CN113815889A - Shutter type aircraft engine wake flow protection special equipment - Google Patents
Shutter type aircraft engine wake flow protection special equipment Download PDFInfo
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- CN113815889A CN113815889A CN202111205408.9A CN202111205408A CN113815889A CN 113815889 A CN113815889 A CN 113815889A CN 202111205408 A CN202111205408 A CN 202111205408A CN 113815889 A CN113815889 A CN 113815889A
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- flow guide
- wake
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- barrier
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- 230000004888 barrier function Effects 0.000 claims abstract description 53
- 229920000742 Cotton Polymers 0.000 claims description 5
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 4
- 238000000034 method Methods 0.000 claims 1
- 230000030279 gene silencing Effects 0.000 description 14
- 230000000694 effects Effects 0.000 description 9
- 230000008030 elimination Effects 0.000 description 3
- 238000003379 elimination reaction Methods 0.000 description 3
- 230000007423 decrease Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/26—Ground or aircraft-carrier-deck installations for reducing engine or jet noise; Protecting airports from jet erosion
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention provides special equipment for protecting the wake flow of a shutter type aircraft engine, which comprises a barrier component; the barrier component comprises more than two flow guide pieces; the flow guide piece comprises a first flow guide structure; the first flow guide structure is arranged in an upward arc shape from the direction of the jet wake of the airplane to the direction vertical to the direction of the jet wake of the airplane; the first flow guide part extends upwards to form a second flow guide part; the adjacent second flow guide pieces are arranged in parallel; an included angle of 80-90 degrees is formed between the second flow guide piece and the direction of the jet wake of the airplane; the tail flow sprayed out by the airplane enters the arc narrow slit through the diversion inlet and then is discharged through the diversion outlet; because an included angle of 80-90 degrees is formed between the part of the arc narrow slit close to the second flow guide piece and the direction of the jet wake of the airplane; the wake flow entering the arc narrow slit is discharged out of the diversion outlet along an angle close to the vertical angle; thus, the wake flow with high-temperature heat is guided; meanwhile, the discharged wake flow does not influence residents or workers behind the airplane.
Description
Technical Field
The invention relates to the field of aviation equipment, in particular to special equipment for protecting a shutter type aircraft engine wake flow.
Background
When civil aircraft ground is tested, a large amount of high-temperature and high-speed airflow can be generated at the tail of the aircraft, nearby workers or buildings can be impacted if the aircraft can not be tested in an open place, great potential safety hazards exist, noise generated when the aircraft is tested is not disturbing residents, and the aircraft ground is sound pollution.
In Chinese patent No. 201720258330. X; patent document publication No. 2018.1.9 discloses a shutter type wind sound barrier; the screen comprises at least two supporting columns, wherein the supporting columns are distributed at intervals and fixedly connected to the ground or a base, at least two silencing blades which are rotatably connected to the supporting columns and used for absorbing sound, insulating sound, guiding flow and disturbing flow through rotation are arranged between every two adjacent supporting columns, the upper portions or the lower portions of the silencing blades incline towards the leeward wind direction, at least one free plate edge of each silencing blade extends outwards, and a narrow slit used for forming a flow guiding channel and a disturbing flow channel is formed between every two adjacent silencing blades.
