JPH0453360Y2 - - Google Patents

Description

[Detailed explanation of the idea] [Purpose of invention]

(Industrial application field) This idea is based on a rocket that is fixedly installed on the ground and burns, and the thrust, combustion pressure, combustion temperature,
The present invention relates to a rocket combustion test device used to evaluate rocket performance and/or rocket characteristics by measuring vibrations, etc., and particularly relates to a rocket combustion test device equipped with a combustion chamber. (Prior Art) When performing a combustion test on a rocket, for example, a solid rocket, the solid rocket undergoes a high temperature (approximately 1500°C to 2000°C) and high pressure (approximately 50kg) due to the combustion of its propellant.
f/cm ² ) is ejected at high speed (approximately 2000 m/s) and in a short period of time, producing a large amount of noise.
This noise is much louder than the noise generated by normal transportation such as aircraft and vehicles (for example, 180 dB with a thrust of 27 tons and a combustion time of 2 seconds).
When conducting the above-mentioned combustion test, it is important to prevent the noise from affecting the surrounding area of the test site. Therefore, as a device that takes measures against the above-mentioned noise, there is a rocket combustion test device in which a combustion test is conducted with the rocket almost isolated from the outside. Conventional rocket combustion test equipment includes:
For example, there was one shown in Figure 3. That is, the conventional rocket combustion test device 101
The test section 104 includes a combustion chamber 102 and an exhaust duct 103, an intake section 105 for introducing outside air into the test section 104, and an exhaust section 106 for discharging combustion gas from the test section 104. A test rocket (for example, a solid rocket) 100 is fixed to a trolley-shaped test stand 107 installed in a combustion chamber 102 of a test section 104, and a combustion test of the test rocket 100 is performed. This rocket combustion test device 101 includes noise reduction conduits 108, 109, 11 each having a different diameter and capable of injecting cooling water from the inner circumferential side of the exhaust duct 103 near the combustion chamber 102.
0 is set. These muffling conduits 108,1
09 and 110 are fixed to a trolley 117 positioned on a rail 116 laid in the test section 104 so that the combustion gas of the test rocket 100 passes through the inside of each one in turn,
Cooling water is injected onto the combustion gas passing through the muffling pipes 108, 109, 110 to cool the combustion gas, and by reducing its speed, the sound of combustion gas ejected from the test rocket 100 is reduced. Efforts are being made to reduce this. The rocket combustion test device 101 also includes a sound absorbing material 112 that covers the inner surfaces of the exhaust duct 103 and the exhaust section 106, and a sound absorbing material 112 that is provided on the floor surface of the exhaust duct 103 that slopes downward with respect to the direction in which combustion gas is ejected. The sound of combustion gas ejected from the test rocket 100 can also be reduced by the concrete block material 113, the impact deflection plate 114 provided in the exhaust section 106, and the bent passage (not shown) formed in the exhaust section 106. I'm trying to make it possible. Furthermore, this rocket combustion test device 101 has the following features:
The intake section 105 is equipped with a large number of sound absorbing plates 115, so that the sound of combustion gas ejected from the test rocket 100 leaking to the outside through the intake section 105 can be reduced as much as possible. The rocket combustion test device as described above is described in Japanese Patent Application Laid-Open No. 49-21516. (Problems to be Solved by the Invention) Here, although the flow velocity of the combustion gas exhausted from the exhaust section 106 during the combustion test of the test rocket 100 is reduced within the test section 104 and the exhaust section 106, Since the combustion gas is still large in size, if an attempt is made to remove substances such as alumina and ammonium perchlorate contained in this combustion gas in the exhaust section 106, the back pressure within the exhaust section 106 will increase, which is dangerous. Coupled with the short combustion time of the test rocket 100, the conventional rocket combustion test device 101 does not provide a means for removing the substance in the exhaust section 106. However, if the combustion gas and gas smoke remaining in the test section 104 are discharged to the outside without removing the substances after the combustion test of the test rocket 100 is completed, the combustion gas and gas smoke remaining in the test section 104 will be discharged to the outside during the combustion test. Compared to the amount of the above-mentioned substances released into the atmosphere, a much larger amount of the substance will be released into the atmosphere, and in the case of ammonium perchlorate in particular, there is a risk of harm to the surrounding area of the test site. Due to these problems, there has been a demand for a rocket combustion test device equipped with a system for removing the above-mentioned substances from the combustion gas and gas smoke discharged after the combustion test is completed. (Purpose of the invention) This invention was made with a focus on the problems mentioned above. When gas and gas smoke are discharged outside the equipment, the above-mentioned harmful substances are removed from the combustion gas and gas smoke, and when these harmful substances are emitted into the atmosphere, they pose a hazard to the surrounding area of the test site. The object of the present invention is to provide a rocket combustion test device that can prevent such problems.

