JPS6053650A - Bypass type rocket engine and operation method thereof - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

Detailed Description of the Invention The invention operates as a near-ground engine and a high-altitude engine, and has a main combustion chamber provided with a propulsion nozzle and a pre-combustion chamber, in which oxygen-rich gas is pre-combusted. Occurs in the room,
This gas then flows into the main combustion chamber, which is operated with liquid oxygen with an excess of oxygen when operating near the ground and with a reduced excess of hydrogen when operating at altitude. The present invention relates to a method of operating a bypass type rocket engine powered by liquid hydrogen and a bypass type rocket engine for carrying out this method.

The theory of motion of the reaction engines for the propulsion of carrier aircraft for transporting practical payloads into space suggests that for optimal conditions in flight near the ground and at great heights or in vacuum Nearby operations require the use of dense fuel pairs, such as oxygen and kerosene, while very high altitudes require the use of lower density, higher specific power fuel pairs. The reason for this fuel selection is as follows. In other words, when starting and climbing, it is necessary to supply a large amount of fuel by keeping the fuel tank capacity relatively small.On the other hand, when operating in a vacuum space, there is no air resistance, so tank capacity is not an important issue. This is because the advantages of the large specific impulse brought about by hydrogen can be utilized without any disadvantages.

To enable rocket engines to be used as near-ground engines and high-altitude engines, e.g.
A engineering AA/SAP 14 T from July 25th to 27th, 1978
H-Paper ”Joint Propulsion
It is known to operate such engines with liquid hydrogen and liquid oxygen in both operating phases, as shown in particular on page 6 of 1,000 An, P. Terence.

The rocket engine has one main combustion chamber with a propulsion nozzle and three pre-combustion chambers, two of which produce an oxygen-rich propellant and the other a hydrogen-rich propellant. occurs. The rocket engine operates in the near-ground region by transporting the propellants from all three precombustion chambers into the oxygen-rich main combustion chamber. In this case, the specific impulse is small but the fuel density is large. Therefore, the overall structural volume of the carrier aircraft is smaller. At great heights or in a vacuum, this rocket engine operates in an oxygen-enriched pre-combustion chamber.
: Hydrogen-rich state within a narrow range by blocking,
That is, it operates in an optimal impulse state.

The known rocket engines for both operating phases have a high construction quality and quantity and are therefore expensive and have a relatively high starting weight.

The object of the invention is, at the outset, to provide an engine system which is conceptually simpler and therefore cheaper to produce and lighter than known comparable engine arrangements, which eliminates its drawbacks and retains the aforementioned advantages. The object of the invention is to provide a method of operating a bypass rocket engine of the type described and an engine for carrying out this method.

This problem is solved in the method of operating a bypass rocket engine according to the generic concept of claim 1, in which the same amount of liquid oxygen and liquid hydrogen are generated during operation near the ground and at a very high place. It is supplied directly to the main combustion chamber, with a mass ratio of oxygen to hydrogen of approximately 6 = 1, and only when operating near the ground, the mass ratio of oxygen to hydrogen generated in the pre-combustion chamber is An approximately 20:1 oxygen-enriched gas is additionally supplied to the main combustion chamber so that during near-ground operation the main combustion chamber operates at an oxygen to hydrogen mass ratio of approximately 16:1, resulting in an This is solved by shutting off the pre-combustion chamber when operating at high altitudes.

In order to carry out the method according to the invention, an oxygen pump and a hydrogen pump are provided, the oxygen pump conveying oxygen directly from the storage vessel via a pressure line to the injection head of the main combustion chamber, and the hydrogen pump conveying oxygen directly to the injection head of the main combustion chamber. In a bypass type rocket engine, oxygen is transported from the container via a pressure line through the propulsion nozzle and its walls and through the walls of the main combustion chamber to its injection head, where the oxygen bypass line leading to the pre-combustion chamber is connected to the main combustion chamber. An N-1 gas line branches off from the oxygen pressure line leading to the injection head and leads to the pre-combustion chamber. It is proposed that one shut-off valve is provided in each case, both shut-off valves being open when operating close to the ground and closed when operating at very high altitudes.

The inventive method and the apparatus used to carry out the method allow conventional Nonomous rocket engines to operate as near-ground engines and as high-altitude engines.

