CN110905687B - Aircraft engine silencer - Google Patents
Aircraft engine silencer Download PDFInfo
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- CN110905687B CN110905687B CN201911154847.4A CN201911154847A CN110905687B CN 110905687 B CN110905687 B CN 110905687B CN 201911154847 A CN201911154847 A CN 201911154847A CN 110905687 B CN110905687 B CN 110905687B
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- body pipe
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- 230000003584 silencer Effects 0.000 title claims abstract description 61
- 230000030279 gene silencing Effects 0.000 claims abstract description 145
- 238000002347 injection Methods 0.000 claims description 14
- 239000007924 injection Substances 0.000 claims description 14
- 238000003466 welding Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000010425 asbestos Substances 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 229910052895 riebeckite Inorganic materials 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 239000002737 fuel gas Substances 0.000 abstract description 19
- 238000004880 explosion Methods 0.000 abstract description 13
- 230000016615 flocculation Effects 0.000 abstract description 5
- 238000005189 flocculation Methods 0.000 abstract description 5
- 238000005507 spraying Methods 0.000 abstract 2
- 238000004080 punching Methods 0.000 description 26
- 239000007789 gas Substances 0.000 description 22
- 239000003570 air Substances 0.000 description 9
- 230000000694 effects Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 7
- 239000006185 dispersion Substances 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000001743 silencing effect Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000011358 absorbing material Substances 0.000 description 1
- 239000012080 ambient air Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000009365 direct transmission Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention provides an aircraft engine silencer, which comprises a silencer connecting part and a silencer functional part, wherein the silencer connecting part and the silencer functional part are connected along the axial direction of the silencer. The silencer is a silencing bowl structure and a flow guide emergent structure which are designed on the basis of the principle of flow interception and partial pressure, and are used for carrying out flow interception and partial pressure treatment and flow guide emergent treatment on fuel gas sprayed from a tail nozzle of an engine, so that stamping sonic explosion flow generated by the fuel gas sprayed from the tail nozzle in a centralized mode is subjected to forced structural flow division, the energy of the stamping sonic explosion flow is gradually weakened and the aim of silencing is fulfilled, the silencer is used for changing the concentrated spraying fuel gas from a concentrated spraying flow state to a flocculation flow state through the direction changing function of the silencing bowl structure, and the fuel gas in the flocculation flow state is weakly sprayed to the external atmospheric environment through the flow guide emergent structure, so that the basic high-altitude silencing state is realized.
Description
Technical Field
The invention relates to the technical field of engine silencers, in particular to an aero-engine silencer.
Background
In the working process of the aircraft engine, the tail nozzle of the engine can jet high-temperature, high-pressure and high-speed fuel gas backwards so as to provide forward driving force for the spacecraft, meanwhile, in the process of jetting the fuel gas, the fuel gas can form a high-pressure stamping effect on the surrounding air, the stamping effect can highly extrude the surrounding air, and strong stamping acoustic explosion flow is generated. Therefore, a great sound is generated during the ignition operation of the aircraft engine, and in order to reduce the sound generated by the engine, a corresponding silencer is usually installed on a tail nozzle of the engine to reduce the ram action generated by the gas, so that the squeezing action of the ambient air is reduced, and finally the silencing effect is achieved. At present, a silencer for a spacecraft is mainly realized based on the principle of stamping absorption or stamping dispersion, wherein the stamping absorption is that sound wave energy is directly absorbed through a corresponding sound wave absorbing material so as to achieve the purpose of noise reduction and silencing, and the stamping dispersion is that high-temperature, high-pressure and high-speed fuel gas is subjected to dispersion treatment through a corresponding stamping dispersion structure so as to avoid the fuel gas from being concentrated to generate huge stamping, so that the purposes of energy dispersion and noise reduction and silencing are achieved. However, the prior art muffler is generally complicated in structure and expensive in cost, and it is applicable only to a certain type of engine, which seriously deteriorates the muffling performance and versatility of the muffler.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a silencer of an aircraft engine, which is a silencing bowl structure and a flow guide emergent structure designed on the basis of the principle of intercepting and partial pressure for carrying out intercepting and partial pressure treatment and flow guide emergent treatment on gas injected from a tail nozzle of the engine, so that punching acoustic explosion flow generated correspondingly by the gas injected from the tail nozzle in a concentrated mode is subjected to forced structural flow distribution to force the energy of the punching acoustic explosion flow to be gradually weakened and achieve the aim of silencing, the silencer converts the gas injected in the concentrated mode from the concentrated injection flow state into a flocculation flow state through the direction change function of the silencing bowl structure in the silencer, and then the gas in the flocculation flow state is weakly injected into the external atmospheric environment through the flow guide emergent structure in the silencer, so that the gas injected in the concentrated mode is gradually weakened through the two processes of flow distribution and flow guide, therefore, the impact of the gas on the silencer is effectively reduced, the silencing performance of the silencer is improved, and in practical application, the silencer can reduce the energy of the punching acoustic burst flow by 85% -93% and reduce the noise decibel rate by at least 87%, so that the basically high-altitude mute state is realized; in addition, this muffler can also be connected to the engine exhaust nozzle of different models through corresponding muffler connecting portion to improve this type muffler's commonality.
