RU2519003C1 - Method of fabrication of liquid-propellant rocket engine combustion chamber nozzle - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises production of outer and inner shells, assembly of shell rings, soldering, making of bypass holes of the cooler in one or several commutator rings and welding of one or several commutators with commutator rings. In compliance with this invention, combustion chamber nozzle is soldered prior to making of bypass holes of the cooler in commutator rings or at making said holes not to the entire commutator ring wall depth. Then, after soldering in commutator rings, cooler bypass holes are made to the entire commutator ring wall depth. Commutators with tips are soldered to the nozzle. Note here that said holes are drilled either mechanically or by EDM process.

EFFECT: higher quality of soldered joint, ruled out clogging of commutator ring bypass holes and cooling circuit grooves.

2 cl, 4 dwg

Description

The invention relates to the field of rocket technology and can be used in the development and manufacture of nozzles of combustion chambers of liquid rocket engines (LRE).

One of the main tasks arising in the creation of modern rocket engines is to ensure high reliability indicators of combustion chambers, including their components, such as nozzles. Known designs of nozzles in which the inner and outer shells are interconnected by soldering along the ribs made on the inner shell. Reliability and operability of nozzles largely depend on the quality of soldering. The quality of soldering largely depends on the size of the gaps between the inner and outer shells during soldering. Ensuring the required quality of soldering is achieved by various methods of manufacturing the nozzle.

A known method of manufacturing a nozzle of a combustion chamber of a liquid propellant rocket engine, according to which the outer and inner shells are made. Solder strips are placed on the inner shell and connected to the outer shell. Soldering the nozzle of the LRE combustion chamber is carried out before welding the collector with a collector ring, which is made with an allowance for "mustache" on the outer diameters of the "mustache". Then, a detachable insert is inserted into the annular cavity of the sub-collector ring, and the lateral radii of the insert must be greater than the lateral internal radii of the sub-collector ring. The liner is closed on top with a technological pad welded to the inlet part of both "whiskers", forming a cavity that is sealed before soldering to ensure crushing of the soldered joint. After soldering, the technological pad and the front part of the “mustache” of the collector ring are cut off, the liner is removed and the collector with nozzles is welded to the nozzle (RF patent No. 2465483 C1, 03/31/2011, prototype).

The main disadvantages of this method of manufacturing a nozzle are:

- when welding the technological patch to the underside of the sub-collector ring due to large residual welding stresses, deformation (shrinkage) of the outer and inner shells in the region of the welds occurs. The specified deformation can lead to an uncontrolled increase in the gaps between the inner and outer shells before soldering and, accordingly, worsen the quality of the soldering;

- when cutting off the technological lining and removing the liners, clogging of the bypass openings of the cooler supply (outlet) in the sub-collector ring and grooves of the cooling path of the inner shell may be clogged;

- due to the impossibility of ensuring full coincidence of the profiles of the liners and the collector ring, the efficiency of bilateral compression of the shells decreases.

The objective of the invention is to remedy these disadvantages, namely:

- elimination of deformations of the outer and inner shells before soldering, ensuring minimum gaps during soldering, due to the exclusion of welds of the welding technological lining;

- elimination of possible clogging of the bypass holes in the sub-collector ring and the grooves of the cooling path of the inner shell when cutting the process lining and removing the liners;

- ensuring bilateral compression of the outer and inner shells along the entire profile of the collector ring due to the exclusion of liners.

The solution to this problem is achieved by the fact that in the known method of manufacturing a nozzle of a rocket engine rocket, including the manufacture of outer and inner shells, assembling the shells, soldering, making cooler bypass holes in one or more sub-collector rings, welding one or more collectors with sub-collector rings, according to the invention soldering of the nozzle of the combustion chamber is carried out until the cooler bypass holes are made in the collector rings or when the cooler bypass holes are made not to the entire wall thickness of the sub-collector rings, then after soldering in the sub-collector rings, cooler bypass holes are made to the entire wall thickness of the sub-collector rings and collectors with tips are welded to the nozzle, and the holes are made by mechanical or EDM.

This eliminates the deformation of the outer and inner shells before soldering, ensuring minimal gaps during soldering, eliminates the possible clogging of the bypass holes in the sub-collector ring and grooves of the cooling tract of the inner shell, provides bilateral compression of the outer and inner shells along the entire profile of the sub-collector ring.

The invention is illustrated by figures. Figure 1 shows the nozzle before soldering without holes, figure 2 - nozzle before soldering with holes not to the depth of the wall, figure 3 - nozzle after soldering and making holes throughout the wall thickness, figure 4 - nozzle after soldering and welding manifold.

The main structural elements of the nozzle are:

1 - outer shell;

2 - inner shell;

3 - sub-collector ring;

4 - cooler bypass holes made in the sub-collector ring;

5 - collector;

6 - tip.

The method is as follows.

The design of the nozzle of a liquid-propellant rocket engine is a package of external and internal equidistant shells with collectors for supplying components. The shells are connected by soldering. At the same time, the sub-collector ring 3 is made with allowances for the outer diameters of the weld points of the collector, and the bypass holes of the cooler are either not performed (Fig. 1), or are not mechanically or electroerosive to the entire wall thickness of the sub-collector ring (Fig. 2). Thus, the inner cavity of the collector ring is sealed before soldering. During soldering, the force P is transferred to the area of the collector ring 4 from two sides, thus providing two-sided compression of the shells during soldering. After soldering in the sub-collector ring, the cooler bypass holes are made over the entire wall thickness of the sub-collector ring (Fig. 3) and the collector 5 with tip 6 is welded to the nozzle (Fig. 4).

The proposed method of manufacturing a nozzle of a combustion chamber LRE improves the quality of the solder joint, and also eliminates the possible clogging of the bypass holes in the collector ring and grooves of the cooling tract.

Claims (2)

1. A method of manufacturing a nozzle of a combustion chamber of a liquid propellant rocket engine, including manufacturing of the outer and inner shells, assembling the shells, soldering, making cooler bypass holes in one or more sub-collector rings, welding one or more collectors with sub-collector rings, characterized in that the soldering of the chamber nozzle combustion is carried out before the bypass holes of the cooler in the collector rings or when the bypass holes of the cooler are not made to the entire wall thickness under collector rings, after soldering in the collector rings, cooler bypass holes are made over the entire wall thickness of the collector rings, and then collectors with tips are welded to the nozzle. 2. A method of manufacturing a nozzle of a combustion chamber of a liquid propellant rocket engine according to claim 1, characterized in that the bypass openings of the cooler in the collector rings are performed by mechanical or electroerosive drilling.

Images