In this case, the cooling and injection conditions in the ground phase and the high altitude phase of the original or underlying engine remain unchanged. This is because the same amounts of liquid oxygen and liquid hydrogen are supplied to the main combustion chamber during both operating phases. In this case, the mass ratio of oxygen to hydrogen is approximately 6=1, so that the cooling system of the main combustion chamber and the injection system can be designed optimally over both operating ranges. Furthermore, the extremely large hydrogen cooling capacity ensures sufficient cooling of the propulsion nozzle walls and the combustion chamber walls during near-ground operation. During this near-ground operation, maximum power is generated in the main combustion chamber, increasing the heat release from the propulsion nozzle walls and the combustion chamber walls, even if only half of the hydrogen processed in the main combustion chamber is used for cooling. do.

In order to enable the injection head to operate in the same structural injection conditions during the near-ground and high-altitude operating phases, an inventive embodiment provides that the injection head during the near-ground operation phase It is equipped with a special blowing device to transport the gases generated in the pre-combustion chamber into the main combustion chamber. This blowing device is arranged in the center of the jet head according to another embodiment of the invention.

The figure shows an embodiment according to the invention.

The illustrated bypass rocket engine essentially consists of a main combustion chamber 1 having an injection head 2 at the front and a propulsion nozzle at the rear, a pre-combustion chamber 4, an oxygen pump 5, a hydrogen pump 6, and a pump-driving turbine 7. , oxygen storage container 8, hydrogen storage container 9, bypass propulsion nozzle in, oxygen supply pipe 11,
Hydrogen supply line 12, oxygen pressure line 13, hydrogen pressure line 1
4. Gas pipe 15 leading from the pre-combustion chamber 4 to the injection head 2;
Oxygen branch pipe 1 equipped with a shutoff valve 17 and communicating with the precombustion chamber 4
6. A hydrogen line 1, provided with a shut-off valve 19 and leading to the precombustion chamber 4, a bypass propellant line 20 extending from the end of the propulsion nozzle 3 to the pump drive turbine 7 and to the bypass nozzle 10. Turbine exhaust gas, gas pipe 2
It consists of 1.

In particular, as shown in Fig. 2.4, there are two injection heads and a central blowing device for the oxygen-rich scum G■ generated in the precombustion chamber 4! 22, an oxygen distribution chamber 23, and a hydrogen distribution chamber 25. Oxygen OH reaches the main combustion chamber 1 from the oxygen distribution chamber 23 through a number of injection nozzles Jl/24. Hydrogen H
I( is injected from the hydrogen distribution chamber 25 into the main combustion chamber 1 through a number of injection holes 26.

The inventive bypass rocket engine operates as follows.

When starting and driving close to the ground,
As can be seen from Figure 1.2, the first pre-combustion chamber 4 is also in operation. That is, since both cutoff valves 17 and 19 are open,
Large amounts of oxygen Ov and hydrogen HV pass through bypass line 16.18 into precombustion chamber 4, where they react with each other. The oxygen-enriched gas generated in this way flows through the GV//i injection device 22 into the main combustion chamber 1 . Main combustion chamber 1
Furthermore, oxygen OH is directly supplied via the pressure line 13, distribution chamber 23 and injection nozzle 24, and hydrogen HH is supplied via the pressure line 14, distribution chamber 25 and injection nozzle/I/26 to the main combustion chamber. Flows into chamber 1.

The pressure line 14 is connected to the annular passage 2 in the area of the diverging propulsion nozzle.
It is poured into 7. Part of the hydrogen HHh flows rearward from this annular passage, cooling the rear propulsion nozzle wall portion,
Then, it is collected in the annular passage 28 at the rear. A propellant pipe line 20 is connected to this rear annular passage. The other portion of hydrogen HHv flows through the front region of the wall of the propulsion nozzle 3 and the wall of the combustion chamber 1 and reaches the distribution chamber 25 .

Switching over to high-altitude operation of the bypass rocket engine takes place by blocking both lines 16.18 using valve 17.19. This phase of operation is shown in Figures 3-4. In this case, four pre-combustion chambers will not operate.

