JP3105179B2 - Turbojet high-temperature high-speed burner - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbojet type high-temperature and high-speed burner suitable mainly for use in a combustion furnace, a melting furnace, etc., and particularly for incineration of industrial waste.

[0002]

2. Description of the Related Art Various types of combustion furnaces and melting furnaces for various industries include:
Although a predetermined high temperature is required depending on the application, conventional burners of this type do not overheat the combustion air, especially in the case of using oil as fuel and burning only with air. As long as the temperature obtained efficiently is about 14
00 ° C was the limit.

[0003] If a higher temperature is required, it is necessary to heat the combustion air, which requires an air heating furnace or a heat exchanger, which requires equipment and fuel costs. Is added.

[0004] In addition, the latter heat exchanger utilizing waste heat,
There is a limit to the temperature of the combustion air, and as the temperature rises,
The cost of the constituent steel material also increases several times, and it becomes technically difficult, but the burner temperature that can be obtained stably is limited to around 1600 ° C.

If a higher temperature is required, the combustion air is changed to oxygen O ₂ , and the burner temperature becomes 2000 to 35.
High temperatures of 00 ° C. are easily obtained.

When the high temperature of 1600 ° C. or higher is required, it generally belongs to the melting-related category. However, in these cases, there are substances which extremely dislike oxygen, for example, refractory. Even if alumina, tantalum, artificial graphite, etc. all have a heat resistance of 2300 ° C., they are extremely weak to high-temperature oxygen. Further, it is not economically feasible to use a large amount of oxygen as a fuel in, for example, an industrial waste disposal line.

[0007]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-described aspects, and uses a relatively simple combustion chamber configuration and a combustion medium containing only air to provide a relatively low cost and high combustion. It aims to provide a turbojet burner that can obtain a temperature and a high gas velocity.

[0008]

Therefore, in the present invention, the object is achieved by providing a turbojet type high-temperature high-speed burner according to any of the following items (1) and (2). Is what you do.

(1) A burner nozzle provided on the cylindrical center line of a bottom substrate of a substantially cylindrical combustion chamber having a diameter-restricted portion at an open front end portion, and a burner nozzle provided on a peripheral portion of the substrate, wherein the nozzle center line is provided. A high-temperature, high-speed turbojet burner comprising a plurality of high-pressure air injection ports, each of which focuses a forward burner injection in a swirling direction.

(2) A turbojet high-temperature and high-speed burner according to the above (1), wherein a cooling medium passage is provided between the inner and outer surfaces of the substantially cylindrical wall of the combustion chamber.

[0011] (3) The diameter of the diameter constricted portion is set to 0, and the entire shape of the combustion material is formed in a substantially cylindrical shape, as described in any one of the above items (1) and (2). Turbojet high-temperature high-speed burner.

[0012]

According to the structure of the present invention as described above, the pressure in the combustion chamber is increased, and the chemical reaction speed is increased, so that the internal combustion temperature is increased and the exhaust gas is accelerated. In addition, in addition to the above, when the gas diffuses at high speed in advance, the turbulent flame propagation phenomenon causes combustion at a different speed from the conventional phenomenon.For example, an automobile engine is a good example, and the flame is accompanied by the flow of the air-fuel mixture. Despite moving, 10 times faster than combustion rate
It burns at a burning speed as high as 00 times. Slow combustion speed means that the flame is long and there is unburned material. When the flame is short, it is completely mixed with air and there is no unburned material. High combustion speed means that in addition to high temperature and high pressure, air and fuel are rapidly diffused under high pressure and high temperature to create a turbulent combustion speed. The amount of combustion increases significantly.

In order to increase the specification that does not require high temperature / high speed, the combustion chamber can be simplified by omitting the throttle portion immediately before the combustion gas outlet.

[0014]

Embodiments of the present invention will be described below in detail based on an embodiment with reference to the drawings.

[0015]

【Example】

(Structure) FIG. 1 is a schematic sectional explanatory view of a typical embodiment of a high-temperature and high-speed burner according to the present invention. In FIG. 1, 1
Is a burner nozzle disposed at the center of the circular substrate 8A at the bottom of the combustion chamber, and fuel oil is supplied from three fuel inlets through the combustion transport pipe 2.

The feature of the embodiment of the present invention is that it has a burner combustion chamber (frame) 8 having a substantially cylindrical shape and a throttle portion 23 at an open front end, and is more uniform than the outer peripheral edge of the burner nozzle 1 at the center of the substrate 8A. From the high-pressure air inlet 4
6) that the high-pressure air injection port 5 is arranged so that the burner injection focal points 14 on the center line of the burner combustion chamber 8 of the burner nozzle 1 are respectively intensively directed to give a swirling flow of high-pressure air. Features.

The high-pressure air injection port 5 may be configured to bend obliquely right or left so as to forcibly obtain a swirling flow.

The cylindrical outer wall of the burner combustion chamber 8 is composed of three layers of a combustion chamber outer plate 9, an intermediate plate 10 and an inner plate 11, and a cooling water intake 6 and a discharge port 7 are provided between the respective wall plates. A cooling water passage space that communicates with the cooling water is formed.

A throttle portion 23 having a reduced diameter portion 13 of the combustion chamber 8 is provided immediately before the front end portion 12 of the combustion chamber for injecting the combustion gas. A flange 24 having a plurality of screw holes 25 is fixedly provided.

Reference numeral 15 on the substrate 8A indicates an air cooling chamber, 16 is a temperature monitoring camera, 22 is its camera code, and 27 is a fireproof glass. 17
2 shows a plurality of fixing screws for a combustion chamber 8 and an inner plate 11 of a burner main body.

