CN112502834B - Rotary combustion jet engine - Google Patents
Rotary combustion jet engine Download PDFInfo
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- CN112502834B CN112502834B CN202011452608.XA CN202011452608A CN112502834B CN 112502834 B CN112502834 B CN 112502834B CN 202011452608 A CN202011452608 A CN 202011452608A CN 112502834 B CN112502834 B CN 112502834B
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- combustion chamber
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- shell
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
- F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
- F02C3/09—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage of the centripetal type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
本发明涉及动力机械技术领域，具体涉及一种旋转燃烧喷气发动机，包括定子部件和转子部件，定子部件包括机壳，转子部件包括转动连接在机壳内部且依次固定连接的空气压缩机、旋转燃油泵和旋转燃烧室；空气压缩机包括依次连接在空心轴上的第一离心叶轮、向心叶轮和第二离心叶轮；旋转燃油泵包括连接在空心轴上的向心燃油输送泵，向心燃油输送泵的壳体与机壳之间设有密封圈，机壳上设有与向心燃油输送泵的叶腔连通的燃油进油口；气动燃油喷嘴的不同进口分别与燃油和高压空气连通；旋转燃烧室的侧壁周向均布倾斜喷射的燃气喷口，机壳的侧边设有供废气排出的排气口。本申请的发动机功率密度大、重量轻、效率高、结构简单，制造成本低、可靠性高。
The present invention relates to the technical field of power machinery, and specifically to a rotary combustion jet engine, comprising a stator component and a rotor component, wherein the stator component comprises a casing, and the rotor component comprises an air compressor, a rotary fuel pump and a rotary combustion chamber which are rotatably connected to the inside of the casing and are fixedly connected in sequence; the air compressor comprises a first centrifugal impeller, a radial impeller and a second centrifugal impeller which are connected to a hollow shaft in sequence; the rotary fuel pump comprises a radial fuel delivery pump connected to the hollow shaft, a sealing ring is provided between the housing of the radial fuel delivery pump and the casing, and a fuel inlet which is connected to the blade cavity of the radial fuel delivery pump is provided on the casing; different inlets of the pneumatic fuel nozzle are connected to the fuel and high-pressure air respectively; the side wall of the rotary combustion chamber is uniformly distributed with inclined injection gas nozzles in the circumferential direction, and the side of the casing is provided with an exhaust port for exhausting exhaust gas. The engine of the present application has high power density, light weight, high efficiency, simple structure, low manufacturing cost and high reliability.
Description
Technical Field
The invention relates to the technical field of power machinery, in particular to a rotary combustion jet engine.
Background
The heat engine commonly used at present mainly comprises two main types, namely a piston engine and a jet engine. The piston engine has the advantages that the number of parts is large, the weight is large, the rotating speed which can be achieved by reciprocating motion of the piston is limited, the oil consumption of the jet engine is larger than that of the piston engine at low speed, and the excellent high-speed performance of the jet engine enables the jet engine to rapidly replace the piston engine, so that the jet engine becomes the main stream of an aeroengine. However, the existing turbojet engine has the defects of more parts, high price of turbine blades, poor low-speed performance and the like, and the problem of high temperature resistance of the turbine blades.
Disclosure of Invention
The invention aims to solve the problems and disadvantages and provide a rotary combustion jet engine which has the advantages of high power density, light weight, high efficiency, simple structure, low manufacturing cost and high reliability.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
A rotary combustion jet engine comprises a stator part and a rotor part, wherein the stator part comprises a shell, the rotor part comprises an air compressor, a rotary fuel pump and a rotary combustion chamber, the air compressor, the rotary fuel pump and the rotary combustion chamber are rotatably connected inside the shell and are sequentially and fixedly connected, the air compressor comprises a first centrifugal impeller, a centripetal impeller and a second centrifugal impeller which are sequentially connected to a hollow shaft, the air inlet position of the first centrifugal impeller is an air inlet at the front end of the shell, the air inlet position of the second centrifugal impeller is a plurality of air inlets at the rear end of the shell, the air outlet position of the centripetal impeller is the inside of a hollow shaft, a plurality of air inlets are circumferentially arranged in the hollow shaft, the rotary combustion chamber comprises a centripetal fuel pump connected to the hollow shaft, a sealing ring is arranged between a shell of the centripetal fuel pump and the shell, the sealing ring is fixed on the shell, a fuel inlet communicated with a leaf cavity of the centripetal fuel pump is arranged on the shell, the oil outlet end of the centripetal fuel pump is communicated with a peripheral annular cavity of a pneumatic nozzle arranged in the hollow shaft, the central hole inlet section of the pneumatic nozzle is communicated with the front end of the hollow shaft, the second centrifugal impeller is communicated with the outlet section of the central hole, a plurality of air inlets are radially arranged between the rotary combustion chamber and the shell, a spark plug is uniformly distributed on the side wall of the shell, the spark plug is arranged on the side wall is in the side wall of the rotary combustion chamber, which is in the spark plug is in contact with a spark plug, and is arranged on the side of the side wall of the spark plug, and is in the rotary plug, and the spark plug is connected with the spark plug and has a rotary plug.