The invention provides an aircraft engine silencer, which comprises a silencer connecting part and a silencer functional part and is characterized in that,
the muffler connecting portion and the muffler functional portion are connected along an axial direction of the muffler;
the muffler connecting portion includes a connecting main body pipe and an engaging structure;
one end of the connecting main body pipe is connected with the silencer function part, and the other end of the connecting main body pipe is provided with the joint structure;
the silencer function part comprises a silencing bowl assembly and a flow guide piece;
the silencing bowl assembly comprises a plurality of silencing bowls which are sequentially stacked;
the flow guide pieces are distributed on the peripheral surface of the outer side of the silencing bowl assembly to guide the gas which is divided by the silencing bowls;
further, the main connecting body pipe is a cylindrical hollow main pipe;
a reserved cavity is formed in the hollow main pipe and used for accommodating an airflow injection port connected with the silencer;
the joint structure comprises a connecting ring and a plurality of connecting ring screw holes;
the connecting ring is arranged on the inner wall surface of the other end of the connecting main body pipe;
the connecting ring screw holes are uniformly distributed at the other end of the connecting main body pipe along the circumferential direction of the connecting main body pipe and penetrate through the connecting ring;
further, the one end of the connecting main body pipe is integrally connected with the flow guide piece;
the flow guide piece comprises a plurality of flow guide grooves which are uniformly distributed along the circumferential direction, and one ends of the flow guide grooves are integrally connected with the connecting main body pipe;
in the plurality of diversion trenches, two adjacent diversion trenches are connected through the extension wall of the main body pipe,
one end of the extending wall of the main body pipe is integrally connected with the main body pipe;
the extension wall of the main body pipe and the outer wall surface of the main connecting body pipe are positioned on the same cylindrical surface;
each flow guide groove is arranged in a hollow convex structure relative to the outer wall surface of the connecting main body pipe;
further, each guide groove comprises a guide groove outer wall and a guide emergent opening; wherein,
the outer wall of the diversion trench comprises a first diversion sub-wall, a second diversion sub-wall, a third diversion sub-wall and a fourth diversion sub-wall;
the first flow guide sub-wall and the outer wall of the connecting main body pipe are arranged at an inclined angle;
one end of the second flow guide sub-wall is connected with the first flow guide sub-wall and is arranged in parallel with the outer wall of the connecting main body pipe;
the third flow guide sub-wall and the fourth flow guide sub-wall are respectively arranged at two sides of the first flow guide sub-wall and the second flow guide sub-wall and are connected with the first flow guide sub-wall, the second flow guide sub-wall and the main pipe extension wall;
the diversion emergent port is formed by the second diversion sub-wall, the third diversion sub-wall and the fourth diversion sub-wall which are enclosed together;
further, each of the silencing bowls comprises an upper end opening part and a lower end opening part;
the cross section size of the upper end opening part is larger than that of the lower end opening part;
in the bowl assembly, an upper end opening portion of each bowl is arranged toward the muffler connecting portion;
in two adjacent stacked silencing bowls, the lower opening part of one silencing bowl and the upper opening part of the other silencing bowl are connected with each other, so that each silencing bowl can shunt gas;
further, each of the silencing bowls further comprises a silencing bowl wall part connecting the upper end opening part and the lower end opening part;
the upper end opening part and the lower end opening part are both provided with a circular cross section shape;
the wall part of the silencing bowl is a closed circular truncated cone side wall;
the smaller opening end of the circular truncated cone side wall is connected with the upper end opening part, and the larger opening end of the circular truncated cone side wall is connected with the lower end opening part, so that each silencing bowl is integrally horn-shaped;
further, the upper end opening part of each silencing bowl comprises a silencing bowl shunting brim;
the silencing bowl diversion eave is a hollow cylindrical side wall, and one end of the hollow cylindrical side wall of the silencing bowl diversion eave is smoothly connected with one end of the wall part of the silencing bowl;
the lower end opening part of each silencing bowl comprises a silencing bowl connecting brim;
the silencing bowl connecting brim is a hollow cylindrical side wall, and one end of the hollow cylindrical side wall of the silencing bowl connecting brim is connected with the other end of the wall part of the silencing bowl;
further, in the silencing bowl assembly, the plurality of silencing bowls which are sequentially stacked are arranged in the following way,
