CN221483678U - Combustion chamber of turbojet engine - Google Patents
Combustion chamber of turbojet engine Download PDFInfo
- Publication number
- CN221483678U CN221483678U CN202322767895.9U CN202322767895U CN221483678U CN 221483678 U CN221483678 U CN 221483678U CN 202322767895 U CN202322767895 U CN 202322767895U CN 221483678 U CN221483678 U CN 221483678U
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- oil
- combustion chamber
- oil outlet
- fuel
- pipeline
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 80
- 239000000446 fuel Substances 0.000 claims abstract description 55
- 239000003595 mist Substances 0.000 claims description 21
- 238000009434 installation Methods 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 2
- 239000003921 oil Substances 0.000 description 98
- 239000000295 fuel oil Substances 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Landscapes
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The application provides a combustion chamber of a turbojet engine, which relates to the technical field of engine combustion chambers and comprises a combustion chamber main body and an oil delivery assembly, wherein the oil delivery assembly comprises a first oil delivery pipeline and a second oil delivery pipeline, the first oil delivery pipeline comprises a plurality of first oil delivery pipelines, one ends of the first oil delivery pipelines are respectively provided with a main fog nozzle, the second oil delivery pipeline comprises a plurality of second oil delivery pipelines, and one sides of the second oil delivery pipelines are respectively provided with a plurality of auxiliary fog nozzles; a plurality of mounting caps are processed on one side of the combustion chamber main body, and an igniter is assembled in the mounting caps; the technical key points are as follows: through setting up first oil pipeline in the inboard of second oil pipeline, install a plurality of second oil pipelines and a plurality of first oil pipelines to the inside back of combustion chamber main part, can guarantee that the combustion chamber main part is full of fuel fast, make the second oil pipeline be longer than first oil pipeline simultaneously to make the play oily direction of both in opposite directions, can increase the combustion time of fuel in the combustion chamber main part inside, improve combustion efficiency.
Description
Technical Field
The utility model relates to the technical field of engine combustion chambers, in particular to a combustion chamber of a turbojet engine.
Background
Turbojet engines rely solely on the flow of combustion gases to produce thrust and are commonly used as power for high speed aircraft. Compared with centrifugal turbojet engines, the axial flow type turbojet engines have the advantages of small cross section and high compression ratio, and most of the currently used turbojet engines are of an axial flow type. The turbojet engine comprises an air inlet channel, a gas compressor, a combustion chamber, a turbine and a tail nozzle, wherein an afterburner is arranged between the turbine and the tail nozzle of some aircraft.
Air enters a combustion chamber to be mixed with kerosene for combustion after being compressed by a gas compressor, and expansion work is done; immediately after flowing through the turbine, the turbine is driven to rotate at a high speed. Because the turbine and the compressor rotor are connected on a shaft, the rotational speed of the compressor and the turbine are the same. And finally, the high-temperature and high-speed fuel gas is sprayed out through the spray pipe to provide power by the reaction force. The combustion chamber is initially in the form of several small cylindrical combustion chambers annularly juxtaposed around the rotor shaft, each of which is not sealed but is perforated in place so that the whole combustion chamber is in communication and later developed into an annular combustion chamber, of compact construction.
When the combustion chamber disclosed in the prior Chinese patent document No. CN114659139B and the combustion chamber 1000 provided by the turbojet engine are used, an oil way assembly is started to feed oil, one part of liquid fuel is atomized through an atomization centrifugal nozzle and sprayed into a flame tube, the other part of liquid fuel is conveyed into a cavity between an igniter and a base of the igniter to be ignited so as to form a fire source, and the gaseous fuel in the flame tube is rapidly ignited, which is equivalent to the diffusion enhancement of the fire source, so that the ignition reliability is improved. In addition, the combustion chamber 1000 is an evaporation tube type combustion chamber, which reduces the cost of the combustion chamber 1000 compared to an atomizing nozzle type combustion chamber.
However, in the process of implementing the above technical solution, the following technical problems are found in the above technical solution:
The combustion chamber of the existing turbojet engine is mainly used for atomizing fuel through the atomizing centrifugal nozzle, meanwhile, too much fuel is conveyed into the cavity of the igniter base to form a fire source, and the ignition reliability can be improved by means of the enhanced fire source, but because the atomizing centrifugal nozzle is provided with two parts, the lower part of the igniter is connected with the oil inlet pipe, and atomized fuel is not beneficial to quickly filling the inside of the whole combustion chamber, so that the combustion efficiency of the fuel is affected.