Further, in the rotary combustion jet engine, the rotary combustion chamber comprises a combustion chamber shell which tapers from the middle to the upper end and the lower end, heat dissipation rib plates which extend continuously from top to bottom are uniformly distributed on the circumference of the inner wall of the combustion chamber shell, the spark plugs are arranged on the side wall of the inlet of the combustion chamber shell, the gas nozzle is arranged on the circumference of the middle of the combustion chamber shell, the pneumatic fuel nozzle is connected in the hollow shaft through a plurality of radial support plates, the lower end of the pneumatic fuel nozzle extends into an upper opening of the combustion chamber shell, and the upper end of the heat dissipation rib plates corresponds to the radial support plates of the outer ring of the pneumatic fuel nozzle.
Further, in the rotary combustion jet engine, the combustion chamber housing has an arc transition from the middle to the upper and lower ends, the passage between the adjacent heat dissipation rib plates of the upper inner wall and the lower inner wall of the combustion chamber housing is a first cooling air passage, and the passage between the adjacent heat dissipation rib plates of the middle inner wall of the combustion chamber housing is a second cooling air passage.
Further, in the rotary combustion jet engine, a high-pressure plunger fuel pump is arranged in the vane cavity of the centripetal fuel delivery pump, a plunger pump oil inlet on the high-pressure plunger fuel pump is positioned in the vane cavity of the centripetal fuel delivery pump, an oil outlet end of the high-pressure plunger fuel pump is communicated with a peripheral annular cavity of a pneumatic fuel nozzle arranged in the hollow shaft, a cam is arranged on the side edge of a pressurizing column of the high-pressure plunger fuel pump, and the cam is connected with a cam handle penetrating out of the casing.
Further, in the rotary combustion jet engine, the oil outlet end of the high-pressure plunger fuel pump is sequentially connected with the one-way valve, the pressure stabilizing chamber and the pressure valve, the pressure stabilizing chamber is provided with the oil inlet and outlet hole, and the pressure stabilizing spring and the piston connected with the pressure stabilizing spring are arranged in the pressure stabilizing chamber.
Further, in the rotary combustion jet engine, the casing is provided with two symmetrical half structures, and the butt joint surface of the casing is provided with a plurality of bolt holes.
Further, in the rotary combustion jet engine, a baffle is disposed on the inner wall of the casing at positions corresponding to the first centrifugal impeller, the centripetal impeller and the second centrifugal impeller.
Further, in the rotary combustion jet engine, the hollow shaft is arranged into a front section and a rear section, and is connected with the rotary combustion chamber through a flange and a bolt, the rear section hollow shaft is connected with the rotary combustion chamber through a flange and a bolt, the front section hollow shaft and the rotary combustion chamber are connected with the casing through a bearing, and the bearing is connected in the casing or a radial supporting rib in the casing.
The rotary combustion jet engine has the beneficial effects that:
Compared with the existing turbojet engine, the rotary combustion jet engine does not need a high-temperature turbine part, and is also used as a turbine to provide torque, so that the rotary combustion jet engine has the advantages of high power density, light weight, high efficiency, simple structure, low manufacturing cost and high reliability, and can be used as an automobile engine to obviously improve the speed.
According to the invention, the combustion chamber of the rotary combustion jet engine rotates, the heat dissipation rib plates are arranged on the inner wall of the combustion chamber shell, channels between the heat dissipation rib plates correspond to cooling air in the circumferential direction of the pneumatic fuel nozzle, the cooling air can be introduced, and the cooling air can be enabled to form a gas film on the wall surface of the combustion chamber, so that the problems of cooling and ablation of the combustion chamber are effectively solved.
