CN114046874A - Test device for measuring supersonic jet near-field noise - Google Patents
Test device for measuring supersonic jet near-field noise Download PDFInfo
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- CN114046874A CN114046874A CN202210024791.6A CN202210024791A CN114046874A CN 114046874 A CN114046874 A CN 114046874A CN 202210024791 A CN202210024791 A CN 202210024791A CN 114046874 A CN114046874 A CN 114046874A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the other groups of this subclass
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Abstract
The invention discloses a test device for measuring near-field noise of supersonic jet flow, which comprises a base body spray pipe and a support frame, wherein the support frame axially sequentially comprises a first support ring, a second support ring and a third support ring, the base body spray pipe is coaxially connected to the first support ring, a nozzle of the base body spray pipe extends into the support frame, the second support ring is connected with the third support ring through a connecting beam, a plurality of radial through holes are respectively arranged on the second support ring, the third support ring and the connecting beam, a support rod is arranged in at least part of the radial through holes, and one end of the support rod, which is connected with a sensor, points to the axis of the base body spray pipe. The invention can meet the test requirement by adjusting the position and the inserting length of the support rod inserted into the support frame, can synchronously measure the noise load of each component of the jet flow noise, and improves the accuracy and precision of test measurement.
Description
Technical Field
The invention relates to the field of experimental hydrodynamics, in particular to a test device for measuring supersonic jet near-field noise.
Background
The nozzle structure widely exists in the aerospace navigation field and typical configurations of industrial equipment due to the special structural form and characteristics of the nozzle structure, is mainly applied to airplanes, rockets and chemical equipment, and generally has the characteristics of various structures, unconventional configurations, harsh working environment and the like. The mechanism of generation of jet noise is a very complex problem in pneumatic acoustics, due to the turbulence problem. In wind tunnel tests, turbulence structures at different levels in the jet flow can generate noise, and the proportion of the turbulence structures depends on the Mach number, the temperature and the observation angle of the jet flow. Therefore, the design and processing of the supersonic jet near-field noise measuring device become a very important key link, and the key link is a basic condition influencing pneumatic load test data.
Aiming at the problems of unsteady flow and flow-induced noise of jet flow, domestic and foreign scholars develop a great deal of experimental research by means of wind tunnels and ground test beds. It has been found that supersonic jet noise, in addition to jet at full expansion, mainly comprises three basic components, turbulent mixing noise, broadband shock noise and whistling noise. The turbulent mixing noise is dominant in the downstream direction, broadband shock wave noise gradually appears in the upstream direction after 90 degrees from the downstream, and jet flow whistle mainly propagates in the upstream direction. In addition, the axisymmetric circular nozzles, rectangular nozzles and the like which are equipped and used at present all have the noise problem under the supersonic working condition. Therefore, different near-field noise measurement test devices need to be designed and processed aiming at different nozzle models and different jet noise problems.
The pressure field measurement means is mainly divided into wall surface measurement, near field measurement and far field measurement. As can be seen from many existing examples at home and abroad, various test measurement requirements are often included in the research process aiming at specific problems, but the design and the processing of noise measurement devices at different positions of the model are mutually independent, and a plurality of sets of test devices are needed to complete all test contents to obtain noise load data, so that the test measurement cost is increased. Meanwhile, according to different experimental research contents, the device needs to be disassembled and assembled and the position of the device needs to be adjusted, so that the workload of the wind tunnel test is obviously increased; most critical is the difficulty of simultaneously and simultaneously measuring the noise loads of the jet noise components and ensuring the accuracy and precision of the test measurement.
Disclosure of Invention
The invention aims to provide a test device for measuring near-field noise of supersonic jet, which can measure circumferential sound pressure load of a nozzle lip plane at multiple distances, sound pressure load of a jet outer flow field cross section and sound pressure load of a jet flow field boundary layer. The measured sound pressure load characteristics can solve the problems in the background technology, and the data measured by the test can be used for researching the generation mechanism of the supersonic jet turbulent mixing noise, the broadband shock wave noise and the howling.
