NL2024736B1 - Aircraft noise reduction device - Google Patents

Aircraft noise reduction device Download PDF

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Publication number
NL2024736B1
NL2024736B1 NL2024736A NL2024736A NL2024736B1 NL 2024736 B1 NL2024736 B1 NL 2024736B1 NL 2024736 A NL2024736 A NL 2024736A NL 2024736 A NL2024736 A NL 2024736A NL 2024736 B1 NL2024736 B1 NL 2024736B1
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NL
Netherlands
Prior art keywords
housing
spoiler
noise reduction
jet flow
fan
Prior art date
Application number
NL2024736A
Other languages
Dutch (nl)
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NL2024736A (en
Inventor
Li Qingzhao
Zheng Binguo
Qin Xiaoyan
Niu Junling
Wang Zehua
Liu Lei
Duan Yongkang
Lyu Mingzhe
Dong Gaosheng
Wang Yufei
Original Assignee
Univ Zhengzhou Aeronautics
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Application filed by Univ Zhengzhou Aeronautics filed Critical Univ Zhengzhou Aeronautics
Priority to NL2024736A priority Critical patent/NL2024736B1/en
Publication of NL2024736A publication Critical patent/NL2024736A/en
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Publication of NL2024736B1 publication Critical patent/NL2024736B1/en

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Classifications

    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B64D33/06—Silencing exhaust or propulsion jets
    • 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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Abstract

The present disclosure relates to an aircraft noise reduction device, and effectively solves the problems of existing aircraft noise reduction devices such as low noise reduction effect of and poor control effect of the temperature difference. The technical 5 solutions of the present disclosure are as follows. The aircraft noise reduction device includes a housing. The inner wall of the housing is fixedly connected to a muffler plate. An air mixing fan is coaxially connected to the muffler plate to be rotatable. The rear side of the air mixing fan is provided with a spoiler fixing ring, and the spoiler fixing ring is slidably connected to the housing and can slide forward and backward. A 10 plurality of spoilers are fixedly connected inside the spoiler fixing ring, and each of the plurality of spoilers is provided with a plurality of spoiler muffler holes. The rear end of the housing is fixedly connected to a collecting pipe, and the rear end of the collecting pipe is coaxially fixed to a flow dividing plate. The outer wall of the flow dividing plate is coaxially and fixedly connected to a jet nozzle. A plurality of sawtooth spoilers are 15 fixedly connected to the jet nozzle. In the present disclosure, the jet flow is spoiled and converged multiple times, in conjunction with multiple holes and temperature control, which effectively solves the problem of jet noise, has a simple and stable structure, and possesses a high universality.

Description

i
AIRCRAFT NOISE REDUCTION DEVICE
TECHNICAL FIELD The present disclosure relates to the technical field of aircraft noise reduction, and specifically relates to an aircraft noise reduction device.
BACKGROUND The turbojet engine is commonly a device with multiple flow passages. and contains the heated central primary airflow discharged by the engine components that constitute the fuel gas generator, and at least one kind of cold airflow concentric with the primary airflow. The cold airflow is also called the secondary airflow. The fuel gas generator includes a gas turbine engine that drives the fan. The air is directly compressed by the fan and 1s introduced into the secondary airflow passage which is concentric with the primary airflow passage. These airflows are mixed on an uprightly downstream side of the fuel gas generator before being ejected into the atmosphere through a single jet nozzle or separately through a plurality of concentric jet nozzles. The noise sources are strong and numerous. However, the jet noise always dominates during the take-off stage of the aircraft with the engine which operates at the maximum power. The jet noise is caused by a severe disturbance and the shear layer generated in the airflow mixing area, and the airflow mixing area has different physical characteristics. For example, the noise between the primary airflow and the secondary airflow or between the secondary airflow and the surrounding atmosphere is called the broadband noise. Particularly, the intensity of the broadband noise increases as the jet speed increases. The jet noise is dramatically reduced in the modern aircrafts by increasing the dilution ratio that is the ratio between the cold airflow and the hot airflow. Theoretically, sound waves in the porous honeycomb structure cause the sound energy to be dissipated due to the friction and damping characteristics of air during repeated refractions, thereby weakening the noise.
However, the aircraft engine noise reduction devices in the prior art have the following issues:
1. Only the sawtooth jet exit is used to accomplish the noise reduction, which has a poor noise reduction effect, and cannot satisfy the requirements of the healthy environment.