in two adjacent stacked silencing bowls, the outermost end face of the lower end opening part corresponding to the silencing bowl close to one side of the silencer connecting part and the outermost end face of the upper end opening part corresponding to the other silencing bowl are flush with each other, so that no overlapped region exists between the two adjacent stacked silencing bowls;
furthermore, the silencing bowl connecting brim of the lower end opening part of each silencing bowl is connected with the flow guide piece in a welding mode, so that the plurality of silencing bowls are sequentially stacked along the flow guide direction of the flow guide piece;
furthermore, the connecting main body pipe is provided with a double-layer wall structure formed by mutually sleeving a first main body pipe wall and a second main body pipe wall;
a crack space is also arranged between the first main body pipe wall and the second main body pipe wall;
the interval size of the crack space is 10mm-18 mm;
flocculent asbestos materials or carbon fiber materials are filled in the crack space.
Compared with the prior art, the aero-engine silencer provided by the invention has the advantages that the high-temperature, high-pressure and high-speed fuel gas from the tail nozzle of the engine is subjected to structural flow dividing treatment and flow guiding emergent treatment through the silencing bowl structure and the flow guiding emergent structure in the aero-engine silencer, so that the energy of the finally emergent fuel gas is greatly reduced, and the effect of high-altitude silencing is realized. The silencer changes the gas in the centralized injection from the centralized injection flow state to the flocculent flow state through the direction changing function of the silencing bowl structure, and weakly injects the gas in the flocculent flow state to the external atmospheric environment through the flow guide emergent structure, so that the silencer gradually weakens the gas in the centralized injection through two processes of flow division and flow guide, thereby effectively reducing the impact of the gas on the silencer and improving the silencing performance of the silencer.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the embodiments or technical descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic side view of an aircraft engine muffler according to the present invention.
FIG. 2 is a schematic cross-sectional view of an aircraft engine muffler according to the present invention.
FIG. 3 is a schematic cross-sectional perspective view of an aircraft engine muffler according to the present invention.
Fig. 4 is a schematic structural diagram of a silencing bowl in an aircraft engine silencer provided by the invention.
Reference numerals: 1. a muffler connecting portion; 2. a muffler function section; 3. connecting the main body tube; 4. a bonding structure; 5. a silencing bowl assembly; 6. a flow guide member; 7. a silencing bowl; 8. reserving a cavity; 9. a connecting ring; 10. a connecting ring screw hole; 11. a diversion trench; 12. a main tube extension wall; 13. the outer wall of the diversion trench; 14. a diversion emergent port; 15. a first flow guide sub-wall; 16. a second flow guide sub-wall; 17. a third flow guide sub-wall; 18. a fourth flow guide sub-wall; 19. an upper end opening part; 20. a lower end opening part; 21. a silencing bowl wall portion; 22. the silencing bowl shunting brim; 23. the silencing bowl is connected with the brim.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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.
Referring to fig. 1-3, a schematic side view structure, a schematic cross-sectional structure and a schematic sectional perspective structure of an aircraft engine silencer according to the present invention are shown. The aircraft engine silencer comprises a silencer connecting part 1 and a silencer functional part 2. Wherein,
the muffler connecting part 1 and the muffler functional part 2 are connected along the axial direction of the muffler; the muffler connecting portion 1 includes a connecting main body pipe 3 and an engaging structure 4; one end of the connection main body pipe 3 is connected to the muffler function portion 2, and the other end of the connection main body pipe 3 is provided with the engagement structure 4; the silencer function part 2 comprises a silencing bowl assembly 5 and a flow guide piece 6; the silencing bowl assembly 5 comprises a plurality of silencing bowls 7 which are sequentially stacked; the flow guide pieces 6 are distributed on the outer circumferential surface of the silencing bowl assembly 5 to guide the gas which is divided by the silencing bowls 7. It can be seen that the silencer connecting part 1 is used for fixedly connecting the silencer with a tail nozzle of an engine so as to directly transmit gas injected by the tail nozzle of the engine into the silencer for subsequent silencing treatment; in addition, the silencing bowl assembly 5 and the flow guide piece 6 respectively perform structural diversion and flow diversion treatment and flow guide emission treatment on the fuel gas, so that the energy of the punching acoustic explosion flow in the fuel gas is gradually weakened in multiple stages, and finally the silencing and silencing effects are achieved.
