Drosselweg oxygen-hydrocarbon liquid propellant rocket engine with afterburning gas recovery

 

Drosselweg oxygen-hydrocarbon liquid propellant rocket engine with afterburning reducing gas includes a fuel line, a cooled hydrocarbon fuel chamber operating on oxygen and hydrocarbon fuel with an excess of fuel gas generator and fuel pumps driven by gas turbines. The control system of the engine includes installed in highways oxygen oxidizer the throttle and choke control fuel ratio of the components. In the system control is provided by sagastume on throttle mode, the device creating an additional burden for hydrocarbon fuel pump. Device additional burden for hydrocarbon fuel pump is either hydraulic resistance introduced directly into the supply line of the gas generator fuel, or by-pass line with a hydraulic resistance. The invention will ensure that the performance of liquid rocket engines in a wide range of throttling and will prevent the formation of soot in the gas generator. 1 Il., 1 PL.

The invention relates to a liquid of realities and fuel.

Known LRE, including a line of liquid and gaseous bodies, designed for cooling flow of hydrocarbon fuel chamber with the nozzle head and the supersonic jet nozzle operating on the oxygen and hydrocarbon fuel with an excess of fuel gas generator, the fuel pump is driven by a gas turbine, an exhaust pipe connected to the nozzle head camera system control with traction control and throttle control fuel ratio of components - see Acta Astronautica, Vol.41, Nos 4-10, pp.209-217, published by Elsevier Science Ltd, 1997 - the prototype of the invention.

LRE, made by the scheme with afterburning, are widely used in boosters, which are the output of payloads into space. These rocket engines can operate at high pressure in the chamber (pto) that provides a high degree of conversion of chemical energy used two-component liquid fuel to generate thrust. However, the device prototype has a significant drawback. In fact, by throttling known LRE (that is, when the managed reduction of thrust) within the defined flight conditions booster, along with the decline of paramedic the camera. This fact narrows the range of the rocket engine throttling.

The present invention solves the technical problem of providing health LRE in a wide range of throttling.

The technical problem is solved by the fact that in the LRE, including a line of liquid and gaseous bodies, designed for cooling flow of hydrocarbon fuel chamber with the nozzle head and the supersonic jet nozzle operating on the oxygen and hydrocarbon fuel with an excess of fuel gas generator, the fuel pump is driven by a gas turbine, an exhaust pipe connected to the nozzle head camera system control with traction control and throttle control fuel ratio of the components according to the invention in the system control is provided by sagastume on throttle mode, the device creating an additional burden for hydrocarbon fuel pump.

In some cases, of the invention:

mentioned device is a nonadjustable or adjustable hydraulic resistance introduced directly into the supply line of the fuel gas generator;

- mentioned device includes a bypass was magistrala technical result coinciding with the essence of the problem being solved.

The invention is illustrated with the aid of the drawing, which shows a functional diagram of the LRE, arranged according to the invention. LRE contains creating traction camera 1 with the nozzle head 1A, supersonic jet nozzle 1B and intended for the supply of liquid fuel turbopump Assembly (TNA). It includes single-spaced diagram of a two-stage pump oxygen oxidant (e.g., liquid oxygen) 2 with booster stage 2A, the two-stage pump of hydrocarbon fuels (such as liquefied methane) 3 with booster stage 3A and the gas turbine 4. It is connected at the inlet to the gas generator 5 and the output - through exhaust pipe (gazvoda) 6 - mentioned jet head 1A. This head is connected also with the oxidizer pump through the high-pressure line 7 installed in it a motorized throttle 8. The gas generator 5 is intended to provide a working fluid turbine, carried out by combustion of part of the spent rocket engine, two fuel with an excess of fuel (in the case of methane). Jet head 5A of the gas generator is connected to pump fuel through the high energy of obsen managing pipeline 11 by line 12, which in GG enters the oxidizer from the pump stage 2A. In the specified trunk-mounted motorized regulator 13. The camera has a housing with two walls forming the flow path of the cooling 1C. He communicated through the inlet pipeline 14 with the output of the pump stage 3 and indicated by a discharge line 15 to the input of the pump stage 3A.

As shown in the drawing by the dashed lines, is described in LRE through the supply line YY fuel may be provided instead of the controller 10 of the bypass line 16, normally closed valve 17.

