JPH0814105A - Gas pressure adjusting device for air turbo ram jet engine - Google Patents

Abstract

PURPOSE:To provide a gas pressure adjusting device for an air turbo ram jet engine capable of maintaining the pressure of a gas generator high from a low speed to a high speed (supersonic speed) and stably operating the gas generator and a combustor. CONSTITUTION:A gas pressure adjusting device is provided with a gas generator 12 for generating high pressure fuel gas by incorporating a self-decomposing type solid fuel 11, a low pressure line 14 having an ejector 13 for introducing low pressure air by means of high pressure gas fuel, and guiding a mixed gas consisting of the introduced air and the fuel gas and a high pressure line 16 for directly guiding the high pressure fuel gas generated by the gas generator to a turbine 2. A low pressure opening/closing valve 15 and a high pressure opening/closing valve 17 are respectively provided in low and high pressure lines and thus by opening a low pressure opening/closing valve when the pressure in a turbine entrance is low and opening a high pressure opening/closing valve when the pressure therein is high, so that the fuel gas may be guided to a turbine entrance.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an air turbo ramjet engine which is a combined turbojet and ramjet cycle engine, and more particularly to a gas pressure regulator for the engine.

[0002]

2. Description of the Related Art As shown in FIG. 4, an air turbo ramjet engine includes a gas generator 1, a turbine 2, a mixer 3, a fan 4 (compressor), a combustor 5, an exhaust nozzle 6,
Etc., the high temperature and high pressure fuel gas 7 is generated in the gas generator 1, and the turbine 2 is directly driven by the generated fuel gas 7,
The turbine 2 drives the fan 4 to compress and introduce the air 8, the introduced air 8 and the fuel gas 7 are mixed in the mixer 3, the mixed gas is burned in the combustor 5, and the combustion exhaust gas 9 is exhausted to the exhaust nozzle. It is inflated at 6 and ejected rearward to generate thrust.

Compared with a ramjet, such an air turbo ramjet engine generates a high thrust even at a low speed of Mach 1 or less, can take off by itself, and is capable of supersonic flight of Mach 3 or more like a ramjet. There is.
Regarding the air turbo ramjet engine, AI
AA-84-0075, "Synthesis and Performance of an Air-Tu
rboramjet-Propelled Supersonic Target Vehicle "and the like.

[0004]

A solid fuel gas generator for an air turbo ramjet engine is a self-decomposing solid fuel that contains almost no oxidant and decomposes by heating or impact to generate a fuel gas. It is used to increase the specific thrust (thrust / weight). However, the pressure adjustment range of the self-decomposing solid fuel is narrow, and when the pressure falls below, for example, about 20 ata, self-cracking may stop. Therefore, the inlet pressure of the turbine 2 is low at low speeds (for example, 5 to 20 at).
At the time of a), there is a problem that the operation of the gas generator becomes unstable.

Further, in order to solve this problem, if the operating pressure of the self-decomposing solid fuel is always kept high, the fuel gas introduced into the engine becomes excessive due to the small amount of introduced air at low speed, and the combustor 5 The adjustment range of the air-fuel ratio in (3) becomes difficult, and blowout may occur. Furthermore,
If you increase the proportion of oxidant so that it operates stably even at low pressure,
Not only the weight of fuel increases and the specific thrust decreases, but
There is a problem that the combustible content in the combustor 5 decreases, and the air introduced from the outside at a high speed and increased in pressure by the ram pressure cannot be effectively used sufficiently.

The present invention was devised to solve such problems. That is, an object of the present invention is to maintain a high gas generator pressure from a low speed to a high speed (supersonic speed), and to stably operate the gas generator and the combustor. To provide an adjusting device.

[0007]

According to the present invention, an air turbo ramjet having a turbine driven by fuel gas, a fan driven by the turbine for introducing air, and a combustor for burning fuel gas is provided. In a gas pressure regulator for an engine, a gas generator that contains self-decomposing solid fuel and generates high-pressure fuel gas, and an air that has and has an ejector that introduces low-pressure air by high-pressure fuel gas A low pressure line for guiding the mixed gas of the fuel gas to the turbine and a high pressure line for directly guiding the high pressure fuel gas generated in the gas generator to the turbine are provided, and the low pressure line and the high pressure line respectively have low pressures on the upstream side thereof. An on-off valve and a high-pressure on-off valve are provided so that when the turbine inlet pressure is low, the low-pressure on-off valve is opened to introduce fuel gas and when the turbine inlet pressure is high. Introducing fuel gas by opening the high pressure on-off valve, an air turbo ram jet engine for a gas pressure regulator, characterized in that there is provided on.