Preferably, the main connection body tube 3 is a hollow main tube in a cylindrical shape; a reserved cavity 8 is arranged in the hollow main pipe, and the reserved cavity 8 is used for accommodating an airflow injection port connected with the silencer; the coupling structure 4 comprises a coupling ring 9 and a plurality of coupling ring screw holes 10; the connecting ring 9 is arranged on the inner wall surface of the other end of the connecting main body pipe 3; the plurality of connection ring screw holes 10 are uniformly distributed at the other end of the connection main body pipe 3 along the circumferential direction of the connection main body pipe 3, and are arranged to penetrate through the connection ring 9. Wherein, the connecting ring 9 can be provided with a thread structure or a buckle structure so as to ensure that the connecting main body pipe 3 is stably connected with the airflow injection port of the engine; the screw or bolt can be threaded through the connecting ring screw holes 10, so that when the airflow injection port of the engine is connected into the reserved cavity 8 of the hollow main pipe, the airflow injection port is abutted and fixed through the screw or bolt, and the airflow injection port is fixed in the corresponding depth position of the reserved cavity 8. An air-tight sealing ring can be arranged at the port side of the connecting main body pipe 3 to avoid air leakage when the connecting main body pipe 3 is connected with an airflow injection port of an engine; the arrangement of the reserved cavity 8 can ensure that airflow jet ports with different types and sizes can be connected into the connecting main body pipe 3, so that the universality of the silencer is improved; in addition, because the gas that this air current jet port jetted has higher impact nature, in order to improve the shock resistance of this reservation chamber 8, can make corresponding mechanical reinforcement structure on this reservation chamber 8 avoids to improve the mechanical strength of this reservation chamber 8.
Preferably, the one end of the connecting main body pipe 3 is integrally connected with the flow guide member 6; the flow guide part 6 comprises a plurality of flow guide grooves 11, the flow guide grooves 11 are uniformly distributed along the circumferential direction, and one ends of the flow guide grooves 11 are integrally connected with the connecting main body pipe 3; in the plurality of diversion trenches 11, two adjacent diversion trenches 11 are connected through a main body pipe extension wall 12, and one end of the main body pipe extension wall 12 is integrally connected with the main body pipe 3; the main tube extension wall 12 and the outer wall surface of the main connecting tube 3 are positioned on the same cylindrical surface; each flow guide groove 11 is arranged in a hollow convex structure relative to the outer wall surface of the connecting main body pipe 3.
Preferably, each of the guiding grooves 11 comprises a guiding groove outer wall 13 and a guiding emergence port 14; wherein, the outer wall 13 of the diversion trench comprises a first diversion sub-wall 15, a second diversion sub-wall 16, a third diversion sub-wall 17 and a fourth diversion sub-wall 18; the first flow guiding sub-wall 15 and the outer wall of the connecting main body pipe 3 are arranged in an inclined angle; one end of the second flow guiding sub-wall 16 is connected with the first flow guiding sub-wall 15 and is arranged in parallel with the outer wall of the main connecting body pipe 3; the third flow guiding sub-wall 17 and the fourth flow guiding sub-wall 18 are respectively disposed at two sides of the first flow guiding sub-wall 15 and the second flow guiding sub-wall 16, and are connected to the first flow guiding sub-wall 15 and the second flow guiding sub-wall 16 and the main tube extension wall 12; the diversion exit port 14 is formed by the second diversion sub-wall 16, the third diversion sub-wall 17 and the fourth diversion sub-wall 18, which are enclosed together, and the flocculated gas obtained by the diversion of the silencing bowl 7 is transmitted to the diversion trench 11, and finally directly discharged from the diversion exit port 14 to the external atmosphere through the diversion trench 11, in the process, the energy of the gas flow is rapidly reduced.
