RU2665601C1 - Nozzle of the liquid-propellant engine chamber - Google Patents

Abstract

FIELD: rocket technics.

SUBSTANCE: invention relates to rocket technology, namely to a method for manufacturing a nozzle of a liquid rocket engine chamber. Nozzle of the liquid rocket engine chamber including the inner and outer shells, interconnected by fins forming the cooling channels, a subcollective ring with holes that are connected to the cooling channels, and the collector, according to the invention the nozzle of the chamber is a single integral structure, manufactured by the method of layer-by-layer powder laser sintering of granules. Collector can be made of a non-circular shape, of variable cross-section, and the openings connecting the collector with the cooling path have a section of non-circular shape, are a continuation of the cooling path and are not overlapped by the fins.

EFFECT: invention provides a reduction in labor intensity and rigidity in the manufacture of the nozzle.

4 cl, 5 dwg

Description

The invention relates to rocket technology, and in particular to a method for manufacturing a nozzle of a chamber of a liquid propellant rocket engine (LRE).

One of the main tasks arising in the creation of a liquid propellant rocket engine is to ensure high reliability and strength indicators of the chambers, including their constituent parts, 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 the connection of the inner and outer shells.

A known method of manufacturing a nozzle of a combustion chamber of a liquid propellant rocket engine, including the manufacture of parts of the inner and outer shells from sheet blanks by stamping, welding, double-sided turning of the inner shell, milling grooves, joining the parts of the inner and outer shells into blocks, fitting and soldering, and then from individual blocks by welding receive a nozzle (Gakhun G.G. et al. "Design and Design of Liquid Rocket Engines", M., Mechanical Engineering, 1989, pp. 108-118).

A known method of manufacturing a welded-soldered construction of a large-sized nozzle of a chamber of a liquid propellant rocket engine, consisting of interconnected inner and outer shells with a collector ring and a collector, comprising manufacturing shells from sheet blanks using stamping, assembly, welding, groove milling, soldering. After welding the collector ring with the collector with the outer shell, the nozzles are soldered (RF patent No. 2323363 C1 of 04/27/2008).

Closest to the proposed invention is a method of manufacturing a nozzle of a combustion chamber of a liquid propellant rocket engine (RF patent No. 2465483 C1 of 03/31/2011, prototype), according to which the outer and inner shells are made. Solder is placed on the inner shell and connected to the outer shell. Soldering the nozzle is carried out before welding the collector to the collector ring.

The disadvantage of the above methods of manufacturing a nozzle are:

- high complexity and equipment;

- the need to use stamps;

- Milling grooves on the inner shell;

- making holes in the sub-collector ring;

- the use of soldering and welding when assembling the nozzle.

This invention eliminates these disadvantages of the prototype.

The technical task is solved using the nozzle of the chamber of a liquid propellant rocket engine, including inner and outer shells interconnected by ribs forming cooling channels, a collector ring with holes that connect to the cooling channels and a manifold, according to the invention, the chamber nozzle is a single integral design, made by the method of layer-by-layer powder laser sintering of granules, the collector is non-circular in shape, of variable cross-section, holes are made, soy inyayuschie collector cooling path have any cross-section, are a continuation of the cooling path and does not overlap the edges.

This design allows you to get away from the complex and time-consuming operations associated with the manufacture of the nozzle of the LRE chamber.

The essence of the invention is illustrated by the circuits shown in FIG. 1-5.

In FIG. 1 shows a chamber nozzle made by the method of layer-by-layer powder laser sintering of granules. The nozzle includes an inner shell with ribs 1, an outer shell 2, a sub-collector ring 3 and a collector 4. To complete the collector 4, columns (supports) were introduced into the structure of the inner cavity 5. The whole structure is a single solid-state structure without soldering and welding.

In FIG. 2 shows a sub-collector ring 6 and a non-circular collector 7. An example of a non-circular collector is an egg-shaped collector. To optimize the strength characteristics, the design of the collector has a different thickness in the cross section. This form of collector eliminates support in the internal cavity and reduces hydraulic resistance. With this method of manufacturing a nozzle, the collector can be of any shape.

In FIG. 3 shows a sub-collector ring 8 and a collector 9 made of variable cross section. This example shows the transition from a section of a non-circular collector made in the shape of an "egg" to a round one. This type of collector allows you to optimize the hydraulic resistance and uniformity of the cooler along the channels of the cooling path.

In FIG. 4 and 5 show a non-circular hole 10 connecting the collector to the cooling path. This example shows a rectangular hole with rounding at the edges. Thanks to this method of manufacturing the chamber nozzle, an annular groove on the inner shell was excluded, which allows the cooler to be supplied directly to each channel of the cooling path.

The process is as follows.

At the first stage, a volumetric model of the nozzle is constructed. Then, in the second stage, this volumetric model is converted to an apparatus for laser sintering of granules. And at the third stage, the direct manufacture (baking) of the nozzle of the LRE chamber is performed. The process of manufacturing a chamber nozzle by laser sintering of granules takes several times less time than when manufacturing a nozzle in the traditional way (prototype), and does not require complex technological processes.

Thus, the nozzle of the LRE chamber, made by the method of layer-by-layer powder laser sintering of granules, allows to reduce the complexity and equipment, to exclude the operations of soldering, welding, stamping and milling of grooves and thereby increase the strength characteristics of the structure.

Claims (4)

1. The nozzle of the chamber of a liquid-propellant rocket engine, comprising inner and outer shells interconnected by ribs forming cooling channels, a collector ring with holes that connect to the cooling channels, and a collector, characterized in that the chamber nozzle is a single integral structure made by the method of layered powder laser sintering of granules. 2. The nozzle of the chamber of a liquid propellant rocket engine according to claim 1, characterized in that the collector is non-circular in shape. 3. The nozzle of the chamber of a liquid rocket engine according to claim 2, characterized in that the collector is made of variable cross-section. 4. The nozzle of the chamber of a liquid propellant rocket engine according to claim 1, characterized in that the openings connecting the collector to the cooling path have a non-circular cross section, are a continuation of the cooling path and are not overlapped by fins.

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