RU114343U1 - COMBINED AIR-ROCKET ENGINE WITH PULSE-BURNING DIRECTIONAL CAMERA, FORCAMERA AND AIR START SYSTEM - Google Patents

Abstract

A combined rocket engine with a direct-flow pulsating combustion chamber, a prechamber and an air launch system containing tanks with an oxidizer and fuel, a combustion chamber, a Laval nozzle, oxidizer and fuel valves, an ignition system, a resonance tube installed in the supercritical part of the Laval nozzle, characterized by that a prechamber with an air-oxygen check valve installed at an angle of 90 ° to the combustion chamber axis and connected to the air intake with a throttle valve, a nitrogen cylinder connected by a pipeline of the air start system through a nitrogen start-up valve installed in it and a system check valve are introduced into it air start with an air intake, and the air start system pipeline is connected to the oxidizer tank through the pressurizing pipeline and the oxidizer start valve, an oxidizer supply pipeline is installed in the oxidizer tank, connected through a heat exchanger installed on the resonance pipe through the oxidizer valve, with a return air-acid a native valve of the prechamber, the fuel tank is connected to the prechamber, a pipeline for sampling gaseous combustion products with a check valve and a fuel supply pipeline through a fuel valve with a fuel injector installed in the prechamber, while the pipeline of the air start system after the check valve of the air start system is connected by a boost pipeline to pipeline for sampling gaseous combustion products after the check valve.

Description

The proposed utility model relates to aerospace engineering, can be used on aircraft used both in the national economy and the defense industry, and is intended to improve technology — the economic and expenditure parameters of propulsion systems.

Known pulsating detonation single-chamber rocket engine on liquid fuel components containing tanks with fuel and oxidizer, a combustion chamber with a Laval nozzle, fuel and oxidizer valves located on the combustion chamber, as well as receivers of fuel and oxidizer, a pipeline for the selection of gaseous products of combustion, a check valve, pistons fuel and oxidizer tanks, hot gas cooling heat exchanger, connecting pipe, pressurization pipelines of fuel and oxidizer tanks (utility model patent No. 43315 of 01/10/2005 )..

The disadvantages of a pulsating detonation single-chamber rocket engine on the liquid components of hydrogen and oxygen fuel are:

- the Laval nozzle in the atmosphere operates at an off-design mode;

- the inability to use atmospheric air as an oxidizing agent.

Closest to the proposed technical solution is a pulsating detonation single-chamber rocket engine with a combined exhaust system of combustion products operating on the liquid components of the fuel, hydrogen and oxygen, containing tanks with an oxidizer and fuel, a combustion chamber, a Laval nozzle, oxidizer and fuel valves, an ignition system, heat exchangers fuel and oxidizer systems located on the combustion chamber, as well as fuel and oxidizer receivers, a resonance tube installed in the supercritical part with pla Laval (utility model patent №51118 from 27.01.2006 city).

The disadvantage of this pulsating detonation single-chamber rocket engine is the small life of the intake valves due to the effect of a hot pulsating gas stream on them; the impossibility of using atmospheric air as an oxidizing agent and the clogging of the fuel and reagent supply pipelines.

The purpose of the utility model is to enable the propulsion system to operate both in the atmosphere and beyond.

This goal is achieved by the fact that in a combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air start system, containing tanks with an oxidizer and fuel, a combustion chamber, a Laval nozzle, oxidizer and fuel valves, an ignition system, a resonant pipe installed in the supercritical part of the Laval nozzle, introduced, a prechamber with a non-return air-oxygen valve, installed at an angle of 90 degrees to the axis of the combustion chamber and connected to the air intake with a throttle, ba a bosom with nitrogen, connected by an air-start system pipe, through a nitrogen start-up valve and an air-start system check valve installed in it, with an air intake, and an air-start system pipe is connected to the oxidizer tank via a boost pipe and an oxidizer start-up valve, a feed pipe is installed in the oxidizer tank an oxidizer connected through a heat exchanger mounted on a resonant pipe, an oxidizer valve, with an air-oxygen check valve of the prechamber, and a fuel tank is connected to the prechamber, a combustion gas sampling pipeline, with a non-return valve and a fuel supply pipe through a fuel valve with a fuel nozzle installed in the prechamber, while the air start system pipe after the air start system check valve is connected by a boost pipe to the combustion gas sampling pipe after the check valve.

An analysis of the known technical solutions (analogues) in the studied area and related areas allows us to conclude that there are no signs in them that are similar to significant distinguishing features in the claimed device.

Figure 1 presents a diagram of a combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air-start system.

Combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air start system containing tanks with an oxidizer 1 and a fuel 2, a combustion chamber 3, a Laval nozzle 4, oxidizer valves 5 and fuel 6, an ignition system 7, a resonance pipe 8 installed in the supercritical part of the Laval nozzle 4, a prechamber 9 with a non-return air-oxygen valve 10, mounted at an angle of 90 degrees to the axis of the combustion chamber 3 and connected to the air intake 11 with a throttle valve 12, a nitrogen cylinder 13 connected to the air start system 14 through the nitrogen start-up valve 15 installed therein and the air start system check valve 16, with an air intake 11, and the air start system pipe 14 is connected to the oxidizer tank 1 through the inflation pipe 17 and the oxidizer start-up valve 18, to the oxidizer tank 1, an oxidizer supply pipe 19 is installed, connected through a heat exchanger 20, mounted on a resonant pipe 8, an oxidizer valve 5, with an air-oxygen check valve of the pre-chamber 10. A fuel tank 2 is connected to the pre-chamber 9, the pipe with a sampling valve for gaseous products of combustion 21, with a check valve 22 and a fuel supply pipe 23 through a fuel valve 6 with a fuel nozzle 24 installed in the pre-chamber 9. In this case, the pipeline of the air-start system 14 after the check valve of the air-start system 16 is connected by a boost pipe 25 to the pipeline selection of gaseous products of combustion 21 after the check valve 22.

A combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air launch system works as follows.

In the air mode, when starting into the engine through the nitrogen start-up valve 15 and the check valve of the air-starting system 16, nitrogen from the cylinder with nitrogen 13 is fed through the inflation pipe 25 through the gas sampling line 21 to the fuel tank 2 and creates pressure (boost pressure) on fuel components. Air passes through the air-oxygen check valve 10 and enters the pre-chamber 9. Under the influence of nitrogen pressure, liquid fuel from the fuel tank 2 through the fuel supply pipe 23 enters through the check valve 6 to the nozzle 24 located on the pre-chamber 9. Next, the fuel enters the pre-chamber 9 , where it is mixed with air entering through the air-oxygen check valve 10. The spark plug included in the ignition system 7 ignites the fuel mixture. The nitrogen start valve 15 closes. In the phase of excess of pressure in the combustion chamber 3 over the pressure in the tank 2, part of the outflowing combustion products enters through the sampling line of gaseous products of combustion 21 into the check valve 22 and passes into the tank 2, and creates pressure (boost pressure) on the components of the fuel. The main part of the combustion products flows from the combustion chamber 3 through the resonant pipe 8 and due to the inertia of the gases creates a reduced pressure at the end of the expiration phase. The air-oxygen check valve 10 opens under the influence of atmospheric pressure, and the fuel valve 6 under the influence of fuel pressure, and the process is repeated.

In the rocket operation mode (in airless space), the oxidizer start valve 18 opens smoothly. At the same time, nitrogen flows from the nitrogen tank 13 through the inflation pipe 17 through the oxidizer 18 start valve to the oxidizer tank 1, and the oxidizer tank 1 is forced to pressurize. Oxidizer through the oxidizer supply pipe 19 it enters the heat exchanger 20, is gasified and supplied through the oxidizer valve 5 to the air intake 11 and then through the air-oxygen valve 10 enters the prechamber 9. Simultaneously with the valve PU Single oxidizer 18 with a mechanical actuator closes the throttle valve 12. The atmospheric air is replaced with a gaseous oxidant. As a result, the throttle valve 12 closes and the engine consumes gaseous oxidizer and fuel.

The technical analysis of the proposed combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air launch system compared with the prototype showed that:

- installation of the prechamber at an angle of 90 degrees to the axis of the ramjet chamber of pulsating combustion excluded the effect of the hot gas stream on the air-oxygen valve;

- the new engine design allows the use of atmospheric oxygen as an oxidizing agent in the air mode of operation of the power plant.

Therefore, the proposed technical solution allows to increase the technical and economic parameters of a combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air launch system, as well as to increase its efficiency.

Claims (1)

Combined air-rocket engine with a ramjet pulsating combustion chamber, a prechamber and an air start system, containing tanks with an oxidizer and fuel, a combustion chamber, a Laval nozzle, oxidizer and fuel valves, an ignition system, a resonance tube installed in the supercritical part of the Laval nozzle, characterized in that a prechamber with a non-return air-oxygen valve is inserted into it, mounted at an angle of 90 ° to the axis of the combustion chamber and connected to the air intake with a throttle valve, a nitrogen cylinder, connected to the pipeline of the air-start system through the nitrogen start-up valve installed in it and the check valve of the air-start system with an air intake, and the air-start system pipe is connected to the oxidizer tank through the boost pipe and the oxidizer start-up valve, the oxidizer supply pipe connected to the oxidizer tank is connected through the heat exchanger, mounted on a resonant tube through an oxidizer valve, with a back-up air-oxygen valve of the prechamber, the fuel tank is connected to the prechamber, a pipeline the selection of gaseous products of combustion with a non-return valve and a fuel supply pipe through a fuel valve with a fuel nozzle installed in the prechamber, while the pipeline of the air start system after the non-return valve of the air start system is connected by a charging line to the pipeline for the selection of gaseous products of combustion after the check valve.