Gas turbine

Abstract

The invention provides a gas turbine. Comprising a shell, an air inlet channel, a rotor, a piston assembly, an output assembly, a combustion chamber and an exhaust channel. The air inlet channel is arranged at the top of the machine shell and provided with an air inlet carburetor connector. The rotor is concentrically assembled in the shell, and a cylinder barrel and air inlet and outlet holes are radially arrayed at the front end; a turbine and blades are arrayed at the rear end; the piston assembly comprises an eccentric shaft, a connecting rod and a piston; the eccentric shaft is in sliding connection with the piston through a connecting rod, the piston reciprocates in the cylinder barrel around the eccentric shaft along with the rotor, and the eccentric shaft is fixed on the front end cover in a cantilever manner; the output assembly is arranged at the rear end cover end of the machine shell. One end of the combustion chamber radially corresponds to an intake and exhaust hole of the cylinder barrel, and the other end radially corresponds to the turbine excircle; the exhaust channel is arranged at the side end of the machine shell and radially corresponds to the outer circle of the turbine. The radius of the turbine and the number of the blades are increased; the combustion chamber is arranged outside the machine shell, and fuel gas is ignited and exploded in the combustion chamber through a spark plug. And the service life is prolonged.

Description

Technical Field

[0001] This invention relates to turbines in the field of gas turbines, and more particularly to a gas turbine. Background Technology

[0002] A gas turbine is a type of thermal engine based on the Brayton cycle. Its core working process is: intake → compression → combustion → expansion to do work → exhaust, through which the chemical energy of fuel is efficiently converted into mechanical energy.

[0003] Chinese Patent Publication No. CN10120688A discloses a piston rotor internal combustion engine, which describes that: an eccentric shaft 1 and a power output shaft 2 are respectively installed on both sides of the engine housing 3, an intake duct 4 and an exhaust duct 6 are provided on one side of the engine housing, and a combustion chamber 5 is provided on the other side.

[0004] Four rotor pistons are symmetrically cross-mounted inside the housing via an outer piston mounting ring 8 and an inner piston mounting ring 9. Each piston rod 12 is slidably connected to the eccentric shaft 1. The connecting rod 12 is connected to the piston 13, which is slidably connected within the cylinder.

[0005] A scroll 15 is installed between each adjacent cylinder 11, and the scroll 15 is provided with a scroll through rod 15.1 and a scroll spring 15.2.

[0006] A cylinder spring 14 is installed outside the cylinder block 11.

[0007] An intake passage 4 and an exhaust passage 6 are provided on the outer side of the outer piston mounting ring 8, and a combustion chamber 5 is provided, in which an igniter 7 is installed.

[0008] However, in the process of implementing the technical solutions of the embodiments of this application, the inventors of this application discovered that the above technical solutions have at least the following technical problems: 1. A vortex vane 15 is installed between each adjacent cylinder 11. The piston 13 and the vortex vane 15 are staggered. The radius and number of the vortex vane 15 are limited, and the efficiency of the vortex vane 15 in doing work is low. 2. An intake manifold 4 and an exhaust manifold 6 are located on the outer side of the outer piston mounting ring 8, along with a combustion chamber 5. (Refer to the attached instruction manual.) Figure 2 As can be seen, the combustion chamber 5 is directly connected to the cylinder block 11, which means that the combustion gas ignites and explodes in the cylinder block 11, driving the turbine blades 15 to do work. This inevitably causes damage, and the service life of the cylinder block 11 is limited. Summary of the Invention

[0009] To address the shortcomings of existing technologies and improve the service life and thermal efficiency of gas turbines, this application provides a gas turbine. This gas turbine improves thermal efficiency by having the turbine and rotor of the same diameter, increasing the turbine radius and the number of blades, and placing the combustion chamber outside the casing to allow combustible gas to ignite and explode within the combustion chamber, thus avoiding damage to the cylinder and piston and extending the service life of the gas turbine.