According to a preferred embodiment of the present invention,
A throttle valve provided at the air inlet of the ejector for continuously changing the opening area thereof, a pressure sensor for detecting the outlet pressure of the ejector, and a control device for controlling the throttle valve according to the output of the pressure sensor are provided.

[0009]

According to the above-mentioned structure of the present invention, when the turbine inlet pressure is low, the low-pressure on-off valve is opened to introduce the high-pressure fuel gas generated by the gas generator into the low-pressure line, and the ejector introduces the low-pressure air. Can be introduced into the turbine as a mixed gas of air and fuel gas. Therefore, when the turbine inlet pressure is low at low speeds, the pressure of the self-decomposing solid fuel is kept high, and the amount of air introduced at low speed is increased by the air introduced by the ejector to improve the air-fuel ratio in the engine combustor. It can be maintained within an appropriate range and its blowout can be prevented.

When the turbine inlet pressure is high, the high pressure on-off valve can be opened to directly introduce the fuel gas generated by the gas generator to the turbine inlet through the high pressure line. It is possible to sufficiently effectively utilize the air whose pressure has been increased by. Furthermore, a throttle valve that is provided in the air inlet of the ejector and that continuously changes the opening area, a pressure sensor that detects the outlet pressure of the ejector, and a control device that controls the throttle valve according to the output of the pressure sensor are provided. In preparation, if the throttle valve is controlled so as to have the optimum outlet pressure, it is possible to adapt to the turbine inlet pressure that fluctuates drastically from takeoff to supersonic speed, and always operate the gas generator and combustor stably. be able to.

[0011]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT A preferred embodiment of the present invention will be described below with reference to the drawings. In addition, in each figure, the same parts are denoted by the same reference numerals. FIG. 1 is an overall configuration diagram of an air turbo ramjet engine including a gas pressure adjusting device according to the present invention. In this figure, an air turbo ramjet engine includes a turbine 2 driven by a fuel gas 7 and a fan 4 driven by the turbine 2 for introducing air 8.
And a combustor 5 for burning the fuel gas 7.
Such a configuration is similar to that of the conventional air turbo ramjet engine shown in FIG. In this figure, 3 is a mixer and 6 is an exhaust nozzle. The introduced air 8 and fuel gas 7 are mixed in the mixer 3, the mixed gas is burned in the combustor 5, and the combustion exhaust gas 9 is discharged in the exhaust nozzle 6. It is inflated and ejected rearward to generate thrust.

The gas pressure adjusting apparatus 10 of the present invention has a gas generator 12 which contains a self-decomposing solid fuel 11 and generates a high pressure fuel gas, and an ejector 13 which introduces low pressure air by the high pressure fuel gas. And a low pressure line 14 for introducing the introduced mixed gas of air and fuel gas to the turbine,
And a high pressure line 16 for directly guiding the high pressure fuel gas generated in the gas generator to the turbine. The low pressure line 14 and the high pressure line 16 are provided with a low pressure on-off valve 15 and a high pressure on-off valve 17, respectively, on their upstream sides.

The gas pressure adjusting device 10 of the present invention further comprises a switching control device 18 for detecting the turbine inlet pressure P1 and switching between the on-off valves 15 and 17. This switching control device 18 opens the low pressure on-off valve 15 to introduce the fuel gas to the turbine inlet through the low pressure line 14 when the turbine inlet pressure P1 is low, and opens the high pressure on-off valve 17 when the turbine inlet pressure P1 is high. It is designed to be introduced through the high pressure line 16.