2. When the jet flow impacts the outside air, the noise level is increased due to the collision of the high-temperature jet gas and the outside cold air. Moreover, existing devices have a poor control effect of the temperature difference.
Therefore, the present disclosure provides an aircraft noise reduction device to solve the above-mentioned problems.
SUMMARY In view of the above-mentioned problems, in order to overcome the drawbacks of the prior art, the present disclosure provides an aircraft noise reduction device, which effectively solves the problems of the existing aircraft noise reduction devices such as single sawtooth jet exit, low noise reduction effect, and poor control effect of the temperature difference.
The aircraft noise reduction device of the present disclosure includes a housing. The inner wall of the housing is fixedly connected to a muffler plate. An air mixing fan is coaxially connected to the muffler plate to be rotatable. The rear side of the air mixing fan is provided with a spoiler fixing ring, and the spoiler fixing ring is slidably connected to the housing and can slide forward and backward. The ends of a plurality of buffer springs are all fixedly connected to the rear end of the spoiler fixing ring, and the other ends of the plurality of buffer springs are all fixedly connected to the housing.
A plurality of spoilers are fixedly connected inside the spoiler fixing ring, and each of the plurality of spoilers is provided with a plurality of spoiler muffler holes. The plurality of spoilers are inclined and distributed from both sides toward the center.
The rear end of the housing is fixedly connected to a collecting pipe, and the rear end of the collecting pipe is coaxially fixed to a flow dividing plate. A plurality of flow guide holes are arranged on the flow dividing plate, and the outer wall of the flow dividing plate is coaxially and fixedly connected to a jet nozzle. A plurality of sawtooth spoilers are fixedly connected to the jet nozzle, and the plurality of sawtooth spoilers are converged and inclined toward the axial center.
Preferably, a cooling chamber is fixedly connected to the front end of the housing, and a plurality of nozzle holders are fixedly connected inside the cooling chamber. A plurality of nozzles are fixedly connected to each of the plurality of nozzle holders. The plurality of nozzles are all fixed and connected to an annular water pipe which is fixedly connected to the outer wall of the cooling chamber. The annular water pipe is fixed and connected to a water storage tank which is coaxially and fixedly connected to the outer wall of the housing. The water storage tank is connected to the water source in the engine compartment.
Preferably, a plurality of air inlet holes are arranged at the front end of the housing. The inside of the housing is connected to the cooling chamber through the plurality of air inlet holes. The plurality air inlet holes are all coaxially and fixedly connected to a plurality of airflow tubes, and a primary spoiler fan is coaxially connected inside each of the plurality of airflow tubes to be rotatable.
Preferably, the airflow tube is in the shape of a hollow truncated cone. The primary spoiler fan and the secondary spoiler fan are rotatably and coaxially connected to the front end and the rear end of the airflow tube, respectively.
Preferably, the front surface and the rear surface of the fan blade of the primary spoiler fan and the secondary spoiler fan are both provided with a plurality of spoiler fan muffler holes.
Preferably, an airflow tube sleeve is coaxially sleeved outside the airflow tube, the inner wall of the airflow tube sleeve is in clearance fit with the outer wall of the airflow tube to form a liquid storage chamber, and the liquid storage chamber is filled with a coolant.
Preferably, a liquid injection hole and a liquid discharge hole are respectively arranged at the upper portion and the lower portion of the rear end of the liquid storage chamber, and a water stopper is detachably connected inside the liquid injection hole and the liquid discharge hole, respectively.
Preferably, the outer wall surface of the housing is streamline-shaped, and the fixed connection portion between the housing and the collecting pipe are provided with a rounded corner.
The outer wall surface of the water storage tank is a smooth curved surface, and the windward side of the outer wall surface of the water storage tank is provided with a rounded corner.
The present disclosure is directed to improve the existing aircraft noise reduction device to realize the objectives of dividing the jet flow and changing the swirling state by the additionally arranged spoiler. The problem of the large temperature difference between the jet flow and the outside air is solved by the additionally arranged nozzles and airflow tube. The hot jet flow and the cold jet flow are mixed by the additionally arranged air mixing fan and primary spoiler fan. The noise of the jet flow is reduced by the muffler hole. In the present disclosure, the jet flow is spoiled and converged multiple times, in conjunction with multiple holes and temperature control, which effectively solves the problem of jet noise, has a simple and stable structure, and possesses a high universality.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a first perspective view showing the present disclosure.