[0010] The solution adopted by the embodiments of this application to solve the technical problem is: A gas turbine includes a housing, an intake passage, a rotor, a piston assembly, an output assembly, a combustion chamber, and an exhaust passage; The casing has a cylindrical structure with a front cover at one end and a rear cover at the other end; The intake passage has an arc-shaped structure and is located on the top of the engine casing; an intake carburetor interface is located at the end of the intake passage. The rotor is a hollow cylindrical structure, concentrically assembled inside the housing, and has a receiving cavity including a cylinder, a turbine, a sealing ring, and a front bearing. The cylinders are arranged radially in the receiving cavity near the front end cover, and the top of the cylinders has an intake and exhaust port with a sealing ring. A ring-groove turbine is provided near the rear end cover, with blades arranged at an inclined angle. An inner sleeve is provided along the axis of the turbine, and sealing rings are arranged on the outer circumference of the rotor. A bearing support seat is provided near the front end cover of the rotor for assembling the front bearing. The piston assembly is located at the front end of the housing and includes an eccentric shaft, a connecting rod connecting plate, a connecting rod, and a piston. The eccentric shaft is not concentric with the housing and rotor, and is fixed to the front cover in a cantilever manner; the piston is assembled inside the cylinder; the connecting rod connecting plate is assembled on the eccentric shaft; the connecting rod is connected to the piston at one end by a pin, and the other end is connected to the connecting rod connecting plate; the eccentric shaft is slidably connected to the piston, and the piston reciprocates around the eccentric shaft inside the cylinder when it accompanies the rotor. The output components are located at the rear end of the housing and include the output shaft, rear bearing, and flywheel. One end of the output shaft is provided with a flange that is connected to the inner sleeve along the turbine; a rear bearing is assembled on the output shaft, and the rear bearing, housing, rotor, and front bearing are concentric, forming a rotational support for the rotor through the limit of the rear end cover; a flywheel is assembled at the extended end of the output shaft. The combustion chamber is located on the side of the engine casing, with one end radially corresponding to the intake and exhaust ports of the cylinder and the other end radially corresponding to the outer circle of the turbine; a spark plug is installed on the combustion chamber. The exhaust passage is located on the other side of the casing, radially corresponding to the outer circle of the turbine; The cylinder and turbine are arranged on the rotor, forming two independent units, which increases the radius of the turbine and the number of blades; the combustion chamber is located outside the casing, and the combustible gas is ignited and exploded in the combustion chamber.

[0011] In order to further solve the technical problems to be solved by the embodiments of this application, the gas turbine provided by the embodiments of this application has an eccentric shaft that is not concentric with the casing and the rotor, and the eccentric distance of the eccentric shaft is half of the piston reciprocating stroke.

[0012] Furthermore, the turbine and rotor are concentric and have the same diameter, so that the turbine blades can be continuously propelled when the rotor rotates.

[0013] Furthermore, the combustion chamber is designed as an annular or cylindrical shape, with its inner walls resistant to high temperatures and equipped with a cooling system.

[0014] Furthermore, the side of the engine casing is provided with a combustion chamber input interface and a combustion chamber output interface; one end of the combustion chamber is connected to the combustion chamber input interface, and the other end is connected to the combustion chamber output interface; an exhaust interface is provided on the other side of the engine casing for connecting to the exhaust passage.

[0015] Furthermore, the cylinder is matched with the piston and connecting rod.

[0016] Positive effects: The technical solutions provided in this application embodiment have at least the following technical effects or advantages: 1. Because the embodiments of this application use a piston that is slidably connected to the eccentric shaft in the cylinder inside the rotor, the technical problems of low compression efficiency and complex structure of gas turbines in the prior art are effectively solved. The rotor rotates in the housing, the cylinder rotates with the rotor, and the piston rotates in the cylinder while reciprocating around the eccentric shaft, thereby achieving the technical effects of intake, compression and exhaust strokes of the gas turbine.

[0017] 2. Because the embodiments of this application adopt the technical means of separating the cylinder and turbine on the rotor to form two independent units, and the turbine and rotor have the same diameter, the radius of the turbine and the number of blades are increased, which effectively solves the technical problem of low thermal efficiency of gas turbines in the prior art. The blades can be continuously pushed every time the turbine rotates. The radius of the turbine is larger than the crank radius of the crankshaft of the piston engine. Under the same displacement and fuel consumption, more power density and greater output power can be obtained at a lower speed, thereby achieving the technical effect of improving the thermal efficiency of the gas turbine.

[0018] 3. As this application embodiment adopts the technical means of setting the combustion chamber outside the casing, one end of the combustion chamber is radially corresponding to the intake and exhaust ports of the cylinder, and the other end is radially corresponding to the outer circle of the turbine. The combustible mixture enters the combustion chamber from the cylinder under the push of the piston. The combustible gas ignites and explodes in the combustion chamber. The ignited mixture drives the turbine blades to rotate and do work, generating torque output power. This effectively solves the technical problem of cylinder and piston damage in the prior art, thereby achieving the technical effect of improving the service life of the gas turbine.