[Structure of the idea]

(Means for Solving Problems) This invention provides a forced air supply means on the intake path side of the combustion chamber in a rocket combustion test device equipped with a combustion chamber, and a silencing device on the exhaust path side of the combustion chamber. The present invention is characterized in that the passage and the smoke eliminating passage are provided in a branched manner, and a switching door between the noise eliminating passage and the smoke eliminating passage is provided. (Example) This invention will be explained below based on the drawings. 1 and 2 show a rocket combustion test device according to an embodiment of this invention. That is, as shown in FIG. 1, the rocket combustion test device 1 includes a test section 2 in the form of a duct with one end (left side in FIG. 1) closed, and an air intake for introducing outside air into the test section 2. part 3, and an exhaust part 4 connected to the opening 2a on the other end side of the test part 2 and for discharging combustion gas from the test part 2. The test section 2 has a ceiling surface 2b and both side walls 2.
c, 2c, the floor surface 2d and the end wall 2e that closes one end are all made of reinforced concrete, and the end wall 2e side is a combustion chamber in which the test rocket (in this case, a solid rocket) R is burned. 5, and from the combustion chamber 5 to the opening 2a on the other end side is the test rocket R.
It is formed as an exhaust duct 6 that guides the combustion gas spouted out to the exhaust section 4. In this case, the exhaust duct 6
In order to minimize the amount of combustion gas discharged from the exhaust section 4 during combustion of the test rocket R, it is preferable to make it as long as possible so as to retain a large amount of combustion gas. In the combustion chamber 5, a stand block 5a is installed adjacent to the end wall 2e and equipped with a load cell for thrust measurement, etc., and is movable on a rail (not shown) laid in the longitudinal direction of the test section 2. A trolley-shaped test stand 7 is fixed.
In this case, the test rocket R is placed and fixed on the test stand 7 with its nozzle Rn facing the exhaust duct 6 side. On the other hand, the exhaust duct 6 has a plurality of (three in this case) muffling pipes 8, 9, 1 on the combustion chamber 5 side.
It is equipped with 0. These muffling conduits 8, 9, 10
have different diameters, and each has funnel-shaped openings 8a, 9a, and 10a at one end. The muffling conduits 8, 9, and 10 are arranged with their funnel-shaped openings 8a, 9a, and 10a facing the nozzle Rn of the test rocket R, respectively, and with a small diameter muffling conduit (in this case, the muffling conduit 8) are sequentially arranged in series. In this case, the muffling conduit 8,
9 and 10 are respectively fixed to carts 8b, 9b, and 10b positioned on the rails so that their axes coincide with the axis of the test rocket R. The combustion gas ejected from the nozzle Rn flows through these muffling pipes 8, 9,
10 are sequentially passed through. and,
Each funnel-shaped opening 8a, 9 of the muffling conduit 8, 9, 10
On the outer periphery of a, 10a, there is a floor surface 2d of the test section 2.
Annular pipes 11, 11, and 11 are provided, respectively, to communicate with a water supply pipe (not shown) buried below. These annular pipes 11, 11, 11 have
Spray nozzles (not shown) are provided for spraying cooling water in the axial direction of each of the muffling conduits 8, 9, and 10, respectively. In other words, the muffling conduit 8,
9 and 10, when the combustion gas ejected from the test rocket R sequentially passes through the interior thereof, a large amount of cooling water is injected from the spray nozzle to the combustion gas, and each funnel-shaped opening 8a, 9
Air is introduced from a and 10a and cooled, lowering the gas temperature and causing contraction, thereby reducing the gas velocity and reducing the noise of combustion gas ejected from the test rocket R. In this case, by injecting cooling water into the combustion gas, substances such as alumina and ammonium perchlorate contained in the combustion gas can be washed off to some extent. Further, the exhaust duct 6 includes the muffling pipes 8, 9,
Exhaust duct 6 at the rear of 10 (right side in Figure 1)
The ceiling surface 2b and side walls 2c, 2c are coated with a sound absorbing material (not shown) such as foamed concrete material or concrete block material.
This is intended to reduce the noise of combustion gas ejected from the test rocket R. Furthermore, the muffling conduits 8, 9, 10 of the exhaust duct 6
