CN103743570A - Muffling device for supersonic combustion ramjet engine test bench - Google Patents
Muffling device for supersonic combustion ramjet engine test bench Download PDFInfo
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- CN103743570A CN103743570A CN201310688019.5A CN201310688019A CN103743570A CN 103743570 A CN103743570 A CN 103743570A CN 201310688019 A CN201310688019 A CN 201310688019A CN 103743570 A CN103743570 A CN 103743570A
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- supersonic combustion
- noise
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- testing table
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Abstract
The invention discloses a muffling device for a supersonic combustion ramjet engine test bench. The muffling device comprises a muffler system, a cooling water injection system and a fan exhaust system which are linearly connected in sequence, wherein the three systems are respectively provided with an ejection channel, and the ejection channels of the three systems are coaxial. The muffler system is arranged right behind the tail end of a combustion chamber of a supersonic combustion ramjet engine to suppress noise generated by jet flow at the tail end of the combustion chamber of the supersonic combustion ramjet engine; the cooling water injection system is used for cooling jet flow passing through the ejection channel thereof and reducing the flow speed of the jet flow; and the fan exhaust system is used for providing ejection for the jet flow at the tail end of the combustion chamber of the supersonic combustion ramjet engine and carrying out air exhausting. The problem of survival of a muffler in extremely-high-temperature and extremely-high-speed jet flow is solved, ejection is provided for jet flow at the tail end of the combustion chamber of the supersonic combustion ramjet engine and air is exhausted, and the muffling device has the advantages of being long in service life, stable in work and capable of well eliminating jet flow noise of the supersonic combustion ramjet engine test bench.
Description
Technical field
The present invention relates to noise-abatement equipment, particularly for the noise-abatement equipment of supersonic combustion punching engine testing table.
Background technology
Supersonic combustion punching engine testing table can produce very serious noise when work, especially the broadband supersonic jet noise at engine export place, for reducing noise, need take to this noise countermeasure, but due to the supersonic jet speed of engine export place discharge be exceedingly fast (about 1000m/s), extreme temperatures (about 2200K), pressure lower (being often less than 1atm), existing sound suppressor cannot bear washing away of high-temperature high-speed airflow like this at all and provide enough power to discharge tail end jet.
Summary of the invention
The problem existing for existing sound suppressor, the invention provides a kind of noise-abatement equipment for supersonic combustion punching engine testing table, to eliminate preferably the jet noise of supersonic speed punching engine testing table.
To achieve these goals, technical scheme of the present invention is as follows:
A kind of noise-abatement equipment for supersonic combustion punching engine testing table, it comprises the muffler system that straight line links together successively, chilled water injection system and blower fan exhaust system, described three systems all have injection passage, and its injection passage is coaxial, described muffler system is arranged on the dead astern of supersonic combustion scramjet combustor tail end, and near the tail end of supersonic combustion scramjet combustor, to suppress the noise of supersonic combustion scramjet combustor tail end jet generation, described chilled water injection system is sprayed chilled water in its injection passage, with the jet of its injection passage of cooling process and reduce jet velocity, the tail end jet that described blower fan exhaust system is supersonic combustion scramjet combustor provides injection and carries out exhaust.
Preferably, described muffler system consists of a sound suppressor or two sound suppressors that are cascaded above.
Preferably, described sound suppressor comprises shell, honeycomb sandwich blank pipe and high temperature resistant hydrophobic acoustic absorbant, the end of described shell is provided with joint flange, the setting of described honeycomb sandwich blank pipe in the enclosure, and between the outer wall of honeycomb sandwich blank pipe and the inwall of shell, leave gap, on the inner and outer wall of honeycomb sandwich blank pipe, be all evenly covered with hole, between its inner and outer wall, be folded with cavity, in described cavity, be provided with high temperature resistant hydrophobic acoustic absorbant, the cavity that the inwall of honeycomb sandwich blank pipe surrounds is its injection passage.
The aperture in the hole preferably, being evenly covered with on the inner and outer wall of described honeycomb sandwich blank pipe is 2mm.
