JPH084587A - Gas generator for air turbo ramjet engine - Google Patents

Abstract

(57) [Summary] [Purpose] An air turbo that has a low proportion of oxidant and can operate stably even at low pressures, which has a large specific thrust and can effectively use air that has been increased in pressure by ram pressure at high speeds. A gas generator for a ramjet engine is provided. [Structure] A reaction vessel 12 containing a solid fuel 11 containing a small amount of an oxidant and generating a combustible gas by a reaction of the solid fuel.
An oxidant container 14 containing a liquid oxidant, an oxidant supply line 15 that connects the oxidant container and the reaction container to each other and supplies the liquid oxidant to a fixed fuel reaction surface in the reaction container, and an oxidant supply line. A flow rate control valve 16 provided to control the flow rate of the liquid oxidant, and a pressure sensor 1 for detecting the pressure in the reaction vessel.
7 and a control device 18 that controls the flow rate control valve according to the output of the pressure sensor, and reduces the flow rate of the liquid oxidant according to the increase in the pressure in the reaction container.

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 generator for an air turbo ramjet 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 by the gas generator 1, the turbine 2 is driven by the generated fuel gas 7, the fan 4 is driven by this turbine 2, and the air 8 is compressed and introduced. The introduced air 8 and fuel gas 7 are mixed in the mixer 3,
The mixed gas is combusted in the combustor 5, the flue gas 9 is expanded by the exhaust nozzle 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.

[0004]

DISCLOSURE OF THE INVENTION Problems to be Solved by the Invention
A gas generator for a ducted rocket engine shown in FIG. 5 is conventionally known. This gas generator uses a solid fuel in which the proportion of the oxidizer is reduced, the oxidizer in the fuel is small, and the total specific thrust (thrust / weight) can be increased.

However, the ducted rocket engine
It is a kind of ramjet engine and can be used only under high ram pressure conditions. On the other hand, in the air turbo ramjet engine described above, the turbine inlet pressure at low speed is low,
When the proportion of the oxidizer in the solid fuel is reduced, there is a problem that the gas generator does not operate stably at low pressure. Further, if the proportion of the oxidizer in the solid fuel is increased so that the solid fuel operates stably even at a low pressure, not only the specific thrust becomes smaller, but also the combustible content in the combustor 5 decreases, and the ram pressure introduced from the outside at high speed is increased. However, there is a problem in that the high-pressure air cannot be effectively used and the above-mentioned characteristics cannot be sufficiently exhibited.

The present invention was devised to solve such problems. That is, an object of the present invention is to provide an air turbo ram that has a low proportion of oxidant and can operate stably even at a low pressure, thereby having a large specific thrust and effectively using the air that has been increased in pressure by the ram pressure at a high speed. It is to provide a gas generator for a jet engine.

[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 generator for an engine, a reaction container that contains a solid fuel containing a small amount of an oxidant and generates the fuel gas by a reaction of the solid fuel, an oxidant container that contains a liquid oxidant, and a reaction with the oxidant container An oxidant supply line that communicates with the container and supplies the liquid oxidant to the fixed fuel reaction surface in the reaction container, a flow rate control valve that is provided in the oxidant supply line and that controls the flow rate of the liquid oxidant, and A pressure sensor for detecting the pressure, and a control device for controlling the flow control valve according to the output of the pressure sensor,
There is provided a gas generator for an air turbo ramjet engine, which is characterized in that a flow rate of a liquid oxidizer is reduced according to an increase in pressure in a reaction vessel.

According to a preferred embodiment of the present invention, the solid fuel is an internal combustion type fuel, and the oxidant supply line has an injector extending axially through a central opening of the internal combustion type fuel. The injector is provided with a plurality of axially spaced injection holes for spraying an oxidant outward in the radial direction, and the injection holes are circumferentially out of phase with each other. Further, the solid fuel is end-face combustion type fuel, the oxidant supply line has an injector on the end face side to which the end-face combustion type fuel reacts,
The injector is provided with a plurality of injection holes for spraying the oxidizer on the end surface of the end surface combustion type fuel. Furthermore, it is preferable that the solid fuel is a self-decomposing fuel.

[0009]

According to the above configuration of the present invention, when the pressure in the reaction vessel is low (takeoff, low speed, etc.), the liquid oxidant can be supplied from the oxidant supply line to the reaction surface of the solid fuel,
This makes it possible to compensate for the shortage of the oxidant at low pressure and to operate the gas generator stably. Also, by reducing the flow rate of the liquid oxidizer according to the rise in the pressure inside the reaction vessel by the control device, the air introduced from the outside at high speed can be effectively used, and it is possible to flexibly change to the optimum air-fuel ratio at all times. Therefore, the fuel consumption rate can be suppressed from increasing and the specific thrust can be increased.

[0010]

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 generator according to the present invention. In this figure, an air turbo ramjet engine includes a turbine 2 driven by a fuel gas 7,
The fan 4 is driven by the turbine 2 and introduces air 8. The combustor 5 burns 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, which mixes the introduced air 8 and fuel gas 7 in the mixer 3, combusts the mixed gas in the combustor 5, expands the combustion exhaust gas 9 in the exhaust nozzle 6 and ejects it backward to generate thrust. It is supposed to do.