The floor surface 2d of the exhaust duct 6 at the rear of the test rocket R is formed into an inclined surface 2f that slopes downward with respect to the direction in which combustion gas is ejected from the test rocket R. In this case, the silencing conduit 8, 9, When the combustion gas from the test rocket R is cooled in the interior of the test rocket R, wastewater containing substances such as alumina and ammonium perchlorate that are washed away from the combustion gas is passed through this slope 2f for good drainage. It is arranged so that it can flow through the hole 12. The intake section 3 includes an intake duct 14. It is more preferable to make this intake duct 14 as long as possible, but in the illustrated example, it is formed of reinforced concrete in the upper part from the approximate center of the test section 2 to the combustion chamber 5, and one end (left side in FIG. ) is closed by the end wall 14a. The intake duct 14 is in communication with the test section 2 via an intake port 2k formed in the ceiling surface 2b of the combustion chamber 5 of the test section 2, so that the intake section 3 Outside air is introduced into the test section 2 through the test section 14 to prevent the inside of the test section 2 from becoming under negative pressure when the test rocket R burns. In addition, the intake section 3 is provided with noise muffling mufflers 15, 15 equipped with noise reduction means such as rectifying plates inside the intake duct 14 near the opening end 14b and inside the intake port 2k.
The inner surface of the rocket is coated with a sound-absorbing material (not shown) to reduce the sound of combustion gas ejected from the test rocket R leaking to the outside through the intake duct 14. Further, the intake section 3 includes a blower 16 as a forced air supply means above the open end 14b of the intake duct 14.
It is equipped with This blower 16 is connected to the intake duct 1
4 is connected to the communication port 14c formed near the open end 14b of the
Then, outside air is introduced into the test section 2 through the intake duct 14, and the combustion gas and gas smoke remaining in the test section 2 are forcibly discharged from the smoke extinguishing chimney 24, which will be described later, in the exhaust section 4. It is designed to do so. In this case, a rotating door 18 is provided on the right side of the communication port 14c in FIG. 16, the opening end 14b side is closed (the state shown by the imaginary line in FIG. 1), while during the combustion test of the test rocket R, the communication port 14c is closed (the state shown by the solid line in FIG. 1). Thus, outside air is naturally introduced into the intake duct 14. The exhaust section 4 has an opening 2a on the other end side of the test section 2.
The silencing chamber 19 located on the extension of the silencing chamber 1 and the silencing chamber 1
Sound-muffling chimney 2 as a sound-muffling passage located above 9
0, and this noise-reducing chimney 20 is equipped with a smoke-reducing chimney 24 as a branched smoke-reducing passage. As shown in FIG. 2, the silencing chamber 19 is located at the center of an end wall 19a made of reinforced concrete located in the direction in which the combustion gas is ejected, and at the same time branches the combustion gas in the left and right (up and down in FIG. 2) direction. It is equipped with a deflection plate 21 made of a perforated member that leads to the noise-reducing chimney 24 side, and on the upper and lower sides of this deflection plate 21 in FIG. 2, obstacle walls 22 and 22 made of reinforced concrete are respectively formed. Refraction path 2
It is equipped with 3,23. In this case, there is a hollow space between the deflection plate 21 and the end wall 19a, and the obstruction wall 22 and the wall surface 19b of the sound deadening chamber 19 are each coated with a sound absorbing material (not shown). In other words,
The silencing chamber 19 branches the combustion gas spewed out by the test rocket R, and while guiding it to the silencing chimney 20 side by meandering through the bending paths 23 and 23, the kinetic energy of the combustion gas is transferred to the deflection plate 21 and the silencing chamber 19. Obstacle wall 2
2 and 22, the noise of combustion gas ejected from the test rocket R is reduced. The sound-muffling chimney 20 is made of reinforced concrete, and inside thereof, although not shown, a large number of barrier walls similar to the barrier walls 22 provided in the sound-muffling chamber 19 extend in both vertical and horizontal directions. By making the combustion gas meander in the refracted path (not shown) formed by these, the sound of combustion gas ejected from the test rocket R is ultimately reduced. The smoke-killing chimney 24 is formed of reinforced concrete above the opening 2a of the test section 2, and is provided adjacent to the side wall 20a of the noise-killing chimney 20 on the left side in FIG. The smoke-eliminating chimney 24 has a smoke-eliminating filter 25 made of a filamentous metal or synthetic fiber sufficiently moistened with water at approximately the center in the vertical direction inside thereof. In this case, a branching port 20b is formed at the lower end side of the side wall 20a of the noise-reducing chimney 20, and the branching port 20b can be closed, and the side of the refractive road (not shown) of the noise-reducing chimney 20 can also be closed. A switching door 26 is provided, and by closing the bending path side with this switching door 26, combustion gas can flow from the branch port 20b to the smoke-extinguishing chimney 24. That is, during the combustion test of the test rocket R, the branch port 20b is closed with the switching door 26 (the state shown by the solid line in FIG. 1), and the combustion gas flowing at high speed is transferred to the silencing chimney