With this configuration, when the inlet pressure P1 of the turbine is low at low speeds, the pressure of the self-decomposing solid fuel 11 is kept high, and the amount of air introduced at low speeds is increased by the air introduced by the ejector 13. It is possible to maintain the air-fuel ratio in the combustor 5 of the engine within a proper range and prevent the blowout. Also, the turbine inlet pressure P
Gas generator 1 via high pressure line 16 when 1 is high
The fuel gas generated in 2 can be directly introduced to the inlet of the turbine, and the air introduced from the outside and increased in pressure by the ram pressure can be sufficiently used effectively. Further, since the self-decomposing solid fuel 11 is used, the required amount of the oxidizer can be reduced, the total weight can be reduced, and the specific thrust can be increased.

FIG. 2 is a detailed configuration diagram of the ejector portion of FIG. The gas pressure adjusting device 10 of the present invention further includes
A throttle valve 22 provided at the air inlet of the ejector 13 for continuously changing the opening area thereof, a pressure sensor 23 for detecting the outlet pressure of the ejector, and a pressure sensor 2
Control device 24 for controlling the throttle valve 22 in accordance with the output of No. 3
And The control device 24 controls the throttle valve 22 so that the outlet pressure P of the ejector becomes the optimum pressure from the turbine inlet pressure P1, the atmospheric pressure P0, the rotation speed N of the air turbo ramjet engine, and the like. There is. With such a configuration, it is possible to adapt to the turbine inlet pressure that varies greatly from takeoff to supersonic speed, and the gas generator and the combustor can always be stably operated.

FIG. 3 is a characteristic diagram of the ejector, showing the relationship between the pressure P0 and flow rate W0 of the air introduced into the ejector, the high-pressure fuel gas amount W and the outlet pressure P of the ejector. As is clear from this figure, a large amount of air W0 can be introduced with a small amount of fuel gas W, and the outlet pressure P can be changed by controlling the flow rate W0 of the introduced air.

The present invention is not limited to the above-mentioned embodiments, and it goes without saying that various modifications can be made without departing from the gist of the present invention.

[0018]

As described above, the gas pressure regulator for an air turbo ramjet engine according to the present invention can maintain the pressure of the gas generator high from low speed to high speed (supersonic speed) and can generate gas. It has excellent effects such as stable operation of the burner and combustor.

[Brief description of drawings]

FIG. 1 is an overall configuration diagram of an air turbo ramjet engine including a gas pressure adjusting device according to the present invention.

FIG. 2 is a detailed configuration diagram of an ejector portion in FIG.

FIG. 3 is a characteristic diagram of an ejector.

FIG. 4 is a configuration diagram of a conventional air turbo ramjet engine.

[Explanation of symbols]

 1 Gas Generator 2 Turbine 3 Mixer 4 Fan 5 Combustor 6 Exhaust Nozzle 7 Fuel Gas 8 Air 9 Combustion Exhaust Gas 10 Gas Pressure Regulator 11 Self-degrading Solid Fuel 12 Gas Generator 13 Ejector 14 Low Pressure Line 15 Low Pressure Open / Close Valve 16 High Pressure Line 17 High-pressure on-off valve 18 Switching control device 22 Throttle valve 23 Pressure sensor 24 Control device

Claims (2)

[Claims] 1. A gas pressure regulator for an air turbo ramjet engine, comprising: a turbine driven by fuel gas; a fan driven by the turbine for introducing air; and a combustor for burning fuel gas. A low-pressure gas generator that contains a decomposing type solid fuel and that generates high-pressure fuel gas, and an ejector that introduces low-pressure air by high-pressure fuel gas, and that introduces the mixed gas of the introduced air and fuel gas to the turbine. A line and a high-pressure line for directly guiding the high-pressure fuel gas generated in the gas generator to the turbine, and the low-pressure line and the high-pressure line are provided with a low-pressure on-off valve and a high-pressure on-off valve, respectively, on their upstream sides, With this, when the turbine inlet pressure is low, the low-pressure on-off valve is opened to introduce the fuel gas, and when the turbine inlet pressure is high, the high-pressure on-off valve is opened to open the fuel gas. Introduction to the gas pressure regulating device for an air turbo ram jet engine, characterized in that. 2. A throttle valve provided at the air inlet of the ejector for continuously changing the opening area thereof, a pressure sensor for detecting the outlet pressure of the ejector, and the throttle valve controlled according to the output of the pressure sensor. The control device for controlling the gas pressure for an air turbo ramjet engine according to claim 1.