Two-component gas-fluid atomiser

FIELD: machine building.

SUBSTANCE: atomiser of, primarily, liquid-propellant rocket engine comprises casing with fuel feed adapter. Note here that the latter is arranged inside said case at pylons while its channel is connected with fuel chamber via bores made in said pylons. In includes the sleeve arranged with ring clearance at said case to make circular gaseous oxidiser channel connected with oxidiser chamber via channels in the casing between its wall and fuel feed pylons. Adapter channel is closed at its inlet while its inner chamber communicates with ring gap between adapter and said sleeve via radial bores made at outlet. Note here that sleeve outlet has stepped expansion with its chamber connected with fuel chamber via tangential channels made in sleeve wall. In compliance with one version, sleeve outlet expansion accommodated hollow cylinder making an extension of sleeve inner channel to make ring gap with ring expansion outlet cylindrical surface. Chamber of said dap communicates via tangential bores with fuel chamber. Axial bore is made at adapter end. Stepped expansion is made at adapter outlet. Note here that bores equally spaced in circle and at angle to adapter axis are made at adapter end. Stepped expansion is made at adapter outlet. Note here that bores equally spaced in circle and at angle to adapter axis are made at adapter end located in the plane of sleeve tangential bores.

EFFECT: higher completeness combustion and better mix formation.

5 cl, 11 dwg

 

The invention relates to a device for mixing and atomization of the fuel components of liquid rocket engine.

One of the main problems arising in the creation of devices that are designed for mixing and atomization of the fuel components is to provide the highest possible completeness of combustion of the fuel components.

Known coaxial coaxial-jet nozzle containing the tip in the form of a hollow cylinder, which connects the cavity of the liquid oxidizer to the combustion zone of the cavity of the combustion chamber, the sleeve covering a gap tip and connecting the cavity of the gaseous fuel with the combustion zone (V.E. Almasov and other "Theory of rocket engines": a Textbook for students of engineering specialties. M., engineering, 1980, RES, str-226).

In this nozzle the oxidizer is fed into the combustion zone through the axial channel within the handpiece, and fuel - annular space between the sleeve and tip. At the exit of the nozzle jet of oxidizer has the shape of a solid cone, facing the top to the tip of the nozzle and jet fuel - the form of a hollow cone. The contact of the fuel and oxidizer occurs on the surface of a solid cone. Such filing does not provide quality spray propellants, which leads to the decrease in the completeness of combustion is fuel and accordingly, the loss of specific impulse.

Known coaxial coaxial-jet nozzle, containing a hollow tip, which connects the cavity of one component of the fuel with the combustion zone, the sleeve covering the annular gap tip and connecting the cavity of another component of the fuel with the combustion zone, in the output part of the tip is made of radially spaced grooves. The output section of the inner surface of the sleeve is made equidistant outer surface of the grooves of the tip, while the cross-sectional area at the outlet between the equidistant surface of the sleeve and the grooves of the tip is F=(0,6-2,2)·Fo, where Fo is the cross-sectional area of the slots on the output tip (Patent RF №2161719, IPC: F02K 9/52, F23D 11/12).

The main disadvantage of this nozzle is that the flame front approaches the fire plate, which leads to increased heat flow in firing the bottom and a wall portion of the fire wall of the combustion chamber.

Known fuel injector combustion chamber of a liquid rocket engine, containing a tubular housing, and is fixed coaxially inside the dead of the tube. The pylon is made not less than one inlet. The channel of the hollow tube is formed from the outlet side of her hollow axial channel, and from the entrance - the entrance hole in the pylon. The main axial channel of trubka the th body on the output side can be performed with step extension in which are tangentially directed relative to the axis of the nozzle through holes. Inside the tubular body, in place of the stepped extension coaxially between the tubular body and a hollow tube may be made pipe. Between the nozzle and the tubular body can be formed annular end pocket, open side directed toward the exit from the housing (Patent RF №2232916, IPC: F02K 9/52 - prototype).