When the barrier is applied to the ground test run of the airplane, the airplane can be arranged in front of the barrier; the adjacent silencing blades can act with the wake flow sprayed by the airplane; namely, the adjacent silencing blades can act with the wind flow in the same direction; the rotating directions of the adjacent silencing blades are consistent and synchronously rotate; when the adjacent silencing blades rotate simultaneously, the narrow slits between the adjacent silencing blades are unchanged, and are shown in the attached drawings; the adjacent silencing blades are arranged in parallel; the narrow slit is in a linear structure, so that when the narrow slit passes through the narrow slit, the air pressure is uneven, and the local pressure of the air is too high; thereby shortening the service life of the barrier; meanwhile, the structure cannot play a role in accelerating the air flow to leave the narrow slit;
meanwhile, the upper part or the lower part of the noise elimination blade inclines towards the leeward direction, namely the noise elimination blade is inclined, the noise elimination blade guides airflow in an inclined mode, and compared with the structure without a barrier, the structure only improves the height of wake flow; the wake flow sprayed by the airplane still can affect residents or workers behind the airplane; the flow guide effect is poor;
meanwhile, the screen is lapped with the adjacent fixed wind shield through the free plate edge of the silencing blade so as to form the rotation angle limitation of the silencing blade; but because the silencing vanes can be rotatably arranged; under the effect of wake flow, the adjacent silencing blades are parallel; at this time, the barrier cannot guide the wake flow ejected by the airplane.
Disclosure of Invention
The invention provides special equipment for protecting the wake flow of a shutter type aircraft engine; accelerating the wake flow to leave the device; the jet wake flow of the aircraft engine has good diversion effect, and the pressure of the wake flow is uniform during diversion; the influence of the jet wake of the airplane on residents or workers behind the airplane is avoided.
In order to achieve the purpose, the technical scheme of the invention is as follows: a special equipment for protecting the wake flow of louver-type airplane engine is composed of more than one airflow-guiding noise-reducing module; the flow guide and noise reduction assembly comprises a barrier assembly; the barrier assembly comprises a barrier bracket and more than two groups of flow guide structures arranged on the barrier bracket; a baffle plate is connected between the adjacent flow guide structures; the flow guide structure, the baffle plate and the barrier bracket are connected in a sealing way; each group of flow guide structures comprises two first flow guide pieces; the first flow guide piece is arranged in an upward arc shape from the direction of the wake flow sprayed out of the airplane to the direction vertical to the direction of the wake flow sprayed out of the airplane; the first flow guide part extends upwards to form a second flow guide part; the adjacent second flow guide pieces are arranged in parallel; an alpha included angle is formed between the second flow guide piece and the jet wake flow direction of the airplane, and the alpha included angle is 80-90 degrees; arc narrow strip slits are formed between adjacent first flow guide pieces and between adjacent second flow guide pieces in the same flow guide structure; the width of the arc narrow slit gradually decreases from the first diversion part to the second diversion part; the arc narrow slit comprises a diversion inlet and a diversion outlet; the adjacent first flow guide pieces of the flow guide structures in the same group form a flow guide inlet at the position where the wake enters the flow guide structures; the adjacent second flow guide pieces in the same group of flow guide structures form flow guide outlets at the positions where the wake flows out of the flow guide structures; the opening size of the flow guide inlet is larger than that of the flow guide outlet; an included angle of 80-90 degrees is formed between the opening direction of the flow guide inlet and the opening direction of the flow guide outlet; the ratio of the area of the flow guide inlet to the area of the barrier component is 15% -20%; the tail flow sprayed out by the airplane enters the arc narrow slit through the flow guide inlet; the tail flow sprayed out by the airplane leaves the arc narrow slit through the diversion outlet.
According to the arrangement, the tail flow sprayed out of the airplane enters the arc-shaped narrow slit through the flow guide inlet and then is discharged through the flow guide outlet; the opening direction of the flow guide inlet and the opening direction of the flow guide outlet form an included angle of 80-90 degrees; the wake flow entering the arc narrow slit is discharged out of the diversion outlet along an angle close to the vertical angle; thus, the wake flow with high-temperature heat is guided; meanwhile, the discharged wake flow does not influence residents or workers behind the airplane; the narrow slit arranged in an arc shape has good guiding effect on the wake flow; meanwhile, the pressure of the wake flow entering the arc narrow slit is uniform, so that the overlarge partial pressure of the wake flow is avoided; the service life of the flow guide noise reduction assembly is further shortened;
meanwhile, a baffle is connected between the adjacent flow guide structures; the flow guide structure, the baffle plate and the barrier bracket are connected in a sealing way; the wake flow can only be guided through the arc narrow slit; the ratio of the sum of the flow guide inlet areas to the area of the barrier component is 15% -20%; the noise in the wake flow can generate resonance sound absorption with the arc narrow slit; so that the acoustic energy of the noise in the wake is dissipated; meanwhile, when the wake flow passes through the arc narrow slit; most of sound waves generated by the wake flow are absorbed and reflected by the arc narrow slit; the noise of the wake flow discharged from the arc narrow slit is low; the effect of reducing noise is achieved. In addition, because the baffle is arranged between the flow guide structures and the alpha angle is combined, the phenomenon of wake interference is not easy to occur at the flow guide outlet, and the wake is favorably discharged.
