CN211739169U

CN211739169U - Turbojet engine combustion chamber

Info

Publication number: CN211739169U
Application number: CN201922118134.4U
Authority: CN
Inventors: 徐超
Original assignee: Fengcheng Wantong Machinery Manufacturing Co ltd
Current assignee: Fengcheng Wantong Machinery Manufacturing Co ltd
Priority date: 2019-12-02
Filing date: 2019-12-02
Publication date: 2020-10-23
Anticipated expiration: 2029-12-02

Abstract

The utility model discloses a turbojet engine combustion chamber, which comprises a tray, a plurality of air inlet pipes with the same structure are inserted in the bottom of the tray and positioned on the outer circumference, a tail spray pipe is inserted in the bottom of the tray, a combustion chamber is installed on the tail spray pipe, a top spray pipe is installed on the combustion chamber, a plurality of first oil holes with the same structure are arranged on the outer circumferential surface of the combustion chamber, the utility model relates to the technical field of turbine engines, the turbojet engine combustion chamber has the combustion precondition that the flame normally burns when the air is sufficient, the fuel oil must be fully atomized, the method has centrifugal atomization, airflow atomization, sleeve evaporation, and the like, the evaporation type is that the fuel oil is gasified by utilizing the heat of the combustion chamber, and the oxygen becomes mixed gas which is ignited when flowing through a speed reduction zone, and provides enough thrust for the engine, is convenient for people to use better.

Description

Turbojet engine combustion chamber

Technical Field

The utility model relates to a turbine engine technical field specifically is a turbojet engine combustion chamber.

Background

A Turbine engine (Turbine engine, or Turbine for short) is a form of engine that uses rotating parts to extract kinetic energy from a fluid passing through it, one type of internal combustion engine. Are commonly used as engines for aircraft and large ships or vehicles.

The combustion chamber of the worm gear engine is used as an important component of the engine, and the existing combustion chamber of the engine has insufficient power because of overlarge air blowing strength or low utilization rate of engine oil, so that the requirement of modern society on the turbine engine cannot be met.

SUMMERY OF THE UTILITY MODEL

Not enough to prior art, the utility model provides a turbojet engine combustion chamber has solved the not enough problem of current burning.

In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: a turbojet engine combustion chamber comprises a tray, wherein a plurality of pairs of air inlet pipes with the same structure are inserted at the bottom of the tray and positioned on the outer circumference of the tray, a plurality of first guide pipes with the same structure and a plurality of second guide pipes with the same structure are alternately arranged on the tray, the plurality of first guide pipes and the plurality of second guide pipes are respectively connected with the plurality of pairs of air inlet pipes, a tail spray pipe is inserted at the bottom of the tray, a combustion chamber is arranged on the tail spray pipe, a top spray pipe is arranged on the combustion chamber, and a plurality of first oil holes with the same structure are formed in the outer ring surface of the combustion chamber;

the tray is characterized in that a shell is installed on the tray, a plurality of second oil holes with the same structure are formed in the shell, a flow guide cover is installed on the shell, a first fixing hole is installed in the position, located on the front side, of the outer annular surface of the shell, a second fixing hole is installed in the position, located on the right rear side, of the outer annular surface of the shell, and a third fixing hole is installed in the position, located on the left rear side, of the outer annular surface of the shell.

Preferably, a plurality of first support rods with the same structure are mounted on the inner annular surface of the shell, second support rods are inserted into the first support rods and connected with the outer annular surface of the combustion chamber, and springs are mounted between the first support rods and the second support rods.

Preferably, the centers of the air inlet pipes are located on the same circumference, and the distances between the air inlet pipes are equal.

Preferably, the first conduit and the second conduit are both U-shaped, the first conduit and the second conduit are at a preset angle, the air outlet end of the first conduit is inclined outwards, the air outlet end of the second conduit is inclined inwards, the first conduit is point-symmetrical through the center of a circle of the tray, and the second conduit is point-symmetrical through the center of a circle of the tray.

Preferably, the shapes of the tail spray pipe and the top spray pipe are both equilateral trapezoids.

Preferably, a steel wire rope is installed between the first guide pipe and the second guide pipe.

Preferably, the top nozzle is provided with a plurality of screw holes with the same structure

Advantageous effects

The utility model provides a turbojet engine combustion chamber. The turbojet engine combustion chamber has the advantages that oxygen and fuel oil are changed into a mixture, the air compressor provides enough oxygen, but the air flow from the air compressor is too fast, and flames cannot burn in the fast air flow, so the air blown in is slowed through the first guide pipe and the second guide pipe, the flames can burn normally while the air is sufficient, the fuel oil is required to be atomized fully, the method comprises centrifugal atomization, air flow atomization and sleeve evaporation, and the like.

Drawings

Fig. 1 is a schematic view of the bottom view structure of the present invention.

Fig. 2 is a schematic top view of the present invention.

Fig. 3 is a schematic top view of the cross-sectional structure of the present invention.

Fig. 4 is a schematic view of a front view partial section structure of the present invention.

Fig. 5 is a schematic view of the front view cross-section structure of the present invention.

In the figure: 1. a tray; 2. an air inlet pipe; 3. a first conduit; 4. a second conduit; 5. a tail nozzle; 6. A combustion chamber; 7. a top nozzle; 8. a housing; 9. a pod; 10. a first fixing hole; 11. a second fixing hole; 12. a third fixing hole; 13. a first support bar; 14. a second support bar; 15. a spring.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution: a turbojet engine combustion chamber comprises a tray 1, wherein a plurality of pairs of air inlet pipes 2 with the same structure are inserted at the bottom of the tray 1 and positioned on the outer circumference, a plurality of first guide pipes 3 with the same structure and a plurality of second guide pipes 4 with the same structure are alternately installed on the tray 1, the plurality of first guide pipes 3 and the plurality of second guide pipes 4 are respectively connected with the plurality of pairs of air inlet pipes 2, a tail spray pipe 5 is inserted at the bottom of the tray 1, a combustion chamber 6 is installed on the tail spray pipe 5, a top spray pipe 7 is installed on the combustion chamber 6, and a plurality of first oil holes with the same structure are formed in the outer ring surface of the combustion chamber 6; the tray 1 is provided with a shell 8, the shell 8 is provided with a plurality of second oil holes with the same structure, the shell 8 is provided with a flow guide cover 9, the outer annular surface of the shell 8 is provided with a first fixing hole 10 at the front side, the outer annular surface of the shell 8 is provided with a second fixing hole 11 at the right rear side, the outer annular surface of the shell 8 is provided with a third fixing hole 12 at the left rear side, the inner annular surface of the shell 8 is provided with a plurality of first supporting rods 13 with the same structure, second supporting rods 14 are inserted in the first supporting rods 13, the second supporting rods 14 are connected with the outer annular surface of the combustion chamber 6, springs 15 are arranged between the first supporting rods 13 and the second supporting rods 14, the centers of a plurality of pairs of air inlet pipes 2 are all positioned on the same circumference, the intervals between the air inlet pipes 2 are equal, the first guide pipe 3 and the second guide pipe 4 are both in a U shape, first pipe 3 with be preset the angle between the second pipe 4, the end slant of giving vent to anger of first pipe 3 is outside, the end slant of giving vent to anger of second pipe 4 is inside, be point symmetry through the 1 centre of a circle of tray between the first pipe 3, be point symmetry through the 1 centre of a circle of tray between the second pipe 4, jet-tail pipe 5 with its shape of jet-tail pipe 7 is equilateral trapezoid, first pipe 3 with install wire rope between the second pipe 4, set up the same screw of a plurality of structures on the jet-tail pipe 7.

The following working principles, detailed connecting means thereof, and the following main descriptions of the working principles and processes thereof are well known in the art, and will be referred to by those skilled in the art for the specific connection and operation sequence of the components in the present disclosure.

Example (b): the turbojet engine combustion chamber 6, the combustion precondition of the turbojet engine is that oxygen and fuel oil are changed into a mixture, the compressor provides enough oxygen, but the air flow from the compressor is too fast, and the flame can not burn in the fast air flow, so the speed of the blown air is slowed through the first conduit 3 and the second conduit 4, the flame is ensured to burn normally while the air is sufficient, and the fuel oil must be atomized fully, the specific method is evaporation, namely, the fuel oil is gasified by using the heat of the combustion chamber 6, the oxygen is changed into a mixed gas, the mixed gas flows through the speed reduction zone and is ignited, specifically, the engine oil permeates into the shell 8 from the second oil hole on the shell 8, a part of the engine oil flows into the combustion chamber 6 along the first oil hole on the combustion chamber 6 and is ignited, the temperature outside the combustion chamber 6 is increased, and the engine oil between the shell 8 and the combustion chamber 6 is gasified, and the air is mixed with the air introduced into the first conduit 3 and the second conduit 4 and is discharged along the flow guide cover 9, so that enough energy is provided for the engine, the thrust of the engine is improved, and the engine is convenient for people to use better.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation. The use of the phrase "comprising one of the elements does not exclude the presence of other like elements in the process, method, article, or apparatus that comprises the element.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A turbojet engine combustion chamber comprises a tray (1) and is characterized in that a plurality of pairs of air inlet pipes (2) with the same structure are inserted at the bottom of the tray (1) and positioned on the outer circumference, a plurality of first guide pipes (3) with the same structure and a plurality of second guide pipes (4) with the same structure are alternately arranged on the tray (1), the plurality of first guide pipes (3) and the plurality of second guide pipes (4) are respectively connected with the plurality of pairs of air inlet pipes (2), a tail spray pipe (5) is inserted at the bottom of the tray (1), a combustion chamber (6) is arranged on the tail spray pipe (5), a top spray pipe (7) is arranged on the combustion chamber (6), and a plurality of first oil holes with the same structure are formed in the outer ring surface of the combustion chamber (6);

install shell (8) on tray (1), a plurality of second oilholes that the structure is the same have been seted up on shell (8), install kuppe (9) on shell (8), the outer anchor ring of shell (8) just is located front side department and installs first fixed orifices (10), just be located right back side department on the outer anchor ring of shell (8) and install second fixed orifices (11), just be located left back side department and install third fixed orifices (12) on the outer anchor ring of shell (8).

2. The turbojet engine combustion chamber of claim 1, characterized in that a plurality of first struts (13) of the same structure are mounted on an inner circumferential surface of the housing (8), second struts (14) are inserted into the first struts (13), the second struts (14) are connected with an outer circumferential surface of the combustion chamber (6), and springs (15) are mounted between the first struts (13) and the second struts (14).

3. The turbojet engine combustion chamber of claim 1, characterized in that the centres of the pairs of intake pipes (2) are located on the same circumference, and the distances between the pairs of intake pipes (2) are equal.

4. The turbojet engine combustion chamber of claim 1, wherein the first conduit (3) and the second conduit (4) are both U-shaped, a preset angle is formed between the first conduit (3) and the second conduit (4), the air outlet end of the first conduit (3) is inclined outwards, the air outlet end of the second conduit (4) is inclined inwards, the first conduit (3) is point-symmetrical through the circle center of the tray (1), and the second conduit (4) is point-symmetrical through the circle center of the tray (1).

5. The turbojet engine combustion chamber of claim 1, characterized in that the exhaust nozzle (5) and the top nozzle (7) are both equilateral trapezoids in shape.

6. A turbojet engine combustion chamber according to claim 1, characterized in that a steel cord is mounted between the first conduit (3) and the second conduit (4).

7. The turbojet engine combustion chamber of claim 1, characterized in that the top nozzle (7) is provided with a plurality of threaded holes of identical configuration.