Described LPRE works as follows. Liquefied oxygen enters the pump 2, from which the main part of the liquid (80%) through line 7 is fed to the jet head 1A of the camera 1. The remaining portion of the oxidant enters the secondary pumping stage 2A, from which the line 12 is fed in the nozzle head 5A of the gas generator 5. Liquefied methane is fed into the pump 3. Part of the fuel through the pipeline 14 is pumped into the flow path of the cooling 1C of the camera, and the heated refrigerant is discharged through pipe 15 to the input of charge pump stage 3A. She increases the pressure of the entire mass of fuel to supply his labour produces the reducing gas with temperature Tyyabout 500...1000). He goes to the turbine 4, resulting in the rotation of its rotor, and with it the fuel pumps. The exhaust turbine gas flows through gazivoda 6 jet head 1A of the camera and digiguide in fire space with oxidizer received from highway 7. High temperature combustion products are expanded in the jet nozzle 1B, creating thrust rocket engine.

Control operating mode LRE exercise influence on the bodies 8, 10, 13, 17. In this case, rotation of the throttle valve 8 leads to a change in the flow rate of the oxidizer through the engine, thus achieving necessary (for simultaneous production of fuel from tanks booster) changing ratio of the fuel components. The movement of the needle controller 13 changes the flow rate of the oxidant (maboutin line power BIENNIUM, resulting in the changing ratio of the fuel components in GG (Kyyand, therefore, the temperature of the gas generator. As a consequence, changes the power TNA, and LRE is translated into another thrust. With increasing mothe value of Tyyincreases, and the engine is forced, and with decreasing maboutthe value of Tyyis reduced, and the engine throttled.

When throttling is th body of the regulator 10 is moved to the position 10A to cover the orifice. Made this additional hydraulic resistance (R) creates an additional load on the pump hydrocarbon fuel, which is compensated in order to ensure the necessary flow of fuel through the YEARS (mg) - elevated (compared to the rocket engine prototype) speed TNA (n). The relative flow rate of fuel flowing through the pipeline 14 to the cooling chamber (mg, OHL), also increases (compared to the rocket engine prototype). The selection of the appropriate values ofp and n provide the value of mg, OHLsufficient for reliable cooling of the camera on the throttle mode. The same effect can be achieved and the opening of the valve 17, perepuskajutsja part of the flow of fuel from the pipe 9 to the inlet of the pump stage 3A.

The invention is not limited to the above specific LRE. For example, pumps of oxidizer and fuel can operate from its own gas turbines, the number of impellers in pumps and turbines may be different. Select the unit type (valve, regulator, throttle), providing additional load pump hydrocarbon fuel, is determined by the specific technical requirements of LRE. Specified the highway I can get directly between the outlet of the pump (pumping speed) and another spot on the desktop tract LPRE with a lower pressure (for example, the engine inlet).

We show the effectiveness of our invention on the example of a specific project rocket engine turbopump with a supply of two-component fuel oxygen - methane". This rocket engine rated thrust 2 MN at pto=24 MPa and at work in the booster should grossulariata up to Rto, min= 0,4 ptothat corresponds to the same reduction in thrust. Values of other parameters LRE nominal and minimum modes of traction presented in the table below. For comparison, the last column in italics is given the parameter values at the minimum mode for rocket engine prototype. The table contains, along with mentioned in the text, the parameter Ng- power pump methane fuel.

As can be seen from the table, when the rocket engine throttling up to 40% of the nominal pressure in the chamber, the fuel consumption for the cooling is reduced to 36%, i.e. approximately in the same degree that ensures reliable cooling chamber. In contrast, when the throttling rocket engine prototype camera would be burnt, because the value of mg, OHLwould have fallen to 25%, which is unacceptable under the terms of the cooling design.

So, on a specific project shows that the proposed invention solves t technical result of the invention is confirmed.

In some cases it is possible to obtain a very important additional technical result. It is due to the fact that by throttling the proposed LRE is possible to prevent the decrease of Tyyto dangerous levels, which in the generator gas would be formed soot deposited on the structure elements with subsequent breach of the engine. This danger exists for a liquid propellant rocket engine at two oxygen-hydrocarbon fuels, when (as in our case) the drive turbine is reductive gas generator. The invention resolves that danger.

Claims

Drosselweg oxygen-hydrocarbon liquid propellant rocket engine with afterburning reducing gas, including line of liquid and gaseous bodies, designed for cooling flow of hydrocarbon fuel chamber with the nozzle head and the supersonic jet nozzle operating on the oxygen and hydrocarbon fuel with an excess of fuel gas generator, the fuel pump is driven by a gas turbine, an exhaust pipe connected to the nozzle head camera control system work with regulyatornogo oxidant, characterized in that the system control is provided by sagastume on throttle mode, the device creating additional load for the pump hydrocarbon fuel, which represents either a hydraulic resistance introduced directly into the supply line of the gas generator fuel, or by-pass line with a hydraulic resistance.

 

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