[0019] It is suitable for use as a gas turbine. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is the southeast isometric view of this embodiment; Figure 2 This is the southwest isometric view of this embodiment; Figure 3 This is the front view of this embodiment; Figure 4 This is the rear view of this embodiment; Figure 5 This is the northwest isometric view of this embodiment; Figure 6 This is the southeast isometric view of this embodiment; Figure 7 This is the left view of this embodiment; Figure 8 This is an isometric view of section AA in this embodiment; Figure 9 This is an isometric view of section BB in this embodiment; Figure 10 This is the right view of this embodiment; Figure 11 This is a CC cross-sectional view of this embodiment; Figure 12 This is a DD cross-sectional view of this embodiment; Figure 13 This is a top view of this embodiment; Figure 14 This is a cross-sectional view of EE in this embodiment; Figure 15 This is a cross-sectional view of FF in this embodiment; Figure 16This is a 1 / 4 isometric view of the GG section in this embodiment; Figure 17 This is a 1 / 4 isometric view of the HH section in this embodiment; Figure 18 This is a 1 / 4 southeast isometric view of the casing; Figure 19 This is a 1 / 4 northwest isometric view of the casing; Figure 20 This is a 1 / 4 southeast isometric view of the rotor; Figure 21 This is a 1 / 4-degree isometric view of the rotor from the northwest.

[0022] In the picture: 100. Housing, 110. Front cover, 120. Rear end cover 130. Exhaust port, 140. Combustion chamber input interface, 150. Combustion chamber output interface; 200. Air intake passage, 210. Intake carburetor interface, 300. Rotor 310. Cylinder barrel, 311. Inlet and outlet ports, 320. Turbo, 321. Leaf blade 330. Sealing ring, 340. Front bearing; 400. Piston assembly, 410. Eccentric shaft, 411. Lubrication channel, 420. Linkage connecting plate, 430. Connecting rod, 440. Piston; 500. Output component, 510. Output shaft, 520. Rear bearing, 530. Flywheel; 600. Combustion chamber, 610. Spark plugs; 700. Exhaust passage. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0024] This application provides a gas turbine that solves the problems of low service life and low thermal efficiency in existing gas turbines. By using a turbine with the same diameter as the rotor, increasing the turbine radius and the number of blades, the thermal efficiency of the gas turbine is improved. By placing the combustion chamber outside the casing, the combustible gas is ignited and exploded inside the combustion chamber, avoiding damage to the cylinder and piston, thus improving the service life of the gas turbine.

