Rotary jet engine

Abstract

The rotary jet engine is composed of a stator ring groove, a rotor, a combustion chamber, thrust helical teeth or thrust blades, an exhaust hole 2 and an exhaust port 3. The rotary jet engine is characterized in that the thrust helical teeth 4 or the thrust blades 13 arranged on the circumference of the rotor 5 are located in the stator ring groove 1; a combustion chamber 9 is arranged above one side of the stator ring groove 1, high-pressure fuel pressurized by a pressurizing device enters the combustion chamber 9 through a high-pressure pipe 8, and after the high-pressure fuel is ignited by an ignition device in the combustion chamber 9, generated high-temperature and high-pressure gas is communicated with a combustion chamber nozzle on the stator ring groove 1 through the combustion chamber 9. And the high-speed jet is sprayed to the vertical surfaces of the rotor thrust helical teeth 4 or the thrust blades 13 in the stator ring groove 1 to push the rotor 5 to rotate at a high speed, and power is output through the rotor rotating shaft 7. The device has the advantages of being simple in structure, free of crankshaft transmission, high in efficiency and low in noise. Ethanol fuel can be directly used, greenhouse gas emission is reduced, and dependence on fossil fuel is reduced and abandoned.

Description

Technical Field

[0001] The present invention provides a power device, specifically a power device that generates thrust by fuel combustion. Background Technology

[0002] Currently, the most widely used engines include rocket jet engines, turbine engines, cylinder piston engines, and rotary engines. Among them, rocket jet engines propel forward by burning fuel in the tail nozzle and ejecting high-temperature, high-pressure gas; turbine engines propel forward by compressing air and fuel in the turbine and then burning it in the tail; and cylinder piston engines output power by burning fuel in the cylinder to drive the piston and crankshaft.

[0003] Rocket engines and turbine engines have the advantage of high thrust and are widely used in the aerospace field. Their disadvantages include high noise levels and severe exhaust emissions, impacting the environment. Cylinder engines are widely used in automobiles and general power applications. Their disadvantages include a complex piston-crankshaft transmission system, a tendency for carbon buildup and incomplete combustion within the cylinder, fuel combustion within the cylinder, high vibration and noise levels, and severe exhaust emissions that negatively impact the environment.

[0004] Another type of rotary engine uses fuel combustion inside the casing to drive an internal rotor that is eccentrically mounted on a drive shaft. Its disadvantages are that the eccentric gear meshing transmission is noisy, wears a lot, has a short service life, and produces serious exhaust emissions, which affects the environment. Summary of the Invention

[0005] The purpose of this invention is to provide an engine that generates thrust by fuel combustion. This invention is achieved by the following technical solutions.

[0006] The rotary injection engine comprises a stator annular groove, a rotor, a combustion chamber, thrust helical teeth or thrust blades, and exhaust ports 2 and 3. Its key feature is that the thrust helical teeth 4 or thrust blades 13 arranged on the circumference of the rotor 5 are located within the stator annular groove 1. A combustion chamber 9 is located above the stator annular groove 1. High-pressure fuel, pressurized by a booster, enters the combustion chamber 9 through a high-pressure pipe 8 and is ignited by an ignition device within the combustion chamber 9. The resulting high-temperature, high-pressure gas is injected at high speed through the combustion chamber nozzle on the stator annular groove 1, connected to the combustion chamber 9, and is directed towards the vertical surface of the rotor thrust helical teeth 4 or thrust blades 13 within the stator annular groove 1. This propels the rotor 5 to rotate at high speed and outputs power through the rotor shaft 7. As the thrust helical teeth or thrust blades rotate, the high-temperature, high-pressure gas reaches the exhaust ports 3 and 2 and is discharged from them.

[0007] A high-pressure air inlet can be provided on the stator ring groove, through which a high-pressure air pump 10 supplies fresh air to the stator ring groove to increase oxygen.

