CN111075564B - turbo rotary engine - Google Patents

Abstract

The invention discloses a turbine rotor engine which comprises a shell, a high-speed starter, a front turbine, a one-stroke combustion chamber and a rear-end turbine set, wherein a protective cover is arranged at one side end of the shell, a solid shaft is arranged in the shell, one end of the solid shaft penetrates through the protective cover and is connected with the high-speed starter, the front turbine is arranged on the left side of the solid shaft, which is positioned in the shell, the one-stroke combustion chamber is arranged on the right side of the front turbine, which is positioned on the solid shaft, and the rear-end turbine set is arranged on the right side of the one-stroke combustion chamber, which is positioned on the solid shaft. The turbine rotor engine has the advantages of simple transmission structure, saving of a compression process, improvement of transmission efficiency, sufficient fuel combustion, low manufacturing cost, avoidance of pollutant emission, improvement of working efficiency of the engine, reduction of engine tail gas pollution and belongs to a new energy environment-friendly engine.

Description

turbo rotary engine

technical field

The invention relates to an engine, in particular to a turbine rotor engine.

Background technique

An engine is a machine that can convert other forms of energy into mechanical energy, including internal combustion engines, external combustion engines, jet engines, electric motors, etc. For example, internal combustion engines usually convert chemical energy into mechanical energy. The engine is not only applicable to the power generating device, but also refers to the whole machine including the power device. The engine was first born in the UK, so the concept of the engine also comes from English, and its original meaning refers to the kind of "mechanical device that generates power".

The existing wheel engine has a simple structure and low combustion conversion efficiency, while an ordinary internal combustion engine has many transmission parts, the structure is too complicated, the cost is high and exhaust gas pollution is generated. Therefore, those skilled in the art provide a turbo rotor engine to solve the problems raised in the background art above.

SUMMARY OF THE INVENTION

The object of the present invention is to provide a turbo rotor engine to solve the problems raised in the background art above.

To achieve the above object, the present invention provides the following technical solutions:

A turbo rotor engine, comprising a casing, a high-speed starter, a front turbine, a one-stroke combustion chamber and a rear-end turbine group, a protective cover is provided at one end of the casing, and a solid shaft is arranged inside the casing, and the solid shaft One end of the shaft passes through the protective cover and is connected with the high-speed starter. The front turbine is located on the left side of the housing on the solid shaft, and a one-stroke combustion chamber is located on the right side of the front turbine on the solid shaft. The right side of the one-stroke combustion chamber is provided with a rear-end turbine group;

The one-stroke combustion chamber is a 120-degree three-blade circular turbine divided into three equal parts. The interior of the three-blade circular turbine is a hollow structure, and the one-stroke combustion chamber is equipped with an inlet port two, a high-speed pulse continuous igniter and an exhaust hole. And the second intake port includes an air intake port and a hydrogen gas intake port;

The hydrogen intake channel of the intake channel 2 of the one-stroke combustion chamber is connected to the hydrogen storage tank through a pipeline, and the air intake channel is connected to the air filter through a pipeline, and the air intake channel and the air filter pipeline are close to the air intake channel. An inlet checker is installed on one side, and a spout checker is installed on the pipeline connecting the hydrogen gas inlet and the hydrogen storage tank near the hydrogen gas inlet, and a nozzle checker is installed on the pipeline between the nozzle checker and the hydrogen storage tank. A combustible gas controller, a check valve and a flame arrester are provided in sequence, and the one-stroke combustion chamber can be replaced with a two-stroke combustion chamber, a three-stroke combustion chamber or a four-stroke combustion chamber.

As a further solution of the present invention: an air exchange channel is provided between the rear turbine group and the housing, and an air intake channel 1 is formed on the protective cover.

As a further solution of the present invention: the distances between the combustible gas controller, the check valve and the flame arrester and the hydrogen storage tank gradually increase.

As a further solution of the present invention: the two-stroke combustion chamber is a 60-degree sextant six-lobed circular turbine.

As a further solution of the present invention: the three-stroke combustion chamber is a circular turbine with nine equal parts at 40 degrees.

As a further solution of the present invention: the four-stroke combustion chamber is a 30-degree twelve-bladed circular turbine.

As a further solution of the present invention: the rear turbine group in the one-stroke combustion chamber and the two-stroke combustion chamber adopts a three-stage turbine group, and the three-stage turbine group includes a first-stage turbine, a second-stage turbine and a third-stage turbine, and the three-stage turbine One side of the group is provided with an exhaust gas inlet, the other side is provided with an exhaust port, and a heat dissipation layer is provided on the outer sides of the first-stage turbine, the second-stage turbine and the third-stage turbine.

As a further solution of the present invention: the three-stroke combustion chamber and the four-stroke combustion chamber adopt a five-stage turbine group, the difference between the five-stage turbine group and the three-stage turbine group is that there are more four-stage turbines and five-stage turbines, and the remaining structures are the same as The three-stage turbine group is the same.

As a further solution of the present invention: the turbo-rotor engine can be applied to automobile engines, small and medium-sized ship engines, small aircraft, helicopters, and propeller-type aircraft engines.

Compared with the prior art, the beneficial effects of the present invention are:

The transmission structure of the turbine rotor engine of the present invention is simple, the compression process is omitted, the transmission efficiency is improved, the fuel is fully burned, the cost is low, the pollutant discharge is avoided, the working efficiency of the engine is improved, and the exhaust gas pollution of the engine is reduced, which belongs to new energy Eco-friendly engine.

Description of drawings

Fig. 1 is a structural schematic diagram of a turbo rotor engine.

Fig. 2 is a schematic diagram of the internal structure of a one-stroke combustion chamber in a turbo rotor engine.

Fig. 3 is a schematic diagram of the structure of a one-stroke combustion chamber connected to a hydrogen storage tank and an air filter in a turbo rotor engine.

Fig. 4 is a structural schematic diagram of a two-stroke combustion chamber (a), a three-stroke combustion chamber (b) and a four-stroke combustion chamber (c) in a turbo rotor engine.

Fig. 5 is a structural schematic diagram of the one-stroke and two-stroke combustor turbine groups of the rear-end turbine group in a turbo-rotary engine.

Fig. 6 is a structural schematic diagram of the three-stroke combustion chamber and the turbine group above the three-stroke combustion chamber in a turbo rotor engine.

In the figure: 1-housing; 2-protective cover; 3-solid shaft; 4-high-speed starter; 5-front turbine; 6-one-stroke combustion chamber; 72-two-stage turbine; 73-three-stage turbine; 74-four-stage turbine; 75-five-stage turbine; 76-heat dissipation layer; 8-air exchange channel; 9-inlet one; 10-intake two; 11 -air inlet; 12-hydrogen inlet; 13-high-speed pulse continuous igniter; 14-exhaust port; 15-exhaust hole; 16-hydrogen storage tank; 17-air filter; 18-nozzle check 19-import check device; 20-combustible gas controller; 21-check valve; 22-flame retardant; 23-two-stroke combustion chamber; 24-three-stroke combustion chamber; 25-four-stroke combustion chamber.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In the embodiment of the present invention, a turbo rotor engine, as shown in Figure 1-2, includes a housing 1, a high-speed starter 4, a front turbine 5, a one-stroke combustion chamber 6 and a rear turbine group 7, the housing 1 One end of one side is provided with a protective cover 2, and the housing 1 is provided with a solid shaft 3, one end of the solid shaft 3 passes through the protective cover 2 and is connected to the high-speed starter 4, and the solid shaft 3 is located inside the housing 1. A front turbine 5 is arranged on the left side, a one-stroke combustion chamber 6 is arranged on the right side of the front turbine 5 on the solid shaft 3, and a rear turbine group 7 is arranged on the right side of the one-stroke combustion chamber 6 on the solid shaft 3;

An air exchange channel 8 is provided between the rear turbine group 7 and the casing 1, and an air intake channel 9 begins to appear on the protective cover 2;

The one-stroke combustion chamber 6 is a 120-degree three-blade circular turbine divided into three equal parts. The inside of the three-blade circular turbine is a hollow structure, and the one-stroke combustion chamber 6 is respectively provided with an air intake port 2 10, a high-speed pulse continuous igniter 13 and Exhaust hole 15, and air intake channel 2 10 comprises air intake channel 11 and hydrogen gas intake channel 12;

As shown in Figure 3, Fig. 3 is the structural representation that one-stroke combustor is connected with hydrogen storage tank, air filter, and the hydrogen gas inlet passage 12 of the intake channel two 10 of one-stroke combustion chamber 6 is connected hydrogen storage tank 16 by pipeline , the air inlet passage 11 is connected to the air filter 17 through a pipeline, and the side near the air inlet passage 11 is installed with an import checker 19 on the pipeline of the air inlet passage 11 and the air filter 17, and the hydrogen inlet passage 12 On the pipeline connected to the hydrogen storage tank 16, a nozzle checker 18 is installed on the side near the hydrogen gas inlet 12, and a combustible gas controller 20 is arranged on the pipeline between the nozzle checker 18 and the hydrogen storage tank 16 in sequence. , check valve 21 and flame retardant 22, the distance between combustible gas controller 20, check valve 21 and flame retardant 22 and hydrogen storage tank 16 gradually gradually;

As shown in Figure 4, Fig. 4 is the structural representation of two-stroke combustor 23, three-stroke combustor 24 and four-stroke combustor 25, wherein, two-stroke combustor 23 is a 60-degree sextile six-lobed circular turbine; The stroke combustion chamber 24 is a 40-degree nine-blade circular turbine; the four-stroke combustion chamber 25 is a 30-degree twelve-blade circular turbine;

When the one-stroke combustion chamber 6, the two-stroke combustion chamber 23, the three-stroke combustion chamber 24 and the four-stroke combustion chamber 25 are working, they are all intake air mixing, ignition, and exhaust, and this process is repeated like this;

As shown in Figure 5, Figure 5 is a structural schematic diagram of the specific use of the rear turbine group 7 in the one-stroke combustion chamber 6 and the two-stroke combustion chamber 23. In the one-stroke combustion chamber 6 and the two-stroke combustion chamber 23, the rear turbine Group 7 adopts a three-stage turbine group, including a first-stage turbine 71, a second-stage turbine 72 and a third-stage turbine 73, and one side of the three-stage turbine group is provided with an exhaust gas inlet, and the other side is provided with an exhaust port 14, and is located in a The outer side of the first-stage turbine 71, the second-stage turbine 72 and the third-stage turbine 73 is also provided with a cooling layer 76;

As shown in Figure 6, Figure 6 is a structural schematic diagram of the rear turbine group 7 in the three-stroke combustion chamber 24, the four-stroke combustion chamber 25, and the combustion chamber above four strokes, which is a five-stage turbine group, which is different from a three-stage turbine group Be that four-stage turbine 74 and five-stage turbine 75 are added, and all the other structures are identical with the three-stage turbine group.

In the turbine rotor engine of the present invention, hydrogen is stored in the hydrogen storage tank 16, which is the best fuel. Other fuels are also possible but must have explosive properties, and can be mixed with air to form explosive mixed gases or mixtures. Hydrogen reacts with oxygen to generate water. The reaction of other combustibles with oxygen may produce pollutants, which require tail gas treatment, and the hydrogen-oxygen combustion reactants can be directly discharged without treatment;

The hydrogen gas flows out from the hydrogen storage tank 16 and enters the one-stroke combustion chamber 6 (two/three/four-stroke combustion chamber) through the combustible gas controller 20, check valve 21, flame retardant 22 and nozzle check device 18, and the air passes through the air The filter 17 and the inlet checker 19 enter the one-stroke combustion chamber 6 (two/three/four-stroke combustion chamber), where hydrogen and oxygen are mixed. When initially starting, it is started by the high-speed starter 3, and the turbine rotates to a high-speed pulse continuous The igniter 13 ignites, and the high-temperature exhaust gas enters the rear turbine group 7 through the exhaust hole 15, and performs secondary combustion with the warmed fresh air inhaled by the front turbine 5 through the intake channel 9 to prevent insufficient combustion. After the turbine is discharged, the process is repeated.

Compared with the four-stroke gasoline and diesel engine, the turbo-rotor engine of the present invention has simple structure, saves the compression process, reduces transmission parts such as crankshaft and connecting rod, simple transmission process, improves transmission efficiency, and avoids pollution such as hydrocarbons emissions;

Compared with the rotary engine: due to the structure of the triangular rotor and the combustion chamber of the rotary engine, the combustion is uneven, the structure is simple, and the combustion efficiency is low, while the structure of the turbine rotor engine is relatively complex, the structure of the combustion chamber and the combustion efficiency are better than the rotary engine, and pollution is avoided emissions;

Compared with the turboprop engine: the structure is simple, the front high-pressure turbine group and the combustion chamber are omitted, the cost is low, and the emission of pollutants is avoided;

The turbo rotor engine can be applied to automobile engines, small and medium-sized ship engines, small aircrafts, helicopters, propeller aircraft engines and the like.