Disclosure of utility model
In order to overcome the defect that the combustion efficiency of the fuel oil is affected by the fact that two atomizing centrifugal nozzles are arranged in a combustion chamber of the existing turbojet engine and are positioned below an igniter and connected with an oil inlet pipe, atomized fuel oil is not beneficial to quickly filling the inside of the whole combustion chamber, the embodiment of the application provides the combustion chamber of the turbojet engine, and the first oil delivery pipeline is arranged on the inner side of a second oil delivery pipeline, after a plurality of second oil outlet pipes and a plurality of first oil outlet pipes are arranged in the combustion chamber main body, the periphery of the inner side of the combustion chamber main body can be guaranteed to quickly receive the fuel oil, and the speed of the fuel oil conveyed to the combustion chamber main body from the plurality of first oil outlet pipes and the plurality of second oil outlet pipes can be respectively controlled.
The technical scheme adopted by the embodiment of the application for solving the technical problems is as follows:
the combustion chamber of the turbojet engine comprises a combustion chamber main body and an oil delivery assembly, wherein the oil delivery assembly is arranged on one side of the combustion chamber main body;
The fuel delivery assembly comprises a combustion chamber main body, wherein air inlets are formed in the periphery of the combustion chamber main body, the fuel delivery assembly comprises a first fuel delivery pipeline and a second fuel delivery pipeline, fuel is delivered to one end of the first fuel delivery pipeline through one end of the second fuel delivery pipeline, and fuel delivered from one end of the first fuel delivery pipeline and fuel delivered from one end of the second fuel delivery pipeline move in opposite directions.
In one possible implementation manner, the first oil delivery pipeline comprises a first oil inlet pipe, a first flow distribution ring is machined at one end of the first oil inlet pipe, a plurality of first oil outlet pipes are machined at one side of the first flow distribution ring, a plurality of main fog nozzles are machined at one end of the first oil outlet pipes, and the first oil outlet pipes are equidistantly arranged around the center of the first flow distribution ring.
In one possible implementation manner, the second oil delivery pipeline comprises a second oil inlet pipe, a second split ring is machined at one end of the second oil inlet pipe, a plurality of second oil outlet pipes are machined at one side of the second split ring, a plurality of auxiliary mist nozzles are machined at one side of the second oil outlet pipes, and the second oil outlet pipes are equidistantly arranged around the center of the second split ring.
In one possible implementation manner, the first flow dividing ring is arranged at the inner side of the second flow dividing ring, and the plurality of auxiliary mist nozzles are all obliquely arranged and face the main mist nozzles on the first oil outlet pipe.
In one possible implementation manner, a plurality of mounting caps are machined on one side of the combustion chamber main body, an igniter is connected to the mounting caps in an assembled mode, and a plurality of mounting caps are equidistantly arranged around the combustion chamber main body and extend into the combustion chamber main body.
In one possible implementation manner, the length of the second oil outlet pipe is longer than that of the first oil outlet pipe, and the plurality of auxiliary mist nozzles are all located on one side of the first oil outlet pipe.
In one possible implementation, a plurality of the second oil outlet pipes pass through the center of the mounting cap, and one end of the igniter passes through the inside of the mounting cap and is located between the second oil outlet pipe and the first oil outlet pipe.
In summary, the present utility model includes at least one of the following beneficial technical effects:
1. Through setting the first oil pipeline on the inner side of the second oil pipeline, after a plurality of second oil pipelines and a plurality of first oil pipelines are installed in the combustion chamber main body, the periphery of the inner side of the combustion chamber main body can be ensured to quickly receive fuel oil, and the rate of the fuel oil conveyed to the combustion chamber main body from the plurality of first oil pipelines and the plurality of second oil pipelines can be respectively controlled;
2. Through setting the second to be longer than first oil outlet pipe's form, when the inside some firearm of installation cap ignites, can burn earlier by auxiliary fog spout spun fuel on the second oil outlet pipe, with the help of this fuel ignites from main fog spout spun fuel on the first oil outlet pipe, because of first oil outlet pipe's overall length is short, has increased the time that the fuel stayed to the combustion chamber main part inside, and auxiliary fog spout spun fuel's direction is opposite with main fog spout spun fuel, can increase the burning time of atomizing fuel, guarantee combustion efficiency.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a schematic view of the internal structure of the combustion chamber body of the present utility model;
FIG. 3 is a cross-sectional view of the combustion chamber body of the present utility model;
fig. 4 is a schematic diagram of the first oil outlet pipe and the second oil outlet pipe in the oil injection state according to the present utility model.
