CN209800097U

CN209800097U - Short aircraft engine structure

Info

Publication number: CN209800097U
Application number: CN201920485533.1U
Authority: CN
Inventors: 林瑞长
Original assignee: Individual
Current assignee: Individual
Priority date: 2019-04-11
Filing date: 2019-04-11
Publication date: 2019-12-17
Anticipated expiration: 2029-04-11

Abstract

the utility model relates to a short type aircraft engine structure, including the casing that has air inlet, jet and combustion chamber and be located the main shaft at casing center, install the compressor that is located casing air inlet department on the main shaft, the gas outlet that is located combustion chamber week portion is seted up to the casing inside wall, is located the combustion chamber and is provided with the toper wind-guiding ware with gaseous leading-in gas outlet towards jet one side, is provided with the exhaust passage who communicates gas outlet and jet on the casing inside wall, install the turbine between exhaust passage and the gas outlet. The utility model discloses produce backward impulsive force when short type aircraft engine structure can the interior burning of dispersed combustion chamber, change the direction of backward impulsive force, and then promote the effect of forward impulsive force, increase the air input, effectively promote power, practice thrift the energy consumption.

Description

Short aircraft engine structure

Technical Field

The utility model relates to a short type aircraft engine structure.

Background

In the traditional aircraft engine, the combustion chamber directly exhausts backwards, forward impulsive force and backward impulsive force generated by combustion of the combustion chamber are positioned on the same straight line, and the two forces with the same size and opposite directions are offset, so that the impulsive force is not well utilized, the power of the engine is influenced, and the energy consumption is large.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model aims at providing a can effectively promote power, practice thrift the short type aircraft engine structure of energy consumption.

The utility model discloses a following scheme realizes: a short aircraft engine structure comprises a shell with an air inlet, an air jet and a combustion chamber and a main shaft located in the center of the shell, wherein a compressor located at the air inlet of the shell is installed on the main shaft, an air outlet located on the periphery of the combustion chamber is formed in the inner side wall of the shell, a conical air deflector which guides air into the air outlet is arranged on one side, facing the air jet, of the combustion chamber, an exhaust channel which is communicated with the air outlet and the air jet is arranged on the inner side wall of the shell, and a turbine is installed between the exhaust channel and the air outlet.

Furthermore, an oil nozzle and a spark plug are installed on the conical air deflector.

furthermore, a containing cavity is arranged in the shell and behind the conical air deflector, and a generator, a gearbox and a battery box are arranged in the containing cavity.

Further, the turbine comprises an annular body connected with the main shaft through a connecting frame, and blades distributed annularly are arranged in an annular cavity of the annular body.

Furthermore, the rear part of the machine shell is in a conical shape with a large front part and a small rear part, and the exhaust channel is positioned on the inner side of the rear part of the machine shell.

Compared with the prior art, the utility model discloses following beneficial effect has: the utility model discloses produce backward impulsive force when short type aircraft engine structure can the interior burning of dispersed combustion chamber, change the direction of backward impulsive force, and then promote the effect of forward impulsive force, increase the air input, effectively promote power, practice thrift the energy consumption.

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to specific embodiments and related drawings.

Drawings

FIG. 1 is a schematic view of the internal structure of the embodiment of the present invention;

FIG. 2 is a cross-sectional view taken along line A-A of FIG. 1;

FIG. 3 is a schematic view of a turbine configuration in an embodiment of the present invention;

The reference numbers in the figures illustrate: 100-casing, 110-air inlet, 120-air outlet, 130-combustion chamber, 140-air outlet, 150-conical air deflector, 160-exhaust channel, 170-containing cavity, 200-main shaft, 300-compressor, 400-turbine, 410-annular body, 420-blade, 430-connecting frame, 500-oil nozzle, 600-spark plug, 700-generator, 800-gearbox and 900-battery box.

Detailed Description

As shown in fig. 1 ~ 3, a short aircraft engine structure includes a casing 100 having an air inlet 110, an air nozzle 120 and a combustion chamber 130, and a main shaft 200 located at the center of the casing 100, wherein a compressor 300 located at the air inlet of the casing is mounted on the main shaft 200, an air outlet 140 located at the periphery of the combustion chamber 130 is opened on the inner side wall of the casing 100, a tapered air guide 150 for guiding air into the air outlet 140 is arranged on the side of the combustion chamber 130 facing the air nozzle 120, an exhaust passage 160 communicating the air outlet 140 with the air nozzle 120 is arranged on the inner side wall of the casing 100, and a turbine 400 is mounted between the exhaust passage 160 and the air outlet 140.