The gas generator 10 of the present invention contains a solid fuel 11 containing a small proportion of an oxidizer, a reaction container 12 for generating the fuel gas 7 by the reaction of the solid fuel 11, and an oxidizer containing a liquid oxidizer. The agent container 14 and the oxidant supply line 15 which connects the oxidant container 14 and the reaction vessel 12 to each other and supplies the liquid oxidant to the reaction surface of the fixed fuel 11 in the reaction vessel 12.
A flow rate control valve 16 provided in the oxidant supply line 15 for controlling the flow rate of the liquid oxidant, a pressure sensor 17 for detecting the pressure in the reaction vessel 12, and a flow rate control valve 16 according to the output of the pressure sensor 17. And a control device 18 for controlling the. Further, the control device 18, as illustrated in FIG.
The flow rate W of the liquid oxidant is reduced as the pressure P in the reaction container 12 increases.

With this configuration, when the pressure P in the reaction vessel 12 is low (takeoff, low speed, etc.), the oxidant supply line 1
The liquid oxidizer can be supplied to the reaction surface of the solid fuel 11 from 5, and thus the shortage of the oxidizer at low pressure can be compensated and the gas generator can be operated stably. Further, by reducing the flow rate W of the liquid oxidizer according to the increase in the pressure P in the reaction vessel 12 by the control device 18, the air introduced from the outside at high speed can be effectively used, and the air-fuel ratio can always be flexibly adjusted to the optimum air-fuel ratio. This can be changed, and the increase in fuel consumption rate can be suppressed and the specific thrust can be increased.

The solid fuel 11 is preferably a self-decomposing fuel. This reduces the required amount of oxidant,
The total weight can be reduced. The liquid oxidant is preferably dinitrogen tetraoxide (N2 O4).

In the embodiment of FIG. 1, the solid fuel 11 is an internal combustion fuel, and the oxidant supply line 15 has an injector 15a extending axially through the central opening of the internal combustion fuel. The device 15a is provided with a plurality of injection holes that are axially spaced from each other and spray the oxidant outward in the radial direction. Further, the injection holes are out of phase with each other in the circumferential direction. The shape of the central opening of the internal combustion fuel may be circular, star-shaped, or any other shape. With such a configuration, the oxidizing agent can be uniformly sprayed on the reaction surface (inner surface) of the inner combustion type fuel, and a stable reaction can be performed.

FIG. 2 shows a second embodiment of the gas generator of the present invention. In this figure, the solid fuel 11 is an end-face combustion type fuel, and the oxidant supply line 15 has an injector 15a on the end face side where the end-face combustion type fuel reacts.
In a, a plurality of injection holes for spraying an oxidizer are provided on the end surface of the end surface combustion type fuel. The other part is the first part of FIG.
It is similar to the embodiment. With such a configuration, the oxidizing agent can be uniformly sprayed on the reaction surface (end surface) as in the case of the internal combustion type fuel, and a stable reaction can be performed. Further, the solid fuel 11 may be an inner end surface combustion which can use both inner surface combustion and end surface combustion, and in this case, it is preferable to provide both injectors 15a of FIG. 1 and FIG.

As described above, according to the gas generator for an air turbo ramjet engine of the present invention, stable operation at a low pressure, which is impossible with the conventional self-cracking solid fuel, is possible, and the air-fuel ratio is optimized. It can be controlled, and the increase in fuel consumption rate can be suppressed. The present invention is not limited to the above-described embodiments, and it goes without saying that various modifications can be made without departing from the spirit of the present invention.

[0017]

As described above, the gas generator for an air turbo ramjet engine according to the present invention has a low proportion of oxidant and can operate stably even at a low pressure, which results in a large specific thrust and a ram. It has an excellent effect that air that has been increased in pressure can be effectively used.

[Brief description of drawings]

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

FIG. 2 is a configuration diagram showing a second embodiment of a gas generator according to the present invention.

FIG. 3 is a diagram showing control characteristics of a control device.

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

FIG. 5 is a configuration diagram of a conventional ducted rocket 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 Generator 11 Solid Fuel 12 Reaction Vessel 14 Oxidant Vessel 15 Oxidant Supply Line 15a Injector 16 Flow Control Valve 17 Pressure sensor 18 Control device

Claims (4)

[Claims] 1. A gas generator for an air turbo ramjet engine, comprising: a fuel gas driven turbine; a fan driven by the turbine for introducing air; and a combustor for burning the fuel gas. Of a solid fuel containing a small proportion of the solid fuel and generating the fuel gas by the reaction of the solid fuel, an oxidizer container containing a liquid oxidant, an oxidizer container communicating with the reaction container, and fixing in the reaction container An oxidant supply line for supplying a liquid oxidant to the fuel reaction surface, a flow rate control valve provided in the oxidant supply line for controlling the flow rate of the liquid oxidant, a pressure sensor for detecting the pressure in the reaction vessel, A control device for controlling a flow rate control valve according to the output of the pressure sensor, and reducing the flow rate of the liquid oxidizer according to the rise of the pressure in the reaction vessel. A gas generator for Ttoenjin. 2. The solid fuel is an internal combustion fuel,
The oxidant supply line has an injector that extends axially through a central opening of the internal combustion fuel, and the injector has a plurality of injections that spray the oxidant radially outward at intervals in the axial direction. The gas generator for an air turbo ramjet engine according to claim 1, wherein holes are provided and the injection holes are out of phase with each other in the circumferential direction. 3. The solid fuel is end-face combustion type fuel,
The oxidant supply line has an injector on the end face side where the end-face combustion type fuel reacts, and the injector is provided with a plurality of injection holes for spraying the oxidizer on the end face of the end-face combustion type fuel.
The gas generator for an air turbo ramjet engine according to claim 1, wherein: 4. The solid fuel is a self-decomposing fuel.
The gas generator for an air turbo ramjet engine according to claim 1, wherein: