RU2205289C2 - Injector assembly of liquid-propellant rocket engine - Google Patents

Abstract

FIELD: rocket engines. SUBSTANCE: injector assembly of liquid-propellant rocket engine contains oxidizer unit, propellant unit, coaxial spray injectors installed in said units in concentric rows and containing hollow tip and bushing enclosing the tip with ring clearance and communicating space of units with space of combustion chamber. Space of tip of each even injector in each even row following peripheral row following peripheral row are placed in communication with space of propellant unit. Ring clearance between tip and bushing communicates with space of oxidizer unit. Spaces of tips of the rest of injectors communicate with space of oxidizer unit. Ring clearance between tip and bushing is placed in communication with space of propellant unit. EFFECT: provision of injector assembly with improved quality of mixing in combustion chamber of rocket engine. 2 cl, 5 dwg

Description

 The invention relates to the field of rocket technology and can be used to create liquid rocket engines.

 Currently, one of the main problems in creating liquid-propellant rocket engines is to obtain a high specific thrust impulse, which mainly depends on the quality of mixture formation in the combustion chamber.

 A condition for improving the quality of mixture formation in the LRE combustion chamber is to create an optimal mixture of fuel components using nozzles that meet the following requirements: uniform flow rate and concentration of fuel components across the combustion chamber; high quality (fineness) of spraying the liquid component of the fuel.

 These characteristics of the combustible mixture are provided by the adopted scheme for mixing fuel components, implemented in the design of the nozzles, and the optimal location of the nozzles on the mixing head of the combustion chamber.

 A known LPRE mixing head containing an oxidizer block, a fuel block, coaxial jet nozzles installed in the indicated blocks in concentric rows and containing a hollow tip and a sleeve covering the tip with an annular gap and communicating cavity of the blocks with the cavity of the combustion chamber (Gakhun G. G. et al. Design and engineering of liquid-propellant rocket engines, Moscow, Mechanical Engineering, 1989, pp. 131, 135, 136, Fig. 7.13 - prototype).

 This design ensures that a combustible mixture with high characteristics is obtained in the combustion chamber due to the coaxial-jet scheme for mixing fuel components sold by nozzles with a central oxidizer cavity and the uniform distribution of these nozzles along the cross section of the mixing head.

 However, in the zones of the combustion chamber, between the jets of gaseous fuel, the concentration of the fuel components is different from the optimal one due to the impossibility of receiving there a part of the oxidizer from the central jet of the nozzle. This feature of the specified mixing head reduces the uniformity of the concentration of fuel components along the cross section of the chamber and leads to a decrease in the specific impulse of thrust.

 The objective of the invention is to remedy these shortcomings of the mixing head and to provide improved quality of mixture formation in the combustion chamber of the rocket engine.

 This task is achieved by the fact that in the mixing head of the rocket engine containing an oxidizer block, a fuel block, coaxial-jet nozzles installed in the indicated blocks in concentric rows and containing a hollow tip and a sleeve covering the tip with an annular gap and communicating the cavity of the blocks with a cavity the combustion chamber, according to the invention, the tip cavity of each even nozzle in each even row following the peripheral one is in communication with the cavity of the fuel block, the annular gap between the tip and the sleeve is with the cavity oxidizer block, while the cavity of the tips of the remaining nozzles are in communication with the cavity of the oxidizer block, and the annular gap between the tip and the sleeve with the cavity of the fuel block.

 To intensify the process of mixing the fuel components inside each of the nozzle tips with a cavity in communication with the cavity of the fuel block, a central body with a shaped outlet part is installed with a gap.

 The proposed technical solution will improve the quality of mixture formation in the combustion chamber and increase the specific thrust impulse of the rocket engine due to the use of two types of nozzles in the mixing head design and the organization of mixing of fuel components both between components of the same nozzle and between components of adjacent nozzles of different types.

 The design of the mixing head of the rocket engine is shown in the drawings, where in FIG. 1 shows the mixing head of the rocket engine; in FIG. 2 is a diagram showing the arrangement of nozzles with a central fuel cavity and nozzles with a central oxidizer cavity in the cross section of the mixing head; in FIG. 3 - nozzle design with a central fuel cavity; figure 4 - design of the nozzle with a Central cavity of the oxidizer; in FIG. 5 - nozzle design with a central fuel cavity with a central body installed inside the tip.