FIG. 2 is a second perspective view showing the present disclosure. FIG. 3 is a cross-sectional view showing the present disclosure. FIG. 4 is a first partial perspective view showing the spoiler of the present disclosure. 5 FIG. 5 is a second partial perspective view showing the spoiler of the present disclosure. FIG. 6 is a first perspective view showing the airflow tube of the present disclosure. FIG. 7 is a first cross-sectional view showing the airflow tube of the present disclosure. FIG. 8 is a second cross-sectional view showing the airflow tube of the present disclosure. FIG. 9 is a perspective view showing the cooling device of the present disclosure. FIG. 10 is a perspective view showing the housing of the present disclosure. FIG. 11 is a perspective view showing the flow dividing plate of the present disclosure.
DETAILED DESCRIPTION OF THE EMBODIMENTS The description and other technical contents, features, and advantages of the present disclosure will be clearly illustrated hereinafter with reference to the embodiments and FIGS. 1-11. The structures and contents mentioned in the following embodiments can refer to the drawings of the specification. The illustrative embodiments of the present disclosure will be described hereinafter with reference to the drawings. In the first embodiment, the aircraft noise reduction device includes the housing 1,
and the housing 1 includes the front end with a small hole diameter and the rear end with a large hole diameter, which facilitates the jet flow to gradually diffuse in the housing 1, and buffers the impact force of the jet flow in the housing 1 and the velocity of the jet flow. The jet flow is preliminarily premixed with the gas at the rear end of the housing 1 during the diffusion process. The muffler plate 2 is fixedly connected to the inner wall of the housing 1. The noise generated by the jet flow flowing in the housing 1 is reduced by the muffler plate 2. Specifically, a plurality of silencing honeycombs are arranged on the inner wall of the muffler plate 2. The noise reflects multiple times in the silencing honeycomb to reduce the energy of the noise. Therefore, the noise of the jet flow in the housing 1 is buffered by the silencing honeycomb. The air mixing fan 3 is coaxially connected inside the muffler plate 2, and the fan blade of the air mixing fan 3 is an inclined surface. In addition, the air mixing fan 3 drives the air mixing fan 3 to rotate under the action of the jet flow. During the rotation of the air mixing fan 3, the jet flow is sheared to change the direction of the sound spectrum in the jet flow and change the direction of the shear layer of the jet flow. The rear side of the air mixing fan 3 is provided with the spoiler fixing ring 4, and the spoiler fixing ring 4 is slidably connected to the housing 1 and can slide forward and backward. The ends of the plurality of buffer springs 5 are fixedly connected to the rear end of the spoiler fixing ring 4, and the other ends of the plurality of buffer springs 5 are fixedly connected to the housing 1. The spoiler fixing ring 4 is driven to slide forward and backward along the housing 1 under the action of the buffer spring 5 and the jet flow, so that the jet flow is spoiled to reduce the swirling state of the jet flow, thereby avoiding the noise caused by the shear layer which is generated by the swirling state jet flow and the outside air after the jet flow is ejected.
The plurality of spoilers 6 are fixedly connected inside the spoiler fixing ring 4. The plurality of spoilers 6 are provided with the plurality of spoiler muftler hole 7. The front side and the back side of the spoiler 6 are both provided with the plurality of spoiler muffler holes 7. Since the noise is transmitted in all directions during the flowing of the jet flow, and thus the spoiler muffler hole 7 needs to be arranged on the front end face and the rear end face of the spoiler 6 to reduce the noise. The plurality of spoilers 6 are distributed obliquely from the center to both sides. The axial center has a relatively large velocity since the jet flow ejected from the engine is swirling. The plurality of spoilers 6 are obliquely placed to ensure that the jet flow can be dispersed along the spoiler 6 and from the axial center toward the side wall of the housing 1 when flowing, so as to disperse the swirling jet flow and buffer the velocity of the jet flow at the axial center, so that the jet flow can be uniform and is distributed along the inside of the housing 1 with a uniform velocity, and the original swirling jet flow turns into a stable airflow.