Meanwhile, the width of the arc narrow slit gradually decreases from the first diversion part to the second diversion part; the opening size of the flow guide inlet is larger than that of the flow guide outlet; because the diversion outlet is reduced, the flow reducing speed of the wake flow passing through the diversion outlet is increased, and meanwhile, the pressure of the wake flow in the arc-shaped narrow slit is increased, so that the reflection and mutual offset of the wake flow in the arc-shaped narrow slit are facilitated, and the noise reduction effect is improved.
Furthermore, an included angle of 85 degrees is formed between the second flow guide piece and the direction of the jet wake of the airplane.
Through the arrangement, the wake flow entering the arc narrow slit is discharged out of the diversion outlet along a vertical angle.
Furthermore, the opening direction of the flow guide inlet and the opening direction of the flow guide outlet form an included angle of 85 degrees.
Furthermore, the flow guide and noise reduction assembly also comprises a supporting piece and a fixing piece; the barrier bracket is obliquely arranged; one end of the barrier bracket is connected with the fixing piece; the other end of the barrier bracket is supported; the supporting piece and the fixing piece are used for fixing the barrier component; the support member, the fixing member and the barrier assembly constitute a triangular structure. Thus the support is stable.
Further, the barrier bracket comprises a bracket I and a bracket II; the first bracket and the second bracket are arranged oppositely; a first groove is formed in the inner side of the first support; a second groove is formed in the inner side of the second support; the first groove is connected with one end of the flow guide piece, and the second groove is connected with the other end of the flow guide piece. Thus, the first bracket and the second bracket protect the end parts of the flow guide elements.
Further, the first support comprises a first branch part and a second branch part; the groove one is positioned between the branch part one and the branch part two; gaps are arranged between the flow guide piece and the first branch part and between the flow guide piece and the second branch part; the second bracket comprises a third branch part and a fourth branch part; the second groove is positioned between the third branch part and the fourth branch part; gaps are arranged between the flow guide piece and the third and fourth branch parts.
Further, the sum of the flow guide inlet areas accounts for 18% of the area of the barrier module.
Further, the baffle comprises a first baffle and a second baffle; the first baffle is arranged close to the flow guide inlet; the second baffle is arranged close to the flow guide outlet; the first baffle and the second baffle are hermetically connected with the flow guide structure and the barrier bracket; a noise reduction space is formed among the first baffle plate, the second baffle plate and the adjacent flow guide structures; the first flow guide piece is provided with a first through hole communicated with the noise reduction space; the second flow guide piece is provided with a second through hole communicated with the noise reduction space; the noise reduction space is internally provided with sound absorption cotton.
The above arrangement allows part of the noise which is not consumed to enter the noise reduction space; the sound absorbing cotton absorbs sound waves of noise.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
FIG. 2 is a front view of an airflow directing and noise reducing assembly of the present invention.
FIG. 3 is a side view of the flow guiding and noise reducing assembly of the present invention secured to the ground.
Fig. 4 is a sectional view taken in the direction D-D of fig. 2.
Fig. 5 is an enlarged view of a in bitmap 4.
FIG. 6 is a schematic structural view of the second stent of the present invention.