[0008] The fuel that enters the combustion chamber 9 through the high-pressure pipe 8 can be a flammable liquid fuel such as gasoline or ethanol, or a flammable gas fuel such as liquefied petroleum gas or natural gas. The fuel that enters the combustion chamber 9 through the high-pressure pipe 8 can be pre-mixed with air or oxygen by a pressure device.

[0009] The combustion chamber 9 and its nozzle on the stator annular groove 1 are located on the circumferential tangent of the stator annular groove.

[0010] The rotor 5 has a rotating shaft 7 mounted on the connecting components (end covers) 11 at both ends of the stator ring groove 1 via bearings 12.

[0011] The thrust blade 13 or the thrust helical tooth is provided with rotor annular grooves 14 on both sides, so that the high-speed airflow ejected from the combustion chamber 9 nozzle is more concentrated between the combustion chamber nozzle and the vertical surface of the thrust blade 13 or the thrust helical tooth, thereby increasing the thrust.

[0012] The combustion chamber 9 can also be located on the side of the stator annular groove 1. The combustion chamber 9 is connected to the side of the stator annular groove 1 through the inclined surface 15 at the front end, thereby forming an inclined nozzle on the side of the combustion chamber. The high-speed airflow ejected from it enters the stator annular groove through the nozzle along the direction of the inclined surface 15, and is sprayed onto the vertical surface of the thrust blades or thrust helical teeth in the stator annular groove 1, thereby driving the rotor to rotate.

[0013] The thrust helical teeth or thrust blades on the rotor may also be located on the side of the rotor, with their vertical surfaces facing the nozzle of the combustion chamber.

[0014] The inner side of the thrust blade 13 or thrust helical tooth located on one side of the rotor may be provided with a rotor annular groove 16, and the outer side may be provided with a rotor annular groove 17.

[0015] The rotary injection engine consists of an outer rotor annular groove, an inner stator, a high-pressure pipe, a combustion chamber, and thrust helical teeth or thrust blades. Its key feature is that the outer rotor annular groove 18 is equipped with thrust helical teeth 4 or thrust blades 13; the inner stator 19 is located within the outer rotor annular groove 18, and the combustion chamber 9, with its nozzle facing the vertical surface of the thrust helical teeth 4 or thrust blades 13, is supplied with fuel by the high-pressure pipe 8. When the fuel enters the combustion chamber 9 and is ignited by the ignition device, the resulting high-temperature, high-pressure gas is injected from the combustion chamber 9 nozzle towards the vertical surface of the thrust helical teeth 4 or thrust blades 13, thereby driving the outer rotor annular groove 18 to rotate at high speed.

[0016] The outer rotor annular groove 18 is mounted on the bearing 12 of the fixed shaft 20 of the inner stator via connecting members (end caps) 11 at both ends.

[0017] In application, the high-pressure pipe 8 is inserted through the center hole of the inner stator 19 fixing shaft 20 and connected to the combustion chamber 9.

[0018] The advantages of this invention are its simple structure, elimination of crankshaft transmission, high efficiency, low failure rate, low noise, and long service life. It allows for the direct use of alcohol fuel, significantly reducing greenhouse gas emissions and having significant environmental implications. Furthermore, ethanol can be produced from biological resources (such as crops), greatly reducing dependence on fossil fuels. The figure shows

[0019] Figure 1 Front view of the stator annular groove

[0020] Figure 1-1 for Figure 1 3D image

[0021] Figure 2 Front view of the rotor

[0022] Figure 2-1 for Figure 2 Side view of the middle rotor

[0023] Figure 3 A schematic diagram showing the rotor located within the stator annular groove.

[0024] Figure 3-1 for Figure 3 Side view diagram

[0025] Figure 3-2 A schematic diagram showing the rotor shaft mounted on the stator annular groove via bearings.