The collecting pipe 8 18 fixedly connected to the rear end of the housing 1, and the collecting pipe 8 is in the shape of a truncated cone. The inner diameter of the front end of the collecting pipe 8 is smaller than the inner diameter of the rear end of the housing
1. In this way, the jet flow can be collected and accelerated so as to accelerate and pressurize the jet flow. Thus, the jet flow has an increased pressure and an increased velocity after passing through the collecting pipe 8, and the jet pressure and the velocity of the jet flow are the same as the pressure and the velocity when the jet flow enters the housing 1. The rear end of the collecting pipe 8 is coaxially and fixedly connected to the flow dividing plate 9. The flow dividing plate 9 is provided with the plurality of flow guide holes 10, and the jet flow is discharged into the outside air through the plurality of flow guide holes 10. The jet flow is divided into a plurality of airflows and discharged to the outside under the action of the flow guide holes 10. the plurality of airflows. The jet flow can achieve sufficient contact with the outside air in the course of discharging to the outside, which increases the contact area between the jet flow and the outside air to achieve extremely quick mixing of the jet flow and the outside air, and reduces the noise caused by the long mixing time during the mixing process of the jet flow and the outside air. The outer wall of the flow dividing plate 9 is coaxially and fixedly connected to the jet nozzle 11, and the plurality of sawtooth spoilers 6 are fixedly connected to the jet nozzle 11. The plurality of sawtooth spoilers 6 are converged and inclined toward the direction of the axial center. The shear layer generated by the jet flow and the outside air is reduced under the action of the plurality of sawtooth spoilers 6, so as to accelerate the mixing process of the outside cold air and the jet flow, and reduce the noise.
In the implementation of the present embodiment, the jet flow generated by the aircraft engine passes through the front end of the housing 1, enters the housing 1 and flows toward the rear end. The jet flow is gradually diffused in the course of flowing along the housing 1, so as to reduce the velocity of the jet flow. The swirling state of the jet flow is alleviated during the diffusion process of the jet flow. The jet flow drives the air mixing fan 3 to rotate when flowing. The jet flow is mixed and sheared during the rotation of the air mixing fan 3. In addition, the shear layer of the jet flow is spoiled during the rotation of the air mixing fan 3, thereby reducing the noise generated by the subsequent impact and mixing of the jet flow and the outside air. The jet flow continues to flow into the rear end along the housing 1 and passes through the plurality of spoilers 6 to spoil the shear layer of the jet flow, and the noise inside the jet flow is reduced through the plurality of spoiler muffler holes 7. The jet flow passes through the flow dividing plate 9 and is ejected to the outside through the plurality of flow guide holes 10, and the jet flow is ejected to the outside from the jet nozzle 11. Meanwhile, the noise of the jet flow is further reduced by the sawtooth spoiler 6 fixed on the jet nozzle
11.
In the second embodiment, based on the first embodiment, the temperature of the ejected jet flow is excessively different from the outside temperature during the flowing process of the jet flow. Due to the difference in temperature, the increase in the ratio between the cold airflow and the hot airflow produces noise effects. In addition, the excessively high temperature has a certain impact on the muffler plate 2 in the housing 1, which shortens the service life of the muffler plate 2. The present embodiment provides a cooling method. Specifically, the cooling chamber 13 is fixedly connected to the front end of the housing 1, and the plurality of nozzle holders 14 are fixedly connected inside the cooling chamber 13. The plurality of nozzles 15 are fixedly connected to each of the plurality of nozzle holders 14. The plurality of nozzles 15 spray the water mist into the cooling chamber 13 to cool the jet flow which passes through the cooling chamber 13. The plurality of nozzles 15 are all fixed and connected to the annular water pipe 16 which is fixedly connected to the outer wall of the cooling chamber 13. The annular water pipe 16 is fixed and connected to the water storage tank 17 which is coaxially and fixedly connected to the outer wall of the housing 1. The water storage tank 17 is connected to the water source in the engine compartment, and the water source in the engine compartment is supplied to the plurality of nozzles 15. When the nozzle 15 sprays water to the jet flow, the liquid is vaporized the high temperature gas emitted by the jet flow, enters the housing 1 along with the jet flow, and continuously passes through the jet nozzle 11 and is ejected into the outside.
The jet flow is cooled to reduce the impact on the muffler plate 2, and the temperature of the jet flow is correspondingly reduced.
In this way, the temperature difference between the jet flow and the outside air is reduced, thereby reducing the noise generated by the mixing process of the jet flow and the air.
In the third embodiment, based on the second embodiment, the jet flow presents a swirling state and has a high velocity when ejecting.
Therefore, when the jet flow flows in a swirling state, the noise is increased and the temperature distribution of the cooled jet flow is nonuniform.
The present embodiment provides a method of uniformly mixing the temperature and reducing the swirling jet flow.