Fig. 7 is an enlarged view of b in fig. 6.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1-7; a special equipment for protecting the wake flow of a shutter type airplane engine comprises more than one flow guide noise reduction assembly 1; the flow guiding and noise reducing assembly 1 comprises a barrier assembly 2; the barrier module 2 comprises a barrier frame and more than two sets of flow directing structures 22 mounted on the barrier frame. In this embodiment, the flow guide structure has seven groups.
Each set of flow guide structures 22 comprises two first flow guide parts 221; the first flow guide part 221 is arranged in an upward arc shape from the direction of the jet wake of the airplane to the direction vertical to the direction of the jet wake of the airplane; the first guide member 221 extends upward to form a second guide member 222; an angle alpha is formed between the second flow guide piece 222 and the jet wake direction of the airplane, and the angle alpha is 80-90 degrees; in this embodiment, the second flow guide 222 forms an angle of 85 ° with the direction of the aircraft jet wake. Causing the wake to exit the diversion exit 2232 at a perpendicular angle.
The adjacent first flow guide parts 221 and the adjacent second flow guide parts 222 in the same group of flow guide structures are provided with arc narrow strip slits 223 in the same shape; the width of the narrow arc slit is gradually reduced from the first diversion part to the second diversion part. The arc narrow slit 223 comprises a diversion inlet 2231 and a diversion outlet 2232; a flow guide inlet 2231 is formed at an inlet of an adjacent first flow guide part in the same group of flow guide structures; a flow guide outlet 2232 is formed at the outlet of the adjacent second flow guide part in the same group of flow guide structures; the opening size of the flow guide inlet is larger than that of the flow guide outlet; the opening direction of the flow guide inlet and the opening direction of the flow guide outlet form an included angle of 85 degrees. A baffle is arranged between the adjacent flow guide structures. The flow guide structure, the baffle plate and the barrier bracket are connected in a sealing way; the sum of the diversion inlet areas of the seven groups of diversion structures accounts for 18 percent of the area of the barrier component. Thus, the wake flow can only enter the arc narrow slit to realize flow guide; the ratio of the sum of the flow guide inlet areas to the area of the barrier component is 15% -20%; the noise in the wake flow can generate resonance sound absorption with the arc narrow slit; so that the acoustic energy of the noise in the wake is dissipated. In the invention, the area of the diversion inlet refers to the area of the windward side C of the special equipment for protecting the wake flow of the shutter type aircraft engine.
The tail flow sprayed by the airplane enters the arc narrow slit 223 through the diversion inlet 2231; the aircraft jet wakes exit the curved narrow slot 223 through the diversion exit 2232. As shown in fig. 4 and 5; the aircraft jet wake flow enters the arc narrow slit 223 along the X-axis direction; away from the curved narrow strip slit 223 in the Y-axis direction.
In this embodiment, the opening size of the diversion inlet 2231 is larger than the opening size of the diversion outlet 2232; meanwhile, the first flow guide part is close to the second flow guide part; the width of the arc narrow slit is gradually reduced; because the width of the arc-shaped narrow slit is gradually reduced, the flow reducing speed of the wake flow passing through the diversion outlet is increased, and meanwhile, the pressure of the wake flow in the arc-shaped narrow slit is increased, so that the reflection and mutual offset of the wake flow in the arc-shaped narrow slit are facilitated, and the noise reduction effect is improved.
The baffles include a first baffle 51 and a second baffle 52; the first baffle 51 is disposed adjacent to the guide inlet 2231; the second baffle 52 is disposed adjacent to the diversion outlet 2232; the first baffle plate 51 and the second baffle plate 52 are hermetically connected with the flow guide structure and the barrier bracket; a noise reduction space 53 is formed between the first baffle 51, the second baffle 52 and the adjacent flow guide structures; the first flow guide piece is provided with a first through hole (not shown in the figure) communicated with the noise reduction space; the second flow guide part is provided with a second through hole (not shown in the figure) communicated with the noise reduction space; the noise reduction space 53 is provided with sound absorbing cotton (not shown). Thus, part of the noise which is not consumed enters the noise reduction space; the sound absorbing cotton absorbs sound waves of noise.