By discharging from the zero side, the sound of combustion gas ejected from the test rocket R is reduced, and at the same time, the back pressure in the exhaust section 4 is prevented from increasing, and the After the combustion test is completed, the switching door 26 closes the bending path side of the noise-reducing chimney 20 (the state shown by the temporary solid line in FIG. 1), and the combustion gas and gas smoke remaining in the test section 2 are removed from the The smoke-extinguishing chimney 2 along with the outside air introduced by the blower 16
By forcibly discharging from the 4 side, the smoke filter 25 can remove substances such as alumina and ammonium perchlorate contained in the combustion gas and gas smoke. Note that, although it is preferable that the switching door 26 is interlocked with the rotating door 18 of the intake section 3, the present invention is not limited thereto. Therefore, when performing a combustion test on a test rocket (solid rocket) R using the rocket combustion test device 1 described above, the rotation door 18 of the intake section 3 is used to close the intake duct 14 connected to the blower 16 side. Simultaneously with closing the communication port 14c, the switching door 26 of the exhaust section 4 closes the branch port 20b formed in the muffling chimney 20, and a combustion test is started. First, the combustion gas ejected from the nozzle Rn of the test rocket R passes through the interior of the muffling pipes 8, 9, and 10, and the thrust as a reaction is received by the stand block 5a. During this time, the silencing conduit 8,
9, 10, their funnel-shaped openings 8
Annular pipes 11, 1 provided in a, 9a, 10a
Cooling water is injected to the combustion gas from spray nozzles 1 and 11 (not shown), and at the same time air is introduced from the funnel-shaped openings 8a, 9a, and 10a, so the combustion gas is cooled and its gas volume is reduced. As the gas velocity decreases, the gas velocity also decreases, and the level of the ejection sound becomes considerably lower. At this time, substances such as alumina and ammonium perchlorate contained in the combustion gas are washed away to some extent by the cooling water jetted from the spray nozzle, but the waste water containing these substances is removed from the exhaust duct 6. slope 2
It is discharged to the drainage hole 12 through f. Next, the combustion gas whose velocity has been reduced by passing through the muffling conduits 8, 9, and 10 passes through the exhaust duct 6 and flows into the muffling chamber 19 of the exhaust section 4. Even during this period, the kinetic energy of the combustion gas is absorbed by the sound absorbing material provided on the ceiling surface 2b and both side walls 2c, 2c of the exhaust duct 6, so that the level of the ejection sound further decreases. Further, the combustion gas whose velocity has been reduced as described above is branched left and right by the deflection plate 21 of the muffling chamber 19, and collides with the obstacle wall 22, forming a refraction path 23 formed by the obstacle wall 22. It meanders inside and flows to the noise-reducing chimney 20. Since the combustion gas is exhausted to the outside after meandering both vertically and horizontally within the refracted path (not shown) in this noise-reducing chimney 20, the combustion gas ejection sound level from the test rocket R is higher than this test. It is reduced to a level (110dB or less) that does not harm the surrounding area. Note that the above combustion test is conducted for a short time (for example, 2 seconds).
During this period, not much combustion gas is discharged to the outside, and therefore the amount of substances such as alumina and ammonium perchlorate that are dispersed into the atmosphere is small. Furthermore, during the combustion test, most of the combustion gas flows to the exhaust duct 6 side, so the amount of combustion gas flowing out through the intake section 3 is small, and the intake duct 14 of the intake section 3 includes a noise muffler 15, 15, the level of the ejection sound leaking from the intake section 3 to the outside can be suppressed to a low level. After the combustion test of the test rocket R is completed, fire extinguishing personnel must immediately enter the combustion chamber 5 because the test rocket R needs to be extinguished as soon as possible. Therefore, the switching door 26 is operated at the same time as the rotating door 18 that closes the communication port 14c of the intake section 3, and the branch port 20b is opened at the same time as the opening end 14b side of the intake duct 14 is closed. Next, the outside air is sent into the test section 2 through the intake duct 14 by the blower 16, and the test section 2 is
A large amount of combustion gas and gas smoke remaining in the combustion chamber are forcibly discharged to the outside through an exhaust part 4. At this time, as described above, in the exhaust section 4, the switching door 2 blocking the branch port 20b of the noise-reducing chimney 20
6 is operated to close off the bending path side of the silencing chimney 20, so the combustion gas and gas smoke pushed out from the test section 2 by the outside air introduced by the blower 16 are guided to the smoke quenching chimney 24 side. , the smoke-extinguishing chimney 2
By passing through the smoke eliminating filter 25 of No. 4,
Substances such as alumina and aluminum perchlorate are removed, and the combustion gas and gas smoke are discharged outside as only water vapor. Therefore, said substances are not emitted into the atmosphere after the combustion test is completed.