Specifically, the plurality of air inlet holes 18 are arranged at the front end of the housing 1. The inside of the housing 1 is connected to the cooling chamber 13 through the plurality of air inlet holes 18. The jet flow is divided into a plurality of airflows through the plurality of air inlet holes 18, and the swirling airflow is decomposed to allow the airflow to flow horizontally, so that the noise generated in the flowing process of the jet flow is reduced and the jet flow is decomposed, which contributes to a rapid heat uniformity.
The plurality air inlet holes
18 are all coaxially and fixedly connected to the plurality of airflow tubes 19, and the primary spoiler fan 20 is coaxially connected inside each of the plurality of airflow tubes 19 to be rotatable. The jet flow entering the airflow tube 19 continues to flow toward the rear end and drives the primary spoiler fan 20 to rotate. The primary spoiler fan 20 rotates to stir and mix the jet flow with nonuniform temperature in the airflow tube 19, which contributes to uniformize the temperature of the jet flow in the airflow tube 19. The jet flow that passes through the plurality of airflow tubes 19 is converged into one jet flow in the rear portion of the housing 1. At this time, the phenomenon of the swirling flow of the jet flow is significantly improved, and the temperature of the jet flow which passes through the airflow tube 19 reaches the uniform mixing state. In the fourth embodiment, based on the third embodiment, the present embodiment provides an efficient processing method in order to effectively spoil and uniformly mix the jet tlow. Specifically, the airflow tube 19 is in the shape of a hollow truncated cone. The airflow tube 19 has a small front end and a large rear end, so that the airflow is gradually decelerated when entering the airflow tube 19, thereby avoiding the noise of the airflow turbulence caused by the airflow in the airflow tube 19 which directly enters the housing 1 without buffering. The primary spoiler fan 20 and the secondary spoiler fan 21 are rotatably and coaxially connected to the front end and the rear end of the airflow tube 19, respectively. The multi-stage turbulence is performed on the jet flow in the airflow tube 19. Since the airflow tube 19 is in the shape of a truncated cone, the radius of the secondary spoiler 21 is larger than the radius of the primary spoiler 20. The primary spoiler fan 20 and the secondary spoiler fan 21 of the airflow tube 19 are configured to achieve a greater degree of turbulence and agitation of the jet flow, so as to spoil the shear layer of the jet flow, reduce the impact of the shear layer, stir the jet flow multiple times to make the temperature distribution uniform, and reduce the noise caused by the nonuniform temperature distribution during the flowing process of the jet flow.
In the fifth embodiment, based on the fourth embodiment, in order to reduce the noise that produces when the jet flow flows in the airflow tube 19, the present embodiment provides a noise reduction method. Specifically, the front end and the rear end of the primary spoiler fan 20 and the secondary spoiler fan 21 are both provided with the plurality of spoiler fan muffler hole 22. The plurality of spoiler fan muffler holes 22 absorb and perform multiple refractions on the sound generated during the flowing process of the jet flow to consume the energy of the sound during the transmission process, so as to reduce the decibel of the sound, thereby reducing the noise transmission.
In the sixth embodiment, based on the third embodiment, the temperature of the jet flow which passes through the cooling chamber 13 is appropriately reduced. However, the temperature is still high relative to the outside temperature. Therefore, the present embodiment provides an auxiliary cooling device. Specifically, the airflow tube sleeve 23 is coaxially sleeved outside the airflow tabe 19, the inner wall of the airflow tube sleeve 23 is in clearance fit with the outer wall of the airflow tube 19 to form the liquid storage chamber 24, and the liquid storage chamber 24 is filled with a coolant. The temperature 1s further reduced by the coolant in the liquid storage chamber 24 during the flowing process of the jet flow in the airflow tube 19. The jet flow is further cooled to reduce the temperature difference between the jet flow and the outside air, so that the jet flow and the outside air can be mixed quickly, which reduces the impact force generated in the mixing process of the jet flow and the outside air, thereby reducing the noise.
In the seventh embodiment, based on the sixth embodiment, the coolant inevitably occurs failures when in use, and thus needs to be replaced regularly. The present embodiment provides a method of replacing the coolant. Specifically, the liquid injection hole 25 and the liquid discharge hole 26 are respectively arranged at the upper portion and the lower portion of the rear end of the liquid storage chamber 24. The liquid injection hole 25 and the liquid discharge hole 26 are fixedly connected to a liquid injection valve and a liquid discharge valve, respectively. The liquid injection hole 25 and the liquid discharge hole 26 can be opened and closed by opening and closing the liquid injection valve and the liquid discharge valve. The coolant is injected into the liquid storage chamber 24 through the liquid injection hole 25. The ineffective coolant is eliminated through the liquid discharge hole 26 to replace the coolant.