The above description is only a preferred embodiment of the present invention, but the protection scope of the present invention is not limited to this. The equivalent replacement or change of the inventive concept thereof shall be included within the protection scope of the present invention.

Claims (7)

1. A turbine rotor engine is characterized by comprising a shell (1), a high-speed starter (4), a front turbine (5), a one-stroke combustion chamber (6) and a rear-end turbine set (7), wherein a protective cover (2) is arranged at one side end of the shell (1), a solid shaft (3) is arranged in the shell (1), one end of the solid shaft (3) penetrates through the protective cover (2) and is connected with the high-speed starter (4), the front turbine (5) is arranged on the left side, located inside the shell (1), of the solid shaft (3), the one-stroke combustion chamber (6) is arranged on the right side, located on the front turbine (5), of the solid shaft (3), and the rear-end turbine set (7) is arranged on the right side, located on the one-stroke combustion chamber (6), of the solid shaft (3);

the one-stroke combustion chamber (6) is a 120-degree trisection three-blade circular turbine, the interior of the three-blade circular turbine is of a hollow structure, an air inlet channel II (10), a high-speed pulse continuous igniter (13) and an exhaust hole (15) are respectively arranged on the one-stroke combustion chamber (6), and the air inlet channel II (10) comprises an air inlet channel (11) and a hydrogen inlet channel (12);

a hydrogen inlet channel (12) of an inlet channel II (10) of the one-stroke combustion chamber (6) is connected with a hydrogen storage tank (16) through a pipeline, the air inlet channel (11) is connected with an air filter (17) through a pipeline, an inlet non-return device (19) is arranged on one side, close to the air inlet channel (11), of the pipeline of the air inlet channel (11) and the air filter (17), a spout non-return device (18) is arranged on one side, close to the hydrogen inlet channel (12), of the pipeline of the hydrogen inlet channel (12) and the hydrogen storage tank (16), a combustible gas controller (20), a check valve (21) and a flame retardant device (22) are sequentially arranged on the pipeline between the spout non-return device (18) and the hydrogen storage tank (16), and the one-stroke combustion chamber (6) can be replaced by a two-stroke combustion chamber (23), a three-stroke combustion chamber (24) or a four-stroke combustion chamber (25);

a rear end turbine group (7) in the first-stroke combustion chamber (6) and the two-stroke combustion chamber (23) adopts a three-stage turbine group, the three-stage turbine group comprises a first-stage turbine (71), a second-stage turbine (72) and a third-stage turbine (73), one side of the three-stage turbine group is provided with a waste gas inlet, the other side of the three-stage turbine group is provided with an exhaust port (14), and a heat dissipation layer (76) is arranged on the outer sides of the first-stage turbine (71), the second-stage turbine (72) and the third-stage turbine (73);

a five-stage turbine group is adopted in the three-stroke combustion chamber (24) and the four-stroke combustion chamber (25), the five-stage turbine group is different from the three-stage turbine group in that a four-stage turbine (74) and a five-stage turbine (75) are added, and the rest structure is the same as that of the three-stage turbine group.

2. A turbo-rotor engine according to claim 1, characterized in that a scavenging duct (8) is provided between the rear turbine group (7) and the casing (1), and the first inlet duct (9) starts on the shroud (2).

3. A turbine rotor engine according to claim 1, characterised in that the combustible gas controller (20), the non-return valve (21) and the flame arrester (22) are located at successively greater distances from the hydrogen storage tank (16).

4. A turbine rotor engine according to claim 1, characterised in that the two-stroke combustion chamber (23) is a 60 degree six-lobed circular turbine.

5. A turbo-rotor engine according to claim 1, characterized in that said three-stroke combustion chamber (24) is a 40 degree nine-lobed circular turbine.

6. A turbo-rotor engine according to claim 1, characterized in that said four-stroke combustion chamber (25) is a 30 degree twelve-segment ten-two-blade circular turbine.

7. The turbine rotor engine as claimed in claim 1, wherein the turbine rotor engine is applicable to automobile engines, small and medium sized ship engines, small aircraft, helicopters, and propeller type aircraft engines.

Images