RU2338083C1 - Hybrid rocket engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: proposed hybrid rocket engine incorporates a compartment accommodating liquid fuel component tank and feed system, combustion chamber housing, solid propellant charge, nozzle. At that the working gas regeneration and bleed system to drive the turbo-pump unit (TPU) comprises a bleeder-gas generator mounted on the nozzle bottom and nozzle with its inlet cooled gas duct tightly and rigidly fitted in the combustion chamber housing inserted element and, at the same time, in the bleeder-gas generator manifold. The said bleeder-gas generator liquid fuel component inlet communicates with the liquid component pump outlet branch pipe via a line accommodating an assembly of hydraulic automatic control. Note that the said bleeder-gas generator outlet communicates, via a line, with the turbine inlet manifold that features a gas communication with the auxiliary engines. Note also that the aforesaid turbine outlet manifold represents a cryogenic heat exchanger with its inlet receiving the liquid component via the line accommodating the aforesaid hydraulic automatic control assembly and communicating with the liquid component pump outlet branch pipe, while its outlet is coupled with the gasified component feed duct with a supercharger arranged inside the liquid component tank.

EFFECT: higher efficiency, stability and reliability of hybrid engine turbo-pump unit, use of turbine exhaust gas in gas turbine engine auxiliary devices.

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Description

The invention relates to the field of rocket and space technology, and in particular to hybrid rocket engines (hereinafter referred to as GRD). Search for a reduction in the cost of delivering payloads to the orbit of the artificial Earth satellite (OISS) and vice versa, from the orbit of the satellite to the orbit of the artificial satellite of the Moon (OISL) and vice versa, from the OSSL to the surface of the Moon and back, transport operations to deliver ³ Not from the planet, for example, Uranium is an urgent task for all countries developing launch vehicles and interorbital manned tugs (BCHs). Moreover, the design of the propulsion system involved in such a launch vehicle or BCH should be simple and reliable [1].

Famous family of hybrid rocket engines developed by the American company AMROC [2]. As a prototype, a hybrid rocket engine was selected according to US patent No. 5119627, patented by employees of the aforementioned company on June 9, 1992.

GRD according to patent No. 5119627 includes a compartment with a liquid component tank placed in it, a combustion chamber, a charge of a solid component, automation units partially placed in charge by a gasification cylinder of a liquid component, a nozzle.

The prototype engine works as follows. At first, the valves located on the lines for supplying the liquid component open, and the latter, under the influence of the initial boost pressure, begins to enter the combustion chamber. Next, ignition occurs and the combustion of the charge of the solid component begins. As a result of heat input to the cylinder mounted in the charge of the solid component, the liquid component located in the cylinder is gasified and fed through the line to the upper part of the tank of the liquid component. The gas entering the tank of the liquid component compresses the liquid component and displaces it into the combustion chamber of the main engine, where an intracameral working process is carried out.

This prototype has several disadvantages:

- gasification of the balloon of the liquid component is located in the high-temperature combustion chamber of the engine, wherein the combustion temperature is T _kc ≈3500 K or more,

- destruction of the thermal protection of the cylinder, burnout of the cylinder and the explosion of the entire engine;

- the use in this engine of a displacing system for supplying a liquid component leads to a thickening of the walls and bottoms of the tank of the liquid component and to make the aircraft heavier (in this scheme P _b > P _k , here P _b is the boost pressure in the tank of the liquid component, P _k is the product pressure combustion in the gas-turbine engine chamber; if Р _к ≈30 kgf / cm ² ≈3 MPa, then Р _б ≈ (35 ... 40) kgf / cm ² ≈ (3.5 ... 4) MPa;

- it is very difficult to control and provide a constant boost pressure in the tank of the liquid component;

- the reliability of this design is low.

The aim of the present invention is to increase the efficiency, stability and reliability of a hybrid rocket engine, the use of working gas generated on a turbine in auxiliary devices of the main engine.

This goal is achieved by the fact that the system of selection and generation of working gas for driving a turbine of a turbopump unit (TNA) contains a sampler-gas generator mounted on the nozzle bottom and nozzle, the inlet cooled gas duct of which is hermetically and rigidly fixed in the embedded element of the combustion chamber housing and at the same time in the collector manifold -gas generator, the inlet of the liquid component of the sampler-gas generator is connected to the outlet pipe of the pump of the liquid component by a main line with a hydraulic unit located in it e of this sample-gas generator is connected by a highway to the turbine inlet manifold, while the turbine output manifold, connected by gas connection to auxiliary engines, is made in the form of a cryogenic heat exchanger, to the input of which the liquid component is fed through the mains containing hydraulic power unit connected to the outlet of the liquid component pump and the outlet of this cryogenic heat exchanger is connected to the gas supply duct for the gasified component with a boost device located inside the tank of the liquid component ta.

