RU2728657C1 - Chamber of liquid-propellant rocket engine operating on gas-free generator circuit (embodiments) - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: invention relates to liquid-propellant rocket engines. Liquid-propellant rocket engine chamber operating in gas-free scheme comprises chamber housing, mixing head consisting of peripheral and central parts, outer bottom, fuel and oxidizer supply lines and heat exchanger located in chamber cavity, according to the exposition, cooling channels in heat exchanger are arranged with double-sided arrangement, on external and (or) internal surface of heat exchanger there are heat exchange intensifiers, heat exchanger in at least one plane of section consists of two or more segments, input collector and (or) outlet of heat exchanger fixed on outer bottom and pylons of head housing, are located outside chamber cavity.

EFFECT: invention provides increase in engine thrust.

3 cl, 3 dwg

Description

A liquid-propellant rocket engine operating according to a gas generator scheme has a number of significant advantages over engines operating according to a gas generator scheme.

These benefits include:

- a simpler pneumohydraulic circuit due to the absence of a gas generator;

- reduced engine weight;

- provision of reliable ignition of fuel components under vacuum conditions;

- increased reliability of engine operation due to improved turbine operating conditions (significant reduction of peak loads).

The main disadvantage of an engine with a gas generating scheme is the impossibility of creating engines with high thrust.

All currently in operation or under development engines operating according to a gas-free scheme (RL-10, USA; MV60, Japan - USA; Vinci-EU; RD0146 and RD0146D, Russia; RD0126 Yastreb, Russia) LE - 5A and Hipex - Japan) have a thrust of no more than 15 tf.

The limitation of the magnitude of the thrust is associated with the impossibility of obtaining intensive heating of the entire mass of fuel to a high temperature and the implementation of the required power on the turbine.

On the RD0126 Yastreb engine with a thrust of 4 tf, described in BBK 39.62 UDC629.78 N34 (on pages 64-69) "Development and testing of a unique chamber of the RD0126 Yastreb liquid propellant rocket engine with a 180 ° flow turn in the nozzle" to increase Intensive heating of the fuel, the combustion chamber was located in the cavity of the supersonic nozzle and the turn of the supersonic flow in the nozzle by 180 ° was carried out with the outflow of the sound flow through a narrow annular critical section. The stated design solution allows increasing the heating of the fuel due to the location of the chamber inside the supersonic nozzle and increasing the nozzle surface with a limited chamber length.

But the main disadvantage of this design is the impossibility of reliable cooling of the annular critical section located on a large diameter and having a small width of ~ 1 ÷ 2.5 mm. In addition, during the manufacturing process and firing tests, large uneven power and thermal loads appear, which change the shape of the critical section, which disrupts the normal operation of the engine.

The known design of the chamber is described in the patent RU 2 610 624 C1, in which heat exchange elements are installed in the cavity of the combustion chamber in order to gain additional heat, made in the form of Field tubes, in which the cooling path is connected to the cavities of the mixing head (analogue).

The disadvantage of this design is the impossibility of significant heating of the fuel component due to the insignificant heat exchange surface and, as a consequence, the implementation of the necessary differential on the turbine. The known design of a heat exchange system with a channel plate, described in patent RU 2 575 954. In the described design, the flow plate has two mirrored plates with respect to each other, having a curved shape and which are covered with outer jackets (analogue).

The disadvantage of this structure is: the absence of frequent connections mirror plate to the outer jackets which does not allow to realize the high-pressure paths in the order of 200 ÷ 400 kg / cm ² - lack of frequent connections mirror plate to the outer jackets do not allow to increase by 8-10% of the heat transfer through the the wall to the cooler (which takes place in the finned cooling path), which generally reduces the output energy characteristics of the structure.

Known design of a cylindrical plate heat exchanger, described in patent RU 2 364 812, which is used for heating or cooling liquid or gaseous media (analogue).

The cylindrical plate heat exchanger contains a heat exchange matrix of a set of corrugated plates enclosed in a common cylindrical jacket.

