JP3564273B2 - Engine test equipment - Google Patents

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to an engine test apparatus having a low-pressure chamber (chamber) used for a combustion test of a rocket engine or the like.
[0002]
[Prior art]
FIG. 4 shows a conventional rocket engine test apparatus. A supersonic diffuser 12 is disposed at an outlet of a chamber (low-pressure chamber) 11 that houses a test rocket engine 30. On the surface of the diffuser 12 is a cooling passage 28. The water storage tank 22 is connected to a cooling passage 28 via a water pump 21 by a water line 23.
[0003]
The hydrogen gas storage 16 is connected to the liquid hydrogen run tank 13 via the valve 9, the pressure regulating valve 2, and the valve 10 in order. The liquid hydrogen run tank 13 is connected to a test rocket engine 30 via a valve 3, a valve 6, and a valve 7 in that order. Further, it branches off from the inlet side of the valve 9 and joins the outlet of the valve 3 through the valve 8, the evaporator 15, the booster pump 14 and the valve 5 in that order.
[0004]
The LN ₂ storage tank 17 is connected to the nozzle type ejector 14 through the pressure pump 19, the evaporator 20, and the nitrogen gas storage 18 in this order.
[0005]
In the figure, reference numeral 29 denotes an oxidizer line.
In the above, during the test of the test rocket engine 30, the nitrogen gas of the predetermined pressure is The gas is supplied to the nozzle type ejector 14 and is ejected as a primary stream. The primary flow flows through the supersonic diffuser 12 to exhaust the gas in the chamber 11 to a predetermined low pressure.
[0006]
The line on the side of the LN ₂ storage tank 17 such as the booster pump 19 is a supply system to the nitrogen gas storage device 18.
[0007]
On the other hand, a predetermined pressure of hydrogen gas is supplied to the liquid hydrogen run tank 13 via the hydrogen gas storage device 16, the pressure regulating valve 2, and the valve 10. Thereby, liquid hydrogen is supplied to the engine 30 as fuel through the valves 3, 6, and 7, and the engine 30 operates.
[0008]
Further, the supersonic diffuser 12 under test is supplied with water to the cooling passage 13 by the water pump 21 and cooled.
[0009]
[Problems to be solved by the invention]
The above prior art has the following problems.
[0010]
(1) The combustion gas of a rocket engine or the like has a large momentum, and generally requires a large mass flow rate for nitrogen and water used for the primary flow of the ejector. For this reason, nitrogen and water supply facilities were separately installed, and the facilities were large.
[0011]
(2) Since the combustion gas of a rocket engine or the like has a high temperature, a large amount of water has been supplied to the diffuser cooling passage to cool the combustion gas. For this reason, a separate water supply facility was installed, and the facility was large.
[0012]
(3) Since the primary flow of the ejector needs to be a gas, a pressurizing vaporizer such as a pressurizing pump and a gas storage device are required for that.
[0013]
An object of the present invention is to solve the above problems.
[0014]
[Means for Solving the Problems]
The present invention takes the following measures to solve the above-mentioned problems.
[0015]
(1) In an engine test apparatus having a chamber for accommodating a test engine and gas exhaust means for depressurizing the chamber, the gas exhaust means is an annular type ejector for ejecting a primary flow from the periphery. A primary flow supply means for supplying a part of the refueling of the test engine as the primary flow is provided.
[0016]
In the above, when the test engine is tested, a part of the refueling of the test engine is supplied as a primary flow to the gas discharge means for decompression by the primary flow supply means. The gas in the chamber is exhausted by the ejector action by the primary flow, and is reduced to a predetermined pressure. In this way, the engine can be tested at low cost with a simple device.
[0017]
(2) In an engine test apparatus having a chamber for accommodating a test engine and gas exhaust means for depressurizing the chamber, a cooling means for cooling the gas exhaust means, and a part of refueling of the test engine. And a cooling supply means for supplying the cooling medium to the cooling means.
[0018]
In the above, at the time of the test of the test engine, the inside of the chamber is set to a predetermined low pressure by the gas discharging means for reducing the pressure. On the other hand, the cooling of the gas discharge means during that time is performed by the cooling means receiving a part of the oil supply of the test engine from the cooling supply means as a coolant. In this way, the engine can be tested at low cost with a simple device.
[0019]
(3) In the above (2), the gas discharging means is an annular type ejector for ejecting a primary flow from the surroundings, and the cooling means is caused to flow the coolant on the peripheral surface of the annular gas discharging means. The cooling material was made an integral type, and the cooling material was used as a primary flow of the gas discharge means.
[0020]
In the above, during the test of the test engine, a part of the refueling of the test rocket engine is sent to the integral and annular gas discharge means by the primary flow and cooling supply means. Then, the refueling flows on the peripheral surface of the gas discharging means as a coolant, and after cooling, is ejected as a primary flow. The gas in the chamber is exhausted and depressurized by the ejector action by the primary flow. In this way, the device becomes very simple and the engine can be tested inexpensively.
[0021]
BEST MODE FOR CARRYING OUT THE INVENTION
(1) A first embodiment of the present invention will be described with reference to FIG. The parts described in the conventional example are assigned the same reference numerals, and the description thereof will be omitted, and the parts related to the present invention will be mainly described.
[0022]
A supersonic diffuser 12 is provided at an outlet of the chamber 11. An annular type ejector having a primary flow nozzle a is provided at a connection portion of the supersonic diffuser 12, and is connected to an outer cooling passage 28 through an outlet manifold 34.
[0023]
Fuel is supplied from the liquid or gaseous fuel supply device 31 to the test rocket engine 30. A liquid or gaseous fuel supply device 31 is connected to the cooling passage 13 via an ejector primary flow supply device (primary flow and cooling supply means) 32 and an inlet manifold 33 in that order.