[Effect of the idea]

As explained above, according to this idea,
In a rocket combustion test device equipped with a combustion chamber,
A forced air supply means is provided on the intake path side of the combustion chamber, and a silencing passage and a smoke eliminating passage are provided branchingly on the exhaust path side of the combustion chamber, and a switching door between the silencing passage and the smoke eliminating passage is provided. Because of the structure, when the combustion gas and gas smoke remaining inside the device are discharged to the outside of the device after the combustion test of the test rocket is completed, harmful substances contained in the combustion gas and gas smoke are removed. Since it becomes possible to do so, it can bring about an extremely excellent effect of being able to prevent harm to the surrounding area of the test site.

[Brief explanation of the drawing]

FIG. 1 is a sectional view of a rocket combustion test device according to an embodiment of the invention, as seen from the side, FIG. 2 is a partially cutaway plan view of the rocket combustion test device in FIG. 1, and FIG. The figure is a sectional view of a conventional rocket combustion test device viewed from the side. 1... Rocket combustion test device, 5... Combustion chamber,
16... Blower (forced air supply means), 20... Noise-reducing chimney (noise-reducing passage), 24... Smoke-eliminating chimney (smoke-eliminating passage), 26... Switching door.

Claims (1)

[Scope of utility model registration request] In a rocket combustion test device equipped with a combustion chamber, a forced air supply means is provided on the intake path side of the combustion chamber, and a silencing passage and a smoke quenching passage are provided branchingly on the exhaust path side of the combustion chamber, and the silencing A rocket combustion test device characterized by having a switching door between a passageway and a smoke-extinguishing passageway.