JP3149612B2 - Air turbo ram jet engine - Google Patents

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.

[0002]

2. Description of the Related Art FIG. 5 shows a schematic structure of an example of an air turbo ramjet engine. Reference numeral 1 denotes a housing. 4 is an air compressor disk rotatably supported at the front end of the housing 1, 5 and 6 are air compressor rotor blades mounted on the outer peripheral surface of the air compressor disk 4, and 7 is a front end A. The side end is located closer to the rear end B side of the engine outer shell 2 than the air compressor rotor blades 5 and 6 and has a predetermined distance from the inner peripheral surface of the engine outer shell 2 via the frame strut 3. The cylindrical partition walls 8 and 9 supported so as to be held are air compressor stationary blades attached to the inner peripheral surface of the cylindrical partition wall 7.

[0003] Reference numeral 10 denotes a blade tip of the air compressor rotor blade 5;
An annular turbine disk 11 mounted coaxially with the air compressor disk 4, a tip turbine blade 11 provided on the outer peripheral surface of the turbine disk 10, 12
Is a tip turbine vane provided on the inner peripheral surface of the front end A side portion of the engine outer shell 2 so as to surround the turbine disk 10 in the circumferential direction. 13 is the turbine mounted in the front end inside the engine outer shell 2. An air intake cylinder having substantially the same diameter as the disk 10.

[0004] The air intake cylinder 13 and the turbine disk 1
0, an air flow path 14 extending toward the front end A of the engine outer shell 2 is formed inside the cylindrical partition wall 7.

Further, between the inner peripheral surface of the engine outer shell 2 and the air intake cylinder 13, the turbine disk 10, and the cylindrical partition wall 7, the front end A is closed to the outside and the engine outer shell 2 is closed. A fuel passage 15 extending toward the rear end B is formed, and a manifold 16 is provided at a front end of the fuel passage 15.

[0006] Reference numeral 17 denotes an annular mixer attached to the rear end of the cylindrical partition wall 7, a combustion chamber 18 is provided at the rear inside the engine outer shell 2, and a combustion chamber 18 is provided inside the engine outer shell 2. A heat exchanger 19 is provided behind the chamber 18.

The mixer 17 mixes the air 20 flowing through the air flow path 14 with the fuel (hydrogen gas) 21 flowing through the fuel flow path 15 by mixing them.

[0008] In the air turbo ramjet engine having the above-described structure, cryogenic liquid hydrogen 22, which is a fluid fuel maintained at a high pressure, is guided to the heat exchanger 19, and the combustion chamber 18 is cooled.
Gas 2 flowing from the front end A side to the rear end B side
3 and liquid hydrogen 22 to perform heat exchange to generate high-temperature and high-pressure hydrogen gas 21 and guide the hydrogen gas 21 to the manifold 16. The hydrogen gas 21 rotates the tip turbine blade 11 and the turbine disk 10. Then, with the rotation of the turbine disk 10, the air compressor rotor blades 5, 6 rotate.

When the air compressor rotor blades 5 and 6 rotate, air 20 is sucked from the front end A side of the air intake cylinder 13 into the inside,
The air 20 is compressed by the air compressor moving blades 5 and 6 and the air compressor stationary blades 8 and 9, then flows through the air flow path 14 and is discharged toward the combustion chamber 18.

On the other hand, the hydrogen gas 21 that drives the tip turbine blade 11 also flows through the fuel passage 15 and is discharged toward the combustion chamber 18. At this time, the air 20 and the hydrogen gas 21 are mixed by the mixer 17, and the mixed flow of the air 20 and the hydrogen gas 21 is burned in the combustion chamber 18.

Further, a combustion gas 23 generated by burning the mixed stream is generated by the heat exchanger 19 to generate the hydrogen gas 21 and then connected to a nozzle (not shown) connected to the rear end of the engine shell 2. As a result, thrust is generated in the air turbo ramjet engine.

In order to improve the performance of such an air turbo ramjet engine, it is necessary to raise the temperature of the combustion gas.