Preferably, described shell and honeycomb sandwich blank pipe are made by heat-resisting alloy.
Preferably, described sound suppressor is cylindrical.
Preferably, described chilled water injection system comprises cooling water source, pump, water-supply-pipe, shower and cooling induction tunnel, described shower is connected with water-supply-pipe, described shower is arranged on cooling induction tunnel, on it, be provided with several and lead to the spout in cooling induction tunnel, and these spouts distribute ringwise.
Preferably, described blower fan exhaust system comprises axial flow blower, fan power and attached supporting construction.
Preferably, described axial flow blower comprises motor and blade, and described motor is explosion-proof waterproof machine, and described blade is made by heat-resisting alloy.
Preferably, the air capacity of described axial flow blower is 15000m
3/ h.
The present invention provides injection and carries out exhaust for the tail end jet of supersonic combustion scramjet combustor by adopting blower fan exhaust system not only to realize, also at the very high temperature hypervelocity tail end Around Jet of supersonic combustion punching engine, caused the cold air stream of enough flows simultaneously, wherein, the internal layer cold air stream of adjacent high temperature tail end jet will inevitably carry out blending with high temperature tail end jet again, thereby correlation miscarriage raw food but and decelerating effect, and the peripheral cold air that surrounds high temperature tail end jet flows, can prevent that high temperature tail end jet from directly washing away silencer internal wall face, play the effect of protection and cooling sound suppressor, sound suppressor can be worked long-term and stably, and air-flow is when passing through, can eliminate preferably the wideband jet noise of supersonic speed punching engine testing table, meanwhile, the present invention also adopts chilled water injection system to spray chilled water in its injection passage, with the jet of its injection passage of cooling process and reduce jet velocity, thereby has protected blower fan exhaust system below.Further, the honeycomb sandwich blank pipe that sound suppressor of the present invention adopts can block heat radiation and airflow scouring for high temperature resistant hydrophobic acoustic absorbant largely, thereby has improved the viability of sound suppressor.
The invention solves the existence problem of sound suppressor in very high temperature hypervelocity jet, and can injection is provided and carry out exhaust for the tail end jet of supersonic combustion scramjet combustor, there is long service life, working stability, and can eliminate preferably the jet noise of supersonic speed punching engine testing table.
Accompanying drawing explanation
Fig. 1 is the structural representation of one embodiment of the invention;
Fig. 2 is the structural representation for a sound suppressor of the embodiment of the present invention shown in Fig. 1;
Fig. 3 is the layout schematic diagram for the hole on the inner and outer wall of the honeycomb sandwich blank pipe of sound suppressor shown in Fig. 2;
In figure: 1, firing chamber tail end; 2,3,4,5, sound suppressor; 51, shell; 511, joint flange; 52, honeycomb sandwich blank pipe; 53, high temperature resistant hydrophobic acoustic absorbant; 6, water-supply-pipe; 7, cooling induction tunnel; 8,9,10, shower; 11, axial flow blower; 12, blower fan rear.
Embodiment
Hereinafter in connection with accompanying drawing, embodiments of the invention are elaborated.It should be noted that, in the situation that not conflicting, the combination in any mutually of the feature in embodiment and embodiment in the application.
As shown in Figure 1, the noise-abatement equipment for supersonic combustion punching engine testing table of the embodiment of the present invention, it comprises straight line links together successively muffler system, chilled water injection system and blower fan exhaust system, described three systems all have injection passage, and its injection passage is coaxial, described muffler system is arranged on the dead astern of the firing chamber tail end 1 of supersonic combustion punching engine, and the firing chamber tail end 1 of close supersonic combustion punching engine.
Described muffler system consists of 4 sound suppressors that are cascaded 2,3,4 and 5.Wherein, sound suppressor 5 is main noise elimination level, mainly for the jet noise centered by 1100Hz, eliminates the noise; Sound suppressor 2,3 and 4 is dismountable auxiliary noise elimination level, can partly weaken high-frequency noises, and can be used for regulating sound suppressor entry position, to mate different test engine length.The structure of sound suppressor 2,3,4 can be identical with sound suppressor 5, also can be different.