As shown with reference to FIG. 4; the aircraft sprays wake flow to enter the arc narrow slit along the A direction; then leave from the direction B; the direction of the wake flow is changed under the action of the arc narrow slit; meanwhile, the wake flow with the changed direction can drive the wake flow without changing the direction from the direction B. The flow guiding and noise reducing assembly 1 further comprises a supporting piece 3 and a fixing piece 4; one end of the barrier bracket is connected with the fixing piece 4; the other end support 3 of the barrier frame; the support 3 and the fixing piece 4 are used for fixing the barrier component 2; the support 3, the fixing 4 and the barrier assembly 2 constitute a triangular structure. Thus the support is stable. The barrier assembly 2 is arranged obliquely. In use, the fixing member 4 and one end of the supporting member 3 are fixed to the ground.
The barrier bracket comprises a first bracket 211 and a second bracket 212; the first bracket 211 and the second bracket 212 are oppositely arranged; a first groove 217 is formed in the inner side of the first support 211; the inner side of the second bracket 212 is provided with a second groove 218; the first groove 217 is connected to one end of the flow guide 22, and the second groove 218 is connected to the other end of the flow guide 22. Thus, the first bracket 211 and the second bracket 212 protect the end of the baffle 22. The first support 211 comprises a first branch part 213 and a second branch part 214; the first groove 217 is positioned between the first branch part 213 and the second branch part 214; gaps are arranged between the flow guide 22 and the first and second branch parts 213 and 214. The second bracket 212 comprises a third branch part 215 and a fourth branch part 216; the second groove 218 is positioned between the third branch part 215 and the fourth branch part 216; gaps are arranged between the flow guide 22 and the third and fourth branch parts 215 and 216.
The wake flow sprayed by the airplane enters the arc-shaped narrow slit 223 through the diversion inlet 2231 and then is discharged through the diversion outlet 2232; an included angle of 85 degrees is formed between the second flow guide piece 222 and the direction of the jet wake of the airplane; the wake entering the narrow arc slit 223 is discharged out of the diversion outlet 2232 at a vertical angle; thus, the wake flow with high-temperature heat is guided; meanwhile, the discharged wake flow does not influence residents or workers behind the airplane; the narrow slit arranged in an arc shape has good guiding effect on the wake flow; meanwhile, the pressure of the wake flow entering the arc narrow slit is uniform, so that the overlarge partial pressure of the wake flow is avoided; the service life of the flow guide noise reduction assembly is further shortened; while the wake is passing through the narrow arc slit 223; the sound waves generated by the wake will be mostly absorbed and reflected by the arc-shaped narrow slit 223; the noise of the wake flow after being discharged from the arc narrow slit 223 is low; the effect of reducing noise is achieved. The tail flow sprayed out by the airplane enters the arc narrow slit through the diversion inlet and then is discharged through the diversion outlet; the opening direction of the flow guide inlet and the opening direction of the flow guide outlet form an included angle of 80-90 degrees; the wake flow entering the arc narrow slit is discharged out of the diversion outlet along an angle close to the vertical angle; thus, the wake flow with high-temperature heat is guided; meanwhile, the discharged wake flow does not influence residents or workers behind the airplane; meanwhile, the ratio of the area of the flow guide inlet to the area of the barrier component is 15% -20%; the noise in the wake flow can generate resonance sound absorption with the arc narrow slit; so that the acoustic energy of the noise in the wake is dissipated.