Preferably, the inner wall surfaces of the first flow guiding sub-wall 15, the second flow guiding sub-wall 16, the third flow guiding sub-wall 17 and the fourth flow guiding sub-wall 18 may further be provided with flow guiding textures, and the flow guiding textures extend along the length direction of the flow guiding groove. The flow guiding texture structure can be a plurality of fine texture grooves which are arranged in parallel with each other along the length direction or a plurality of irregular fine texture grooves which are approximately arranged along the length direction. Through setting up this water conservancy diversion texture, can improve the transmission directionality and the transmission dwell time of air current in this guiding gutter to further reduce the energy of this air current.
Fig. 4 is a schematic structural diagram of a silencing bowl in an aircraft engine silencer according to the present invention. Each of the silencing bowls 7 comprises an upper end opening part 19 and a lower end opening part 20; the cross-sectional dimension of the upper end opening 19 is larger than the cross-sectional dimension of the lower end opening 20; in the bowl assembly 5, the upper end opening portion 19 of each bowl 7 is disposed toward the muffler connecting portion 1; in two adjacent range upon range of amortization bowls 7, the lower extreme opening 20 of one of them amortization bowl 7 sets up with the upper end opening 19 interconnect of another amortization bowl 7 to make each amortization bowl 7 homoenergetic shunt gas, thereby make the high temperature high pressure high speed gas that sprays from this air current injection port can be carried out the structural reposition of redundant personnel by each amortization bowl 7, in order to carry out diversion reposition of redundant personnel conversion with the gas that will originally have concentrated complete air current structure in order to become the dispersed air current that is the flocculation state, thereby greatly reduce the energy intensity and the energy concentration degree of gas.
Preferably, each of the silencing bowls 7 further comprises a silencing bowl wall part 21 connecting the upper end opening part 19 and the lower end opening part 20; the upper end opening 19 and the lower end opening 20 each have a circular cross-sectional shape; the wall part 21 of the silencing bowl is a closed circular truncated cone side wall; the smaller opening end of the circular truncated cone side wall is connected with the upper end opening part 19, the larger opening end of the circular truncated cone side wall is connected with the lower end opening part 20, so that each silencing bowl 7 is integrally horn-shaped, and the silencing bowls 7 are horn-shaped, so that the punching acoustic blast flow shunted by each silencing bowl 7 can be transmitted to the flow guide groove 11 to the maximum extent, and the scattered transmission of the punching acoustic blast flow is realized to the maximum extent.
Preferably, the upper opening part 19 of each silencing bowl 7 comprises a silencing bowl diversion brim 22; the silencing bowl shunt brim 22 is a hollow cylindrical side wall, and one end of the hollow cylindrical side wall of the silencing bowl shunt brim 22 is smoothly connected with one end of the silencing bowl wall part 21; the lower end opening part 20 of each silencing bowl 7 comprises a silencing bowl connecting brim 23; the silencing bowl connecting brim 23 is a hollow cylindrical side wall, and one end of the hollow cylindrical side wall of the silencing bowl connecting brim 23 is connected with the other end of the silencing bowl wall part 21; because this amortization bowl reposition of redundant personnel eaves 22 sets up in this upper end opening 19 department of this amortization bowl 7, make this punching press acoustic explosion flow can first take place interact with this amortization bowl reposition of redundant personnel eaves 22 after getting into amortization bowl 7 like this, this amortization bowl reposition of redundant personnel eaves 22 self position and structure can carry out the structure reposition of redundant personnel of compulsive to this punching press acoustic explosion flow to force the energy that this punching press acoustic explosion flows to weaken, this punching press acoustic explosion flow passes through an amortization bowl 7 like this, it all can take place the structure reposition of redundant personnel correspondingly, thereby reach the effect that makes this punching press acoustic explosion flow energy reduce gradually.
Preferably, since the silencing bowl shunting brim 22 is used for structurally shunting the punching acoustic blast flow, in order to further improve the structural shunting performance of the silencing bowl shunting brim 22, the edge of the silencing bowl shunting brim 22 may be provided with a non-periodically distributed shunting microstructure, the shunting microstructure may have a wave, square or tooth shape, since the punching acoustic blast flow itself has a complete regular acoustic energy distribution, in order to effectively convert the acoustic energy into a randomly disordered distribution state respectively, the shunting microstructure needs to be set to be non-periodic in structure, so that when the punching acoustic blast flow passes through the silencing bowl shunting brim 22, the punching acoustic blast flow can be cut by the non-periodically distributed shunting microstructure, thereby enabling the energy distribution inside the punching acoustic blast flow to be effectively and randomly destroyed to be converted into a randomly turbulent flow state, thereby effectively reducing the ram acoustic blast energy.
