CN111963316B - Low-noise engine for aerospace - Google Patents
Low-noise engine for aerospace Download PDFInfo
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- CN111963316B CN111963316B CN202010854911.6A CN202010854911A CN111963316B CN 111963316 B CN111963316 B CN 111963316B CN 202010854911 A CN202010854911 A CN 202010854911A CN 111963316 B CN111963316 B CN 111963316B
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- 230000009467 reduction Effects 0.000 claims abstract description 18
- 238000013016 damping Methods 0.000 claims description 34
- 230000035939 shock Effects 0.000 claims description 32
- 230000000087 stabilizing effect Effects 0.000 claims description 22
- 230000000694 effects Effects 0.000 claims description 13
- 230000006837 decompression Effects 0.000 claims description 11
- 239000003381 stabilizer Substances 0.000 claims description 8
- 230000006835 compression Effects 0.000 claims description 7
- 238000007906 compression Methods 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 230000006978 adaptation Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 17
- 230000008569 process Effects 0.000 abstract description 12
- 230000008602 contraction Effects 0.000 abstract description 3
- 238000010521 absorption reaction Methods 0.000 description 10
- 230000009471 action Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 241000282414 Homo sapiens Species 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
The invention relates to the technical field of aerospace equipment, and discloses a low-noise engine for aerospace, which comprises a shell, wherein a cross rod is arranged on the left side in the shell, a low-pressure compressor is fixedly arranged in the middle of an inner cavity of the shell, the left end of the low-pressure compressor extends to the inner cavity of the cross rod and is fixedly provided with a rotating rod, the left end of the rotating rod extends to the outer part of the shell and is fixedly sleeved with a propeller shaft, and a reduction gear positioned in the inner cavity of the cross rod is fixedly sleeved on the outer part of the rotating rod. The low-noise engine for aerospace is communicated with the cross rod through the air inlet pipe and the vent pipe, so that the air pressure difference caused by the propeller in the high-speed operation process can drive the sliding block to perform reciprocating contraction movement, the air pressure difference inside and outside the engine is reduced, the problem that the external pressure drives the engine to vibrate integrally due to the fact that the air pressure difference inside and outside the engine is too large is solved, and the noise of the whole engine can be reduced in the aspect of pressure difference.
Description
Technical Field
The invention relates to the technical field of aerospace equipment, in particular to a low-noise engine for aerospace.
Background
Although the development of aerospace is closely related to military application, more importantly, the great progress of human beings in the field has great influence on a plurality of departments of national economy and many aspects of social life, the face of the world is changed, and an aerospace vehicle is the most important equipment in the development process of aerospace.
The engine in the aerospace craft is the final part in the aircraft, the existing aircraft engine utilizes fuel to enable the rotor to operate at a high speed in the operation process so as to provide flight power, the high-speed operation of the rotor in the engine causes the high-speed movement of airflow in the engine, so that extremely high air pressure difference is generated inside and outside the engine, meanwhile, the internal mechanism is driven along with the movement of the rotor to vibrate at a high speed, finally, great noise is generated, the rest of passengers in the aircraft is influenced very much, and therefore the design of the aircraft engine for reducing the noise is urgently needed.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides a low-noise engine for aerospace, which has the advantages of reducing the noise of the engine and the like, and solves the problems that the prior aircraft engine utilizes fuel to enable a rotor to run at a high speed in the running process so as to provide flight power, the high-speed running of the rotor in the engine causes the high-speed movement of airflow in the engine, so that extremely high air pressure difference is generated inside and outside the engine, and simultaneously, the rotor moves to drive an internal mechanism to vibrate at a high speed, so that extremely high noise is finally generated, and the rest of passengers in the aircraft is very influenced.