Drawings
Fig. 1 is a schematic structural diagram of a rotary combustion jet engine according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of the oil supply principle of a rotary combustion jet engine according to an embodiment of the present invention.
FIG. 3 is a schematic top cross-sectional structural view of a rotary combustor according to an embodiment of the present invention.
In the figure, 1 is a first centrifugal impeller, 2 is a centripetal impeller, 3 is a centripetal fuel delivery pump, 4 is a high-pressure plunger fuel pump, 5 is a cam, 6 is a rotary combustion chamber, 7 is a fuel nozzle, 8 is a bearing, 9 is a flange, 10 is a spark plug, 11 is a spark plug conducting ring, 12 is a carbon brush, 13 is a pneumatic fuel nozzle, 14 is a shell, 15 is an air inlet, 16 is an air outlet, 17 is a cooling air channel I, 18 is a cooling air channel II, 19 is a cam handle, 20 is a fuel oil inlet, 21 is a bolt, 22 is a heat dissipation rib plate, 23 is a one-way valve, 24 is a centripetal fuel delivery pump vane cavity, 28 is a plunger pump oil inlet, 29 is a second centrifugal impeller, 30 is a bolt hole, 31 is a pressure stabilizing chamber, 31-1 is a piston, 31-2 is a pressure stabilizing spring, 32 is a deflector, 34 is a radial sealing piece, 34 is a pressure valve, 35 is a sealing ring, 36 is a hollow shaft.
Detailed Description
A rotary combustion jet engine according to the invention will be described in more detail below with reference to the accompanying drawings and by way of specific embodiments.
In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1-3, the present embodiment discloses a rotary combustion jet engine comprising a stator component and a rotor component, the stator component comprising a housing, the rotor component comprising an air compressor, a rotary fuel pump and a rotary combustion chamber rotatably connected inside the housing and fixedly connected in sequence; the air compressor comprises a first centrifugal impeller, a centripetal impeller and a second centrifugal impeller which are sequentially connected on a hollow shaft, wherein the air inlet position of the first centrifugal impeller is an air inlet at the front end of a shell, the air inlet position of the second centrifugal impeller is a plurality of air inlets at the rear end of the shell, the air outlet position of the centripetal impeller is the inside of the hollow shaft, a plurality of air inlets are arranged in the circumference of the hollow shaft, air is firstly pressed to the circumferential side by the first centrifugal impeller and the second centrifugal impeller and then compressed by the centripetal impeller and then enters the inside of the hollow shaft through the air inlets on the hollow shaft, the rotary fuel pump comprises a centripetal fuel delivery pump connected on the hollow shaft, a sealing ring is arranged between a shell of the centripetal fuel delivery pump and the shell, the sealing ring is fixed on the shell and used for preventing fuel from entering the shell, a fuel oil inlet communicated with a leaf cavity of the centripetal fuel delivery pump is arranged on the shell, the oil outlet end of the centripetal fuel delivery pump is communicated with a peripheral annular cavity of a pneumatic fuel nozzle arranged in the hollow shaft, the central hole inlet section of the pneumatic fuel nozzle is communicated with the inside the front end of the hollow shaft, the peripheral annular cavity outlet of the pneumatic fuel nozzle is communicated with the central hole outlet section, high-speed air is driven to be sprayed through jet effect, and simultaneously mixed with the air in an atomized state, a rotary fuel chamber is arranged between the rotary fuel pump and a rotary fuel chamber capable of radially exhausting a sealing gap is arranged between the rotary fuel chamber and the shell and a rotary sealing piece is capable of preventing exhaust gas from entering into the rotary sealing chamber, the spark plug is arranged on the side wall of the rotary combustion chamber, the spark plug conducting ring penetrating out of the rotary combustion chamber is connected to the outer side of the spark plug, the spark plug conducting ring is in sliding contact with the carbon brush connected to the shell, the spark plug can be ensured to be electrified and ignited, the gas nozzles for oblique injection are uniformly distributed on the circumferential direction of the side wall of the rotary combustion chamber, the gas is obliquely injected, the rotor part can be driven to rotate at a high speed, and an exhaust port for exhaust gas is arranged on the side edge of the shell.