In the eighth embodiment, based on the second embodiment, during the flight of the aircraft, the air resistance needs to be reduced to improve the utilization rate of the engine power. Therefore, the present embodiment provides a method of reducing the air resistance. Specifically, the outer wall surface of the housing 1 1s streamline-shaped, and the fixed connection portion between the housing 1 and the collecting pipe 8 are provided with a rounded corner. The resistance of the aircraft is reduced by the streamlined-shape housing 1 and the rounded corner arranged between the housing 1 and the collecting pipe 8 when flying, so that the engine power is efficiently utilized.
The outer wall surface of the water storage tank 17 is a smooth curved surface. The windward side of the outer wall surface of the water storage tank 17 is provided with arounded corner to buffer the air resistance and reduce the resistance of the aircraft in flight.
Specifically, when in use, the liquid storage chamber 24 and the water storage tank 17 are put into use after passing through a safety inspection. The front end of the cooling chamber 13 is fixedly connected to the jet hole of the aircraft engine. The aircraft engine operates to spray the jet flow to the cooling chamber 13, and activates the nozzle 15 to spray the water mist to the cooling chamber 13 when the aircraft is activated. The jet flow ejected from the aircraft engine passes through the cooling chamber 13 and is cooled by the jet nozzle. The jet flow passes through the cooling chamber 13, undergoes the preliminary cooling, and passes through the airflow tube 19. The jet flow is spoiled and undergoes the noise reduction of the primary spoiler fan 20 and the secondary spoiler fan 21 in the airflow tube 19, and is converged in the rear portion of the housing
1.
The converged jet flow gradually diffuses when flowing along the housing 1, so as to reduce the flow velocity of the jet flow. The jet flow drives the air mixing fan 3 to rotate when tlowing. The jet flow is mixed and sheared during the rotation of the air mixing fan 3, to completely change the swirling flow characteristic of the jet flow. In addition, during the rotation of the air mixing fan 3, the shear layer of the jet flow is spoiled to reduce the noise generated by the subsequent impact and mixing of the jet flow and the outside air. The jet flow continues to flow into the rear end along the housing 1 and passes through the plurality of spoilers 6 to spoil the shear layer of the jet flow, and the noise inside the jet flow is reduced through the plurality of spoiler muffler holes 7. The jet flow passes through the flow dividing plate 9 and is ejected to the outside through the plurality of flow guide holes 10, and the jet flow is ejected to the outside from the jet nozzle 11. Meanwhile, the noise of the jet flow is further reduced by the sawtooth spoiler 6 fixed on the jet nozzle 11.
It should be noted that, the actual flow velocity and pressure of the jet flow would be affected in the process of cooling and spoiling the jet flow, thereby affecting the thrust of the jet flow and the air. Therefore, the inner diameter of the jet nozzle 11 1s smaller than the inner diameter of the cooling chamber 13, so as to accelerate and pressurize the jet flow, and the thrust generated by the jet flow and the outside air is sufficient to ensure the needed power of the aircraft in flight.
The present disclosure is directed to improve the existing aircraft noise reduction device to realize the objectives of dividing the jet flow and changing the swirling state by the additionally arranged spoiler. The problem of the large temperature difference between the jet flow and the outside air is solved by the additionally arranged nozzles and airflow tube. The hot jet flow and the cold jet flow are mixed by the additionally arranged air mixing fan and primary spoiler fan. The noise of the jet flow is reduced by the muffler hole. In the present disclosure, the jet flow is spoiled and converged multiple times, in conjunction with multiple holes and temperature control, which effectively solves the problem of jet noise, has a simple and stable structure, and possesses a high universality.