(II) technical scheme
In order to achieve the purpose of reducing the noise of the engine, the invention provides the following technical scheme: a low-noise engine for aerospace comprises a shell, wherein a cross rod is arranged on the left side inside the shell, a low-pressure compressor is fixedly arranged in the middle of an inner cavity of the shell, the left end of the low-pressure compressor extends to an inner cavity of the cross rod and is fixedly provided with a rotating rod, the left end of the rotating rod extends to the outside of the shell and is fixedly sleeved with a propeller shaft, a reduction gear positioned in the inner cavity of the cross rod is fixedly sleeved on the outside of the rotating rod, a propeller is fixedly arranged on the outside of the reduction gear, vent pipes are fixedly communicated with the upper surface and the lower surface of the cross rod, a decompression bin is fixedly communicated with the top end of each vent pipe, a sliding block is movably arranged in the inner cavity of the decompression bin, a stabilizing loop bar is fixedly arranged on the right side surface of the sliding block, a telescopic rod is movably sleeved on the right end of the stabilizing loop bar, a thin rod is fixedly arranged on the left side surface of the inner cavity of the telescopic rod, the right end of the thin rod is movably sleeved with the left end of the telescopic rod, the right side face of the decompression bin is fixedly communicated with an air inlet pipe, the left end of the air inlet pipe extends to the outside of the shell, the outside of the low-pressure compressor is sequentially fixedly sleeved with a radiating fin and a damping plate from left to right, the side face of the damping plate is provided with a stabilizing groove, one end, far away from the low-pressure compressor, of the inner cavity of the stabilizing groove is fixedly provided with a fixed block, the side face of the fixed block is fixedly provided with a locking sleeve rod, the other end of the locking sleeve rod is movably sleeved with a stabilizing rod, the other end of the stabilizing rod extends to the outside of the damping plate and is fixedly provided with a clamping block, the other side face of the clamping block is fixedly connected with the outer surface of the low-pressure compressor, the side face, far away from the low-pressure compressor, of the inner cavity of the locking sleeve rod is fixedly provided with a vertical rod, and the other end of the vertical rod is movably sleeved with one end of the stabilizing rod, the right flank fixed mounting of low pressure compressor has another dwang, another the right-hand member fixed mounting of dwang has high-pressure turbine, high-pressure turbine's outside fixed mounting has the stay, high-pressure turbine's right flank fixed mounting has low-pressure turbine, low-pressure turbine's outside fixed mounting has the lock sleeve, the positive fixed mounting of lock sleeve has the locking bolt with low-pressure turbine looks adaptation, the inner chamber fixed mounting of shell has the combustion chamber that is located between damper plate and the high-pressure turbine, the equal fixed mounting in upper and lower two sides of lock sleeve has the joint piece, the fixed cover in inside of joint piece is equipped with damping device, damping device's the other end and the right flank fixed connection of stay.
Preferably, damping device includes the shock attenuation loop bar, the right-hand member movable sleeve of shock attenuation loop bar is equipped with the shock attenuation pole, the right side fixed mounting of shock attenuation loop bar inner chamber has the thin pole of shock attenuation, the fixed suit of left end and the right side of shock attenuation pole of the thin pole of shock attenuation.
Preferably, the outer surface of the sliding block is in friction connection with the inner wall of the pressure reduction bin, and the cross street area of the bottom surface of the sliding block is larger than that of the vent pipe.
Preferably, the outside movable sleeve of pin is equipped with connecting spring, both ends are connected with the right flank of slider and the left side fixed connection of telescopic link respectively about connecting spring.
Preferably, the outside movable sleeve of montant is equipped with compression spring, compression spring's both ends respectively with the inner wall of locking loop bar and the side fixed connection of stabilizer bar.
Preferably, the outside activity cover of shock attenuation pin is equipped with damping spring, damping spring's the left and right sides both ends respectively with the right flank of shock attenuation pole and the right flank fixed connection of shock attenuation loop bar inner chamber.
Preferably, the number of the stabilizing grooves is four, and the four stabilizing grooves are uniformly arranged on the side surfaces of the damping plate respectively.
Preferably, the low-pressure turbine is funnel-shaped, and the left side of the low-pressure turbine is fixedly connected with the right side of the locking piece.
(III) advantageous effects
Compared with the prior art, the invention provides a low-noise engine for aerospace, which has the following beneficial effects:
1. the low-noise engine for aerospace is communicated with the cross rod through the air inlet pipe and the vent pipe, so that the air pressure difference caused by the propeller in the high-speed operation process can drive the sliding block to perform reciprocating contraction movement, the air pressure difference inside and outside the engine is reduced, the problem that the external pressure drives the engine to vibrate integrally due to the fact that the air pressure difference inside and outside the engine is too large is solved, and the noise of the whole engine can be reduced in the aspect of pressure difference.