The centrifugal impeller in the embodiment is opposite to the working principle of the centrifugal impeller, the centrifugal impeller is axially air-inlet and radially air-outlet, the centrifugal impeller increases the speed of gas by virtue of centrifugal force generated by high-speed rotation of the centrifugal impeller to improve kinetic energy and convert the kinetic energy into pressure energy, the centrifugal impeller is radially air-inlet and axially air-outlet, the air inlet is large, the air outlet is small, the air is compressed towards the axis by high-speed rotation of the centrifugal impeller, the speed of gas is increased, the kinetic energy is converted into pressure energy, the compression of the centrifugal impeller is similar to the compression of a punching engine, the punching compression needs forward high-speed flight, and the compression of the centrifugal impeller needs high-speed circumferential rotation compression.
In this embodiment, preferably, the rotary combustion chamber includes the combustion chamber casing that tapers from middle to upper and lower both ends, the inner wall circumference equipartition of combustion chamber casing has the heat dissipation gusset that extends from top to bottom in succession, the spark plug is installed in the import department lateral wall of combustion chamber casing, the gas spout is arranged in the middle part circumference of combustion chamber casing, be convenient for combustible mixture diffusion, pneumatic fuel nozzle passes through a plurality of radial backup pads and connects in the hollow shaft, its lower extreme stretches into in the upper portion opening of combustion chamber casing, the upper end of heat dissipation gusset corresponds with the radial backup pad of pneumatic fuel nozzle outer lane, little high-pressure air gets into in the pneumatic fuel nozzle from the middle part, the cooling combustion chamber casing between the heat dissipation gusset is got into to most high-pressure air, the combustion chamber is participated in the combustion with final entering after the combustion chamber cooling, be equivalent to preheat after with the fuel continue mixed combustion, make the fuel burn abundant.
In this embodiment, specifically, the combustor casing has an arc transition from the middle to the upper and lower ends, the channel between the adjacent heat dissipation rib plates of the upper inner wall and the lower inner wall of the combustor casing is a first cooling air channel, and the channel between the adjacent heat dissipation rib plates of the middle inner wall of the combustor casing is a second cooling air channel.
In this embodiment, preferably, be equipped with the high-pressure plunger fuel pump in the leaf chamber of centripetal fuel delivery pump, the plunger pump oil inlet on the high-pressure plunger fuel pump is located the leaf intracavity portion of centripetal fuel delivery pump, the play oil end of high-pressure plunger fuel pump communicates with the periphery annular chamber of the pneumatic fuel nozzle that sets up in the hollow shaft, the booster column side of high-pressure plunger fuel pump is equipped with the cam, the cam is connected with the cam handle that wears out the casing, when a plurality of high-pressure plunger pumps in the centripetal fuel delivery pump rotate along with the centripetal fuel delivery pump high-speed, booster column on each high-pressure plunger pump is compressed by the cam in proper order, can increase fuel pressure, the other end of cam handle wears out the casing, the setting of high-pressure plunger can further increase the pressure of fuel, can conveniently adjust the angle of cam handle outside the casing, thereby control the throttle size, and can be outside through adjusting the cam handle throttle size, the throttle controller promptly, be used for adjusting throttle size and shut down.
In this embodiment, preferably, the oil outlet end of the high-pressure plunger fuel pump is sequentially connected with a check valve, a pressure stabilizing chamber and a pressure valve, the check valve enables fuel to flow unidirectionally, the pressure stabilizing chamber is provided with an oil inlet and outlet hole, a pressure stabilizing spring and a piston connected with the pressure stabilizing spring are arranged in the pressure stabilizing chamber, the oil supply pressure is unstable due to the fact that a gap exists between a cam and a pressurizing plunger in rotary contact, the pressure stabilizing chamber is arranged between an outlet of the high-pressure plunger fuel pump and the check valve, fluctuation of the oil supply pressure can be relieved, when the high-pressure plunger fuel pump presses fuel between the outlet of the high-pressure plunger fuel pump and the check valve, the fuel pressure acts on the pressure stabilizing chamber piston, the piston moves to compress the pressure stabilizing spring, when the high-pressure plunger does not press oil, the pressure stabilizing spring returns to enable the piston to reset, and oil pressure between the outlet of the high-pressure plunger fuel pump and the check valve is stable, and the pressure valve is arranged so that when the fuel pressure of the high-pressure plunger fuel pump reaches a certain pressure, the fuel flows into the pneumatic fuel nozzle through the pressure valve, and the fuel does not flow out when the pressure is lower than the pressure of the pressure valve.
In this embodiment, preferably, the casing is provided with two symmetrical half structures, and the butt joint face of the casing is provided with a plurality of bolt holes, so that the manufacture is convenient.