Preferably, the silencing bowl flow dividing ledge 22 may also have an outer shape with non-uniform thickness, and specifically, the silencing bowl flow dividing ledge 22 has a thickness distribution state with successively thicker thicknesses along the flow dividing direction, that is, the silencing bowl flow dividing ledge 22 has a thinner thickness at the foremost end in the flow dividing direction and a thicker thickness at the rearmost end in the flow dividing direction, and the part of the silencing bowl flow dividing ledge 22 between the foremost end and the rearmost end has uniform or non-uniform thickness variation. When the punching acoustic burst flow passes through the diversion eave 22 of the silencing bowl, the punching acoustic burst flow is firstly cut into a plurality of punching acoustic burst sub-flows by the front end part with the thinner thickness, and the punching acoustic burst sub-flows are further cut by the diversion eave part of the rest silencing bowl which becomes thicker gradually after the subsequent transmission process, so that the punching acoustic burst flow is finally cut and shunted into a turbulent flow state, and the effect of reducing the energy of the punching acoustic burst flow is achieved.
Preferably, in the silencing bowl assembly 5, the plurality of silencing bowls 7 arranged in sequence in a stack are arranged in the following way, in two silencing bowls 7 which are adjacently stacked, the outermost end surface of a lower end opening part 20 corresponding to the silencing bowl 7 close to one side of the silencer connecting part 1 and the outermost end surface of an upper end opening part 19 corresponding to the other silencing bowl 7 are flush with each other, so that no overlapping area exists between the two silencing bowls 7 which are adjacently stacked, by setting the relative positions of the two adjacent silencing bowls 7 in the above way, the shunting function of each silencing bowl 7 can be fully utilized, so that the punching sonic boom can have enough residence time in each silencing bowl 7 for shunting, meanwhile, the direct transmission of the punching acoustic blast flow to the diversion trench 11 under the condition of insufficient diversion can be avoided.
Preferably, the silencing bowl connecting brim 23 of the lower end opening portion 20 of each silencing bowl 7 is connected with the flow guide member 6 in a welding mode, so that the plurality of silencing bowls 7 are sequentially stacked along the flow guide direction of the flow guide member 6, a stable relative position relationship among all the silencing bowls 7 can be ensured through the welding mode, and meanwhile, the installation difficulty and the installation cost of the silencing bowls are reduced.
Preferably, in order to avoid the welding bad point formed by the silencing bowl connecting brim 23 and the flow guide piece 6 in the welding process to reduce the shunting and flow guide effects, a plurality of welding connecting lugs can be uniformly arranged on the edge of the silencing bowl connecting brim 23, so that the welding stability and convenience between the silencing bowl connecting brim 23 and the flow guide piece 6 can be effectively improved, and the welding bad point can be effectively prevented.
Preferably, the connecting main body tube 3 has a double-wall structure formed by mutually sleeving a first main body tube wall and a second main body tube wall; a crack space is also arranged between the first main body pipe wall and the second main body pipe wall; the interval size of the crack space is 10mm-18 mm; flocculent asbestos materials or carbon fiber materials are filled in the crack space, and materials with sound wave absorption characteristics are filled in the crack space, so that the energy of the punching acoustic blast flow can be further reduced, and the noise reduction effect is improved.
Preferably, the number of the flow guiding members 6 is even, and the flow guiding members 6 are symmetrically and uniformly distributed on the outer circumferential surface of the silencing bowl assembly 5, specifically, the number of the flow guiding members 6 can be 4, 6, 8, 10, and the even number of the flow guiding members 6 can improve the uniformity of the airflow outgoing from the flow guiding members 6, so as to avoid the occurrence of the unbalanced airflow output.