2. This low noise engine for aerospace through the cooperation that sets up clamp splice and stabilizer bar, has avoided the low pressure compressor to lead to the skew of low pressure compressor position because pressure changes at high-speed operation in-process, then increases the problem of the range of vibration of low pressure compressor, because the shock attenuation board is located the middle part of low pressure compressor to the absorbing effect of reinforcing has also improved noise reduction effect.
3. This low noise engine for aerospace sets up the fitting together of lock sleeve and damping device through the outside at low-pressure turbine, has reduced low-pressure turbine and has leaded to the too big problem of low-pressure turbine vibration amplitude because pressure variation in high-speed operation in-process because low-pressure turbine is located this very right end that starts to guaranteed the stability of this engine right half, increased the noise reduction effect of device.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a side view of the damper plate according to the present invention;
FIG. 3 is an enlarged view of the structure at A in FIG. 1 according to the present invention;
FIG. 4 is an enlarged view of the structure at B in FIG. 2 according to the present invention;
FIG. 5 is a schematic view of the shock absorbing device of the present invention.
In the figure: 1. a housing; 2. a cross bar; 3. a low pressure compressor; 4. rotating the rod; 5. a propeller shaft; 6. a reduction gear; 7. a propeller; 8. a breather pipe; 9. a pressure reduction bin; 10. a slider; 11. a thin rod; 12. a connecting spring; 13. stabilizing the loop bar; 14. a telescopic rod; 15. an air inlet pipe; 16. a heat sink; 17. a damper plate; 18. a stabilizing slot; 19. a fixed block; 20. a vertical rod; 21. a compression spring; 22. a stabilizer bar; 23. a clamping block; 24. a combustion chamber; 25. a high pressure turbine; 26. a locking piece; 27. a low pressure turbine; 28. a damping device; 281. a shock-absorbing loop bar; 282. a shock-absorbing pin; 283. a damping spring; 284. a shock-absorbing lever; 29. a locking sleeve; 30. locking the bolt; 31. a clamping block; 32. and locking the loop bar.
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. 1-5, a low noise engine for aerospace use comprises a housing 1, a cross bar 2 is disposed on the left side inside the housing 1, a low pressure compressor 3 is fixedly mounted in the middle of the inner cavity of the housing 1, the left end of the low pressure compressor 3 extends into the inner cavity of the cross bar 2 and is fixedly mounted with a rotating bar 4, the left end of the rotating bar 4 extends to the outside of the housing 1 and is fixedly sleeved with a propeller shaft 5, a reduction gear 6 located in the inner cavity of the cross bar 2 is fixedly sleeved on the outside of the rotating bar 4, a propeller 7 is fixedly mounted on the outside of the reduction gear 6, vent pipes 8 are fixedly communicated with the upper and lower surfaces of the cross bar 2, so as to avoid the problem that the external pressure drives the engine to vibrate integrally due to the excessive pressure difference between the inside and outside of the engine, thereby reducing the noise of the whole engine in terms of pressure difference, a decompression chamber 9 is fixedly communicated with the top end of the vent pipe 8, and a slide block 10 is movably mounted in the inner cavity of the decompression chamber 9, the outer surface of the sliding block 10 is in friction connection with the inner wall of the decompression chamber 9, the cross-sectional area of the bottom surface of the sliding block 10 is larger than that of the vent pipe 8, the arrangement of the sliding block 10 is utilized to ensure the sealing performance between the decompression chamber 9 and the sliding block 10, the problem of gap occurrence is avoided, the reciprocating motion of the sliding block 10 is ensured, the problem of overlarge vibration amplitude of the low-pressure turbine 27 caused by pressure change in the high-speed operation process of the low-pressure turbine 27 is reduced, the low-pressure turbine 27 is positioned at the rightmost end of the engine, so that the stability of the right half part of the engine is ensured, the noise reduction effect of the device is increased, the right side surface of the sliding block 10 is fixedly provided with the stable loop bar 13, the right end of the stable loop bar 13 is movably sleeved with the telescopic rod 14, the thin bar 11 is fixedly arranged on the left side surface of the inner cavity of the telescopic rod 14, the external movable sleeve of the thin bar 11 is provided with the connecting spring 12, the left end and the right