As the oxidant in this nozzle is used oxidizing gas with excess oxygen, and as fuel is liquid hydrogen or kerosene.

This fuel injector operates as follows. The oxidizing agent from the cavity of the oxidizer is fed to the main axial channel of the tubular body. Fuel coming from the fuel cavity in the fuel injector, is divided into two parts. Part of the fuel through the inlet holes made in the pylons, arrives in the dead of the tube, and the remaining part is fed through the tangential holes, executed in place of step expansion of the tubular body.

The result from the nozzle components fall into the fire space of the combustion chamber in the form of a three-layer stream, which is part of the fuel, it covers an annular jet of oxidizer, and it, in turn, covers the stream of remaining fuel.

The main disadvantage of this fuel injectors that spray fuel flowing into the combustion chamber of the hollow tube has a long undecayed part of the jet and a great value characteristic transverse size.

The invention aims to remedy these disadvantages and improve the completeness of combustion of the fuel components by improving the quality of mixing.

The solution of the stated problem is achieved by the fact that the proposed gas-liquid two-component nozzle, mainly for chamber liquid propellant rocket engine, according to the invention, includes a housing with a tip for fuel, while the tip of the nozzle is installed inside the pylons, and its channel connected to the cavity of the fuel through the holes made in the pylons, a sleeve mounted annular gap on the housing and forming an annular channel for feeding gaseous oxidant which is connected with the cavity of the oxidant through channels made in the housing between its wall and the pylons for fuel, while the channel of the handpiece is made closed with side of the input part and the internal cavity is connected with the annular gap between the tip and sleeve through the openings, preferably radial, made in its output side, the output side of vtalk is performed stepwise extension the cavity which is connected with the cavity of the fuel through the tangential channels made in the wall of the sleeve.

In the embodiment, the output expansion sleeve has a hollow cylinder, which is a continuation of the inner channel of the sleeve and forming with the output cylindrical surface of the output expansion of the annular gap, the cavity of which is connected by means of tangential holes made in the wall of the sleeve, with the fuel cavity.

In the embodiment, at the end of the handpiece is made of the axial hole.

In the embodiment, in the output part of the tip is performed stepwise expansion, at the end of the lug holes, spaced evenly around the circumference and at an angle to the axis of the tip.

In the embodiment, in the output part of the tip is performed stepwise expansion, at the end of the tip, located in the plane tangential holes of the sleeve holes, spaced evenly around the circumference and at an angle to the axis of the tip.

The proposed gas-liquid two-component nozzle, mainly for cameras liquid-propellant rocket engine, due to its distinctive features provides a solution to a technical problem - increasing the efficiency of combustion of the fuel components due to the fact that the part g is ruego, arriving in gas-liquid two-component nozzle, is fed by a system of jets in cross flow of gaseous oxidant, which, in turn, leads to improved quality of mixing.

The invention is illustrated by drawings, where figure 1 shows a General view of the nozzle in longitudinal section in the mixing head chamber liquid propellant rocket engine, figure 2 - cross section a-a of the nozzle in figure 3 - a section b-B of the nozzle, figure 4 - cross section In the nozzle, figure 5 - cross section G-G injector figure 6 is a longitudinal section of the nozzle in the embodiment, figure 7 - cross section d-D nozzles in the embodiment, Fig is a longitudinal section of the nozzle in the embodiment, figure 9 is a longitudinal section of the nozzle in the variant performance figure 10 - view of the nozzle in the embodiment, figure 11 is a longitudinal section of the nozzle in a version.

The proposed injector includes a housing 1, a sleeve 2 and the tip 3. Axial channel 4 tip 3 is connected through the holes 5 made in the pylons, with the fuel cavity 6 and four radial holes 7 made on the cylindrical surface of the tip, with the annular channel 8. In the sleeve 2 is made tangential holes 9 connected to the fuel cavity 6. The gaseous oxidant is fed to the nozzle from the cavity oxidizer 10.