Claims (8)
1. A special equipment for protecting the wake flow of louver-type airplane engine is composed of more than one airflow-guiding noise-reducing module; the flow guide and noise reduction assembly comprises a barrier assembly; the barrier assembly comprises a barrier bracket and more than two groups of flow guide structures arranged on the barrier bracket; the method is characterized in that: a baffle plate is connected between the adjacent flow guide structures; the flow guide structure, the baffle plate and the barrier bracket are connected in a sealing way; each group of flow guide structures comprises two first flow guide pieces; the first flow guide piece is arranged in an upward arc shape from the direction of the wake flow sprayed out of the airplane to the direction vertical to the direction of the wake flow sprayed out of the airplane; the first flow guide part extends upwards to form a second flow guide part; the adjacent second flow guide pieces are arranged in parallel; an alpha included angle is formed between the second flow guide piece and the jet wake flow direction of the airplane, and the alpha included angle is 80-90 degrees; arc narrow strip slits are formed between adjacent first flow guide pieces and between adjacent second flow guide pieces in the same flow guide structure; the width of the narrow arc slit is gradually reduced from the first diversion part to the second diversion part; the arc narrow slit comprises a diversion inlet and a diversion outlet; the adjacent first flow guide pieces of the flow guide structures in the same group form a flow guide inlet at the position where the wake enters the flow guide structures; the adjacent second flow guide pieces in the same group of flow guide structures form flow guide outlets at the positions where the wake flows out of the flow guide structures; the opening size of the flow guide inlet is larger than that of the flow guide outlet; an included angle of 80-90 degrees is formed between the opening direction of the flow guide inlet and the opening direction of the flow guide outlet; the proportion of the sum of the areas of the flow guide inlets to the area of the barrier component is 15% -20%; the tail flow sprayed out by the airplane enters the arc narrow slit through the flow guide inlet; the tail flow sprayed out by the airplane leaves the arc narrow slit through the diversion outlet.
2. The special equipment for the wake protection of the shutter type aircraft engine according to claim 1, characterized in that: the included angle alpha between the second flow guide piece and the direction of the jet wake of the airplane is 85 degrees.
3. The special equipment for protecting the wake flow of the shutter type aircraft engine is characterized in that: the opening direction of the flow guide inlet and the opening direction of the flow guide outlet form an included angle of 85 degrees.
4. The special equipment for the wake protection of the shutter type aircraft engine according to claim 1, characterized in that: the flow guide and noise reduction assembly also comprises a supporting piece and a fixing piece; the barrier bracket is obliquely arranged; one end of the barrier bracket is connected with the fixing piece; the other end of the barrier bracket is supported; the supporting piece and the fixing piece are used for fixing the barrier component; the support member, the fixing member and the barrier assembly constitute a triangular structure.
5. The special equipment for the wake protection of the shutter type aircraft engine according to claim 1, characterized in that: the barrier bracket comprises a bracket I and a bracket II; the first bracket and the second bracket are arranged oppositely; a first groove is formed in the inner side of the first support; a second groove is formed in the inner side of the second support; the first groove is connected with one end of the flow guide piece, and the second groove is connected with the other end of the flow guide piece.
6. The special equipment for the wake protection of the shutter type aircraft engine according to claim 5, characterized in that: the first support comprises a first branch part and a second branch part; the groove one is positioned between the branch part one and the branch part two; gaps are arranged between the flow guide piece and the first branch part and between the flow guide piece and the second branch part; the second bracket comprises a third branch part and a fourth branch part; the second groove is positioned between the third branch part and the fourth branch part; gaps are arranged between the flow guide piece and the third and fourth branch parts.
7. The special equipment for the wake protection of the shutter type aircraft engine according to claim 1, characterized in that: the sum of the areas of the flow guide inlets accounts for 18% of the area of the barrier module.