end of the connecting spring 12 are respectively and fixedly connected with the right side surface of the sliding block 10 and the left side surface of the telescopic rod 14, the connecting spring 12 is utilized to enable the connecting spring 12 to provide power for the slider 10 to move leftwards, so that the operability of the device is improved, the problem that the vibration amplitude of the low-pressure turbine 27 is overlarge due to pressure variation in the high-speed operation process of the low-pressure turbine 27 is solved, the low-pressure turbine 27 is located at the rightmost end of the engine, so that the stability of the right half part of the engine is ensured, the noise reduction effect of the device is improved, the right end of the thin rod 11 is movably sleeved with the left end of the telescopic rod 14, the right side surface of the decompression bin 9 is fixedly communicated with the air inlet pipe 15, the left end of the air inlet pipe 15 extends to the outside of the shell 1, the outside of the low-pressure compressor 3 is fixedly sleeved with the radiating fins 16 and the damping plate 17 from left to right in sequence, the side surface of the damping plate 17 is provided with the stabilizing groove 18, and the problem that the external pressure drives the engine to vibrate integrally due to overlarge pressure difference between the internal pressure and the external pressure of the engine is solved, therefore, the noise of the whole engine can be reduced in the aspect of pressure difference, the number of the stabilizing grooves 18 is four, the four stabilizing grooves 18 are uniformly and respectively arranged on the side surface of the damping plate 17, one end, far away from the low-pressure compressor 3, of the inner cavity of each stabilizing groove 18 is fixedly provided with a fixing block 19, the side surface of each fixing block 19 is fixedly provided with a locking loop bar 32, the other end of each locking loop bar 32 is movably sleeved with a stabilizing bar 22, the other end of each stabilizing bar 22 extends to the outside of the damping plate 17 and is fixedly provided with a clamping block 23, the other side surface of each clamping block 23 is fixedly connected with the outer surface of the low-pressure compressor 3, the side surface, far away from the low-pressure compressor 3, of the inner cavity of each locking loop bar 32 is fixedly provided with a vertical bar 20, the outside of each vertical bar 20 is movably sleeved with a compression spring 21, the two ends of each compression spring 21 are respectively fixedly connected with the inner wall of each locking loop bar 32 and the side surface of each stabilizing bar 22, and the other end of each vertical bar 20 is movably sleeved with one end of each stabilizing bar 22, the right side surface of the low-pressure compressor 3 is fixedly provided with another rotating rod 4, the right end of the other rotating rod 4 is fixedly provided with a high-pressure turbine 25, the outer part of the high-pressure turbine 25 is fixedly provided with a locking sheet 26, the right side surface of the high-pressure turbine 25 is fixedly provided with a low-pressure turbine 27, the low-pressure turbine 27 is funnel-shaped, the left side surface of the low-pressure turbine 27 is fixedly connected with the right side surface of the locking sheet 26, the outer part of the low-pressure turbine 27 is fixedly provided with a locking sleeve 29, the front surface of the locking sleeve 29 is fixedly provided with a locking bolt 30 matched with the low-pressure turbine 27, the inner cavity of the shell 1 is fixedly provided with a combustion chamber 24 positioned between the damping plate 17 and the high-pressure turbine 25, the upper surface and the lower surface of the locking sleeve 29 are both fixedly provided with clamping blocks 31, the damping device 28 is fixedly sleeved in the clamping blocks 31, the damping device 28 comprises a damping sleeve rod 281, and the damping rod 284 is movably sleeved at the right end of the damping sleeve rod 281, the right side of the inner cavity of the shock absorption sleeve rod 281 is fixedly provided with a shock absorption thin rod 282, the outer part of the shock absorption thin rod 282 is movably sleeved with a shock absorption spring 283, the left end and the right end of the shock absorption spring 283 are fixedly connected with the right side of the shock absorption rod 284 and the right side of the inner cavity of the shock absorption sleeve rod 281, the left end of the shock absorption thin rod 282 is fixedly sleeved with the right side of the shock absorption rod 284, and the other end of the shock absorption device 28 is fixedly connected with the right side of the locking piece 26.