[0025] According to the instruction manual Figure 1-21 As shown, a gas turbine includes a housing 100, an intake passage 200, a rotor 300, a piston assembly 400, an output assembly 500, a combustion chamber 600, and an exhaust passage 700. The housing 100 has a cylindrical structure and is used as the main assembly body of a gas turbine. A front cover 110 is provided at one end of the housing 100 and a rear cover 120 is provided at the other end. The intake channel 200 has an arc-shaped structure and is located on the top of the housing 100. It is used to guide ambient air into the housing 100. An intake carburetor interface 210 is provided at the end of the intake channel 200 to connect to the intake carburetor, ensuring smooth airflow and minimizing the intake of impurities. The rotor 300 is a hollow cylindrical structure, concentrically assembled within the housing 100, and has a receiving cavity including a cylinder 310, a turbine 320, a sealing ring 330, and a front bearing 340. The cylinders 310 are arranged radially in the receiving cavity near the front end cover 110, and the top of each cylinder 310 has an intake / exhaust port 311 with a sealing ring. A ring-groove turbine 320 is located near the rear end cover 120, with blades 321 arranged at an inclined angle to utilize the high temperature and pressure of the combustion gas to drive the turbine 320 to rotate. An inner sleeve is provided along the axis of the turbine 320. Sealing rings 330 are arranged on the outer circumference of the rotor 300 to prevent combustion gas leakage and lubricating oil ingress. A bearing support seat is located near the front end cover 110 of the rotor 300 to assemble the front bearing 340 and support the rotor 300 to rotate within the housing 100. The piston assembly 400 is located at the front end cover 110 of the housing 100 and includes an eccentric shaft 410, a connecting rod connecting plate 420, a connecting rod 430 and a piston 440. The eccentric shaft 410 is a stepped shaft, which is not concentric with the housing 100 and the rotor 300, and is fixed to the front cover 110 in a cantilever manner. Piston 440 is assembled inside cylinder 310. The connecting rod connecting plate 420 is mounted on the eccentric shaft 410; The connecting rod 430 is a structural rod, which is connected to the piston 440 at one end by a pin and connected to the connecting rod connecting plate 420 at the other end. The eccentric shaft 410 and the piston 440 are slidably connected by the connecting rod 430. When the piston 440 accompanies the rotor 300, it also reciprocates around the eccentric shaft 410 in the cylinder 310 to compress the air entering the cylinder 310, thereby significantly increasing its pressure and temperature. The output assembly 500 is located at the rear end cover 120 of the housing 100 and includes an output shaft 510, a rear bearing 520 and a flywheel 530. The output shaft 510 is a stepped shaft, with a flange at one end connected to the inner sleeve of the turbine 320. A rear bearing 520 is mounted on the output shaft 510. The rear bearing 520 is concentric with the housing 100, the rotor 300, and the front bearing 340. It is limited by the rear end cover 120 to form a rotational support for the rotor 300, which is used to support the rotation of the rotor 300 and the output torque of the output shaft 510. In this embodiment, the bearing seat of the rear bearing 520 in the rear end cover 120 is not shown in the drawing. A flywheel 530 is mounted on the extended end of the output shaft 510 for power output. The combustion chamber 600 is located on the side of the housing 100, with one end radially corresponding to the intake and exhaust ports 311 of the cylinder 310 and the other end radially corresponding to the outer circle of the turbine 320. It mixes and burns high-pressure air and fuel to produce high-temperature and high-pressure gas. A spark plug 610 is installed on the combustion chamber 600 to introduce the high-voltage electricity generated by the ignition coil into the combustion chamber 600, generate an electric spark in the electrode gap, ignite the gas mixture, and drive the turbine 320 to do work. In this embodiment, the high voltage generated by the ignition coil is more than 10,000 volts, which breaks down the combustible gas between the center electrode and the side electrode. The gap between the two is 0.6-1.0 mm, generating an electric spark with a temperature of 2000-3000℃, thereby igniting the combustible mixture in the combustion chamber 600. The exhaust passage 700 is located on the other side of the housing 100, radially corresponding to the outer circle of the turbine 320, and is used to discharge the exhaust gas remaining after the turbine 320 has done its work. The cylinder 310 and turbine 320 are arranged on the rotor 300, forming two independent units, increasing the radius of the turbine 320 and the number of blades 321; the combustion chamber 600 is located outside the housing 100, and the combustible gas is ignited and exploded in the combustion chamber 600, and the ignited mixture drives the turbine 320 to do work.

[0026] To ensure the stability of the structure in this embodiment, the eccentric shaft 410 is not concentric with the housing 100 and the rotor 300, and the eccentric distance of the eccentric shaft 410 is half of the reciprocating stroke of the piston 440.

[0027] As a standard technical choice, the eccentric shaft 410 is provided with a lubrication channel 411 having axial and radial through holes for delivering lubricating oil into the rotor 300.

[0028] To further ensure the stability of the structure in this embodiment, the turbine 320 and the rotor 300 are concentric and the outer diameter of the turbine 320 is the same as that of the rotor 300. When the rotor 300 rotates, the turbine 320 can be continuously driven, resulting in smooth operation and high output power. In this embodiment, the radius of the turbine 320 is more than 10 times larger than the crank radius of the piston engine crankshaft. The power arm length for power generation in this embodiment is greater than that of the piston engine and the triangular rotor engine. Therefore, under the same displacement and fuel consumption, more power density and greater output power can be obtained at lower speeds.

[0029] To optimize the structure of this embodiment, the combustion chamber 600 is designed as an annular or cylindrical shape, with its inner wall resistant to high temperatures and equipped with a cooling system. In this embodiment, air film cooling and water cooling are used.

[0030] To further optimize the structure of this embodiment, a combustion chamber input interface 140 and a combustion chamber output interface 150 are provided on the side of the housing 100. One end of the combustion chamber 600 is connected to the combustion chamber input interface 140, and the other end is connected to the combustion chamber output interface 150. An exhaust interface 130 is provided on the other side of the housing 100 for connecting to the exhaust passage 700.