8. The special equipment for the wake protection of the shutter type aircraft engine according to claim 1, characterized in that: the baffle comprises a first baffle and a second baffle; the first baffle is arranged close to the flow guide inlet; the second baffle is arranged close to the flow guide outlet; the first baffle and the second baffle are hermetically connected with the flow guide structure and the barrier bracket; a noise reduction space is formed among the first baffle plate, the second baffle plate and the adjacent flow guide structures; the first flow guide piece is provided with a first through hole communicated with the noise reduction space; the second flow guide piece is provided with a second through hole communicated with the noise reduction space; the noise reduction space is internally provided with sound absorption cotton.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111205408.9A CN113815889A (en) | 2021-10-15 | 2021-10-15 | Shutter type aircraft engine wake flow protection special equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111205408.9A CN113815889A (en) | 2021-10-15 | 2021-10-15 | Shutter type aircraft engine wake flow protection special equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113815889A true CN113815889A (en) | 2021-12-21 |
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ID=78916839
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111205408.9A Pending CN113815889A (en) | 2021-10-15 | 2021-10-15 | Shutter type aircraft engine wake flow protection special equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113815889A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1085681A (en) * | 1964-01-04 | 1967-10-04 | Gruenzweig & Hartmann | An exhaust silencer for jet propulsion engines operating on the ground |
| DE9004005U1 (en) * | 1990-04-06 | 1990-06-13 | Ernst Sorst + Co. Ges. für Blechverarbeitung mbH, 3000 Hannover | Wind protection device equipped with expanded metal panels for the lateral limitation of aircraft berths |
| CN103403359A (en) * | 2011-03-03 | 2013-11-20 | 西门子公司 | Resonator silencer for a radial flow machine, in particular for a radial compressor |
| CN103938559A (en) * | 2014-04-11 | 2014-07-23 | 余江 | Flow guide type air barrier |
| CN104890895A (en) * | 2015-06-16 | 2015-09-09 | 崔乃盛 | Noise reduction guide wall for ground tests of planes |
| CN106672259A (en) * | 2016-12-30 | 2017-05-17 | 北京工业大学 | Barrier wall for achieving efficient flow guiding and noise absorption during test run of airplane |
| CN206859092U (en) * | 2017-03-16 | 2018-01-09 | 中南大学 | Flap type sound of the wind barrier |
| CN207565865U (en) * | 2017-09-07 | 2018-07-03 | 东莞英达士声学设备有限公司 | A kind of aircraft is in wing skid pad deflector |
| CN111634439A (en) * | 2020-06-24 | 2020-09-08 | 天津再发科技有限公司 | Noise reduction flow guide screen for aviation test run honeycomb and use method |
-
2021
- 2021-10-15 CN CN202111205408.9A patent/CN113815889A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1085681A (en) * | 1964-01-04 | 1967-10-04 | Gruenzweig & Hartmann | An exhaust silencer for jet propulsion engines operating on the ground |
| DE9004005U1 (en) * | 1990-04-06 | 1990-06-13 | Ernst Sorst + Co. Ges. für Blechverarbeitung mbH, 3000 Hannover | Wind protection device equipped with expanded metal panels for the lateral limitation of aircraft berths |
| CN103403359A (en) * | 2011-03-03 | 2013-11-20 | 西门子公司 | Resonator silencer for a radial flow machine, in particular for a radial compressor |
| CN103938559A (en) * | 2014-04-11 | 2014-07-23 | 余江 | Flow guide type air barrier |
| CN104890895A (en) * | 2015-06-16 | 2015-09-09 | 崔乃盛 | Noise reduction guide wall for ground tests of planes |
| CN106672259A (en) * | 2016-12-30 | 2017-05-17 | 北京工业大学 | Barrier wall for achieving efficient flow guiding and noise absorption during test run of airplane |
| CN206859092U (en) * | 2017-03-16 | 2018-01-09 | 中南大学 | Flap type sound of the wind barrier |
| CN207565865U (en) * | 2017-09-07 | 2018-07-03 | 东莞英达士声学设备有限公司 | A kind of aircraft is in wing skid pad deflector |
| CN111634439A (en) * | 2020-06-24 | 2020-09-08 | 天津再发科技有限公司 | Noise reduction flow guide screen for aviation test run honeycomb and use method |
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