Reference numeral 18 denotes a burner ignition and flame holding pilot, 19 denotes a pilot oxygen inlet, 20 denotes an ignition gas inlet, and 21 denotes an ignition device.

(Operation / Action) With the above configuration,
Burner injection focal point 14 with high-pressure air swirling flow, throttle section 2
Due to the combustion chamber frame structure 8 having 3, the pressure in the combustion chamber is increased, the chemical reaction rate is accelerated by several tens of times, the combustion temperature rises, and the speed of the gas passing through the throttle 23 increases.

(Operation Example) FIG. 1 shows an example of an actual operation procedure in the configuration: oil as a fuel is supplied to the burner nozzle 1 from the inlet 3 through the transport pipe 2, for example, 17k.
g / cm _{2 at} a pressure of 36 g from the periphery of the substrate 8a.
A jet air is jetted at a wind speed of 20 m / s from the high-pressure air injection ports 5 uniformly so as to designate the focal point 14 in a swirling manner, thereby preparing to gasify the fuel oil.

Next, after checking the pressures of the fuel system, the fuel chamber cooling system, and the air system, and the circulation system, the pilot oxygen inlet 19 and the ignition gas inlet 20 are opened, and the ignition device 2 is turned on.
Ignite with 1. Next, the fuel oil to the nozzle 1 and the air to be injected to each injection port 6 are gradually added by manual or automatic control.

At the time of the ignition "standby",
A cooling pump (not shown) is started, and cooling water enters the inside of the combustion chamber outer plate (cylinder) 9 through a water supply hole of the intake port 6, circulates through the inside and returns to the discharge port 7, and this cooling water is It is configured to be cooled by the illustrated cooling tower, return to the cold water tank, and continue the cooling pump circulation.

(Effects) The turbojet burner as described above can obtain high temperature and high speed, and has high combustion efficiency.
Complete combustion does not leave oxygen in the waste gas after combustion. That is, the mixture ratio of fuel oil-air is controlled by, for example, a computer, so that combustion is performed very efficiently because of high temperature and high pressure.

For this reason, the maximum combustion temperature is 2400 °
K, and by utilizing other advanced technologies, 35
It is possible up to 00 ° K, but practically necessary is 190
Because it is about 0 ° C, it is used as a subsonic burner,
Melting of industrial waste and incinerated ash, especially a heating device for a dioxin decomposition heat mixer, which has recently become a problem, can be used very effectively.

(Other Embodiments) As described above, the turbojet burner according to the present invention has a feature that particularly high temperature and high speed combustion can be obtained. For example, in one operation example, the throttle portion of the combustion chamber 8 is provided. The gas passing through 23 gradually has a sound speed of 300 m /
s, and the combustion temperature reaches 3200 ° C., but depending on the required temperature / speed, the injection pressure / flow rate of the high-pressure air, the cooling means, and the like are necessarily limited to the operation example shown in FIG. For example, in the case of a specification that does not require a particularly high temperature / high speed, the combustion chamber 8 may have a reduced degree of the throttling portion 23 or may be a cylindrical shape having the same diameter. Needless to say, the high-pressure air injection amount, the cooling means, and the like should also be adapted to this.

In this embodiment, an example is shown in which liquid oil is used as fuel. However, the present invention is not limited to this, and may be applied to gas gas or powder or a mixture thereof. You may.

[0030]

As described above, according to the structure of the present invention, high-temperature high-speed combustion can be achieved with extremely high efficiency without containing oxygen in the waste gas after combustion.
Depending on the required specification temperature / velocity of the combustion gas and the like, it is also possible to omit the formation of the throttle portion of the combustion chamber, omit the cooling device and the like, and to simplify it.

[Brief description of the drawings]

FIG. 1 is a sectional view of the configuration of a turbojet high-temperature high-speed burner according to an embodiment.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Burner nozzle 2 Fuel transport pipe 3 Fuel oil inlet 4 High pressure air intake 5 High pressure air injection port 6 Cooling water intake 7 Cooling water discharge port 8 Burner combustion chamber 8A Substrate 9 Combustion chamber outer plate 10 Intermediate plate 11 Inner plate 12 Combustion chamber tip 13 Throttle Size 14 Focus of Burner Injection 15 Air Cooling Chamber 16 Temperature Monitoring Camera 17 Burner Body and Combustion Chamber Fixing Screw 18 Ignition and Flame Holding Pilot 19 Pilot Oxygen Inlet 20 Gas Inlet 21 Ignition Device 22 Monitoring Camera Code 23 Aperture 24 Flange 25 Burner Mounting screw hole 27 Fireproof glass

──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. ⁷ , DB name) F23D 11/24 F23L 1/00 F23D 14/22-14/24 F23D 14/66 F23D 14/78 F23C 7 / 06 F23R 3/28

Claims (3)

(57) [Claims] 1. A burner nozzle provided on the cylindrical center line of a bottom substrate of a substantially cylindrical combustion chamber having a diameter constricted portion at an open front end portion, and a burner nozzle disposed on a peripheral portion of the substrate and forward of the nozzle center line. And a plurality of high-pressure air injection ports which respectively focus and orient the burner injections in a swirling manner. 2. The high-temperature and high-speed turbojet burner according to claim 1, wherein a passage for a cooling medium is provided between the inner and outer surfaces of the substantially cylindrical wall of the combustion chamber. 3. The turbojet high temperature according to claim 1, wherein the diameter of the diameter reduction portion is set to 0, and the entire shape of the combustion substance is formed in a substantially cylindrical shape. High speed burner.