In this embodiment, preferably, the inner wall of the casing is provided with guide plates corresponding to the first centrifugal impeller, the centripetal impeller and the second centrifugal impeller, and the guide plates are used for rectifying air compressed by the centrifugal impeller compressor, so that compressed air flows along a channel between the guide plates, and further compression of the air by the centripetal impeller is facilitated.
In this embodiment, specifically, the hollow shaft may be configured as a front section and a rear section, and connected by a flange and a bolt, and the rear section hollow shaft is also connected by a flange and a bolt to the rotary combustion chamber, and the front section hollow shaft and the rotary combustion chamber are connected to the casing by a bearing, and the bearing is connected to the casing or a radial support rib in the casing.
The working principle of the rotary combustion jet engine of the embodiment is that at the beginning, the starter drives the rotor part of the rotary combustion jet engine to rotate, air enters the shell after being compressed by the first centrifugal impeller and the second centrifugal impeller through the air inlet 15, then enters the hollow shaft after being further compressed by the radial impeller, flows into the rotary combustion chamber to be diffused and heated, meanwhile, fuel is pressurized by the radial fuel delivery pump through the oil inlet 20, is pumped into the peripheral annular cavity of the pneumatic fuel nozzle after being further pressurized by the high-pressure plunger fuel pump, high-pressure air in the central hole of the pneumatic fuel nozzle atomizes and mixes the fuel and the high-pressure air in the peripheral annular cavity through jet flow effect and then is sprayed into the rotary combustion chamber, combustible mixed gas is formed after the fuel and the air are ignited and combusted through the spark plug, the high-temperature high-pressure gas formed after combustion is sprayed out through the gas jet nozzle, so that the rotor part comprising the air compressor, the rotary fuel pump and the rotary combustion chamber is driven to rotate at high speed, the rotary combustion engine enters a self-running working state, then is separated from the starter, and finally exhaust gas is discharged from the air outlet on the shell.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The use of the terms first, second and the like in the description and in the claims, do not denote any order, quantity or importance, but rather are used to distinguish one element from another. Also, the use of the terms "a" or "an" and the like do not necessarily denote a limitation of quantity. The word "comprising" or "comprises", and the like, means that elements or items preceding the word are included in the element or item listed after the word and equivalents thereof, but does not exclude other elements or items. "connected" or "connected" and the like are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect.
While the exemplary embodiments of the present invention have been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that many changes and modifications can be made to the specific embodiments described above without departing from the spirit of the invention, and that many combinations of technical features and structures can be made without departing from the scope of the invention.
Claims (8)
1. The rotary combustion jet engine is characterized by comprising a stator component and a rotor component, wherein the stator component comprises a shell, and the rotor component comprises an air compressor, a rotary fuel pump and a rotary combustion chamber which are rotationally connected in the shell and are sequentially and fixedly connected;
The air compressor comprises a first centrifugal impeller, a centripetal impeller and a second centrifugal impeller which are sequentially connected to a hollow shaft, wherein the air inlet position of the first centrifugal impeller is an air inlet at the front end of a shell, the air inlet position of the second centrifugal impeller is a plurality of air inlets on the shell at the rear end of the second centrifugal impeller, the air outlet position of the centripetal impeller is the inside of the hollow shaft, and a plurality of air inlets are arranged in the circumferential direction of the hollow shaft;
The rotary fuel pump comprises a centripetal fuel delivery pump connected to the hollow shaft, a sealing ring is arranged between a shell of the centripetal fuel delivery pump and a shell, the sealing ring is fixed on the shell, a fuel oil inlet communicated with a vane cavity of the centripetal fuel delivery pump is arranged on the shell, an oil outlet end of the centripetal fuel delivery pump is communicated with a peripheral annular cavity of a pneumatic fuel nozzle arranged in the hollow shaft, a central hole inlet section of the pneumatic fuel nozzle is communicated with the interior of a front section of the hollow shaft, and an outlet of the peripheral annular cavity is communicated with an outlet section of the central hole;
the rotary combustion chamber is characterized in that a radial sealing piece is arranged between the rotary combustion chamber and the casing, a spark plug is arranged on the side wall of the rotary combustion chamber, a spark plug conducting ring penetrating out of the rotary combustion chamber is connected to the outer side of the spark plug, the spark plug conducting ring is in sliding contact with a carbon brush connected to the casing, gas nozzles for oblique injection are uniformly distributed on the side wall of the rotary combustion chamber in the circumferential direction, and an exhaust port for exhaust gas is arranged on the side edge of the casing.