The disadvantage of this design is: impossibility of realizing high pressures, temperatures and flow rates of working bodies;

- the presence of a large hydraulic resistance in the corrugated plate.

The indicated disadvantages do not allow realizing high energy characteristics of the structure.

In the design of the Japanese engine Hipex (taken as a prototype) for additional heat gain in the combustion chamber cavity, a special heat exchanger is installed, made of an inner shell with rectangular milled channels and an outer shell, which are connected by diffusion brazing (V.I. Shlyakhov, S.V. Ovchinnikova. LRE without a generator for interorbital tugs. Review based on the materials of foreign press for 1980-1990 No. 30. Center for scientific and technical information "Poisk" GONTI-8, 1991, pp. 54-56).

This design does not allow the implementation of a thrust of the order of 30 ÷ 35 tf in the chamber, since there is no possibility of significant heat gain due to:

- limited size of the heat exchange surface;

- inoperability of heat transfer at high temperatures due to the presence of a soldered joint.

The listed disadvantages are eliminated, proposed by the invention, which solves the technical problem of more intensive heating of the fuel of a significantly greater mass due to a significantly increased heat exchange surface and a higher temperature, which makes it possible to implement an increased differential on the turbine and thus provide a significant increase in engine thrust.

The problem is solved by the fact that the chamber of a liquid-propellant rocket engine operating according to a gas-free scheme (options), containing a chamber housing, a mixing head consisting of peripheral and central parts, an outer bottom, a fuel and oxidizer supply line and a heat exchanger located in the chamber cavity, according to the statement :

- the cooling channels in the heat exchanger are made with two-sided arrangement, and heat exchange intensifiers are made on the outer and (or) inner surface of the heat exchanger, for example, in the form of ribs or grooves;

- a chamber of a liquid-propellant rocket engine operating according to a gas-free scheme (options), containing a chamber body, a mixing head consisting of peripheral and central parts, an outer bottom, a fuel and oxidizer supply line and a heat exchanger located in the chamber cavity, according to the presentation, a heat exchanger at least in one sectional plane consists of at least two segments, and heat exchange intensifiers are made on the outer and (or) inner surface of the heat exchanger, for example, in the form of ribs or grooves;

- the chamber of a liquid-propellant rocket engine, according to the presentation, the inlet and (or) outlet collector of the heat exchanger fixed on the outer bottom and pylons of the head body is located outside the chamber cavity, and heat exchange intensifiers are made on the outer and (or) inner surface of the heat exchanger, for example, in the form ribs or grooves.

The essence of the invention is illustrated by the diagrams shown in FIG. 1, fig. 2, fig. 3.

The chamber of a liquid-propellant rocket engine operating on a gas-free scheme (Fig. 1) includes:

- the outer bottom 1, the chamber body 2 and the mixing head 3, consisting of the peripheral part 4 and the central part 5, the supply line 7, 8, 9 and the outlet line 10;

- an annular central body 11 with a two-sided arrangement of cooling channels 12 in the cavity of the head 3 and the cavity of the combustion chamber 13, consisting of two parts;

- the line for supplying the coolant 15 to the annular central body and the line 16 for removing the coolant from the central body.

FIG. 2 shows a cross-section of the chamber in the area of the mixing head, where:

- mixing head 3, consisting of a peripheral part 4 with nozzles 17 and a central part 5 with nozzles 18 connected by pylons 6;

- parts of the annular central body 14 with two-sided arrangement of cooling channels 12.

FIG. 3 shows a cross-section of an annular central body located in the cavity of the outer bottom 1, where

- an annular central body 11 with a two-sided arrangement of cooling channels 12 and intensifiers 19.

The chamber of a liquid propellant rocket engine operates as follows.

