SU1509576A1 - Method of lighting fuel mixture - Google Patents

Abstract

The invention relates to energy and can be used for fuel ignition in stationary and transport power plants. The method allows to increase the reliability of ignition. The gaseous component (GC) of the fuel mixture is accelerated in the nozzle to supersonic speed and introduced into the cavity of the resonator, where shock waves are excited, heating the flow of GC. The second component in the form of a jet of liquid fuel is supplied perpendicularly to the flow, which captures a part of the liquid fuel and after the latter is heated to the ignition temperature, the mixture is ignited. The hot fuel mixture is ejected from the opening. 1 il.

Description

The invention relates to energy and can be used for fuel ignition in stationary and transport power plants.

The purpose of the invention is to increase the reliability of ignition.

The drawing shows a device diagram in which the proposed method can be implemented.

The device contains a nozzle 1 for accelerating gas, an acoustic resonator 2 installed opposite the nozzle 1 coaxially with, a nozzle 3 for injecting a liquid component and a chamber 4, in the face of which there is a central hole 5 for releasing combustion products with Nozzle 1 on the side walls of the cooler 4 and an acoustic resonator 2, and opposite to the hole 5 on the opposite end of the chamber 4 coaxially with the hole 5 is installed

nozzle 3, while the axis of the nozzle 3 and the nozzle 1 lie in the same plane. The method is carried out as follows.

The component, being in a gaseous state, under a supercritical pressure differential is accelerated in nozzle 1 to a supersonic speed. From the nozzle 1, the components in the form of a gas jet are introduced into the cavity of the resonator 2. At the same time, some part of the component is retained in the depth of the resonator 2, and the rest is reflected from the resonator 2 and is collected in chamber 4, and then discharged outside through the opening 5. Controlled supply pressure The r.iso-shaped component and the geometrical parameters of the jet, excite gas vibrations inside the resonator 2 of the shock waves and heat it.

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had Ni

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When the temperature of the gas inside the resonator 2 reaches the ignition temperature of the fuel, a run-in nozzle 3 dp of boar-ska: The nozzle 3 is located in the direction of the hole and has a common axis with it,

giving a liquid component through a nozzle which intersects with the accelerating axis

3 and introduce it into the gas flow in the area between the nozzle exit section

1 and the entrance to the resonator 2. As a result, in the flow before entering the resonator

2 a fuel mixture is formed, some of which JQ is carried into the cavity of resonator 2, and the rest is collected in chamber 4.

The fuel mixture inside the resonator 2 comes in contact with 15 heated gas and this causes it to ignite. The flame from the resonator 2 is transferred to the fuel mixture in chamber 4 and flows out through the opening 5 in the form of a torch. 20

The supercritical pressure drop across the nozzle 1 makes the flow rate of the gaseous component independent of the flow rate of the fluid through the nozzle 3. Due to this, a steady burn is ensured.

Example. The elements of the device have the following parameters: nozzle 1 is made in a housing with an angle of 60, passing into a cylindrical channel 30 with a diameter of 3.8 mm and a length of 25 tn-il opposite to the nozzle and coaxially with it placed the resonator 2, performed in the form of a hollow cone with a diameter 6 mm and 4 inlets that go into a deaf 35 cylindrical cavity with a diameter of 2.5 mm and a depth of 20 mm and resonator 2 are embedded in chamber 4 so that the gap between the nozzle section and the entrance to the resonator is inside the chamber / 40

4 and is 9 mm; In the chamber 4, HMeeT-, with an opening 5 with a diameter of 9 mm for the discharge of gases and a centro nozzle installed in the area between the nozzle section and the entrance to the resonator.

During testing, gaseous oxygen under pressure of 8-1 o Pa and at normal temperature is passed through the accelerating nozzle for 3 s, after which kerosene is turned on under pressure of 4-10 Pa. When kerosene is turned on almost instantaneously, a flare begins to flow through the opening in the chamber. . A change in the flow rates of both kerosene and oxygen in a wide range of supply pressures (oxygen from 5 V10 to 10 Ilaj for kerosene from 3 to 10 Pa) does not cause pulsations and flame breaks. Multiple switching on the device according to the proposed method is always accompanied by the instantaneous appearance of a stable torch.

Claims (1)

Invention Formula The method of igniting the fuel mixture by accelerating the flow of the gaseous component of the mixture to supersonic speed in the nozzle, braking it in the resonator with the excitation of shock waves and heating, followed by feeding the second component through the nozzle, igniting the mixture and diverting it through the Exhaust nozzle, so that In order to increase the reliability of the ignition, the second component is introduced into the flow zone of the gaseous component between the nozzle and the resonator in the form of a jet, perpendicular to the flux. nozzle in the area between the nozzle section and the entrance to the resonator. During testing, gaseous oxygen under pressure of 8-1 o Pa and at normal temperature is passed through the accelerating nozzle for 3 s, after which kerosene is turned on under pressure of 4-10 Pa. When kerosene is turned on almost instantaneously, a flare begins to flow through the opening in the chamber. . A change in the flow rates of both kerosene and oxygen in a wide range of supply pressures (oxygen from 5 V10 to 10 Ilaj for kerosene from 3 to 10 Pa) does not cause pulsations and flame breaks. Multiple switching on the device according to the proposed method is always accompanied by the instantaneous appearance of a stable torch. Invention Formula The method of igniting the fuel mixture by accelerating the flow of the gaseous component of the mixture to supersonic speed in the nozzle, braking it in the resonator with the excitation of shock waves and heating, followed by feeding the second component through the nozzle, igniting the mixture and diverting it through the Exhaust nozzle, so that In order to increase the reliability of ignition, the second component is introduced into the flow zone of the gaseous component between the nozzle and the resonator in the form of a jet perpendicular to the mentioned flow. FZ / (M