Therefore, conventionally, various improvements have been made to the shape of the mixer 17 to improve the mixing performance of the mixer 17 so as to raise the temperature of the combustion gas.

[0014]

However, in the above-described air turbo ramjet engine, there is a limit in improving the mixing performance and the combustion efficiency by improving the shape of the mixer 17.

The present invention has been made in view of the above circumstances, and has as its object to provide an air turbo ram jet engine capable of increasing the temperature of a combustion gas by providing a pre-combustion chamber in an air flow passage to preheat air. Things.

[0016]

A first means includes an engine outer shell having a tip turbine vane on an inner surface of a front end, a housing supported in the engine outer shell via a frame strut, and a housing of the housing. An air compressor disk rotatably supported at a front end thereof and having an air compressor rotor blade; a cylindrical partition wall disposed between the engine outer shell and the housing and having an air compressor stationary blade at an inner portion; An annular turbine disk having a tip turbine blade provided on the outer end thereof so as to be coaxial with the air compressor disk, and a rear end of the cylindrical partition wall; In the air turbo ram jet engine having a mixer provided in the section, from the outside of the engine shell to a portion of the space formed between the cylindrical bulkhead and the housing in front of the mixer. Providing a pre-combustion fuel passage passing.

The second means provides the fuel passage for pre-combustion in the first means inside the frame strut.

[0018]

In any of the air turbo ramjet engines according to the first and second aspects of the present invention, the air turbo ramjet engine is formed between the cylindrical partition and the housing via the fuel passage for pre-combustion during operation of the engine. When a small amount of fuel is supplied to the front portion of the space mixer and burned, the temperature of the air passing through the space increases, and the fuel flowing through the space formed between the cylindrical partition and the engine shell is increased. However, since the air is preheated, the mixing performance with the fuel is improved, and the temperature of the combustion gas is increased.

[0019]

Embodiments of the present invention will be described below with reference to the drawings.

FIG. 1 shows an embodiment of an air turbo ramjet engine according to claim 1 of the present invention. In FIG. 1, the same components as those in FIG. .

In the air turbo ramjet engine of the present embodiment, a pre-combustion chamber 24 is formed in a space (air flow path 14) formed between the cylindrical partition 7 and the housing 1 in front of the mixer 17. A configuration is provided in which a pre-combustion fuel passage 25 is provided which communicates with the pre-combustion chamber 24 from the outside of the engine shell 2 and can supply a required amount of hydrogen gas 21.

A required amount of hydrogen gas 21 is supplied to the pre-combustion chamber 24 through the pre-combustion fuel passage 25 during operation of the engine (the supply amount of the hydrogen gas 21 is set so that the temperature of the air 20 is about 500 ° C.). When the fuel is burned, the pre-combustion chamber 24
Is heated, the temperature of which is about 500 ° C.
And flows toward the mixer 17.

A fuel flow path 15 formed between the cylindrical partition wall 7 and the engine outer shell 2 via the manifold 16
The hydrogen gas 21 is supplied to the fuel passage 15 and flows through the fuel passage 15 in the direction of the mixer 17 to be mixed in the mixer 17.

At this time, since the air 20 is preheated,
The mixing performance of the air 20 and the hydrogen gas 21 is improved.

In this embodiment, a pre-combustion chamber 24 is provided upstream of the mixer 17, and the pre-combustion chamber 24 is formed so that the air 20 flowing through the air flow path 14 can be heated to about 500 ° C. Therefore, the mixing performance of the mixer 17 is improved and the temperature of the combustion gas 23 is increased, so that the performance of the air turbo ramjet engine can be improved.

FIGS. 2 to 4 show an embodiment of the air turbo ramjet engine of the present invention. In the drawings, the same components as those in FIG.