[0026] Figure 4 Schematic diagram of mounting thrust blades on a rotor

[0027] Figure 4-1 for Figure 4 Schematic diagram of the rotor located in the stator annular groove

[0028] Figure 4-2 for Figure 4 Schematic diagram of adding blade annular grooves on both sides of a medium-thrust blade.

[0029] Figure 5 A schematic diagram showing the combustion chamber located on one side of the stator annular groove.

[0030] Figure 5-1 A schematic diagram showing the thrust blades located on one side of the rotor.

[0031] Figure 5-2 Schematic diagram of blade annular grooves above the thrust blades on the rotor

[0032] Figure 6 A three-dimensional view of the outer rotor annular groove.

[0033] Figure 6-1 A schematic diagram of thrust helical teeth installed in the outer rotor annular groove.

[0034] Figure 6-2 3D view of the inner stator and fixed shaft

[0035] Figure 6-3 A schematic diagram showing the inner stator located within the outer rotor annular groove.

[0036] Figure 6-4 for Figure 6-3 Side view

[0037] Figure 6-5 A schematic diagram showing the thrust blades installed within the annular groove of the outer rotor.

[0038] Figure 6-6 Schematic diagram of the outer rotor annular groove mounted on the inner stator shaft via bearings. Detailed Implementation

[0039] The present invention will now be further described with reference to the accompanying drawings. Example 1

[0040] See Figure 1 , Figure 2 , Figure 3 , Figure 3 and Figure 3-1 As shown, the thrust helical teeth 4 arranged on the circumference of the rotor 5 are located within the stator annular groove 1; a combustion chamber 9 is arranged above the stator annular groove 1 (see Figure 1). Figure 3-1 The high-pressure fuel, pressurized by the booster, enters the combustion chamber 9 through the high-pressure pipe 8. Ignition by the ignition device in the combustion chamber 9 produces high-temperature, high-pressure gas, which is then injected at high speed through the combustion chamber nozzle connected to the stator annular groove 1. This gas is directed towards the vertical surface 6 (shown by the dashed arrow in the figure) of the rotor thrust helical teeth 4 within the stator annular groove 1, thereby driving the rotor 5 to rotate at high speed and outputting power through the rotor shaft 7. As the thrust helical teeth rotate, the high-temperature, high-pressure gas reaches the exhaust port 3 and exhaust hole 2, where it is discharged. Simultaneously, fresh air is also input through the exhaust port 3 and exhaust hole 2.

[0041] In applications, a high-pressure air pump 10 can also deliver fresh air to the stator ring groove through the air inlet pipe and air inlet to increase oxygen levels. Figure 3-1 As shown, the air intake port is located between the combustion chamber 9 nozzle and the exhaust port 2 and exhaust port 3 on the stator ring groove.

[0042] In application, the fuel sent into the combustion chamber 9 through the high-pressure pipe 8 can be a flammable liquid such as gasoline or ethanol, or a flammable gas such as liquefied petroleum gas or natural gas.

[0043] In application, the fuel entering the combustion chamber 9 through the high-pressure pipe 8 can be pre-mixed with air or oxygen through a pressure device.

[0044] In application, the combustion chamber 9 and its nozzle on the stator annular groove 1 are located on the circumferential tangent of the stator annular groove 1.

[0045] In application, the shaft 7 on rotor 5 is mounted on the connecting member (end cover) 11 at both ends of stator annular groove 1 via bearing 12 (see...). Figure 3-2 ).

[0046] In applications, the thrust helical teeth on the rotor can be replaced by thrust blades 13 (see [reference]). Figure 4 The high-speed airflow ejected from the nozzle of combustion chamber 9 is sprayed onto the vertical surface of thrust blades 13 on rotor 5, driving the rotor to rotate at high speed (see...). Figure 4-1 In applications, rotor annular grooves 14 can also be added to both sides of the thrust blade 13 (see...). Figure 4-2 This concentrates the high-speed airflow ejected from the combustion chamber nozzle 9 between the combustion chamber nozzle and the vertical surface of the thrust blade 13, increasing thrust. In applications, rotor ring grooves can also be installed on both sides of the thrust helical teeth.