[0031] As a conventional technical choice, cylinder 310 is matched with piston 440 and connecting rod 430. In this embodiment, there are four cylinders 310 and four pistons 440, forming a four-cylinder symmetrical compressor.

[0032] The technical solutions described in the embodiments of this application have at least the following technical effects or advantages: Since the cylinder 310 inside the rotor 300 is equipped with a piston 440 that is slidably connected to the eccentric shaft 410, the rotor 300 rotates inside the housing 100, the cylinder 310 rotates with the rotor 300, and the piston 440 rotates inside the cylinder 310 while reciprocating around the eccentric shaft 410, thereby realizing the intake, compression and exhaust strokes.

[0033] Since the cylinder 310 and turbine 320 are located on the rotor 300, forming two independent units, and the turbine 320 and rotor 300 have the same diameter, the radius of the turbine 320 and the number of blades 321 are increased. Therefore, the radius of the turbine 320 is larger than the crank radius of the piston engine crankshaft. Every time the turbine 320 rotates, the blades 321 can be continuously driven. As a result, the turbine 320 operates smoothly and has high output power. Thus, under the same displacement and fuel consumption, more power density and greater output power can be obtained at lower speeds, thereby improving the thermal efficiency of the gas turbine.

[0034] Since the combustion chamber 600 is located outside the housing 100, with one end radially corresponding to the intake and exhaust ports 311 of the cylinder 310 and the other end radially corresponding to the outer circle of the turbine 320, the combustible mixture enters the combustion chamber 600 from the cylinder 310 under the push of the piston 440. The combustible gas ignites and explodes in the combustion chamber 600, and the ignited mixture drives the blades 321 of the turbine 320 to rotate and do work, generating torque to output power. This avoids the damage caused by the ignition and explosion of combustible gas in the cylinder 310, thereby improving the service life of the cylinder 310 and the piston 440, and reducing the operating cost.

[0035] The working principle and process of this embodiment: The rotor 300 is installed inside the housing 100, which has a smooth inner wall and an outer circumference with an intake passage 200, a combustion chamber 600, and an exhaust passage 700. When the starter drives the rotor 300 to rotate clockwise inside the housing 100, the piston 440 inside the cylinder 310 is slidably connected to the eccentric shaft 410 of the front cover 110 through the connecting rod 430 and the connecting rod flange 420. As the cylinder 310 rotates with the rotor 300 and the piston 440 rotates clockwise with the cylinder 310, it also reciprocates around the eccentric shaft 410 inside the cylinder 310. When it begins to move away from the intake and exhaust ports 311 at the top of the cylinder 310, the intake and exhaust ports 311 are exactly at the intake passage 200 of the housing 100, and the intake stroke begins. When the piston 440 reaches bottom dead center and begins to gradually approach the intake / exhaust port 311, which has already passed the intake passage 200, the intake / exhaust port 311 is blocked by a section of the inner wall of the closed housing 100. Then, the piston 440 continues to move towards the intake / exhaust port 311, beginning the compression stroke. When the piston 440 reaches top dead center, the compression stroke ends, and the intake / exhaust port 311 has just moved to the intake port of the combustion chamber 600. The compressed high-temperature, high-pressure combustible mixture enters the combustion chamber 600. The rotor 300 continues to rotate, and the intake port of the combustion chamber 600 is sealed by the solid outer portion of the rotor 300. The spark plug 610 ignites, expelling the combusted gas into the turbine 320, which drives the blades 321 to rotate and perform work. The turbine 320 rotates 180 degrees. o Then, the exhaust gas in the turbine 320 is discharged into the exhaust passage 700 and discharged outside the casing 100, completing the first power cycle. When the blade 321 is pushed to do work and output torque, it also drives the rotor 300 to continue rotating, and causes the next set of pistons 440 to continue to draw in and compress air, and carry out the next cycle. This process is repeated continuously, driving the output shaft 510 and flywheel 530 to output power.

[0036] Features of this embodiment: It combines the advantages of piston engines, triangular rotor engines and gas turbines, and features smooth operation, low vibration, low noise, high thermal efficiency, low fuel consumption, light weight, small size, environmentally friendly emissions, and ease of manufacturing and maintenance. Moreover, its manufacturing and operating costs are far lower than those of existing engines.

[0037] It is worth noting that all the contents not described in detail in the specification are existing technologies known to those skilled in the art, and the model parameters of the front bearing 340, rear bearing 520, intake carburetor and spark plug 610 are not specifically limited and can be determined using conventional equipment. Electrical control components not mentioned in this technical solution are not shown in the figure because they are existing technologies, and will not be described here.

