner wall of the outer shell, and the front ends of the spray pipes are communicated with the gas collecting ring; the pressure measuring pipes of the total pressure measuring rake and the static pressure measuring holes are gathered along a pressure measuring pipe channel and are led out from the upper rear part of the outer shell after being gathered into a whole, and the static pressure measuring holes and the total pressure measuring rake are positioned behind the rectifier. The invention has compact structure, each parameter is strictly calculated, each part and each component are convenient to disassemble and assemble, the experimental performance is stable and reliable, the precision is high, and the data is accurate.
The existing test method is to simulate the performance of a cooling system of an engine in the whole vehicle road environment by manufacturing a windward (environment wind field) through a high-power fan. Because the simulated wind field created by the fan is larger in and out of the wind field in the actual environment, and the randomness of the test environment is larger, the simulated windward wind field is not uniform, and the thermal environment of the engine compartment and the accuracy of the test are directly influenced.
Disclosure of Invention
In order to solve the problems, the invention provides an engine bench test wind field environment simulation wind tunnel structure, which realizes the adjustment of wind field uniformity and flow field quality through the flow stabilization of two stages of honeycomb bodies with different structures, and meets the requirement of simulating a wind field, wind speed and environment required by various machine type tests under the condition of limited space in a laboratory.
The technical scheme adopted by the invention is as follows: the utility model provides an engine bench test wind field environmental simulation wind tunnel structure which characterized in that: the wind source generated by the power section passes through the contraction section, the airflow density is increased to form a mixed gas flow, the mixed gas flow enters the steady flow section, the uniformity of the airflow is improved, the speed of the airflow entering the gradually expanding section is reduced, and the airflow further enters the honeycomb damping section for stabilization.
Preferably, the honeycomb damping section comprises a primary honeycomb damping section, a working section and a secondary honeycomb damping section, and after the airflow passes through the primary honeycomb damping section, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex in the gas flow.
Furthermore, the first-stage honeycomb damping section is provided with a movable honeycomb body which is of a structure with a small excircle aperture and a gradually increased central aperture.
Further, the secondary honeycomb damping section employs a fixed honeycomb.
Furthermore, the primary honeycomb damping section is connected with a stepping motor through a ball screw, and the distance between the primary honeycomb damping section and the secondary honeycomb damping section is adjusted through the stepping motor.
Preferably, a spraying section and a heating section are arranged between the power section and the contraction section.
Furthermore, the spraying section is provided with a spraying device.
Further, the heating section is provided with a heat exchanger.
Preferably, a flow guide section is arranged between the steady flow section and the divergent section.
Furthermore, the flow guide section is provided with a flow guide sheet and a flow guide sheet angle adjusting motor.
The beneficial effects obtained by the invention are as follows: because the space of the laboratory is limited, the wind tunnel device for simulating the head-on wind cannot be too long and too large, and if an ideal test wind field is simulated in a wind tunnel structure with a short distance, the wind tunnel device is very challenging. Through designing two-stage honeycomb structure wind tunnel device (one-level honeycomb damping section and second grade honeycomb damping section), through the broken vortex of two-stage honeycomb, lead in the same direction and draw equal air current to through adjusting the distance between two honeycombs, find the optimum position, through the honeycomb stationary flow of two-stage not isostructure, realize the adjustment to wind field homogeneity and flow field quality, satisfy under the finite space condition of laboratory, simulate out the wind field that is fit for the experimental needs of multiple model, wind speed and environment. The wind tunnel structure integrally adopts a sectional combination and integral connection mode, so that the wind tunnel structure is convenient to combine and move in a limited space of a laboratory. The invention has the following advantages:
1. designing the uniformity of a wind field: through the combination of gradual change aperture honeycomb body design and second grade honeycomb body structural design, can be according to the experimental demand of different models, through adjusting distance between two honeycomb bodies, through two-stage honeycomb body vortex air flow filtering, better leading is in the same direction as and draws equal air current for the simulation wind field is optimized more, and air velocity, wind field distribution more tend to be even. The requirements of different machine types on the uniformity of the wind field are met;
2. designing a wind tunnel diversion tail wing: because the space of the laboratory is limited, the steady flow section of the wind tunnel cannot be very long, and when the air flow is adjusted to the maximum air flow, the wind tunnel easily generates jet flow, so that the distribution uniformity of an air flow field is influenced. The guide vane is additionally arranged on the divergent section through a simulation test, so that jet flow of the wind tunnel in large flow is effectively controlled. The tail wing flow guide structure comprises a tail wing, a return spring, a tail wing angle adjusting pull wire, a positioning device and the like;
3. high-temperature wind field simulation: the exhaust gas waste heat (150-300 ℃) of an exhaust pipe of an engine test is led in, the heat exchanger is adopted for replacement, air at the inlet end of the wind tunnel is heated through the heat exchanger, and the temperature of the air inlet end of the wind tunnel is controlled by controlling the air inflow method of the exhaust gas of the engine into the heat exchanger. Therefore, the state of a cooling system of the engine in the whole vehicle environment in a high-temperature state is simulated;
4. simulating a spraying wind field: a grid-type water mist generator is designed at an inlet of the wind tunnel, a rainwater spraying test state is simulated, and the flow and pressure of a spraying system are controlled by a computer system, so that the aim of a simulated spraying test is fulfilled.
Drawings
FIG. 1 is a schematic structural view of the present invention;
reference numerals: 1. a power section; 1.1, a power fan; 1.2, a variable frequency motor; 2. a spraying section; 2.1, a spraying device; 3. a heating section (heat exchange); 3.1, an external circulation interface; 3.2, a heat exchanger; 4. a contraction section; 5. a steady flow section; 6. a flow guide section; 6.1, flow deflectors; 6.2, a flow deflector angle adjusting motor; 7. a gradual expansion section; 8. a primary honeycomb damping section; 8.1, a moving honeycomb body; 8.2, a stepping motor; 8.3, a guide shaft; 9. a working section; 10. secondary flow stabilization; 10.1, secondary honeycomb damping section.
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.
As shown in figure 1, the wind tunnel structure for simulating the wind field environment in the engine pedestal test comprises a power section 1, a contraction section 4, a steady flow section 5, a gradual expansion section 6 and a honeycomb damping section which are sequentially arranged, wherein a wind source generated by the power section 1 passes through the contraction section 4, the airflow density is increased to form a mixed airflow which enters the steady flow section 5, the airflow uniformity is improved, the airflow speed entering the gradual expansion section 6 is reduced, and the airflow further enters the honeycomb damping section for stabilization.
The first embodiment is as follows: a wind tunnel structure for simulating the wind field environment of an engine pedestal test comprises a power section 1, a contraction section 4, a steady flow section 5, a gradual expansion section 6 and a honeycomb damping section which are sequentially arranged, wherein a wind source generated by the power section 1 passes through the contraction section 4, the density of airflow is increased to form a gas mixed flow, the gas mixed flow enters the steady flow section 5, the uniformity of the airflow is improved, the speed of the airflow entering the gradual expansion section 6 is reduced, and the airflow further enters the honeycomb damping section for stabilization. In this embodiment, the power section 1 is provided with a power fan 1.1 and a variable frequency motor 1.2, and the variable frequency motor 1.2 drives the power fan 1.1 to provide an air source.
Example two: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow.
Example three: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow. The first-stage honeycomb damping section 8 is provided with a movable honeycomb body 8.1, and the movable honeycomb body is of a structure with small excircle aperture and gradually increased aperture close to the central part.
Example four: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow. The first-stage honeycomb damping section 8 is provided with a movable honeycomb body 8.1 which is of a structure that the diameter of an excircle is small and the diameter of a hole close to the central part is gradually increased; the secondary honeycomb damping section 10 uses a stationary honeycomb body 10.1.