In order to achieve the purpose, the invention adopts the following technical scheme:
the utility model provides a supersonic velocity efflux near field noise measurement's test device, includes base member spray tube and support frame, the support frame axial includes first support ring, second support ring and third support ring in proper order, base member spray tube coaxial coupling is to first support ring, and the spout of base member spray tube stretches into in the support frame, the second support ring passes through the tie-beam and is connected with the third support ring, be provided with the radial through-hole of a plurality of on second support ring, third support ring, the tie-beam respectively, have at least partial radial through-hole in be provided with branch, be connected with the axis of the directional base member spray tube of one end of sensor on the branch.
In the technical scheme, the nozzle of the base body spray pipe and the central section of the second support ring are positioned on the same plane.
In the above technical solution, the diameter of the second support ring is at least greater than 6 times the spout diameter of the substrate spout.
In the technical scheme, the central section of the third support ring is 10 times of the diameter of the nozzle from the nozzle of the base body spray pipe, and the diameter of the third support ring is at least more than 10 times of the diameter of the nozzle.
In the above technical scheme, a plurality of connecting beams are connected between the second support ring and the third support ring, and the connecting beams are distributed in a radial structure from the second support ring to the third support ring.
In the above technical solution, each connecting beam is provided with a plurality of radial through holes along the radial direction, and at least one radial through hole is provided with a support rod.
In the above technical scheme, the second support ring and the third support ring are respectively provided with a plurality of radial through holes along the circumferential direction, at least one radial through hole on the second support ring is provided with a support rod, and at least one radial through hole on the third support ring is provided with a support rod.
In the technical scheme, the support rods arranged on the second support ring, the third support ring and the plurality of connecting beams are distributed around the nozzle surface of the base body spray pipe in an array annular mode, and the axis of each support rod points to the center of the array ring.
In the above technical solution, the strut can be inserted into the second support ring, the third support ring and the connecting beam at adjustable positions and lengths.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1) the application range of research content is wide, the noise loads of all components of jet flow noise can be synchronously measured, and the accuracy and precision of test measurement are improved;
2) when the test research content is more, the test requirement can be met by adjusting the position and the insertion length of the support rod inserted into the support frame, so that multiple sets of models are avoided to be processed, raw materials are saved, and the test cost is greatly reduced;
3) the part adjusting mode is simple, the dismounting is convenient, the testing process is simplified, the period is shortened, and the testing efficiency is improved.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of an arrangement of flow direction struts in an adjustable array region;
FIG. 3 is a schematic view of an adjustable array region circumferential strut arrangement;
FIG. 4 is a schematic view of a circumferential array ring strut arrangement;
wherein: 1 is a matrix nozzle, 2 is a first support ring, 3 is a second support ring, 4 is a nozzle, 5 is a connecting beam, 6 is a third support ring, 7 is a strut, and 8 is a sensor.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
Example one
As shown in fig. 1, the structure of the present embodiment includes a substrate nozzle 1 and a support frame, the support frame includes a first support ring 2, a second support ring 3 and a third support ring 6, wherein the first support ring 2 is connected to the substrate nozzle 1, the first support ring 2 is connected to the second support ring 3 through a bracket, the second support ring 3 is connected to the third support ring 6 through a connection beam 5, and the substrate nozzle 1 is axially disposed in the support frame.
In this embodiment, the bodies of the second support ring 3 and the third support ring 6 are provided with a plurality of through holes along the circumferential direction, the through holes are directed toward the center of the ring body, and all the through holes are opened along the radial direction of the ring body. A plurality of connecting beams 5 are connected between the second support ring 3 and the third support ring 6, all the connecting beams 5 are symmetrically distributed in a radial structure from the second support ring 3 to the third support ring 6, a plurality of through holes are formed in the connecting beams 5 in the radial direction, and the through holes are formed in the radial direction of the radial ring surface. The connecting beam 5 is arranged in a radial structure, so that the development trend of jet flow of the nozzle is met, and the physical interference of the connecting beam 5 on a jet flow field is reduced.
In the present exemplary embodiment, the central cross section of the second support ring 3 is in the same plane as the nozzle orifice 4 of the basic nozzle 1, the diameter of the second support ring 3 being at least 6 times greater than the diameter of the nozzle orifice 4. The data can be set to reduce the physical interference of the second support ring 3 to the sound field at the nozzle 4, so that the test measurement precision is ensured.
