CN2413190Y

CN2413190Y - Energy-saving efficient water-oil plane engine with infrared silencer

Info

Publication number: CN2413190Y
Application number: CN 00222783
Authority: CN
Inventors: 周成荣
Original assignee: Individual
Current assignee: Individual
Priority date: 2000-04-14
Filing date: 2000-04-14
Publication date: 2001-01-03
Anticipated expiration: 2010-04-14

Abstract

The utility model relates to an energy saving and high efficiency water and oil plane engine with an infrared silencer, wherein, a gas inlet passage, a combustion chamber and a propelling nozzle are orderly positioned in a machine casing of an engine. A fuel conveying pipe which is provided with nozzles is positioned between the gas inlet passage and the combustion chamber. An inlet of the fuel conveying pipe is connected with a water and oil heating and decomposing pipeline which is round arranged in the combustion and the propelling nozzle. An opening of the propelling nozzle is provided with an infrared silencer which is evenly distributed with through holes. The utility model has the advantages of simple structure, high combustion temperature, large thrust, little oil consumption, low flying cost, high burnout rate, no harmful gas, and no noise pollution. The utility model is an ideal plane engine.

Description

Water-oil efficient energy-saving aircraft engine with infrared silencer

The utility model belongs to the technical field of the aerospace craft, a take energy-conserving aircraft engine of water-oil high efficiency of infrared muffler.

With the improvement of living standard, the airplane is more and more favored by urban people with high life rhythm by the characteristics of quick and comfortable transportation, so that the number of flights is increased and the flight is frequent. However, because the fuels used by various airplanes at present are pure aviation fuel, on one hand, the fuel consumption is large, the cost is high, on the other hand, the burnout rate is low, only 80-85%, and in addition, a large amount of CO and CO are generated in the combustion process₂Harmful gas is discharged into the atmosphere to form pollution. In addition, the aircraft engine generates high noise of more than 120-180 decibels during take-off, on the way and landing, and noise pollution is formed. All of the problems are the problems to be solved urgently in the existing aircraft engine.

The task of the utility model is to solve the problems existing in the prior art and provide an aircraft engine with simple structure, less oil consumption, high burnout rate, low cost and no harmful gas and noise pollution.

The utility model discloses a task is accomplished by such a technical scheme that the aircraft engine that this technical scheme demonstrates includes engine casing, intake duct, combustion chamber, impels the spray tube, fuel delivery pipe and nozzle, intake duct, combustion chamber, impel the spray tube and be located engine casing in proper order, the nozzle is installed side by side on the fuel delivery pipe in the casing, and be located between intake duct and the combustion chamber, its technical essential is that ① still includes a high temperature detector, the probe of this detector is located impels spray tube department, ② still installs water oil heating decomposition pipeline in combustion chamber and impel the spray tube, the export of this water oil heating decomposition pipeline is met with the import of fuel delivery pipe in the casing, its import is met with the export of the water oil mixing tube outside the casing, in addition still install the infrared muffler of equipartition through-hole on it in the mouth of pipe of impel the spray tube department.

When the fuel nozzle is used, pure fuel oil is firstly input, is sprayed out from the nozzle, is ignited by the electronic igniter and is mixed with air entering from the air inlet channel for combustion, and the temperature is rapidly increased. The high-temperature gas is expanded and accelerated through the propelling nozzle, and is discharged from the nozzle at high speed to generate thrust. When the temperature rises to above 1000 ℃, the high-temperature detector sends out an instruction, the water control switch is turned on, water and oil are mixed in the pipeline and enter a water-oil heating decomposition pipeline positioned in the combustion chamber and the propulsion nozzle, the temperature is raised, and the water-oil heating decomposition pipeline is decomposed according to the following formula: the decomposed combustible gas is sprayed out from the nozzle and mixed with air for combustion. The flame is similar to oxyhydrogen flame during combustion, and the temperature can reach 2800-3000 ℃, so that the generated thrust is large. Due to the fact thatThe water-oil mixed combustion is more sufficient than the fuel oil alone combustion,the flame temperature can be increased by 500-800 ℃, so that most of decomposed CO is almost completely combusted, and less CO and O are generated₂CO produced₂And CO₂And continuously decomposing, burning and releasing heat according to the following formula: therefore, the water-oil mixed decomposition combustion can discharge CO and CO compared with the combustion of fuel oil alone₂90% less. In addition, when high-temperature fuel gas is combusted and sprayed out of the propelling spray pipe, high noise generated by friction and vibration with air is eliminated due to the fact that the infrared silencer with the uniformly distributed through holes is arranged at the position of the spray pipe. Meanwhile, the silencer is made of Al₂O₃The heat-resistant material is made of a heat-resistant material, so that infrared waves are generated when high-temperature gas is combusted and sprayed out of the through hole. On one hand, infrared wave radiation promotes the water and oil in the water and oil heating decomposition pipeline positioned at the inner side of the silencer to be heated and decomposed, and on the other hand, promotes high-temperature fuel gas to be further decomposed into C, H, O atoms for combustion.

Compared with the prior art, the utility model, have following advantage:

1. simple structure, high combustion temperature, large generated thrust and capability of improving the navigational speed by 30-40%.

2. Less fuel consumption, 30-40% fuel saving and over 99.8% burning rate, almost no CO and SO₂、CO₂The harmful gas and smoke dust are discharged into the atmosphere, and the environmental pollution is reduced.

3. Because the infrared silencer is arranged, the high noise volume is reduced to below 35 decibels from 185 decibels, and high noise pollution is eliminated.