[0047] In applications, the combustion chamber 9 can also be located on the side of the stator annular groove 1 (see...). Figure 5 The combustion chamber 9 is connected to the side of the stator annular groove 1 via the inclined surface 15 at the front end of the combustion chamber 9, thereby forming an inclined nozzle on the side of the combustion chamber. The high-speed airflow ejected from the combustion chamber enters the stator annular groove through the nozzle along the inclined surface 15 and is sprayed onto the vertical surface of the thrust blades or thrust helical teeth on the rotor in the stator annular groove 1, thereby driving the rotor to rotate.

[0048] In applications, thrust helical teeth and thrust blades can also be located on the side of rotor 5, with their vertical surfaces facing the nozzle of combustion chamber 9. Figure 5-1 As shown, the thrust blade 13 is disposed on the side of the rotor 5. When the thrust blade on the rotor is located in the stator annular groove, the oblique nozzle on the combustion chamber 9 faces the vertical surface of the thrust blade 11 on the rotor 5 (see Figure 1). Figure 5 In applications, a rotor annular groove 16 can be provided on the inner side of the thrust blade located on one side of the rotor (see...). Figure 5-1 The outer side of the rotor can be provided with a rotor annular groove 17 (see...). Figure 5-2 This concentrates the high-speed airflow more between the combustion chamber nozzle and the vertical surface of the thrust blade 13, increasing thrust. In applications, thrust helical teeth can also be used instead of thrust blades and set on the side of the rotor, with rotor annular grooves set on the inner and outer sides to increase thrust.

[0049] In application, the part of rotor 5 located in the stator annular groove maintains a small clearance with the stator annular groove to ensure a high-pressure state between the combustion chamber 9 and the thrust helical teeth or thrust plane on rotor 5.

[0050] In applications, thrust helical gears, due to their high structural rigidity, high temperature resistance, and strong impact resistance, are mainly used in large, high-power, high-thrust rotary jet engines; thrust blades are mainly used in low-power rotary jet engines. Both thrust helical gears and thrust blades are manufactured using high-temperature resistant materials. Example 2

[0051] See Figure 6 , Figure 6-1 The outer rotor annular groove 18 is provided with thrust helical teeth 4; Figure 6-2 The inner stator 19 is located within the outer rotor annular groove 18 (see...) Figure 6-3 The combustion chamber 9 on the inner stator 19 has its nozzle facing the vertical surface 6 of the thrust helical tooth 4. The combustion chamber 9 is supplied with fuel by the high-pressure pipe 8. When the fuel enters the combustion chamber 9 and is ignited by the ignition device, the high-temperature and high-pressure gas generated is injected from the nozzle of the combustion chamber 9 toward the vertical surface 6 of the thrust helical tooth 4, thereby driving the outer rotor annular groove 18 to rotate at high speed.

[0052] In applications, the thrust helical teeth 4 located in the outer rotor annular groove 18 can be replaced by thrust blades 13 (see [reference]). Figure 6-5 ).

[0053] In application, the outer rotor annular groove 18 is mounted on the bearing 12 of the fixed shaft 20 of the inner stator 19 via connecting members (end caps) 11 at both ends (see [reference]). Figure 6-6 ).

[0054] In application, the high-pressure pipe 8 is inserted through the center hole of the fixed shaft 17 and connected to the combustion chamber 9.

