JPH0370108B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention operates as a near-ground engine and a high-altitude engine, and has a main combustion chamber and a pre-combustion chamber provided with a propulsion nozzle. This gas subsequently flows into the main combustion chamber, which is operated with more oxygen when operating near the ground and with slightly more hydrogen when operating at altitude. The present invention relates to a method of operating a bypass rocket engine using liquid oxygen and liquid hydrogen, and a bypass rocket engine for carrying out this method.

According to the theory of motion of the drive reaction engines of carrier aircraft for carrying practical payloads into space, it is necessary to Operation requires the use of dense fuel pairs, such as oxygen and kerosene, and at very high altitudes requires 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. , and the advantage of the large specific impulse brought by hydrogen can be utilized without any inconvenience.

In order to enable rocket engines to be used as near-ground and high-altitude engines, for example, the ATAA/
SAE 14 TH−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 3 of ``Conference''.
This rocket engine is equipped with a propulsion nozzle.
It has two main combustion chambers and three pre-combustion chambers, two of which generate an oxygen-rich propellant.
The other generates a hydrogen-rich propellant.
The rocket engine operates in the near-ground region by directing propellants from all three precombustion chambers into an oxygen-enriched 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 reduced. At great heights or in a vacuum, the rocket engine operates with slightly more hydrogen, ie, at optimum thrust, by shutting off the pre-combustion chamber, which operates in oxygen-enriched conditions.

The known rocket engines for both operating phases have a high cost in terms of structural quality and quantity;
This results in high costs and a relatively high starting weight.

The object of the invention is to provide an initial design which is conceptually simpler and thus cheaper to manufacture and lighter than known comparable engine arrangements, while eliminating its disadvantages and retaining the aforementioned advantages. An object of the present invention is to provide a method of operating a bypass type rocket engine of the type described in 1. and an engine for carrying out this method.

This problem operates as a near-ground engine and a high-altitude engine, and has a main combustion chamber with a propulsion nozzle and a pre-combustion chamber, and contains a large amount of oxygen, which is generated in the gas pre-combustion chamber. It then flows into the main combustion chamber, which is operated with more oxygen when operating near the ground, and with slightly more hydrogen when operating at altitude. In the operating method of a bypass rocket engine powered by liquid hydrogen, the same amount of liquid oxygen and liquid hydrogen are supplied directly to the main combustion chamber during near-ground operation and at very high altitudes, respectively. During operation, the mass ratio of oxygen to hydrogen is about 6:1, and only when operating near the ground, there is additional oxygen-rich gas generated in the precombustion chamber, with a mass ratio of oxygen to hydrogen of about 20:1. is supplied to the main combustion chamber 1 so that when operating near the ground the main combustion chamber operates with an oxygen to hydrogen mass ratio of approximately 13:1, and when operating at very high altitudes the pre-combustion chamber is The problem is solved by blocking the problem.

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 bypass rocket engines, in which oxygen is transported from the vessel via pressure lines through the propulsion nozzle and its walls and through the walls of the main combustion chamber to its injection head, the oxygen bypass line leading to the pre-combustion chamber is connected to the injection head of the main combustion chamber. a hydrogen bypass line leading to the precombustion chamber branches off from the hydrogen pressure line extending to the propulsion nozzle wall, and a shutoff valve is provided in each of these bypass lines; It is proposed that both shutoff valves be open when operating near the ground and closed when operating at very high altitudes.

The method according to the invention and the apparatus used to carry out the method allow conventional bypass rocket engines to be operated 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 oxygen to hydrogen mass ratio of 6:1 allows the cooling system and the injection system of the main combustion chamber to 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 be able to operate the injection head in the same structural injection conditions during the near-ground and high-altitude operating phases, an embodiment of the invention provides that the injection head is It is equipped with a special blowing device to transport the gases generated in the pre-combustion chamber into the main combustion chamber. According to another embodiment of the invention, this blowing device is arranged centrally in the injection head.

The figure shows an embodiment according to the invention.

The illustrated bypass rocket engine essentially consists of a main combustion chamber 1 with a forward injection head 2 and a rearward propulsion nozzle 3, a precombustion chamber 4, an oxygen pump 5, a hydrogen pump 6, and a pump drive turbine 7. , oxygen storage container 8, hydrogen storage container 9, bypass propulsion nozzle 10, oxygen supply line 11, hydrogen supply line 12, oxygen pressure line 13, hydrogen pressure line 14,
Gas pipe 1 from pre-combustion chamber 4 to injection head 2
5, equipped with a cutoff valve 17 and an oxygen branch pipe 16 communicating with the precombustion chamber 4, equipped with a cutoff valve 19 and connected 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 a turbine exhaust gas line 21 extending to the bypass nozzle 10 .

In particular, as shown in FIGS. 2 and 4, the injection head 2
is the oxygen-rich gas GV generated in the pre-combustion chamber 4.
a central blowing device 22 for the oxygen distribution chamber 2
3 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 24. Hydrogen HH is hydrogen distribution chamber 2
5 and is injected into the main combustion chamber 1 through a number of injection holes 26.

The bypass type rocket engine according to the present invention operates as follows.