[Brief explanation of the drawing]

Figure 1 shows the operating status of the bypass type rocket engine near the ground, Figure 2 shows the operating status of the injection head near the ground, and Figure 3 shows the operating status of the bypass type rocket engine at high altitude. FIG. 4 is an enlarged view showing the ejection head operating at a high altitude. 1... Main combustion chamber 2... Injection head 4... Pre-combustion chamber 16... Oxygen pressure line 14... Hydrogen pressure line 16... Oxygen bypass line 17.19... Shutoff valve 18...Hydrogen bypass pipe 22...Blowing device aV-...Gas HH, HV...Hydrogen OH, OV... Oxygen agent Mitsuyoshi Ezaki Agent Mitsufumi Ezaki

Claims (1)

[Claims] (Li) Operates as an engine for use near the ground or as an engine for use at high altitudes, and has a main combustion chamber equipped with a propulsion nozzle and a pre-combustion chamber, and scum containing a large amount of oxygen is generated in the pre-combustion chamber. This gas subsequently flows into the main combustion chamber, which is operated with an excess of oxygen when operating near the ground and with a reduced excess of hydrogen when operating at altitude. In the operating method of a bypass rocket engine powered by oxygen and liquid hydrogen, the same amount of liquid oxygen (O-Yuu and Liquid Hydrogen The mass ratio of oxygen (OH) to hydrogen is approximately 6 = 1, and the pre-combustion chamber is supplied directly to the pre-combustion chamber. An oxygen-rich gas (0'v) with a mass ratio of oxygen (Ov) to hydrogen η of approximately 20 nia is additionally supplied to the main combustion chamber, thereby allowing the main combustion chamber to be The combustion chamber (1) contains about 7521 oxygen (OH1OV) and hydrogen C
The operating method is characterized in that the engine operates at a mass ratio of HH + HV, and the pre-combustion chamber is shut off when operating at very high altitudes. (2) As an engine for use near the ground or as an engine for use at high altitudes. It operates and has a main combustion chamber with a propulsion nozzle and a pre-combustion chamber, oxygen-rich gas is generated in the pre-combustion chamber, this dregs subsequently flows into the main combustion chamber, and this main combustion chamber This is a method of operating a bypass rocket engine powered by liquid oxygen and liquid hydrogen, which is operated with an excess of oxygen when operating near the ground and with a small excess of hydrogen when operating at high altitude. During operation at high altitudes and at very high altitudes, the same quantities of liquid oxygen and liquid hydrogen are fed directly into the main combustion chamber, with the same amount of oxygen and hydrogen The mass ratio of oxygen (OV) and hydrogen (with a force-to-mass ratio of approximately 20:1) is generated in the pre-combustion chamber only when operating near the ground. Oxygen-rich gas (GV) is additionally supplied to the main combustion chamber (1), so that during close-to-ground operation and hydrogen - (
It is a bypass type rocket engine that operates at a mass ratio of HH to HV and is equipped with an oxygen pump and a hydrogen pump to implement an operation method in which the pre-combustion chamber is shut off when operating at very high altitudes. , this oxygen pump conveys oxygen from the storage vessel via a pressure line directly to the injection head of the main combustion chamber, and the hydrogen pump conveys oxygen from the storage vessel via a pressure line to the propulsion nozzle and its walls and the walls of the main combustion chamber. In a bypass type rocket engine, the oxygen bypass line (16) leading to the pre-combustion chamber (the oxygen pressure line (16) leading to the injection head (2) of the main combustion chamber)
A hydrogen bypass line (18) branches from the pre-combustion chamber (13) and leads to a hydrogen pressure line (18) extending to the propulsion nozzle wall.
4), and one shutoff valve (17f/#-119) is installed in each of these bypass pipes (16, 18), and both of these shutoff valves are opened during operation near the ground. , a Nokui bus-type rocket engine that is characterized by being closed when operating at very high altitudes. (3) In order to carry the gas ([)V) generated in the pre-combustion chamber (4) during operation near the ground into the main combustion chamber (1),
3. Bypass rocket engine according to claim 2, characterized in that the injection head (2) is equipped with a special blowing device (22). (4) characterized in that a special blowing device (22) for the pre-combustion chamber (preliminary gas (11) V generated in the chamber) is provided centrally in the injection head (2); A bypass type rocket engine according to claim 3.