In the air turbo ramjet engine according to the present embodiment, the front portion of the space 17 (air flow path 14) formed between the cylindrical partition wall and the housing, which is located in front of the mixer 17, is disposed in the pre-combustion chamber 2.
4, a fuel passage 26 for pre-combustion is provided to communicate with the pre-combustion chamber 24 from outside the engine shell 2 and to supply a required amount of hydrogen gas 21. The pre-combustion fuel flow path 26 has a hole 26a drilled in the longitudinal direction of the frame strut 3 in a substantially central portion of the cross section of the frame strut 3, and penetrates the frame strut 3 in the width direction across the hole 26a. And a plurality of through-holes 26b arranged at predetermined intervals in three longitudinal directions.

Other than the above, there is no difference from that shown in FIG.

A required amount of hydrogen gas 21 is supplied to the pre-combustion chamber 24 via the pre-combustion fuel passage 26 during operation of the engine (the supply amount of the hydrogen gas 21 is set so that the temperature of the air 20 is about 500 ° C.). When the fuel is burned, the pre-combustion chamber 24
Is heated, the temperature of which is about 500 ° C.
And flows toward the mixer 17.

The fuel passage 15 formed between the cylindrical partition 7 and the engine shell 2 via the manifold 16
The hydrogen gas 21 is supplied to the fuel passage 15 and flows through the fuel passage 15 in the direction of the mixer 17 to be mixed in the mixer 17.

At this time, since the air 20 is preheated,
The mixing performance of the air 20 and the hydrogen gas 21 is improved.

In this embodiment, a pre-combustion chamber 24 is provided on the upstream side of the mixer 17, and the pre-combustion chamber 24 is formed so that the air 20 flowing through the air flow path 14 can be heated to about 500 ° C. Therefore, the mixing performance of the mixer 17 is improved and the temperature of the combustion gas 23 is increased, so that the performance of the air turbo ramjet engine can be improved.

It should be noted that the present invention is not limited to the above-described embodiment, and it goes without saying that various changes can be made without departing from the spirit of the present invention.

[0034]

In any of the air turbo ram jet engines according to the first and second aspects of the present invention,
A pre-combustion chamber is provided on the upstream side of the mixer, and the pre-combustion chamber is formed so that the air flowing through the air flow path can be heated to about 500 ° C. Since the performance is improved and the temperature of the combustion gas is increased, an excellent effect that the performance of the air turbo ramjet engine can be improved can be achieved.

[Brief description of the drawings]

FIG. 1 is a sectional view showing an embodiment of an air turbo ramjet engine according to claim 1 of the present invention.

FIG. 2 is a sectional view showing an embodiment of the air turbo ramjet engine according to the second aspect of the present invention.

FIG. 3 is an enlarged view of a frame strut portion related to FIG. 2;

4 is a view taken in the direction of arrows IV-IV in FIG. 3;

FIG. 5 is a cross-sectional view illustrating an example of a conventional air turbo ramjet engine.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Housing 2 Engine shell 3 Frame strut 4 Air compressor disk 5 Air compressor rotor blade 6 Air compressor rotor blade 7 Cylindrical partition 8 Air compressor stator blade 9 Air compressor stator blade 10 Turbine disk 11 Chip turbine rotor blade 12 chip Turbine vane 17 Mixer 25 Pre-combustion fuel passage 26 Pre-combustion fuel passage

Claims (2)

(57) [Claims] An engine shell having a tip turbine vane on an inner surface of a front end, a housing supported in the engine shell via a frame strut, and an air compressor rotatably supported at a front end of the housing. An air compressor disk having moving blades, a cylindrical partition wall disposed between the engine outer shell and the housing and having an air compressor stationary blade inside, and a frontmost row of the air compressor moving blades An air turbine having an annular turbine disk provided at the blade tip so as to be coaxial with the air compressor disk and having a tip turbine blade at an outer portion; and a mixer provided at a rear end of the cylindrical partition wall. In a turbo ramjet engine, a pre-combustion fuel passage communicating from outside of an engine shell is provided at a front portion of a mixer in a space formed between a cylindrical partition and a housing. An air turbo ramjet engine characterized by the following. 2. The air turbo ram jet engine according to claim 1, wherein a fuel passage for pre-combustion is provided inside the frame strut.