As can be seen from Figures 1 and 2, when starting or operating near the ground, the pre-combustion chamber 4
is also in operation. That is, both cutoff valves 17 and 19
is open, so a large amount of oxygen OV and hydrogen HV
pass through the bypass lines 16, 18 to the precombustion chamber 4, where they react with each other. The oxygen-rich gas GV generated in this way flows into the main combustion chamber 1 through the blowing device 22 . Furthermore, oxygen OH is directly supplied to the main combustion chamber 1 via a pressure line 13, a distribution chamber 23 and an injection nozzle 24, and hydrogen
HH is the pressure pipe 14, the distribution chamber 25 and the injection nozzle 2
6 and flows into the main combustion chamber 1.

The pressure line 14 flows into an annular channel 27 in the area of the diverging propulsion nozzle. A portion of the hydrogen HHh flows rearward from this annular passage, cooling the rear propulsion nozzle wall section and cooling the rear annular passage 28.
are collected in. A propellant pipe line 20 is connected to this rear annular passage. Other parts 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 the bypass rocket engine to high-altitude operation is effected by blocking both lines 16, 18 using valves 17, 19. This operating phase is shown in FIGS. 3 and 4. In this case, the pre-combustion chamber 4
is not working.

[Brief explanation of drawings]

Figure 1 shows the operating condition of a bypass type rocket engine near the ground, Figure 2 shows the operating condition of the injection head near the ground, and Figure 3 shows the operating condition of a bypass type rocket engine at high altitude. FIG. 4 is an enlarged view showing the injection head operating at high altitude. 1... Main combustion chamber, 2... Injection head, 4... Pre-combustion chamber, 13... Oxygen pressure line, 14... Hydrogen pressure line, 16... Oxygen bypass line, 17, 19
...Shutoff valve, 18...Hydrogen bypass pipe, 22...
Blow equipment, GV...Gas, HH, HV...Hydrogen,
OH, OV...Oxygen.

Claims (1)

[Claims] 1. An engine that 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, and gas containing a large amount of oxygen is generated in the pre-combustion chamber. , this gas then flows into the main combustion chamber, which is operated with more oxygen when operating near the ground and with slightly more hydrogen when operating at altitude. , a method of operating a bypass rocket engine powered by liquid oxygen and liquid hydrogen, in which the same amount of liquid oxygen OH is used when operating near the ground and when operating at very high altitudes.
and liquid hydrogen HH are supplied directly to the main combustion chamber 1, with a mass ratio of oxygen OH to hydrogen HH of approximately 6:1, and only when operating near the ground.
The oxygen-enriched gas GV generated in the precombustion chamber 4 with a mass ratio of oxygen OV to hydrogen HV of approximately 20:1 is additionally supplied to the main combustion chamber 1, thereby making it possible to operate near the ground. The main combustion chamber 1 contains approximately 13:1 oxygen
This operating method operates with a mass ratio of OH + OV and hydrogen HH + HV, and is characterized in that the pre-combustion chamber 4 is shut off when operating at very high places. 2 It operates as a near-ground engine and a high-altitude engine, and has a main combustion chamber with a propulsion nozzle and a pre-combustion chamber, in which gas containing a large amount of oxygen is generated, and this gas is subsequently Liquid oxygen and liquid hydrogen flow into the main combustion chamber, which is operated with more oxygen when operating near the ground and with slightly more hydrogen when operating at altitude. In this method, the same amount of liquid oxygen OH and liquid hydrogen HH are directly supplied to the main combustion chamber 1 during operation near the ground and at very high altitudes. , at which time the mass ratio of oxygen OH and hydrogen HH is approximately 6:
1, and only during operation close to the ground, the oxygen-rich gas GV generated in the precombustion chamber 4 with a mass ratio of oxygen OV to hydrogen HV of approximately 20:1 is additionally transferred to the main combustion chamber 1. is supplied to the main combustion chamber 1 during near-ground operation so that the main combustion chamber 1 has an oxygen
It is a bypass type rocket engine that operates with a mass ratio of OV and hydrogen HH + HV, and is equipped with an oxygen pump and a hydrogen pump, for implementing an operation method in which the pre-combustion chamber 4 is shut off when operating at a very high place. This oxygen pump conveys oxygen from the storage vessel via pressure lines directly to the injection head of the main combustion chamber, and the hydrogen pump conveys oxygen from the storage vessel via pressure lines to the propulsion nozzle and its walls and into the walls of the main combustion chamber. In a bypass type rocket engine, an oxygen bypass line 16 leading to the precombustion chamber 4 branches off from an oxygen pressure line 13 leading to the injection head 2 of the main combustion chamber 1, A hydrogen bypass line 18 leading to the propulsion nozzle wall branches off from the hydrogen pressure line 14 leading to both bypass lines 1.
One shutoff valve (17 or 19) is provided in each of 6 and 18, and both shutoff valves are opened when operating near the ground and closed when operating at very high places. A bypass type rocket engine featuring: 3. The patent claim is characterized in that the injection head 2 is equipped with a special blowing device 22 in order to carry the gas GV generated in the precombustion chamber 4 into the main combustion chamber 1 during operation near the ground. A bypass type rocket engine according to scope 2. 4. Bypass rocket according to claim 3, characterized in that a special blowing device 22 for the gas GV generated in the precombustion chamber 4 is centrally provided in the injection head 2. engine.