In the embodiment, in ugodnom the expansion sleeve 2, installed the hollow cylinder, which is a continuation of the inner channel of the sleeve and forming with the output cylindrical surface of the output expansion of the annular gap 11, the cavity of which is connected through a tangential opening 12 with the fuel cavity.

In the embodiment, at the end of the tip 3 is made of the axial hole 13.

In the embodiment, in the output part of the tip 3 is made stepwise expansion, at the end of the ferrule 3 with holes 14, spaced evenly around the circumference and at an angle to the axis of the handpiece 3.

In the embodiment, in the output part of the handpiece 3, performed stepwise expansion, at the end of the handpiece 3, located in the plane tangential holes 9 of the sleeve 2, the holes 15, spaced evenly around the circumference and at an angle to the axis of the handpiece 3.

The proposed two-component gas-liquid injector operates as follows.

Fuel is divided into two parts. The first portion of fuel through the holes 5 made in the pylons of the housing 1, is fed in the axial channel 4 tip 3 and, further, is distributed between the four radial holes 7. Jet fuel coming out of each hole 7, is embedded in a cross-flow of gaseous oxidant flowing from the cavity oxidizer 10 through the pylons of the housing 1, in calcev the th channel 8 and intensively mixed with it. The second portion of fuel through the tangential openings 9, is fed in a stepwise expansion sleeve 2, which is twisted about its axis and then is injected into the chamber liquid propellant rocket engine.

In the embodiment, the portion of the fuel enters the annular gap 11, performed inside the sleeve 2.

In the embodiment, part of the fuel flowing into the axial channel 4 tip 3, is distributed between the radial holes 7 and the axial hole 13.

In the embodiment, part of the fuel flowing into the axial channel 4 tip 3, is distributed between the holes 14.

In the embodiment, part of the fuel flowing into the axial channel 4 tip 3, is distributed between the holes 15, and the tip end 3 located in the plane tangential holes 9 of the sleeve 2.

The use of the proposed technical solutions will improve the combustion efficiency of fuel components due to the fact that part of the fuel flowing in the gas-liquid two-component nozzle, is fed by a system of jets in cross flow of gaseous oxidant, which, in turn, leads to improved quality of mixing.

1. Two-component gas-liquid injector, mainly for chamber liquid propellant rocket engine, characterized in that it contains, as a minimum, to the STS with the handpiece for supplying fuel when the tip of the nozzle is installed inside the pylons, and its channel connected to the cavity of the fuel through the holes made in the pylons, a sleeve mounted annular gap on the housing and forming an annular channel for feeding gaseous oxidant which is connected with the cavity of the oxidant through channels made in the housing between its wall and the pylons for fuel, while the channel of the handpiece is made private by its input side, and its internal cavity is connected with the annular gap between the tip and sleeve through the openings, preferably radial, made in his output part, in the output part of the sleeves are made stepwise expansion, the cavity of which is connected with the cavity of the fuel through the tangential channels made in the wall of the sleeve.

2. Two-component gas-liquid injector according to claim 1, characterized in that the output of the expansion sleeve has a hollow cylinder, which is a continuation of the inner channel of the sleeve and forming with the output cylindrical surface of the output expansion of the annular gap, the cavity of which is connected by means of tangential holes made in the wall of the sleeve, with the fuel cavity.

3. Two-component gas-liquid injector according to claim 1, characterized in that on the end of nakone the nick completed the axial hole.

4. Two-component gas-liquid injector according to claim 1, characterized in that the output part of the tip is performed stepwise expansion, at the end of the lug holes, spaced evenly around the circumference and at an angle to the axis of the tip.

5. Two-component gas-liquid injector according to claim 4, characterized in that the end face of the tip, located in the plane tangential holes of the sleeve.



 

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EFFECT: provision of maximum possible combustion of propellants of different types reduced number of mixing elements on burner plate.

2 cl, 2 dwg

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