Description of the drawings: 1. a combustion chamber body; 2. an air inlet hole; 3. an oil delivery assembly; 31. a first oil delivery line; 311. a first oil inlet pipe; 312. a first shunt ring; 313. a first flowline; 314. a main mist nozzle; 32. a second oil delivery line; 321. a second oil inlet pipe; 322. a second split ring; 323. a second oil outlet pipe; 324. an auxiliary fog nozzle; 4. installing a cap; 5. an igniter.
Detailed Description
The technical scheme in the embodiment of the application aims to solve the problems of the background technology, and the general thought is as follows:
Example 1:
The embodiment describes a specific structure of a combustion chamber of a turbojet engine, and specifically referring to fig. 1-4, the structure comprises a combustion chamber main body 1 and an oil delivery assembly 3 arranged on one side of the combustion chamber main body 1, air inlets 2 are formed in the periphery of the combustion chamber main body 1, the oil delivery assembly 3 comprises a first oil delivery pipeline 31 and a second oil delivery pipeline 32, the first oil delivery pipeline 31 comprises a first oil inlet pipe 311, one end of the first oil inlet pipe 311 is provided with a first split ring 312, one side of the first split ring 312 is provided with a plurality of first oil outlet pipes 313, and one end of the plurality of first oil outlet pipes 313 is provided with a main fog nozzle 314;
The second oil delivery pipeline 32 comprises a second oil inlet pipe 321, a second flow dividing ring 322 is processed at one end of the second oil inlet pipe 321, a plurality of second oil outlet pipes 323 are processed at one side of the second flow dividing ring 322, and a plurality of auxiliary mist nozzles 324 are processed at one sides of the second oil outlet pipes 323;
The first oil outlet pipes 313 are equally spaced around the center of the first split ring 312, the second oil outlet pipes 323 are equally spaced around the center of the second split ring 322, and the first split ring 312 is disposed inside the second split ring 322, so that the first oil delivery pipes 31 and the second oil delivery pipes 32 can be separated from each other when the second oil outlet pipes 323 and the first oil outlet pipes 313 are mounted inside the combustion chamber body 1, and the rate of fuel delivered to the combustion chamber body 1 through the first oil delivery pipes 31 and the second oil delivery pipes 32 can be controlled respectively.
By adopting the technical scheme:
In the above-described design, the first oil delivery pipe 31 is disposed inside the second oil delivery pipe 32, so that when the plurality of second oil delivery pipes 323 and the plurality of first oil delivery pipes 313 are mounted inside the combustion chamber body 1, fuel is delivered from the first oil inlet pipe 311 to the inside of the first split ring 312 and is split into the plurality of first oil delivery pipes 313 to be sprayed into the inside of the combustion chamber body 1, and simultaneously delivered from the second oil inlet pipe 321 to the inside of the second split ring 322 and split into the plurality of second oil delivery pipes 323 to be sprayed into the inside of the combustion chamber body 1, so that the fuel can be received quickly around the inside of the combustion chamber body 1, and the rate of the fuel delivered from the plurality of first oil delivery pipes 313 and the plurality of second oil delivery pipes 323 to the inside of the combustion chamber body 1 can be controlled.
Example 2:
Based on the embodiment 1, the specific structure of the present application is described, and as shown in fig. 3 and 4, a plurality of mounting caps 4 are processed on one side of the combustion chamber body 1, and an igniter 5 is connected to the inside of the mounting caps 4 in an assembled manner;
Wherein, a plurality of mounting caps 4 are equidistantly arranged around the combustion chamber main body 1 and extend into the combustion chamber main body 1, so that the igniter 5 mounted in the mounting caps 4 can be prevented from protruding outwards from one side of the combustion chamber main body 1;
Next, as shown in fig. 4, the length of the second oil outlet pipe 323 is longer than that of the first oil outlet pipe 313, the plurality of auxiliary mist nozzles 324 are all located at one side of the first oil outlet pipe 313, and after the plurality of auxiliary mist nozzles 324 are obliquely arranged, the plurality of auxiliary mist nozzles 324 can face the main mist nozzle 314 on the first oil outlet pipe 313;
Meanwhile, by making the plurality of second oil outlet pipes 323 pass through the center of the mounting cap 4, and making one end of the igniter 5 pass through the inside of the mounting cap 4 and between the second oil outlet pipes 323 and the first oil outlet pipe 313, the fuel is delivered to one end of the first oil delivery pipe 31 through one end of the second oil delivery pipe 32, the fuel delivered from one end of the first oil delivery pipe 31 and the fuel delivered from one end of the second oil delivery pipe 32 move in opposite directions, and when the igniter 5 is started, atomized fuel sprayed from the auxiliary mist nozzle 324 can be ignited, and the fuel sprayed from the main mist nozzle 314 is guided to burn by the part of fuel.