Example five: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow. The first-stage honeycomb damping section 8 is provided with a movable honeycomb body 8.1 which is of a structure that the diameter of an excircle is small and the diameter of a hole close to the central part is gradually increased; the secondary honeycomb damping section 10 uses a stationary honeycomb body 10.1. The first-stage honeycomb damping section 8 is connected with a stepping motor 8.2 through a ball screw, the stepping motor 8.2 drives the first-stage honeycomb damping section 8 to move along a guide shaft 8.3, and the distance between the first-stage honeycomb damping section 8 and the second-stage honeycomb damping section 9 is further adjusted. One-level honeycomb body damping section 8 adopts the combination of gradual change aperture honeycomb body and second grade honeycomb body damping section 9, can be according to the experimental demand of different models, through adjusting distance between two honeycomb bodies, through two-stage honeycomb body vortex air flow filtering, better lead in the same direction with draw equal air current for the simulation wind field is optimized more, and air velocity, wind field distribution more tend to be even. The requirements of different machine types on the uniformity of the wind field are met.
Example six: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow. The first-stage honeycomb damping section 8 is provided with a movable honeycomb body 8.1 which is of a structure that the diameter of an excircle is small and the diameter of a hole close to the central part is gradually increased; the secondary honeycomb damping section 10 uses a stationary honeycomb body 10.1. The first-stage honeycomb damping section 8 is connected with a stepping motor 8.2 through a ball screw, the stepping motor 8.2 drives the first-stage honeycomb damping section 8 to move along a guide shaft 8.3, and the distance between the first-stage honeycomb damping section 8 and the second-stage honeycomb damping section 9 is further adjusted. One-level honeycomb body damping section 8 adopts the combination of gradual change aperture honeycomb body and second grade honeycomb body damping section 9, can be according to the experimental demand of different models, through adjusting distance between two honeycomb bodies, through two-stage honeycomb body vortex air flow filtering, better lead in the same direction with draw equal air current for the simulation wind field is optimized more, and air velocity, wind field distribution more tend to be even. The requirements of different machine types on the uniformity of the wind field are met. A spraying section 2 and a heating section 3 are arranged between the power section 1 and the contraction section 4.
Example seven: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow. The first-stage honeycomb damping section 8 is provided with a movable honeycomb body 8.1 which is of a structure that the diameter of an excircle is small and the diameter of a hole close to the central part is gradually increased; the secondary honeycomb damping section 10 uses a stationary honeycomb body 10.1. The first-stage honeycomb damping section 8 is connected with a stepping motor 8.2 through a ball screw, the stepping motor 8.2 drives the first-stage honeycomb damping section 8 to move along a guide shaft 8.3, and the distance between the first-stage honeycomb damping section 8 and the second-stage honeycomb damping section 9 is further adjusted. One-level honeycomb body damping section 8 adopts the combination of gradual change aperture honeycomb body and second grade honeycomb body damping section 9, can be according to the experimental demand of different models, through adjusting distance between two honeycomb bodies, through two-stage honeycomb body vortex air flow filtering, better lead in the same direction with draw equal air current for the simulation wind field is optimized more, and air velocity, wind field distribution more tend to be even. The requirements of different machine types on the uniformity of the wind field are met. A spraying section 2 and a heating section 3 are arranged between the power section 1 and the contraction section 4. The spraying section 2 is provided with a spraying device 2.1, the heating section 3 is provided with a heat exchanger 3.2, and the heat exchanger 3.2 is connected with an engine test exhaust pipe through an external circulation interface 3.1. The exhaust gas waste heat (150-00 ℃) of the exhaust pipe of the engine test is led in, the heat exchanger 3.2 is adopted for replacement, the air at the inlet end of the wind tunnel is heated through the heat exchanger 3.2, and the temperature of the air inlet end of the wind tunnel is controlled by controlling the air inlet method of the exhaust gas of the engine entering the heat exchanger 3.2. Therefore, the state of a cooling system of the engine in the whole vehicle environment in a high-temperature state is simulated. A grid-type water mist generator (a spraying device 2.1) is designed at an inlet of the wind tunnel to simulate a rainwater spraying test state, and the flow and the pressure of a spraying system are controlled by a computer system to achieve the aim of simulating a spraying test.