During operation, at first this engine operation, drive reduction gear 6 and low pressure turbine 27 high operation through fin 16, make the inside air current of horizontal pole 2 high-speed operation thereupon, thereby reduce the inside atmospheric pressure difference of horizontal pole 2, make the left atmospheric pressure of slider 10 promote slider 10 and remove to the right, thereby make intake pipe 15 communicate with horizontal pole 2 each other through breather pipe 8, make the inside and outside atmospheric pressure balance of engine, then slider 10 receives the thrust of coupling spring 12, slowly recover, then the inside atmospheric pressure of horizontal pole 2 reduces, so slider 10 reciprocating motion about, finally reduce the influence of atmospheric pressure difference to the engine inside.
In conclusion, the low-noise engine for aerospace is communicated with the cross rod 2 through the air inlet pipe 15 and the vent pipe 8, so that the air pressure difference caused by the propeller 7 in the high-speed operation process can drive the sliding block 10 to do reciprocating contraction motion, the air pressure difference between the inside and the outside of the engine is reduced, the problem that the external pressure drives the engine to vibrate integrally due to the overlarge air pressure difference between the inside and the outside of the engine is solved, and the noise of the whole engine can be reduced in the aspect of pressure difference; through the matching of the clamp block 23 and the stabilizer bar 22, the problem that the position of the low-pressure compressor 3 is deviated due to pressure intensity change in the high-speed operation process of the low-pressure compressor 3, and then the vibration amplitude of the low-pressure compressor 3 is increased is solved, and the vibration damping plate 17 is positioned in the middle of the low-pressure compressor 3, so that the vibration damping effect is enhanced, and the noise reduction effect is also improved; by arranging the locking sleeve 29 outside the low-pressure turbine 27 to be matched with the damping device 28, the problem that the low-pressure turbine 27 has overlarge vibration amplitude due to pressure change in the high-speed operation process of the low-pressure turbine 27 is solved, and the low-pressure turbine 27 is positioned at the rightmost end of the engine, so that the stability of the right half part of the engine is ensured, and the noise reduction effect of the device is improved; the problem of thereby current aircraft engine utilize fuel to make the high-speed operation of rotor provide flight power at the operation in-process, because the high-speed operation of the inside rotor of engine, caused the inside air current high-speed motion of engine for produce extremely high atmospheric pressure difference inside and outside the engine, simultaneously along with the rotor motion drives interior mechanism along with high-speed vibrations, finally send very big noise, very influence the rest of the inside passenger of aircraft is solved.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. A low noise engine for aerospace, comprising a housing (1), characterized in that: the left side of the inner part of the shell (1) is provided with a cross rod (2), the middle part of the inner cavity of the shell (1) is fixedly provided with a low-pressure compressor (3), the left end of the low-pressure compressor (3) extends to the inner cavity of the cross rod (2) and is fixedly provided with a rotating rod (4), the left end of the rotating rod (4) extends to the outer part of the shell (1) and is fixedly provided with a propeller shaft (5), the outer part of the rotating rod (4) is fixedly provided with a reduction gear (6) positioned in the inner cavity of the cross rod (2), the outer part of the reduction gear (6) is fixedly provided with a propeller (7), the upper surface and the lower surface of the cross rod (2) are fixedly communicated with a vent pipe (8), the top end of the vent pipe (8) is fixedly communicated with a decompression bin (9), the inner cavity of the decompression bin (9) is movably provided with a sliding block (10), the right side surface of the sliding block (10) is fixedly provided with a stable sleeve rod (13), the right-hand member movable sleeve of stabilizing loop bar (13) is equipped with telescopic link (14), the left surface fixed mounting of telescopic link (14) inner chamber has thin pole (11), the right-hand member of thin pole (11) cup joints with the left end activity of telescopic link (14), the fixed intercommunication of the right side in decompression storehouse (9) has intake pipe (15), the left end of intake pipe (15) extends to the outside of shell (1), the outside of low pressure compressor (3) is fixed the cover from a left side to the right side in proper order and is equipped with fin (16) and shock attenuation