[0024]
In the above, at the time of testing the rocket engine 30, the ejector primary flow supply device 32 receives a part of the fuel from the liquid or gaseous fuel supply device 31 as a liquid or gas at a predetermined pressure as the inlet manifold 33, the cooling passage 28 (in the case of liquid, In this process, the gas is ejected as a primary flow from the ejection port a of the annular type ejector 35 through the outlet manifold 34 sequentially. Thus, the pressure in the chamber 11 is reduced to a predetermined low pressure. On the other hand, the supersonic diffuser 12 is cooled by the liquid or gas flowing through the cooling passage 28.
[0025]
As described above, since the fuel of the rocket engine 30 having a small molecular weight is used as the primary flow of the ejector 35, the outflow speed at the injection port a is increased, and the mass flow rate is suppressed to a small value. Therefore, the primary flow supply 32 is very simple and inexpensive. Further, cooling equipment such as the water pump 21 is not required as in the related art, and the cost is reduced.
[0026]
(2) A second embodiment of the present invention will be described with reference to FIG. The parts described in the conventional example are assigned the same reference numerals, and the description thereof will be omitted, and the parts related to the present invention will be mainly described.
[0027]
It branches off from the outlet of the valve 8, and is connected to the inlet manifold 33 through the valve 1, the pressure regulating valve 24, and the valve 2 in that order.
[0028]
As described above, when the rocket engine 30 is tested, the valves 1 and 2 are opened, and hydrogen gas is supplied from the hydrogen gas storage 16 to the inlet manifold 33 at a predetermined pressure via the pressure regulating valve 24.
[0029]
Hereinafter, the operation and effect are substantially the same as described above.
(3) A third embodiment of the present invention will be described with reference to FIG. The parts described in the conventional example are assigned the same reference numerals, and the description thereof will be omitted, and the parts related to the present invention will be mainly described.
[0030]
It branches off from the outlet of the valve 3 and is connected to the inlet manifold 33 via the valve 25, the pressure regulating valve 26, and the valve 27 in order.
[0031]
As described above, during the test of the rocket engine 30, the valves 25 and 27 are opened, and the liquid hydrogen at a predetermined pressure is sent from the liquid hydrogen run tank 13 through the pressure regulating valve 26 to the inlet manifold 33. Thereafter, while passing through the cooling passage 28, the supersonic diffuser 12 is cooled, gasified, and ejected as a primary flow. Hereinafter, the operation and effect are substantially the same as described above.
[0032]
【The invention's effect】
As described above, the present invention has the following effects.
(1) Invention 1 In an engine test apparatus having a chamber for accommodating a test engine and gas exhaust means for depressurizing the chamber, a cooling means for cooling the gas exhaust means, and a part of refueling of the test engine. And cooling supply means for supplying as a coolant to the cooling means. This makes the cooling supply means very simple and inexpensive.
(2) Invention 2
In an engine test apparatus having a chamber for accommodating a test engine and a depressurized gas exhaust means in the chamber, the gas exhaust means is an ejector-type annular type which ejects a primary flow from the surroundings, and refueling of the test engine is performed. Was provided with primary flow supply means for supplying a primary flow. This makes the primary flow supply very simple and inexpensive.
(3) Invention 3
In the above (2), the gas discharging means is an annular type ejector for ejecting a primary flow from the surroundings, and the cooling means is an integrated type in which a coolant flows on the peripheral surface of the annular gas discharging means. The material was used as the primary flow of the gas discharge means, the cooling supply means was omitted, and the primary flow was used as the cooling supply means. This makes the cooling means, cooling supply means and primary flow supply means very simple and inexpensive.
[Brief description of the drawings]
FIG. 1 is a configuration system diagram of a first embodiment of the present invention.
FIG. 2 is a configuration system diagram of a second embodiment of the present invention.
FIG. 3 is a configuration system diagram of a third embodiment of the present invention.
FIG. 4 is a configuration system diagram of a conventional example.
[Explanation of symbols]
1 to 10 Valve 11 Chamber 12 Supersonic diffuser 13 Liquid hydrogen run tank 14 Boost pump 15 Evaporator 16 Hydrogen gas storage 17 LN ₂ storage tank 18 Nitrogen gas storage 19 Booster pump 20 Evaporator 21 Water pump 22 Water tank 23 Water Supply lines 24, 26 Pressure regulating valves 25, 27 Valve 28 Cooling passage 29 Oxidizer line 30 Test rocket engine 31 Liquid or gaseous fuel supply device 32 Ejector primary flow supply device 33 Inlet manifold 34 Outlet manifold 35 Annular type ejector

Claims (3)

In an engine test apparatus having a chamber for accommodating a test engine and gas exhaust means for depressurizing the chamber, the gas exhaust means is an annular type ejector that ejects a primary flow from the surroundings, and the gas exhaust means is used for the test. An engine test apparatus, comprising a primary flow supply means for supplying a part of the engine oil supply as the primary flow. In an engine test apparatus having a chamber for accommodating a test engine and gas exhaust means for depressurizing the chamber, a cooling means for cooling the gas exhaust means, and a part of refueling of the test engine being cooled. And a cooling supply means for supplying a cooling material to the means. The gas discharging means is an annular type ejector that ejects a primary flow from the surroundings, and the cooling means is an integrated type in which the cooling material flows on the peripheral surface of the annular gas discharging means, and the same cooling material is used. 3. The engine test apparatus according to claim 2, wherein the cooling / supplying means is omitted as a primary flow of the gas discharging means and the cooling / supplying means is used as a primary flow.

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