By adopting the technical scheme:
According to the design, the second oil outlet pipe 323 is arranged to be longer than the first oil outlet pipe 313, when the igniter 5 in the installation cap 4 ignites, fuel sprayed from the auxiliary mist nozzle 324 on the second oil outlet pipe 323 can be combusted first, the fuel sprayed from the main mist nozzle 314 on the first oil outlet pipe 313 is ignited by the fuel, the time for the fuel to stay in the combustion chamber main body 1 is prolonged due to the short whole length of the first oil outlet pipe 313, and the direction of the fuel sprayed from the auxiliary mist nozzle 324 is opposite to that of the fuel sprayed from the main mist nozzle 314, so that the combustion time of atomized fuel can be prolonged, and the combustion efficiency is ensured.
Finally, it should be noted that: it is apparent that the above examples are only illustrative of the present utility model and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. And obvious variations or modifications thereof are contemplated as falling within the scope of the present utility model.
Claims (4)
1. A turbojet engine combustor, comprising:
a combustion chamber body (1);
an oil delivery assembly (3) provided on one side of the combustion chamber body (1);
The fuel delivery assembly comprises a combustion chamber main body (1), wherein air inlets (2) are formed in the periphery of the combustion chamber main body (1), the fuel delivery assembly (3) comprises a first fuel delivery pipeline (31) and a second fuel delivery pipeline (32), fuel is delivered to one end of the first fuel delivery pipeline (31) through one end of the second fuel delivery pipeline (32), and fuel delivered from one end of the first fuel delivery pipeline (31) and fuel delivered from one end of the second fuel delivery pipeline (32) move in opposite directions;
the first oil conveying pipeline (31) comprises a first oil inlet pipe (311), a first flow distribution ring (312) is machined at one end of the first oil inlet pipe (311), a plurality of first oil outlet pipes (313) are machined at one side of the first flow distribution ring (312), main mist nozzles (314) are machined at one ends of the first oil outlet pipes (313), and the first oil outlet pipes (313) are equidistantly arranged around the center of the first flow distribution ring (312);
The second oil conveying pipeline (32) comprises a second oil inlet pipe (321), a second flow distribution ring (322) is machined at one end of the second oil inlet pipe (321), a plurality of second oil outlet pipes (323) are machined at one side of the second flow distribution ring (322), a plurality of auxiliary mist nozzles (324) are machined at one side of the second oil outlet pipes (323), and the second oil outlet pipes (323) are equidistantly arranged around the center of the second flow distribution ring (322);
The first flow distribution ring (312) is arranged on the inner side of the second flow distribution ring (322), and the plurality of auxiliary mist nozzles (324) are obliquely arranged and face the main mist nozzles (314) on the first oil outlet pipe (313).
2. The turbojet engine combustion chamber of claim 1 wherein: a plurality of mounting caps (4) are machined on one side of the combustion chamber main body (1), and an igniter (5) is connected to the inside of the mounting caps (4) in an assembled mode;
Wherein, a plurality of installation caps (4) are equidistantly encircling the periphery of the combustion chamber main body (1), and all extend into the inside of the combustion chamber main body (1).
3. The turbojet engine combustion chamber of claim 1 wherein: the length of the second oil outlet pipe (323) is longer than that of the first oil outlet pipe (313), and a plurality of auxiliary mist spray nozzles (324) are all arranged on one side of the first oil outlet pipe (313).
4. The turbojet engine combustion chamber of claim 2 wherein: a plurality of second oil outlet pipes (323) respectively penetrate through the center of the mounting cap (4), and one end of the igniter (5) penetrates through the inside of the mounting cap (4) and is located between the second oil outlet pipes (323) and the first oil outlet pipes (313).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322767895.9U CN221483678U (en) | 2023-10-16 | 2023-10-16 | Combustion chamber of turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322767895.9U CN221483678U (en) | 2023-10-16 | 2023-10-16 | Combustion chamber of turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221483678U true CN221483678U (en) | 2024-08-06 |
Family
ID=92370957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322767895.9U Active CN221483678U (en) | 2023-10-16 | 2023-10-16 | Combustion chamber of turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221483678U (en) |
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2023
- 2023-10-16 CN CN202322767895.9U patent/CN221483678U/en active Active
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