As shown in Figure 2, sound suppressor 5 comprises shell 51, honeycomb sandwich blank pipe 52 and high temperature resistant hydrophobic acoustic absorbant 53, the end of shell 51 is provided with joint flange 511, honeycomb sandwich blank pipe is arranged in shell 51, and leave gap between the outer wall of honeycomb sandwich blank pipe 52 and the inwall of shell, on the inner and outer wall of honeycomb sandwich blank pipe 52, be all evenly covered with hole, the layout in hole as shown in Figure 3, between its inner and outer wall, be folded with cavity, the high temperature resistant hydrophobic acoustic absorbant 53 that certain thickness (as thick in 0.1m) is set in this cavity, the cavity that the inwall of honeycomb sandwich blank pipe surrounds is its injection passage.
The aperture in the hole preferably, being evenly covered with on the inner and outer wall of honeycomb sandwich blank pipe 52 is 2mm.
Preferably, shell 51 and honeycomb sandwich blank pipe 52 are made by heat-resisting alloy (as heat-resistance stainless steel).
Preferably, sound suppressor 5 is cylindrical.
When supersonic combustion scramjet combustor tail end jet passes through sound suppressor 5, the sound suppressor 5 designing for some special frequency channel suppresses the wideband noise of jet generation, now honeycomb sandwich blank pipe 52 can block heat radiation and airflow scouring for high temperature resistant hydrophobic acoustic absorbant 53 largely, thereby has improved the viability of sound suppressor 5.
Preferably, described chilled water injection system comprises cooling water source, pump, water-supply-pipe 6, shower 8,9,10 and cooling induction tunnel 7, shower 8,9,10 is connected with water-supply-pipe 6, shower 8,9,10 is arranged on cooling induction tunnel 7, on every shower, be provided with several and lead to the spout in cooling induction tunnel 7, and these spouts on every shower distribute ringwise.
During the work of described chilled water injection system, chilled water is pressurized to the pressure of 1.0MPa, by water-supply-pipe and shower 8,9,10, sprays in the supersonic jet in cooling induction tunnel 7.Chilled water gasification need to absorb the heat of 2260kJ/kg, and afterbody jet that can cooling very high temperature also reduces its flow velocity, thus protection axial flow blower 11 below.
Preferably, described blower fan exhaust system comprises axial flow blower 11, fan power and attached supporting construction.
Preferably, axial flow blower 11 comprises motor and blade, and described motor is explosion-proof waterproof machine, and described blade is made by heat-resisting alloy (as heat-resistance stainless steel).
Preferably, the air capacity of axial flow blower 11 is 15000m
3/ h.
Blower fan exhaust system has not only realized to be provided injection and carries out exhaust for the tail end jet of supersonic combustion scramjet combustor, also at the very high temperature hypervelocity tail end Around Jet of supersonic combustion punching engine, caused the cold air stream of enough flows simultaneously, wherein, the internal layer cold air stream of adjacent high temperature tail end jet will inevitably carry out blending with high temperature tail end jet again, thereby correlation miscarriage raw food but and decelerating effect, and the peripheral cold air that surrounds high temperature tail end jet flows, can prevent that high temperature tail end jet from directly washing away silencer internal wall face, play the effect of protection and cooling sound suppressor, sound suppressor can be worked long-term and stably.
The invention solves the existence problem of sound suppressor in very high temperature hypervelocity jet, and can injection is provided and carry out exhaust for the tail end jet of supersonic combustion scramjet combustor, there is long service life, working stability, and can eliminate preferably the jet noise of supersonic speed punching engine testing table.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (10)
1. the noise-abatement equipment for supersonic combustion punching engine testing table, it is characterized in that: comprise the muffler system that straight line links together successively, chilled water injection system and blower fan exhaust system, described three systems all have injection passage, and its injection passage is coaxial, described muffler system is arranged on the dead astern of supersonic combustion scramjet combustor tail end, and near the tail end of supersonic combustion scramjet combustor, to suppress the noise of supersonic combustion scramjet combustor tail end jet generation, described chilled water injection system is sprayed chilled water in its injection passage, with the jet of its injection passage of cooling process and reduce jet velocity, the tail end jet that described blower fan exhaust system is supersonic combustion scramjet combustor provides injection and carries out exhaust.
2. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 1, is characterized in that: described muffler system consists of a sound suppressor or two sound suppressors that are cascaded above.
3. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 2, it is characterized in that: described sound suppressor comprises shell, honeycomb sandwich blank pipe and high temperature resistant hydrophobic acoustic absorbant, the end of described shell is provided with joint flange, the setting of described honeycomb sandwich blank pipe in the enclosure, and leave gap between the outer wall of honeycomb sandwich blank pipe and the inwall of shell, on the inner and outer wall of honeycomb sandwich blank pipe, be all evenly covered with hole, between its inner and outer wall, be folded with cavity, in described cavity, be provided with high temperature resistant hydrophobic acoustic absorbant, the cavity that the inwall of honeycomb sandwich blank pipe surrounds is its injection passage.
4. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 3, is characterized in that: the aperture in the hole being evenly covered with on the inner and outer wall of described honeycomb sandwich blank pipe is 2mm.
5. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 3, is characterized in that: described shell and honeycomb sandwich blank pipe are made by heat-resisting alloy.
6. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 3, is characterized in that: described sound suppressor is cylindrical.
7. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 1, it is characterized in that: described chilled water injection system comprises cooling water source, pump, water-supply-pipe, shower and cooling induction tunnel, described shower is connected with water-supply-pipe, described shower is arranged on cooling induction tunnel, on it, be provided with several and lead to the spout in cooling induction tunnel, and these spouts distribute ringwise.
8. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 1, is characterized in that: described blower fan exhaust system comprises axial flow blower, fan power and attached supporting construction.
9. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 8, is characterized in that: described axial flow blower comprises motor and blade, described motor is explosion-proof waterproof machine, and described blade is made by heat-resisting alloy.
10. the noise-abatement equipment for supersonic combustion punching engine testing table according to claim 8, is characterized in that: the air capacity of described axial flow blower is 15000m
3/ h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310688019.5A CN103743570B (en) | 2013-12-16 | 2013-12-16 | For the silencing apparatus of supersonic combustion punching engine testing stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310688019.5A CN103743570B (en) | 2013-12-16 | 2013-12-16 | For the silencing apparatus of supersonic combustion punching engine testing stand |
Publications (2)
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| CN103743570A true CN103743570A (en) | 2014-04-23 |
| CN103743570B CN103743570B (en) | 2016-05-25 |
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| CN201310688019.5A Active CN103743570B (en) | 2013-12-16 | 2013-12-16 | For the silencing apparatus of supersonic combustion punching engine testing stand |
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| CN (1) | CN103743570B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110579329A (en) * | 2019-06-27 | 2019-12-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Subsonic/transonic jet noise research test device |
| CN111537181A (en) * | 2020-05-25 | 2020-08-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal noise wind tunnel based on arc heating and test method |
| CN114856867A (en) * | 2022-05-27 | 2022-08-05 | 哈尔滨工程大学 | Active vibration damper for solid rocket engine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110579329A (en) * | 2019-06-27 | 2019-12-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Subsonic/transonic jet noise research test device |
| CN110579329B (en) * | 2019-06-27 | 2024-04-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Sub/transonic jet noise research test device |
| CN111537181A (en) * | 2020-05-25 | 2020-08-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal noise wind tunnel based on arc heating and test method |
| CN111537181B (en) * | 2020-05-25 | 2022-04-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal noise wind tunnel based on arc heating and test method |
| CN114856867A (en) * | 2022-05-27 | 2022-08-05 | 哈尔滨工程大学 | Active vibration damper for solid rocket engine |
| CN114856867B (en) * | 2022-05-27 | 2024-02-06 | 哈尔滨工程大学 | Active vibration damper of solid rocket engine |
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| Publication number | Publication date |
|---|---|
| CN103743570B (en) | 2016-05-25 |
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