Claims

1. A rotary injection engine comprises a stator annular groove, a rotor, a combustion chamber, thrust helical teeth or thrust blades, and exhaust ports and exhaust outlets, characterized in that: The thrust helical teeth (4) or thrust blades (13) arranged on the circumference of the rotor (5) are located in the stator annular groove (1); a combustion chamber (9) is arranged above the stator annular groove (1). The high-pressure fuel pressurized by the booster device enters the combustion chamber (9) through the high-pressure pipe (8). After being ignited by the ignition device in the combustion chamber (9), the generated high-temperature and high-pressure gas is injected at high speed into the vertical surface of the rotor thrust helical teeth (4) or thrust blades (13) in the stator annular groove (1) through the combustion chamber nozzle connected to the combustion chamber (9) in the stator annular groove (1), driving the rotor (5) to rotate at high speed and outputting power through the rotor shaft (7); as the thrust helical teeth or thrust blades rotate, when the high-temperature and high-pressure gas reaches the position of the exhaust port (3) and exhaust hole (2), it is discharged from the exhaust port (3) and exhaust hole (2).

2. A rotary injection engine comprises an outer rotor annular groove, an inner stator, a high-pressure pipe, a combustion chamber, and thrust helical teeth or thrust blades, characterized in that: The outer rotor annular groove (18) is provided with thrust helical teeth (4) or thrust blades (13); the inner stator (19) is located in the outer rotor annular groove (18), and the combustion chamber (9) provided on the inner stator (19) faces the vertical surface of the thrust helical teeth (4) or thrust blades (13). The combustion chamber (9) is supplied with fuel by the high-pressure pipe (8). When the fuel enters the combustion chamber (9) and is ignited by the ignition device, the generated high-temperature and high-pressure gas is sprayed from the combustion chamber (9) nozzle toward the vertical surface of the thrust helical teeth (4) or thrust blades (13), thereby driving the outer rotor annular groove (18) to rotate at high speed.

3. The rotary jet engine according to claim 1, characterized in that: A high-pressure air inlet can be provided on the stator ring groove, through which a high-pressure air pump (10) delivers fresh air into the stator ring groove.

4. The rotary jet engine according to claim 1, characterized in that: The combustion chamber (9) and its nozzle on the stator annular groove (1) are located on the circumferential tangent of the stator annular groove; or the combustion chamber (9) is located on the side of the stator annular groove (1), and is connected to the side of the stator annular groove 1 through the inclined surface (15) at the front end of the combustion chamber (9), thereby forming an inclined nozzle on the side of the combustion chamber, so that the high-speed airflow ejected from it enters the stator annular groove through the nozzle along the direction of the inclined surface (15), and is sprayed toward the vertical surface of the thrust blade or thrust helical tooth in the stator annular groove (1), thereby driving the rotor to rotate.

5. The rotary jet engine according to claim 1, characterized in that: The shaft (7) on the rotor (5) is mounted on the end cap (11) of the connecting member at both ends of the stator ring groove (1) via bearing (12).

6. The rotary jet engine according to claim 1, characterized in that: The thrust blade (13) or thrust helical tooth is provided with rotor ring grooves (14) on both sides, so that the high-speed airflow ejected from the combustion chamber (9) nozzle is more concentrated between the combustion chamber nozzle and the vertical surface of the thrust blade (13) or thrust helical tooth.

7. The rotary jet engine according to claim 1, characterized in that: The thrust helical teeth or thrust blades on the rotor may also be located on the side of the rotor, with their vertical surfaces facing the nozzle of the combustion chamber.

8. The rotary jet engine according to claim 1 or claim 7, characterized in that: The inner side of the thrust blade (13) or thrust helical tooth located on one side of the rotor may be provided with a rotor annular groove (16), and the outer side may be provided with a rotor annular groove (17).

9. The rotary jet engine according to claim 2, characterized in that: The outer rotor annular groove (18) is mounted on the bearing (12) of the fixed shaft (20) of the inner stator via end caps (11) of the connecting members at both ends.

10. The rotary jet engine according to claim 2, characterized in that: The high-pressure pipe (8) is inserted through the center hole of the inner stator (19) fixing shaft (20) and connected to the combustion chamber (9).

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