From the content of the above embodiment, the silencer of the aircraft engine is a silencing bowl structure and a flow guiding exit structure designed based on the principle of flow interception and partial pressure, which perform flow interception and partial pressure treatment and flow guiding exit treatment on the fuel gas injected from the tail nozzle of the engine, so as to forcedly and structurally divide the ram acoustic explosion flow generated by the fuel gas intensively injected from the tail nozzle, so as to force the energy of the ram acoustic explosion flow to be gradually weakened and achieve the purpose of silencing, the WX-I type silencer converts the fuel gas intensively injected from the centralized injection flow state into the flocculated flow state through the direction changing function of the silencing bowl structure in the WX-I type silencer, and weakly injects the fuel gas in the flocculated flow state into the external atmosphere environment through the flow guiding exit structure in the WX-I type silencer, and the silencer of the aircraft engine gradually weakens the fuel gas intensively injected through the two processes of flow division and flow guiding, therefore, the impact of the fuel gas on the silencer is effectively reduced, the silencing performance of the silencer is improved, and in practical application, the silencer of the aero-engine can reduce the energy of the punching acoustic burst flow by 85% -93% and reduce the noise decibel rate by at least 87%, so that the basically high-altitude mute state is realized; in addition, this aeroengine muffler can also be connected to the engine exhaust nozzle of different models through corresponding muffler connecting portion 1 to improve this muffler's commonality.
Claims (8)
1. An aircraft engine silencer, which comprises a silencer connecting part and a silencer function part, is characterized in that,
the muffler connecting portion and the muffler functional portion are connected along an axial direction of the muffler;
the muffler connecting portion includes a connecting main body pipe and an engaging structure;
one end of the connecting main body pipe is connected with the silencer function part, and the other end of the connecting main body pipe is provided with the joint structure;
the silencer function part comprises a silencing bowl assembly and a flow guide piece;
the silencing bowl assembly comprises a plurality of silencing bowls which are sequentially stacked;
the flow guide pieces are distributed on the peripheral surface of the outer side of the silencing bowl assembly to guide the gas which is divided by the silencing bowls;
the one end of the connecting main body pipe is integrally connected with the flow guide piece;
the flow guide piece comprises a plurality of flow guide grooves which are uniformly distributed along the circumferential direction, and one ends of the flow guide grooves are integrally connected with the connecting main body pipe;
in the plurality of diversion trenches, two adjacent diversion trenches are connected through the extension wall of the main body pipe,
one end of the extending wall of the main body pipe is integrally connected with the main body pipe;
the extension wall of the main body pipe and the outer wall surface of the main connecting body pipe are positioned on the same cylindrical surface;
each flow guide groove is arranged in a hollow convex structure relative to the outer wall surface of the connecting main body pipe;
each guide groove comprises a guide groove outer wall and a guide emergence opening; wherein,
the outer wall of the diversion trench comprises a first diversion sub-wall, a second diversion sub-wall, a third diversion sub-wall and a fourth diversion sub-wall;
the first flow guide sub-wall and the outer wall of the connecting main body pipe are arranged at an inclined angle;
one end of the second flow guide sub-wall is connected with the first flow guide sub-wall and is arranged in parallel with the outer wall of the connecting main body pipe;
the third flow guide sub-wall and the fourth flow guide sub-wall are respectively arranged at two sides of the first flow guide sub-wall and the second flow guide sub-wall and are connected with the first flow guide sub-wall, the second flow guide sub-wall and the main pipe extension wall;
the diversion emergent port is formed by the second diversion sub-wall, the third diversion sub-wall and the fourth diversion sub-wall which are enclosed together.
2. The aircraft engine muffler according to claim 1, wherein:
the main connecting body pipe is a cylindrical hollow main pipe;
a reserved cavity is formed in the hollow main pipe and used for accommodating an airflow injection port connected with the silencer;
the joint structure comprises a connecting ring and a plurality of connecting ring screw holes;
the connecting ring is arranged on the inner wall surface of the other end of the connecting main body pipe;
the connecting ring screw holes are uniformly distributed at the other end of the connecting main body pipe along the circumferential direction of the connecting main body pipe and penetrate through the connecting ring.
3. The aircraft engine muffler according to claim 1, wherein:
each silencing bowl comprises an upper end opening part and a lower end opening part;
the cross section size of the upper end opening part is larger than that of the lower end opening part;
in the bowl assembly, an upper end opening portion of each bowl is arranged toward the muffler connecting portion;
in two adjacent stacked silencing bowls, the lower end opening part of one silencing bowl and the upper end opening part of the other silencing bowl are connected with each other, so that each silencing bowl can divide gas.