2. The rotary combustion jet engine according to claim 1, wherein the rotary combustion chamber comprises a combustion chamber shell which tapers from the middle to the upper end and the lower end, heat dissipation rib plates which extend continuously from top to bottom are uniformly distributed on the circumference of the inner wall of the combustion chamber shell, the spark plugs are arranged on the side wall of the inlet of the combustion chamber shell, the gas nozzle is arranged on the circumference of the middle of the combustion chamber shell, the pneumatic fuel nozzle is connected in the hollow shaft through a plurality of radial support plates, the lower end of the pneumatic fuel nozzle extends into an upper opening of the combustion chamber shell, and the upper end of the heat dissipation rib plates corresponds to the radial support plates of the outer ring of the pneumatic fuel nozzle.
3. The rotary jet engine of claim 2, wherein the combustion chamber housing has an arcuate transition from the middle to the upper and lower ends, the passage between adjacent cooling ribs of the upper and lower inner walls of the combustion chamber housing being a first cooling air passage and the passage between adjacent cooling ribs of the middle inner wall of the combustion chamber housing being a second cooling air passage.
4. The rotary combustion jet engine according to claim 1, wherein a high-pressure plunger fuel pump is arranged in a vane cavity of the centripetal fuel delivery pump, a plunger pump oil inlet of the high-pressure plunger fuel pump is positioned in the vane cavity of the centripetal fuel delivery pump, an oil outlet end of the high-pressure plunger fuel pump is communicated with a peripheral annular cavity of a pneumatic fuel nozzle arranged in the hollow shaft, and a cam is arranged on a side edge of a pressurizing column of the high-pressure plunger fuel pump and connected with a cam handle penetrating out of the casing.
5. The rotary combustion jet engine according to claim 4, wherein the oil outlet end of the high-pressure plunger fuel pump is sequentially connected with a one-way valve, a pressure stabilizing chamber and a pressure valve, the pressure stabilizing chamber is provided with an oil inlet and outlet hole, and a pressure stabilizing spring and a piston connected with the pressure stabilizing spring are arranged in the pressure stabilizing chamber.
6. A rotary combustion jet engine according to claim 1, wherein the casing is provided in a two-half structure which is symmetrical left and right, and the mating surface of the casing is provided with a plurality of bolt holes.
7. A rotary combustion jet engine as set forth in claim 1 wherein the inner wall of the housing is provided with baffles at positions corresponding to the first centrifugal impeller, the centripetal impeller and the second centrifugal impeller.
8. A rotary combustion jet engine according to claim 1, wherein the hollow shaft is provided in two front and rear sections and is connected by flanges and bolts, the rear hollow shaft is also connected by flanges and bolts to the rotary combustion chamber, the front hollow shaft and the rotary combustion chamber are connected by bearings to the casing, said bearings being connected in radial support ribs in the casing or in the casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011452608.XA CN112502834B (en) | 2020-12-12 | 2020-12-12 | Rotary combustion jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011452608.XA CN112502834B (en) | 2020-12-12 | 2020-12-12 | Rotary combustion jet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112502834A CN112502834A (en) | 2021-03-16 |
| CN112502834B true CN112502834B (en) | 2024-12-20 |
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| GB1173566A (en) * | 1966-08-10 | 1969-12-10 | William Hartley | Gas Turbine Improvements. |
| US4463551A (en) * | 1980-11-03 | 1984-08-07 | Harold Morris | Rotary prime mover |
| US5022228A (en) * | 1988-12-22 | 1991-06-11 | Allied-Signal Inc. | Over the shaft fuel pumping system |
| CN1115004A (en) * | 1995-04-20 | 1996-01-17 | 郭颖 | Reaction type jet engine |
| CN104420992A (en) * | 2013-09-04 | 2015-03-18 | 徐建宁 | Jet engine for rotary combustion chamber |
| MD4390C1 (en) * | 2014-11-10 | 2016-07-31 | Юрий ЩИГОРЕВ | Power plant with discrete jet-rotary engine |
| US20180023472A1 (en) * | 2016-07-22 | 2018-01-25 | Brent Wei-Teh LEE | Engine, rotary device, power generator, power generation system, and methods of making and using the same |
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| US11280342B2 (en) * | 2019-04-05 | 2022-03-22 | Pratt & Whitney Canada Corp. | Rotodynamic pump and method |
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