Example seven: the utility model provides an engine bench test wind field environmental simulation wind-tunnel structure, including the power section 1 that sets gradually, the shrink section 4, the stationary flow section 5, gradually expand section 6 and honeycomb body damping section, power section 1 is equipped with power fan 1.1 and inverter motor 1.2, it provides the wind regime to lead to inverter motor 1.2 drive power fan 1.1, the wind regime that power section 1 produced passes through shrink section 4, air current density gathers and forms the gaseous mixed flow and gets into stationary flow section 5, the air current homogeneity is improved, it reduces to get into 6 air current velocities of gradually expanding section, the air current further gets into honeycomb body damping section and stabilizes. In the embodiment, the honeycomb damping section comprises a primary honeycomb damping section 8, a working section 9 and a secondary honeycomb damping section 10, and after the airflow passes through the primary honeycomb damping section 8, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section 10 to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex flow in the gas flow. The first-stage honeycomb damping section 8 is provided with a movable honeycomb body 8.1 which is of a structure that the diameter of an excircle is small and the diameter of a hole close to the central part is gradually increased; the secondary honeycomb damping section 10 uses a stationary honeycomb body 10.1. The first-stage honeycomb damping section 8 is connected with a stepping motor 8.2 through a ball screw, the stepping motor 8.2 drives the first-stage honeycomb damping section 8 to move along a guide shaft 8.3, and the distance between the first-stage honeycomb damping section 8 and the second-stage honeycomb damping section 9 is further adjusted. One-level honeycomb body damping section 8 adopts the combination of gradual change aperture honeycomb body and second grade honeycomb body damping section 9, can be according to the experimental demand of different models, through adjusting distance between two honeycomb bodies, through two-stage honeycomb body vortex air flow filtering, better lead in the same direction with draw equal air current for the simulation wind field is optimized more, and air velocity, wind field distribution more tend to be even. The requirements of different machine types on the uniformity of the wind field are met. A spraying section 2 and a heating section 3 are arranged between the power section 1 and the contraction section 4. The spraying section 2 is provided with a spraying device 2.1, the heating section 3 is provided with a heat exchanger 3.2, and the heat exchanger 3.2 is connected with an engine test exhaust pipe through an external circulation interface 3.1. The exhaust gas waste heat (150-00 ℃) of the exhaust pipe of the engine test is led in, the heat exchanger 3.2 is adopted for replacement, the air at the inlet end of the wind tunnel is heated through the heat exchanger 3.2, and the temperature of the air inlet end of the wind tunnel is controlled by controlling the air inlet method of the exhaust gas of the engine entering the heat exchanger 3.2. Therefore, the state of a cooling system of the engine in the whole vehicle environment in a high-temperature state is simulated. A grid-type water mist generator (a spraying device 2.1) is designed at an inlet of the wind tunnel to simulate a rainwater spraying test state, and the flow and the pressure of a spraying system are controlled by a computer system to achieve the aim of simulating a spraying test. The flow guide section 6 is arranged between the steady flow section 5 and the divergent section 7, the flow guide section 6 is provided with a flow guide sheet 6.1 and a flow guide sheet angle adjusting motor 6.2, the steady flow section of the wind tunnel cannot be very long due to limited laboratory space, and the wind tunnel is easy to generate jet flow when the maximum air flow is adjusted, so that the distribution uniformity of an air flow field is influenced. A flow deflector 6.1 is additionally arranged on the divergent section 7 through a simulation test, so that jet flow of the wind tunnel in large flow is effectively controlled. The tail wing flow guide structure comprises a tail wing, a return spring, a tail wing angle adjusting pull wire, a positioning device and the like.
The foregoing shows and describes the general principles and principal structural features of the present invention. The present invention is not limited to the above examples, and various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Here, it should be noted that the description of the above technical solutions is exemplary, the present specification may be embodied in different forms, and should not be construed as being limited to the technical solutions set forth herein. Rather, these descriptions are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. Furthermore, the technical solution of the present invention is limited only by the scope of the claims.
The shapes, sizes, ratios, angles, and numbers disclosed to describe aspects of the specification and claims are examples only, and thus, the specification and claims are not limited to the details shown. In the following description, when a detailed description of related known functions or configurations is determined to unnecessarily obscure the focus of the present specification and claims, the detailed description will be omitted.