The main elements of the mixing head are:
1 - block oxidizer;
2 - case;
3 - middle bottom;
4 - the outer bottom;
5 - pipe supply oxidizer;
6 - fuel block;
7 - the inner bottom;
8 - collector;
9 - fuel supply pipe;
10 - nozzle with a central cavity of fuel;
11 - nozzle with a Central cavity of the oxidizing agent;
12 - tip with a cavity in communication with the cavity of the fuel block;
13 - pylons;
14 - sleeve with axial channels;
15 - tip with a cavity in communication with the cavity of the oxidizer block;
16 - jet section;
17 - sleeve with radial channels;
18 - the central body.

 The mixing head is a structure containing an oxidizer block 1, formed by a housing 2, an average bottom 3, an outer bottom 4 with an oxidizer supply pipe 5 connected thereto, a fuel block 6 formed by a housing 2, an average bottom 3, an inner bottom 7, communicating through openings with a manifold 8 and a fuel supply pipe 9. Inside the fuel block 6, coaxial-jet nozzles 10, 11 are mounted along concentric circles with a uniform pitch, fixed on average 3 and 7 inner bottoms. Each even nozzle 10 in each even row following the peripheral one contains a tip 12 with a cavity communicated through the holes of the pylons 13 with a cavity of the fuel block 6, and a sleeve 14 covering the tip with a gap communicated through axial channels with the cavity of the oxidizer block 1. The rest the nozzles 11 contain a tip 15 with a cavity communicated through the nozzle section 16, with a cavity of the oxidizer block 1, and a sleeve 17 covering the tip with a gap communicated through radial channels with the cavity of the fuel block 6. Inside the tips 12 could s is set with a clearance from the central body 18 shaped output part.

 The proposed mixing head operates as follows.

 Liquid oxygen through the supply pipe 5 is fed into the cavity of the oxidizer block 1, in which it is evenly distributed among the nozzles 10, 11. In the annular gap formed by the tip 12 and the sleeve 14 of the nozzles 10, oxygen enters through the axial channels of the sleeve 14 to bypass the pylons. In the cavity of the tip 15 of the nozzles 11, oxygen enters through the nozzle section 16.

 Hydrogen gas through the fuel supply pipe 9 is supplied to the manifold 8, from which it is evenly distributed through the holes in the cavity of the fuel block 6 through the nozzles 10, 11. Hydrogen enters the cavity of the tip 12 of the nozzles 10 through the channels of the pylons 13. In the annular gap formed by the tip 15 and the sleeve 17 of the nozzles 11, hydrogen enters through the radial channels of the bushings 17.

 The central body 18 installed inside the tip 12 directs hydrogen at an angle defined by the profiled outlet to the spray of liquid oxygen, which improves the quality of the spray of liquid oxygen due to the direct mechanical action of a gas jet on it and allows achieving the quality of mixture formation on a coaxial jet nozzle with a central the fuel cavity is no worse than on a coaxial-jet nozzle with a central oxidizer cavity. During the operation of the mixing head, a part of the oxidizer from the external spray nozzle 10 enters the chamber region, limited by the jets of gaseous fuel nozzles 11.

 Using the proposed invention will allow to intensify the mixing of fuel components, to align their concentration along the section of the chamber, which will increase the specific thrust of the rocket engine.

Claims (2)

 1. The mixing head of the rocket engine containing an oxidizer block, a fuel block, coaxial jet nozzles installed in the indicated blocks in concentric rows and containing a hollow tip and a sleeve covering the tip with an annular gap and communicating cavity of the blocks with a combustion chamber cavity, characterized in that that the cavity of the tip of each even nozzle in each even row following the peripheral one is in communication with the cavity of the fuel block, the annular gap between the tip and the sleeve is with the cavity of the oxidizer block, while nechnikov remaining nozzles communicated with the cavity of the oxidizer unit, and the annular gap between the tip and the sleeve - with fuel cavity block.  2. The mixing head according to claim 1, characterized in that a central body with a profiled outlet is installed inside each of the nozzle tips, the cavity of which is connected to the cavity of the fuel block.

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