Claims (8)

CONCLUSIESCONCLUSIONS 1. Een vliegtuiggeluidsreductie-inrichting, omvattende: een behuizing (1); een binnenwand van de behuizing (1) is vast verbonden met een demperplaat (2); een lucht-mengende ventilator (3) is coaxiaal verbonden met de demperplaat (2) om roteerbaar te zijn; een achterzijde van de lucht-mengende ventilator (3) is voorzien van een spoilerbevestigingsring (4), en de spoilerbevestigingsring (4) is verschuifbaar verbonden met de behuizing (1) en kan naar voren en naar achteren schuiven; de uiteinden van meerdere bufferveren (5) zijn allemaal vast verbonden met een achtereinde van de spoilerbevestigingsring (4), en de andere uiteinden van de meerdere bufferveren (5) zijn allemaal vast verbonden met de behuizing (1 ); meerdere spoilers (6) zijn vast verbonden in de spoilerbevestigingsring (4), en elk van de meerdere spoilers (0) is voorzien van meerdere spoilerdempergaten (7), de meerdere spoilers (6) lopen schuin en zijn vanaf beide zijden naar het midden verdeeld; en het achtereinde van de behuizing (1) is vast verbonden met een verzamelpijp (8) en het achtereinde van de verzamelpijp (8) is coaxiaal bevestigd aan een stroom verdelende plaat (9); meerdere stroomgeleidingsgaten (10) zijn aangebracht op de stroom verdelende plaat (9) en de buitenwand van de stroom verdelende plaat (9) is coaxiaal en vast verbonden met een straalspuitmond (11); meerdere zaagtandspoilers (12) zijn vast verbonden met het straalspuitmondstuk (11), en de meerdere zaagtandspoilers (12) komen samen in één punt en lopen schuin naar het axiale middelpunt.An aircraft noise reduction device, comprising: a housing (1); an inner wall of the housing (1) is rigidly connected to a damper plate (2); an air-mixing fan (3) is coaxially connected to the damper plate (2) to be rotatable; a rear side of the air mixing fan (3) is provided with a spoiler fixing ring (4), and the spoiler fixing ring (4) is slidably connected to the housing (1) and can slide forward and backward; the ends of a plurality of buffer springs (5) are all rigidly connected to a rear end of the spoiler mounting ring (4), and the other ends of the plurality of buffer springs (5) are all rigidly connected to the housing (1); several spoilers (6) are rigidly connected in the spoiler mounting ring (4), and each of the several spoilers (0) has several spoiler damper holes (7), the several spoilers (6) are sloped and distributed from both sides towards the center ; and the rear end of the housing (1) is rigidly connected to a collection pipe (8) and the rear end of the collection pipe (8) is coaxially attached to a flow dividing plate (9); a plurality of flow guide holes (10) are provided on the flow dividing plate (9) and the outer wall of the flow dividing plate (9) is coaxially and rigidly connected to a jet nozzle (11); a plurality of sawtooth spoilers (12) are rigidly connected to the blast nozzle (11), and the plurality of sawtooth spoilers (12) converge in one point and run obliquely to the axial center. 2. Vliegtuiggeluidsreductie-inrichting volgens conclusie 1, met het kenmerk, dat een koelkamer (13) vast is verbonden met het vooreinde van de behuizing (1), en meerdere spuitmondhouders (14) vast zijn verbonden in de koelkamer (13); meerdere spuitmonden (15) zijn vast verbonden met elk van de meerdere spuitmondhouders (14); de meerdere spuitmonden (15) zijn allemaal vastgezet en verbonden met een ringvormige waterpijp (16) die vast is verbonden met de buitenwand van de koelkamer (13); de ringvormige waterpijp (16) is vastgezet en verbonden met een wateropslagtank (17) die coaxiaal en vast is verbonden met de buitenwand van de behuizing (1); de wateropslagtank (17) is verbonden met een waterbron in een motorruimte.Aircraft noise reduction device according to claim 1, characterized in that a cooling chamber (13) is rigidly connected to the front end of the housing (1), and a plurality of nozzle holders (14) are rigidly connected in the cooling chamber (13); a plurality of nozzles (15) are rigidly connected to each of the plurality of nozzle holders (14); the plurality of nozzles (15) are all fixed and connected to an annular water pipe (16) which is rigidly connected to the outer wall of the cooling chamber (13); the annular water pipe (16) is fixed and connected to a water storage tank (17) which is coaxially and rigidly connected to the outer wall of the housing (1); the water storage tank (17) is connected to a water source in an engine compartment. 