[0038] Finally, it should be noted that: The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A gas turbine, characterized in that: include: The housing (100) is a cylindrical structure with a front cover (110) at one end and a rear cover (120) at the other end. An intake passage (200) is provided, which is an arc-shaped structure and is located on the top of the housing (100); an intake carburetor interface (210) is provided at the end of the intake passage (200). The rotor (300) is a hollow cylindrical structure, concentrically assembled in the housing (100), and provided with a receiving cavity, including a cylinder (310), a turbine (320), a sealing ring (330) and a front bearing (340). The cylinder (310) is arranged radially in the accommodating cavity near the end of the front cover (110). The top of the cylinder (310) is provided with an intake and exhaust port (311) with a sealing ring. The turbine (320) is provided near the end of the rear cover (120). The turbine (320) is arranged with blades (321) with an inclined angle. An inner sleeve is provided along the axial direction of the turbine (320). The sealing ring (330) is arranged on the outer circumference of the rotor (300). A bearing support seat is provided at the end of the rotor (300) near the end of the front cover (110) for mounting the front bearing (340). Piston assembly (400), which is disposed at the front end cover (110) end of the housing (100), includes an eccentric shaft (410), a connecting rod connecting disc (420), a connecting rod (430) and a piston (440). The eccentric shaft (410) is not concentric with the housing (100) and the rotor (300), and is fixed to the front end cover (110) in a cantilever manner; the piston (440) is assembled inside the cylinder (310), and the connecting rod connecting plate (420) is assembled on the eccentric shaft (410); the connecting rod (430) is connected to the piston (440) at one end by a pin, and the other end is connected to the connecting rod connecting plate (420); wherein, the eccentric shaft (410) and the piston (440) are slidably connected, and the piston (440) reciprocates around the eccentric shaft (410) inside the cylinder (310) when it accompanies the rotor (300); Output assembly (500), which is disposed at the rear end cover (120) end of the housing (100), includes an output shaft (510), a rear bearing (520) and a flywheel (530). One end of the output shaft (510) is provided with a flange that is connected to the inner sleeve of the turbine (320); the rear bearing (520) is mounted on the output shaft (510), and the rear bearing (520), the housing (100), the rotor (300), and the front bearing (340) are concentric, forming a rotational support for the rotor (300) by being limited by the rear end cover (120); the flywheel (530) is mounted on the extended end of the output shaft (510). A combustion chamber (600) is disposed on the side of the engine housing (100), one end of which radially corresponds to the intake and exhaust ports (311) of the cylinder (310), and the other end radially corresponds to the outer circle of the turbine (320); a spark plug (610) is disposed on the combustion chamber (600); and An exhaust passage (700) is provided on the other side of the housing (100), and radially corresponds to the outer circle of the turbine (320); The cylinder (310) and the turbine (320) are arranged on the rotor (300) to form two independent units, increasing the radius of the turbine (320) and the number of blades (321); the combustion chamber (600) is located outside the housing (100), and the combustible gas is ignited and exploded in the combustion chamber (600).

2. A gas turbine according to claim 1, characterized in that: The eccentric shaft (410) is not concentric with the housing (100) and the rotor (300), and the eccentric distance of the eccentric shaft (410) is half the reciprocating stroke of the piston (440).

3. A gas turbine according to claim 1, characterized in that: The eccentric shaft (410) is provided with a lubrication channel (411).

4. A gas turbine according to claim 1, characterized in that: The turbine (320) and the rotor (300) are concentric and have the same diameter. When the rotor (300) rotates, the blades (321) of the turbine (320) can be continuously pushed.

5. A gas turbine according to claim 1, characterized in that: The combustion chamber (600) is annular or cylindrical in design, with its inner wall resistant to high temperatures and equipped with a cooling system.

6. A gas turbine according to claim 1, characterized in that: The side end of the housing (100) is provided with a combustion chamber input interface (140) and a combustion chamber output interface (150); one end of the combustion chamber (600) is connected to the combustion chamber input interface (140), and the other end is connected to the combustion chamber output interface (150); an exhaust interface (130) is provided on the other side end of the housing (100) for connecting the exhaust passage (700).

7. A gas turbine according to claim 1, characterized in that: The cylinder (310) is matched with the piston (440) and the connecting rod (430).

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