board (17), the stable groove (18) has been seted up to the side of shock attenuation board (17), the one end fixed mounting that low pressure compressor (3) was kept away from to stable groove (18) inner chamber has fixed block (19), the side fixed mounting of fixed block (19) has locking loop bar (32), the other end movable sleeve of locking loop bar (32) is equipped with stabilizer bar (22), the other end of stabilizer bar (22) extends to the outside of shock attenuation board (17) and fixed mounting has clamp splice (23), the another side of clamp splice (23) is connected with the surface fixed connection of low pressure compressor (3), the side fixed mounting that low pressure compressor (3) were kept away from to locking loop bar (32) inner chamber has montant (20), the other end of montant (20) and the one end activity of stabilizer bar (22) are cup jointed, the right flank fixed mounting of low pressure compressor (3) has another dwang (4), another the right-hand member fixed mounting of dwang (4) has high-pressure turbine (25), the outside fixed mounting of high-pressure turbine (25) has stay (26), the right flank fixed mounting of high-pressure turbine (25) has low-pressure turbine (27), the outside fixed mounting of low-pressure turbine (27) has lock sleeve (29), the positive fixed mounting of lock sleeve (29) has locking bolt (30) with low pressure turbine (27) looks adaptation, the inner chamber fixed mounting of shell (1) has combustion chamber (24) that is located between damper plate (17) and high pressure turbine (25), the equal fixed mounting in upper and lower two sides of lock sleeve (29) has joint piece (31), the fixed cover in inside of joint piece (31) is equipped with damping device (28), the other end of damping device (28) and the right flank fixed connection of stay (26).
2. A low noise engine for aerospace according to claim 1, wherein: damping device (28) are including shock attenuation loop bar (281), the right-hand member movable sleeve of shock attenuation loop bar (281) is equipped with shock attenuation pole (284), the right side fixed mounting of shock attenuation loop bar (281) inner chamber has shock attenuation thin rod (282), the fixed suit of right side of left end and shock attenuation pole (284) of shock attenuation thin rod (282).
3. A low noise engine for aerospace according to claim 1, wherein: the outer surface of the sliding block (10) is in friction connection with the inner wall of the pressure reduction bin (9), and the cross street area of the bottom surface of the sliding block (10) is larger than that of the vent pipe (8).
4. A low noise engine for aerospace according to claim 1, wherein: the outside activity cover of pin (11) is equipped with connecting spring (12), the left and right sides both ends of connecting spring (12) respectively with the right flank of slider (10) and the left side fixed connection of telescopic link (14).
5. A low noise engine for aerospace according to claim 1, wherein: the outside movable sleeve of montant (20) is equipped with compression spring (21), the both ends of compression spring (21) respectively with the inner wall of locking loop bar (32) and the side fixed connection of stabilizer bar (22).
6. A low noise engine for aerospace according to claim 2, wherein: the damping thin rod (282) is movably sleeved with a damping spring (283), and the left end and the right end of the damping spring (283) are fixedly connected with the right side surface of the damping rod (284) and the right side surface of the inner cavity of the damping sleeve rod (281) respectively.
7. A low noise engine for aerospace according to claim 1, wherein: the number of the stabilizing grooves (18) is four, and the four stabilizing grooves (18) are uniformly arranged on the side faces of the damping plate (17) respectively.
8. A low noise engine for aerospace according to claim 1, wherein: the low-pressure turbine (27) is funnel-shaped, and the left side surface of the low-pressure turbine (27) is fixedly connected with the right side surface of the locking sheet (26).
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| CN202010854911.6A CN111963316B (en) | 2020-08-24 | 2020-08-24 | Low-noise engine for aerospace |
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| CN202010854911.6A CN111963316B (en) | 2020-08-24 | 2020-08-24 | Low-noise engine for aerospace |
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| WO2023240377A1 (en) * | 2022-06-13 | 2023-12-21 | 天津大学滨海工业研究院有限公司 | Aerospace low-noise engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US5382134A (en) * | 1993-11-01 | 1995-01-17 | General Electric Company | Active noise control using noise source having adaptive resonant frequency tuning through stiffness variation |
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| CN111963316A (en) | 2020-11-20 |
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