4. The aircraft engine muffler of claim 3, wherein:
each silencing bowl also comprises a silencing bowl wall part which is connected with the upper end opening part and the lower end opening part; the upper end opening part and the lower end opening part are both provided with a circular cross section shape;
the wall part of the silencing bowl is a closed circular truncated cone side wall;
the smaller opening end of the circular truncated cone side wall is connected with the upper end opening portion, and the larger opening end of the circular truncated cone side wall is connected with the lower end opening portion, so that each silencing bowl is integrally horn-shaped.
5. The aircraft engine muffler of claim 4, wherein:
the upper end opening part of each silencing bowl comprises a silencing bowl shunting brim;
the silencing bowl diversion eave is a hollow cylindrical side wall, and one end of the hollow cylindrical side wall of the silencing bowl diversion eave is smoothly connected with one end of the wall part of the silencing bowl;
the lower end opening part of each silencing bowl comprises a silencing bowl connecting brim;
the silencing bowl connecting brim is a hollow cylindrical side wall, and one end of the hollow cylindrical side wall of the silencing bowl connecting brim is connected with the other end of the wall part of the silencing bowl.
6. The aircraft engine muffler according to claim 5, wherein:
in the silencing bowl assembly, the silencing bowls which are sequentially stacked are arranged in the following way,
in two adjacent stacked silencing bowls, the outermost end face of the lower end opening part corresponding to the silencing bowl close to one side of the silencer connecting part and the outermost end face of the upper end opening part corresponding to the other silencing bowl are flush with each other, so that no overlapped area exists between the two adjacent stacked silencing bowls.
7. The aircraft engine muffler of claim 6, wherein:
the silencing bowl connecting eaves of the lower end opening parts of each silencing bowl are connected with the flow guide piece in a welding mode, so that the silencing bowls are sequentially stacked along the flow guide direction of the flow guide piece.
8. The aircraft engine muffler according to claim 1, wherein:
the connecting main body pipe is provided with a double-layer wall structure formed by mutually sleeving a first main body pipe wall and a second main body pipe wall;
a crack space is also arranged between the first main body pipe wall and the second main body pipe wall;
the interval size of the crack space is 10mm-18 mm;
flocculent asbestos materials or carbon fiber materials are filled in the crack space.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911154847.4A CN110905687B (en) | 2019-11-22 | 2019-11-22 | Aircraft engine silencer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911154847.4A CN110905687B (en) | 2019-11-22 | 2019-11-22 | Aircraft engine silencer |
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| CN110905687B true CN110905687B (en) | 2021-03-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112324574B (en) * | 2021-01-04 | 2021-04-06 | 成都裕鸢航空智能制造股份有限公司 | Aeroengine, aeroengine's (air) intake valve and air intake structure |
| CN112324586B (en) * | 2021-01-04 | 2021-04-06 | 成都裕鸢航空智能制造股份有限公司 | Aeroengine combustion chamber and working method thereof |
| CN114962347B (en) * | 2022-06-29 | 2024-06-04 | 广东顺博铝合金有限公司 | Noise reduction device of blower for aluminum ingot production workshop |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE381983B (en) * | 1974-04-05 | 1976-01-12 | Sunne Gummifab Ab | SOUND Muffler BLASZY NOZZLE |
| US4045957A (en) * | 1976-02-20 | 1977-09-06 | United Technologies Corporation | Combined guide vane and mixer for a gas turbine engine |
| CN1036814A (en) * | 1988-04-14 | 1989-11-01 | 安丰宝 | Exhaust silencer for internal-combustion engine |
| CN202707182U (en) * | 2012-07-30 | 2013-01-30 | 湖北万安环保石化设备有限公司 | Pressure reduction variable-frequency silencer |
| CN204877598U (en) * | 2015-07-31 | 2015-12-16 | 杭州金马管业有限公司 | Automobile silencer |
| CN209261648U (en) * | 2018-12-29 | 2019-08-16 | 南京斯庄森金属材料有限公司 | A kind of exhaust pipe with decrease of noise functions |
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Address after: No.18, Xingong Avenue, Xindu Industrial Zone, Chengdu, Sichuan 610000 Applicant after: Chengdu Yuyuan aviation Intelligent Manufacturing Co.,Ltd. Address before: No.18, Xingong Avenue, Xindu Industrial Zone, Chengdu, Sichuan 610500 Applicant before: CHENGDU YUYUAN AVIATION COMPONENT MANUFACTURING Co.,Ltd. |
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