3. Vliegtuiggeluidsreductie-inrichting volgens conclusie 2, met het kenmerk, dat meerdere luchtinlaatgaten (18) aan het vooreinde van de behuizing (1) zijn aangebracht; de binnenkant van de behuizing (1) is verbonden met de koelkamer (13) via de meerdere luchtinlaatgaten (18); de meerdere luchtinlaatgaten (18) allemaal coaxiaal en vast zijn verbonden met meerdere luchtstroombuizen (19), en een primaire spoilerventilator (20) coaxiaal is verbonden in elk van de meerdere luchtstroombuizen (19) om roteerbaar te zijn.Aircraft noise reduction device according to claim 2, characterized in that a plurality of air intake holes (18) are provided at the front end of the housing (1); the inside of the housing (1) is connected to the cooling chamber (13) through the plurality of air inlet holes (18); the plurality of air inlet holes (18) are all coaxially and rigidly connected to a plurality of airflow tubes (19), and a primary spoiler fan (20) is coaxially connected in each of the plurality of airflow tubes (19) to be rotatable. 4. Vliegtuiggeluidsreductie-inrichting volgens conclusie 3, met het kenmerk, dat de luchtstroombuis (19) de vorm heeft van een holle afgeknotte kegel; de primaire spoilerventilator (20) en een secundaire spoilerventilator (21) zijn roteerbaar en coaxiaal verbonden met respectievelijk het voorste uiteinde en het achterste uiteinde van de luchtstroombuis (19).Aircraft noise reduction device according to claim 3, characterized in that the air flow tube (19) is in the form of a hollow truncated cone; the primary spoiler fan (20) and a secondary spoiler fan (21) are rotatably and coaxially connected to the front end and rear end, respectively, of the air flow tube (19). 5. Vliegtuiggeluidsreductie-inrichting volgens conclusie 4, met het kenmerk, dat het vooroppervlak en het achter oppervlak van het ventilatorblad van de primaire spoilerventilator (20) en de secundaire spoilerventilator (21) beide zijn voorzien van meerdere spoilerventilator dempergaten (22).An aircraft noise reduction device according to claim 4, characterized in that the front surface and the rear surface of the fan blade of the primary spoiler fan (20) and the secondary spoiler fan (21) are both provided with a plurality of spoiler fan damper holes (22). 6. Vliegtuiggeluidreductie-inrichting volgens conclusie 3, met het kenmerk, dat een luchtstroombuishuls (23) de luchtstroombuis (19) buiten coaxiaal omhult; de binnenwand van de luchtstroombuishuls (23) nauwsluitend passend met de buitenwand van de luchtstroombuis (19) is om een vloeistofopslagkamer (24) te vormen, en de vloeistofopslagkamer (24) gevuld is met een koelmiddel.An aircraft noise reduction device according to claim 3, characterized in that an airflow tube sleeve (23) coaxially envelops the airflow tube (19) outside; the inner wall of the air flow tube sleeve (23) is tightly fitting with the outer wall of the air flow tube (19) to form a liquid storage chamber (24), and the liquid storage chamber (24) is filled with a coolant. 7. Vliegtuiggeluidsreductie-inrichting volgens conclusie 6, met het kenmerk, dat een vloeistofinjectie-gat (25) en een vloeistofafvoer-gat (25) respectievelijk zijn aangebracht aan een bovenste gedeelte en een onderste gedeelte van het achtereinde van de vloeistofopslagkamer (24), en een waterstop afneembaar is verbonden in respectievelijk het vloeistofinjectie-gat (25) en het vloeistofafvoer-gat (26).An aircraft noise reduction device according to claim 6, characterized in that a liquid injection hole (25) and a liquid discharge hole (25) are respectively provided at an upper portion and a lower portion of the rear end of the liquid storage chamber (24), and a water stop is removably connected in the liquid injection hole (25) and the liquid discharge hole (26), respectively. 8. Vliegtuiggeluidsreductie-inrichting volgens conclusie 2, met het kenmerk, dat het buitenwandoppervlak van de behuizing (1) een gestroomlijnde vorm heeft en het vaste verbindingsgedeelte tussen de behuizing (1) en de verzamelpijp (8) voorzien is van een afgeronde hoek; en het buitenwandoppervlak van de wateropslagtank (17) een glad gebogen oppervlak is en de windwaartse zijde van het buitenwandoppervlak van de wateropslagtank (17) voorzien is van een afgeronde hoek.Aircraft noise reduction device according to claim 2, characterized in that the outer wall surface of the housing (1) has a streamlined shape and the fixed connecting portion between the housing (1) and the collecting pipe (8) is provided with a rounded corner; and the outer wall surface of the water storage tank (17) is a smoothly curved surface and the windward side of the outer wall surface of the water storage tank (17) has a rounded corner.
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US3002341A (en) * 1957-12-31 1961-10-03 Boeing Co Jet engine noise suppression nozzles
US3587778A (en) * 1969-11-06 1971-06-28 Rohr Corp Sound suppression nozzle structure for fan-jet aircraft engine
US4254620A (en) * 1978-02-27 1981-03-10 The Boeing Company Jet engine multiduct noise suppressor
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine

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