According to the appropriate commands, fuel is supplied from the underwater lines 7 and 15 to the cooling paths of the chamber body 2 and the annular central body 11. In accordance with the cyclogram of the engine operation from the underwater line 8, the fuel enters the peripheral part 4 of the head with the nozzles 17 along the pylons 6 to the central part of the head 5 with nozzles 18, and from the underwater lines 9 the oxidizer enters the cavities of the outer bottom and then into the peripheral and central parts 4 and 5 of the mixing head 3. On command, the fuel components are ignited and burned in the chamber, and the fuel components are burned in the chamber ...

As a result of the combustion of the fuel components, the increased mass of the fuel in the cooling path of the chamber 2 and in the cooling paths 12 of the annular central body 11 is heated to the calculated value and enters the outlet lines 10 and 16. Subsequently, this increased mass of fuel with increased heat content is fed to the turbine blades. The use of a heat exchanger with cooling channels, made with a two-sided arrangement, and on the outer and (or) inner surface of the heat exchanger, the use of heat exchange intensifiers, for example, in the form of ribs or grooves, reduces the hydraulic resistance of the heat exchanger cooling channels by about four times while maintaining the heat exchange area, increases the efficiency of heat exchange, which additionally increases the power of the turbine of a liquid-propellant rocket engine operating according to a gas-free scheme, and, accordingly, the pressure in the chamber, which increases the specific thrust impulse of the rocket engine.

The use of a heat exchanger consisting of at least two segments in at least one sectional cavity, and heat exchange intensifiers on the outer and (or) inner surface of the heat exchanger, for example, in the form of ribs or grooves, makes it possible to increase the efficiency of heat exchange, which increases the power on the turbine and organizes the crossflow fuel components in the cavities of the mixing head from the peripheral to the central part without the need for additional manifolds for supplying fuel in the central parts of the mixing head, which reduces the weight of the structure.

The use of a heat exchanger fixed on the outer bottom and pylons of the head body, in which the inlet and (or) outlet collectors are located outside the chamber cavity, and heat exchange intensifiers are made on the external and (or) internal surface of the heat exchanger, for example, in the form of ribs or grooves, simplifies the design of the collectors supply and removal of the coolant, makes it possible to organize the parallel distribution of the coolant between the cooling path of the chamber and the heat exchanger, which reduces the total hydraulic resistance, increases the efficiency of heat exchange, which additionally increases the power of the turbine of a liquid-propellant rocket engine operating according to a gas generator scheme, and, accordingly, the pressure in the chamber, which increases the specific thrust impulse of the liquid propellant rocket engine.

The proposed technical solutions make it possible to provide a significant increase in thrust up to 30 ÷ 35 tf of a rocket engine operating according to a gas generator scheme.

Claims (3)

1. A chamber of a liquid-propellant rocket engine operating according to a gas-free scheme containing a chamber body, a mixing head consisting of peripheral and central parts, an outer bottom, a fuel and oxidizer supply line and a heat exchanger located in the chamber cavity, characterized in that the cooling channels in the heat exchanger are made with a two-sided arrangement, and heat exchange intensifiers are made on the outer and (or) inner surface of the heat exchanger, for example, in the form of ribs or grooves. 2. A chamber of a liquid-propellant rocket engine operating according to a gas-free scheme, containing a chamber body, a mixing head consisting of peripheral and central parts, an outer bottom, a fuel and oxidizer supply line and a heat exchanger located in the chamber cavity, characterized in that the heat exchanger in at least one the section plane consists of at least two segments; heat exchange intensifiers are made on the outer and (or) inner surfaces of the heat exchanger, for example, in the form of ribs or grooves. 3. A chamber of a liquid-propellant rocket engine operating according to a gas-free scheme, containing a chamber body, a mixing head consisting of peripheral and central parts, an outer bottom, a fuel and oxidizer supply line and a heat exchanger located in the chamber cavity, characterized in that the input manifold and (or ) the outlet of the heat exchanger, fixed on the outer bottom and pylons of the head body, are located outside the chamber cavity, and heat exchange intensifiers are made on the outer and (or) inner surface of the heat exchanger, for example, in the form of ribs or grooves.

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