The invention is illustrated in the drawing, which presents the pneumohydraulic diagram of the inventive hydraulic propulsion.

The inventive GRD contains the following main units and assemblies (see drawing):

a tank with a liquid component (e.g., liquid oxygen) 1; filling and drain valve 2; normally closed pyrovalve 3; check valve 4; device for pressurizing the tank 5; filling and drain valve of the liquid component 6; the line of the liquid component 7; liquid component pump 8; TNA 9 turbine; nozzle head 10; a tank with a flammable composition 11; pyrozapal 12; pressure sensor tube 13; the charge of the solid fuel component (for example, polybutadiene rubber With ₄ H ₆ ) 14; combustion chamber 15; gas generator sampler 16; the line for supplying the liquid component to the sampler-gas generator 17; a line for supplying a "working" gas to the inlet manifold of the turbine 18; pyrostarter 19; cryogenic heat exchanger 20; auxiliary engines 21; shut-off valve of the pump of the liquid component 22; a line for supplying a liquid component to a cryogenic heat exchanger 23; the main valve of the liquid component 24; a line for supplying a gasified liquid component to a boost device 25; embedded element of the combustion chamber 26; hydraulic power units 27; chilled duct 28.

The operation of the claimed engine is as follows.

First, the pyro-starter 19 is activated, which spins the TNA 9 turbine and the pump of the liquid component 8. In the case of repeated switching on, the inventive engine is equipped with several pyro-starters. Next, the main valve 24 and the shut-off valve 22 of the liquid component are actuated, as a result of which, through the nozzle head 10 along the lines 17 and 23, on which the hydraulic units 27 are mounted, the liquid component begins to flow respectively into the combustion chamber 15, the sample gas generator 16 and the cryogenic heat exchanger 20 . After a predetermined time interval (of the order of Δt≈0.1 s), a tank with a flammable composition 11 (for example, propane C ₃ H ₈ ) is triggered and the starting fuel also begins to enter the combustion chamber 15. After that, the pyr He caught 12, the starting fuel sprayed in the combustion chamber ignites, the force of the flame warms up and ignites the charge of the solid fuel component 14. The engine is started. The high-temperature combustion products begin to flow into the sampler-gas generator 16. Interacting with the liquid component coming into the gas generator 16, the combustion products form a “working” gas of the required parameters (usually T _p ≈ 970 K), which begins to flow through the line 18 to the turbine 9 and rotate it; pirostarter 19 is finishing its work by this time. Under the influence of the heat of the “working” gas, which was triggered on the turbine ТНА 9 and then flowing through the cryogenic heat exchanger 20 to the auxiliary engines 21, gasification of the liquid component entering this cryogenic heat exchanger 20 occurs. The resulting gasified component along line 25 enters the device for pressurizing the tank of the liquid component 5 and, in the latter, pressurizes the liquid component.

The stop of the inventive engine is carried out using the main valve of the liquid component 24, which blocks the supply of the liquid component to the pump of the liquid component 8.

In the case of a restart of this engine, all of the above operations are repeated again in the same sequence. In conclusion, we note that the mounting of the sampler-gas generator 16 with the combustion chamber 15 is carried out by means of the embedded element 26 and the gas duct 28.

Used sources

1. Akimov V.N., Eskov Yu.M., Koroteev A.S. and others. On the possibility of energy supply to the Earth from space. Prospects and stages. In: Space rocket engines and power plants. 1993, issue 4 (142). M., NIITP them. Acad. M.V. Keldysh, pp. 69-92.

2. Kniffen R.I., Mckinney B. and Estey. Hibrid Rocket Development at the American Roket Company. AIAA - 90-2762.

Claims (1)

A hybrid rocket engine containing a compartment with a tank and a liquid component supply system in it, a combustion chamber housing, a charge from a solid fuel component, a nozzle, characterized in that the working gas extraction and generation system for driving a turbine pump turbine unit (TNA) is mounted on nozzle bottom and nozzle sampler-gas generator, the input cooled gas duct of which is hermetically and rigidly fixed in the embedded element of the housing of the combustion chamber and simultaneously in the collector of the sampler-gas generator, in One of the liquid components of the sampler-gas generator is connected to the outlet pipe of the pump of the liquid component by a line with a hydraulic unit located in it, the output of this sampler-gas generator is connected by a line to the turbine inlet manifold, while the turbine outlet manifold connected by gas communication with auxiliary engines is made in the form of a cryogenic a heat exchanger, to the input of which the liquid component is supplied through the mains containing the hydraulic power unit, connected to the outlet pipe of the pump of the liquid component a, and the outlet of this cryogenic heat exchanger is connected to the gas supply duct for the gasified component with a boost device located inside the tank of the liquid component.