4. Because the cheap water is adopted to replace part of fuel oil, the flying cost is greatly reduced.

Description of the drawings:

fig. 1 is a schematic cross-sectional view of an embodiment of the present invention;

FIG. 2 is a schematic structural view of the infrared silencer of the present invention;

fig. 3 is a schematic structural diagram of another embodiment of the present invention.

The following examples are given in conjunction with the accompanying drawings and further illustrate the present invention.

The first embodiment is as follows:

the present embodiment is designed on the basis of an air jet engine which utilizes the speed reduction of a head-on air flow entering the engine to improve the static pressure of air, and as shown in figure 1, the air jet engine consists of an engine shell 1, an air inlet 2, a combustion chamber 3, a propulsion nozzle 4, a high temperature detector 5, a water-oil heating decomposition pipeline 7, a fuel conveying pipe 9, a nozzle 10 and an infrared silencer 11.

The air inlet 2, the combustion chamber 3 and the propulsion nozzle 3 are sequentially positioned in the engine shell 1 with small ends and large middle and in a streamline shape. The probe 6 of the high temperature detector 5 of the present embodiment is mounted in the thrust nozzle 4 through a hole formed in the casing 1. A water-oil heating decomposition pipeline 7 is also arranged in the combustion chamber 3 and the propulsion nozzle 4. The water-oil heating decomposition pipeline 7 is arranged along the inner walls of the combustion chamber 3, the propulsion nozzle 4 and the infrared silencer 11 in sequence in a surrounding way, the outlet of the water-oil heating decomposition pipeline is connected with the inlet of a fuel conveying pipe 9 positioned between the air inlet 2 and the combustion chamber 3 inthe machine shell 1, and the inlet of the water-oil heating decomposition pipeline is connected with the outlet of a water-oil mixing pipe 8 outside the machine shell 1. The nozzles 10 are arranged in parallel on the combustion outlet conduit 9. The fuel delivery pipe 9 of the present embodiment is one. The infrared silencer 11 is installed at the nozzle of the propulsion nozzle 4, the shape of this embodiment is cap-shaped, the through holes 12 are evenly distributed at the top of the cap, see fig. 2, and are fixedly connected with the end of the propulsion nozzle 4 through the screw holes 13 on the outward-turned edges by connecting pieces. Example two:

the present embodiment is designed on the basis of a gas turbine engine, and as shown in fig. 3, the present embodiment is composed of an engine casing 1, an air inlet 2, a combustion chamber 3, a propulsion nozzle 4, a high temperature detector 5, a water-oil heating decomposition pipeline 7, a water-oil mixing pipe 8, a fuel delivery pipe 9, a nozzle 10 and an infrared silencer 11.

The structures, connection relations, installation positions and the like of the engine casing 1, the air inlet 2, the combustion chamber 3, the propulsion nozzle 4, the high-temperature detector 5, the probe 6, the water-oil heating decomposition pipeline 7 and the water-oil mixing pipe 8 of the embodiment are basically the same as those of the embodiment, and therefore, the descriptions are omitted. The difference is that the fuel delivery pipe 9 of this embodiment, on which the nozzle 10 is installed, has three, is installed in parallel between the air inlet 2 and the combustion chamber 3, the inlet is communicated with the water-oil heating decomposition pipe 7, and the infrared silencer 11 has a shape like a flat-bottom bowl, and the through holes 12 are uniformly distributed at the bottom thereof, and are covered and fixedly connected with the outer side of the end of the propulsion nozzle 4 by the connectingpiece through the edgewise screw hole 13.

Claims

1. The utility model provides a take energy-efficient aircraft engine of water oil of infrared muffler, including engine housing (1), intake duct (2), combustion chamber (3), impel spray tube (4), fuel delivery pipe (9) and nozzle (10) intake duct (2), combustion chamber (3), impel spray tube (4) and be located engine housing (1) in proper order, nozzle (10) are installed side by side on fuel delivery pipe (9) to be located between intake duct (2) and combustion chamber (3), its characterized in that:

① further comprises a high temperature probe (5) having a probe head (6) located at the thrust nozzle (4);

② a water-oil heating decomposition pipeline (7) is arranged in the combustion chamber (3) and the propulsion nozzle (4), the outlet of the water-oil heating decomposition pipeline (7) is connected with the inlet of the fuel conveying pipe (9) in the machine shell (1), and the inlet is connected with the outlet of the water-oil mixing pipe (8) outside the machine shell (1);

③ an infrared silencer (11) with through holes (12) is arranged at the nozzle of the propulsion nozzle (4).

2. The water-oil efficient energy-saving aircraft engine with the infrared silencer according to claim 1 is characterized in that the water-oil heating decomposition pipeline (7) is installed in sequence around the combustion chamber (3), the propulsion nozzle (4) and the inner wall of the infrared silencer (11).

3. The water-oil efficient energy-saving aircraft engine with the infrared silencer according to claim 1 is characterized in that the fuel delivery pipe (9) provided with the nozzle (10) has 1-4 sections, and the inlet of the fuel delivery pipe is communicated with the water-oil heating decomposition pipeline (7).

4. The water-oil efficient energy-saving aircraft engine with the infrared silencer according to the claim 1, 2 or 3 is characterized in that the infrared silencer (11) is in a cap shape, the through holes (12) are evenly distributed on the top part of the cap and are fixedly connected to the end of the propulsion nozzle (4) through the connecting piece at the edge which is turned outwards.

5. The water-oil efficient energy-saving aircraft engine with the infrared silencer according to claim 1, 2 or 3 is characterized in that the infrared silencer (11) is shaped like a flat-bottom bowl, the bottom of the through holes (12) are uniformly distributed, and the through holes are wrapped and fixedly connected to the outer side of the end of the propulsion nozzle (4) by the connecting pieces along the edge.