Where the terms "comprising", "having" and "including" are used in this specification, there may be another part or parts unless otherwise stated, and the terms used may generally be in the singular but may also be in the plural.
It should be noted that although the terms "first," "second," "top," "bottom," "side," "other," "end," "other end," and the like may be used and used in this specification to describe various components, these components and parts should not be limited by these terms. These terms are only used to distinguish one element or section from another element or section. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, with the top and bottom elements being interchangeable or switchable with one another, where appropriate, without departing from the scope of the present description; the components at one end and the other end may be of the same or different properties to each other.
In describing positional relationships, for example, when positional sequences are described as being "on.. above", "over.. below", "below", and "next", unless such words or terms are used as "exactly" or "directly", they may include cases where there is no contact or contact therebetween. If a first element is referred to as being "on" a second element, that does not mean that the first element must be above the second element in the figures. The upper and lower portions of the member will change depending on the angle of view and the change in orientation. Thus, in the drawings or in actual construction, if a first element is referred to as being "on" a second element, it can be said that the first element is "under" the second element and the first element is "over" the second element. In describing temporal relationships, unless "exactly" or "directly" is used, the description of "after", "subsequently", and "before" may include instances where there is no discontinuity between steps. The features of the various embodiments of the present invention may be partially or fully combined or spliced with each other and performed in a variety of different configurations as would be well understood by those skilled in the art. Embodiments of the invention may be performed independently of each other or may be performed together in an interdependent relationship.
Finally, it should be noted that the above embodiments are merely representative examples of the present invention. It is obvious that the invention is not limited to the above-described embodiments, but that many variations are possible. Any simple modification, equivalent change and modification made to the above embodiments in accordance with the technical spirit of the present invention should be considered to be within the scope of the present invention.
Claims (10)
1. The utility model provides an engine bench test wind field environmental simulation wind tunnel structure which characterized in that: the wind source generated by the power section passes through the contraction section, the airflow density is increased to form a mixed gas flow, the mixed gas flow enters the steady flow section, the uniformity of the airflow is improved, the speed of the airflow entering the gradually expanding section is reduced, and the airflow further enters the honeycomb damping section for stabilization.
2. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 1, characterized in that: the honeycomb damping section comprises a primary honeycomb damping section, a working section and a secondary honeycomb damping section, and after airflow passes through the primary honeycomb damping section, the airflow is straightened to be parallel to the axis of the wind tunnel, so that the uniformity of the airflow is optimized; and the gas enters a second-stage honeycomb damping section to further break vortex, guide and pull uniform gas flow, weaken tip jump flow, reduce transverse side component of turbulence and further attenuate gas vortex in the gas flow.
3. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 2, characterized in that: the first-stage honeycomb damping section is provided with a movable honeycomb body, and the movable honeycomb body is of a structure with a small excircle aperture and a gradually increased central-portion aperture.
4. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 3, wherein: the secondary honeycomb damping section adopts a fixed honeycomb.
5. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 4, wherein: the first-stage honeycomb damping section is connected with the stepping motor through a ball screw, and the distance between the first-stage honeycomb damping section and the second-stage honeycomb damping section is adjusted through the stepping motor.
6. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 1, characterized in that: and a spraying section and a heating section are arranged between the power section and the contraction section.
7. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 6, wherein: the spraying section is provided with a spraying device.
8. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 6, wherein: the heating section is provided with a heat exchanger.
9. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 1, characterized in that: and a flow guide section is arranged between the steady flow section and the divergent section.
10. The wind tunnel structure for simulating the wind field environment of the engine bench test according to claim 7, wherein: the flow guide section is provided with a flow guide sheet and a flow guide sheet angle adjusting motor.
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| CN202111269690.7A CN114199497A (en) | 2021-10-29 | 2021-10-29 | Wind field environment simulation wind tunnel structure for engine bench test |
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| CN202111269690.7A CN114199497A (en) | 2021-10-29 | 2021-10-29 | Wind field environment simulation wind tunnel structure for engine bench test |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117928880A (en) * | 2024-03-22 | 2024-04-26 | 南京沃姆传动技术有限公司 | Diversion equipment and diversion method for wind tunnel test |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101750204A (en) * | 2009-12-08 | 2010-06-23 | 中国航空工业第一集团公司沈阳空气动力研究所 | Engine simulator for dynamic simulation test in high-speed wind tunnel |
| JP2011038804A (en) * | 2009-08-06 | 2011-02-24 | Isuzu Motors Ltd | Structure for adjusting pressure loss in model, model for fluid test and method of adjusting pressure loss in model |
| CN202533242U (en) * | 2012-02-21 | 2012-11-14 | 南开大学 | Multifunctional movable type wind erosion wind tunnel |
| CN104019958A (en) * | 2013-08-23 | 2014-09-03 | 中国人民解放军国防科学技术大学 | Wind tunnel rectification device |
| CN204008059U (en) * | 2014-09-02 | 2014-12-10 | 中国人民解放军军事医学科学院军事兽医研究所 | A kind of space tight type low speed environments flow tunnel testing device |
| CN104280204A (en) * | 2014-09-28 | 2015-01-14 | 南车青岛四方机车车辆股份有限公司 | Wind tunnel |
| CN206656846U (en) * | 2017-05-08 | 2017-11-21 | 仲恺农业工程学院 | Novel agricultural small-size straight-flow low-speed wind tunnel |
| CN209372359U (en) * | 2019-03-23 | 2019-09-10 | 国电环境保护研究院有限公司 | A kind of double test section direct current gust wind tunnels |
| CN110702419A (en) * | 2019-10-11 | 2020-01-17 | 中国直升机设计研究所 | Anti-icing conformance test system and method for engine air inlet system |
| CN213985612U (en) * | 2020-12-30 | 2021-08-17 | 恒菱机电科技(苏州)有限公司 | Double-test-section direct-current verification wind tunnel device |
-
2021
- 2021-10-29 CN CN202111269690.7A patent/CN114199497A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011038804A (en) * | 2009-08-06 | 2011-02-24 | Isuzu Motors Ltd | Structure for adjusting pressure loss in model, model for fluid test and method of adjusting pressure loss in model |
| CN101750204A (en) * | 2009-12-08 | 2010-06-23 | 中国航空工业第一集团公司沈阳空气动力研究所 | Engine simulator for dynamic simulation test in high-speed wind tunnel |
| CN202533242U (en) * | 2012-02-21 | 2012-11-14 | 南开大学 | Multifunctional movable type wind erosion wind tunnel |
| CN104019958A (en) * | 2013-08-23 | 2014-09-03 | 中国人民解放军国防科学技术大学 | Wind tunnel rectification device |
| CN204008059U (en) * | 2014-09-02 | 2014-12-10 | 中国人民解放军军事医学科学院军事兽医研究所 | A kind of space tight type low speed environments flow tunnel testing device |
| CN104280204A (en) * | 2014-09-28 | 2015-01-14 | 南车青岛四方机车车辆股份有限公司 | Wind tunnel |
| CN206656846U (en) * | 2017-05-08 | 2017-11-21 | 仲恺农业工程学院 | Novel agricultural small-size straight-flow low-speed wind tunnel |
| CN209372359U (en) * | 2019-03-23 | 2019-09-10 | 国电环境保护研究院有限公司 | A kind of double test section direct current gust wind tunnels |
| CN110702419A (en) * | 2019-10-11 | 2020-01-17 | 中国直升机设计研究所 | Anti-icing conformance test system and method for engine air inlet system |
| CN213985612U (en) * | 2020-12-30 | 2021-08-17 | 恒菱机电科技(苏州)有限公司 | Double-test-section direct-current verification wind tunnel device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117928880A (en) * | 2024-03-22 | 2024-04-26 | 南京沃姆传动技术有限公司 | Diversion equipment and diversion method for wind tunnel test |
| CN117928880B (en) * | 2024-03-22 | 2024-05-28 | 南京沃姆传动技术有限公司 | Diversion equipment and diversion method for wind tunnel test |
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