In this embodiment, the oil jet 500 and the spark plug 600 are mounted on the conical air deflector 150, and the oil jet injects gasoline into the combustion chamber, and the spark plug ignites.

In this embodiment, an accommodating cavity 170 is formed in the casing 100 and located behind the tapered wind deflector 150, a generator 700, a gearbox 800 and a battery box 900 are installed in the accommodating cavity 170, the generator is driven by rotation of the main shaft to work to generate electricity, and then the electricity is stored in the battery box.

In this embodiment, the turbine 400 includes an annular body 410 connected to the main shaft through a connecting frame 430, the annular body has circumferentially distributed blades 420 in an annular cavity, the annular body 410 is composed of two circular plates, the blades 420 are fixedly connected to the annular body, and the turbine 400 can recover energy in the exhaust gas to act on the main shaft to further increase the intake air amount.

In this embodiment, the rear portion of the casing 100 is tapered with a larger front portion and a smaller rear portion, and the exhaust passage is located inside the rear portion of the casing.

Any technical solution disclosed in the present invention is, unless otherwise stated, disclosed a numerical range if it is disclosed, and the disclosed numerical range is a preferred numerical range, and any person skilled in the art should understand that: the preferred ranges are merely those values which are obvious or representative of the technical effect which can be achieved. Because numerical value is more, can't be exhaustive, so the utility model discloses just disclose some numerical values with the illustration the technical scheme of the utility model to, the numerical value that the aforesaid was enumerated should not constitute right the utility model discloses create the restriction of protection scope.

The utility model discloses if disclose or related to mutual fixed connection's spare part or structure, then, except that other the note, fixed connection can understand: a detachable fixed connection (for example using bolts or screws) is also understood as: non-detachable fixed connections (e.g. riveting, welding), but of course, fixed connections to each other may also be replaced by one-piece structures (e.g. manufactured integrally using a casting process) (unless it is obviously impossible to use an integral forming process).

In addition, the terms used in any aspect of the present disclosure as described above to indicate positional relationships or shapes include similar, analogous, or approximate states or shapes unless otherwise stated.

The utility model provides an arbitrary part both can be assembled by a plurality of solitary component parts and form, also can be the solitary part that the integrated into one piece technology was made.

Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting the same; although the present invention has been described in detail with reference to preferred embodiments, it should be understood by those skilled in the art that: the invention can be modified or equivalent substituted for some technical features; without departing from the spirit of the present invention, it should be understood that the scope of the claims is intended to cover all such modifications and variations.

Claims

1. The utility model provides a short type aircraft engine structure, is including the casing that has air inlet, jet and combustion chamber and be located the main shaft at casing center, install the compressor that is located casing air inlet department on the main shaft, its characterized in that: the inner side wall of the casing is provided with a gas outlet which is positioned on the periphery of the combustion chamber, a conical wind deflector which is positioned on one side of the combustion chamber facing the gas jet port and guides gas into the gas outlet is arranged, an exhaust channel which is communicated with the gas outlet and the gas jet port is arranged on the inner side wall of the casing, and a turbine is arranged between the exhaust channel and the gas outlet.

2. a short aircraft engine structure according to claim 1, wherein: and the conical air deflector is provided with an oil nozzle and a spark plug.

3. A short aircraft engine structure according to claim 1, wherein: the shell is internally provided with a containing cavity which is positioned behind the conical air deflector, and the containing cavity is internally provided with a generator, a gearbox and a battery box.

4. A short aircraft engine structure according to claim 1, wherein: the turbine comprises an annular body connected with the main shaft through a connecting frame, and blades distributed annularly are arranged in an annular cavity of the annular body.

5. A short aircraft engine structure according to claim 3, wherein: the rear part of the machine shell is in a conical shape with a large front part and a small rear part, and the exhaust channel is positioned on the inner side of the rear part of the machine shell.