In this embodiment, the distance of the central section of the third support ring 6 from the plane of the spout 4 is 10 times the diameter of the spout, and the diameter of the third support ring 6 is at least 10 times greater than the diameter of the spout 4. The data can ensure the detection range of the whole support frame to the axial symmetry mode, the swing mode and the spiral mode of the squeaking sound, and reduce the physical interference of the support frame to the jet flow field.
In this embodiment, the second support ring 3, the third support ring 6, and the connecting beam 5 can be provided with a strut 7 in the through hole, the end of the strut 7 is provided with a sensor 8, and the end of the strut 7 with the sensor 8 points to the annular center. In this embodiment, the length that branch set up in the through-hole can be adjusted according to experimental needs, and the position that branch set up can be adjusted according to experimental needs to can acquire the test data of more positions.
Example two
As shown in fig. 2, on the basis of the first embodiment, only one of the connecting beams 5 is provided with a strut 7, while the second supporting ring 3 and the third supporting ring 6 are not provided with struts 7, and one strut 7 is provided in each through hole of the connecting beam 5 for measuring the flow direction of the flow field.
EXAMPLE III
As shown in fig. 3, on the basis of the first embodiment, no strut 7 is arranged on the second support ring 3 and the third support ring 6, and each connecting beam 5 is provided with a strut 7 for circumferential measurement of the flow field.
Example four
As shown in fig. 4, on the basis of the first embodiment, no strut 7 is arranged on the connecting beam 5, and the struts 7 are arranged on the second support ring 3 and the third support ring 6 along the circumferential direction of the support rings, so as to realize circumferential measurement of the flow field.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed.
Claims (9)
1. A test device for measuring supersonic jet near-field noise is characterized in that: including base member spray tube and support frame, the support frame axial includes first support ring, second support ring and third support ring in proper order, base member spray tube coaxial coupling is to first support ring, and in the spout of base member spray tube stretched into the support frame, the second support ring passed through the tie-beam and is connected with the third support ring, be provided with the radial through-hole of a plurality of on second support ring, third support ring, the tie-beam respectively, have at least to be provided with branch in the partial radial through-hole, be connected with the axis of the directional base member spray tube of one end of sensor on the branch.
2. The test device for measuring the near-field noise of the supersonic jet according to claim 1, is characterized in that: and the nozzle of the base body spray pipe and the central section of the second support ring are positioned on the same plane.
3. The test device for measuring the near-field noise of the supersonic jet according to claim 2, is characterized in that: the diameter of the second support ring is at least 6 times larger than the spout diameter of the substrate spout.
4. The test device for the near-field noise measurement of the supersonic jet according to claim 2, wherein the central section of the third support ring is 10 times the diameter of the nozzle from the nozzle of the base nozzle, and the diameter of the third support ring is at least 10 times larger than the diameter of the nozzle.
5. The test device for the near-field noise measurement of the supersonic jet according to any one of claims 1 to 4, wherein a plurality of connecting beams are connected between the second support ring and the third support ring, and the plurality of connecting beams are distributed in a radial structure from the second support ring to the third support ring.
6. The test device for the near-field noise measurement of the supersonic jet according to claim 5, wherein each connecting beam is provided with a plurality of radial through holes along a radial direction, and at least one radial through hole is provided with a strut.
7. The test device for the near-field noise measurement of the supersonic jet according to claim 1, wherein the second support ring and the third support ring are respectively provided with a plurality of radial through holes along the circumferential direction, the second support ring is provided with a support rod in at least one radial through hole, and the third support ring is provided with a support rod in at least one radial through hole.
8. The test device for the ultrasonic jet near-field noise measurement according to any one of claims 1, 6 or 7, wherein the struts arranged on the second support ring, the struts arranged on the third support ring, and the struts arranged on the plurality of connecting beams are all distributed around the nozzle face of the base nozzle in an array annular direction, and the axes of the struts point to the center of the array ring.
9. The test device for the near-field noise measurement of the supersonic jet according to claim 8, wherein the strut is capable of adjusting the position and the length of the strut inserted into the second support ring, the third support ring and the connecting beam.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118603298A (en) * | 2024-06-25 | 2024-09-06 | 北京航空航天大学 | Noise characteristic measurement system and method for liquid rocket engine test bench |
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