CN113969836A - Rotary turbojet fuel engine doing work secondarily - Google Patents
Rotary turbojet fuel engine doing work secondarily Download PDFInfo
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- CN113969836A CN113969836A CN202010719427.2A CN202010719427A CN113969836A CN 113969836 A CN113969836 A CN 113969836A CN 202010719427 A CN202010719427 A CN 202010719427A CN 113969836 A CN113969836 A CN 113969836A
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Classifications
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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
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B73/00—Combinations of two or more engines, not otherwise provided for
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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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
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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
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
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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
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
Abstract
The invention relates to the technical field of power energy, and discloses a rotary turbojet fuel engine with secondary work, wherein a rotor is arranged in a closed cavity of the engine in a penetrating manner; the rotor is matched with an engine closed cavity to be connected with a piston rotating along with the rotor, and one side of the piston is matched with a jet burner; the valve is opened and closed to drive the piston to rotate in coordination with the injection of the pressure fuel, and the pressure fuel is ignited and combusted by the ignition device to drive the piston to drive the rotor to rotate in coordination with the pressure fuel; one cavity stores the combusted mixed gas with pressure, and the piston leaves the cavity and enters the other cavity to be exhausted outwards through an exhaust mechanism and do work. The method changes the application mode that the existing engine can only finish primary conversion work in one space, changes the application mode that the existing engine can do secondary conversion work in more than two continuous spaces of the engine, and changes the application mode into the technology that the existing engine can do primary input and secondary conversion work in multiple spaces. The method changes the optimization application of the engine efficiency, and achieves the purposes of real high efficiency, energy conservation and environmental protection.
Description
Technical Field
The invention relates to the technical field of power energy, in particular to the field of fuel engines, and particularly relates to a rotary turbojet fuel engine with secondary work. The technology of the rotary vortex-spraying fuel engine doing work for the second time can be applied to all fields of power supply by fuel (gas) engines.
Background
According to the field of all fuel engines which are currently applied and are used as conversion work-doing equipment, the fuel engines have an application mode that once energy is input and once energy conversion work-doing can be completed only in one space. To piston internal combustion engines, gas turbines, turbojet engines, and the like. Up to now, there has been no application seen and conceived of the division of the pressure gas of the fuel combustion (explosion) into two internal energies. Now, the basic textbook defines a concept that "all energy conversion works when one energy is lost to obtain another converted energy". The applicant knows that the application of secondary work can provide a creative revolution for the energy of human beings all over the world, so that the work efficiency in the application of full-pressure gas generated by fuel combustion is improved to a higher stage, and the application range of real high efficiency is reached; the purpose of high efficiency is to greatly improve the utilization efficiency of energy sources and to realize the real practical application of the energy-saving purpose and concept.
Disclosure of Invention
The invention aims to provide a rotary turbojet fuel engine doing work for the second time, and aims to solve the technical problems that the work-doing efficiency of the fuel engine is not high enough and the fuel engine is not converted as much as possible in the prior art.
In order to achieve the purpose, the invention adopts the technical scheme that:
a rotary turbojet fuel engine doing work for the second time comprises an engine sealed cavity and stators fixed at two ends of the engine sealed cavity; a rotor supported by a stator is arranged in the engine closed cavity in a penetrating manner; an annular cavity is formed between the rotor and the engine closed cavity, a plurality of valves are connected to the engine closed cavity, and the valve separation cavity is a plurality of cavities; the rotor is matched with the closed cavity of the engine to be connected with a piston rotating along with the rotor, and one side of the piston is provided with an injection combustor which is used for injecting gasified pressure fuel to the cavity; the valve is opened and closed to drive the piston to rotate in coordination with the injection of the pressure fuel, and the pressure fuel is ignited and combusted by an ignition device of the injection combustor in coordination with the rotation of the rotor driven by the piston; one of the cavities stores the combusted mixed gas with pressure, and the piston leaves the cavity and enters the other cavity to be exhausted outwards through the exhaust mechanism and do work.
According to the rotary turbojet fuel engine doing work for the second time, a shaft is connected to the rotor, and a fuel feeding pipeline penetrates through the center of the shaft; an air feeding channel is formed between the fuel feeding pipeline and the shaft, and the fuel feeding pipeline and the air feeding channel are respectively communicated with the jet burner.
According to the rotary turbojet fuel engine doing work secondarily, the exhaust mechanism comprises a volute pressure groove formed in the stator and a pressure air groove formed in the rotor; the air compression groove is arranged on the end surface of the rotor; the pressurized mixed gas in the cavity during the rotation of the rotor enters the gas pressing groove and the worm pressure groove, and the pressurized mixed gas is released to punch the rotor and drive the rotor to rotate.
According to the rotary turbojet fuel engine doing work for the second time, the rotor is provided with the exhaust grooves communicated with the air compression grooves, and the air compression grooves and the exhaust grooves are arranged in pairs and are positioned on the two end faces of the rotor; the pressurized mixed gas in the cavity during the rotation of the rotor enters the gas pressing groove and the worm pressure groove through the exhaust groove.
According to the rotary turbojet fuel engine doing work for the second time, the stator is divided into a first stator and a second stator; the worm pressure groove is arranged on the first stator and the second stator; the first stator and the second stator form end face covers, and a shell is arranged between the second stator and the rotor in a matched mode.
According to the rotary turbojet fuel engine doing work for the second time, the first stator and the second stator are provided with the exhaust ports, and the peripheries of the rotors in the first stator and the second stator are connected with the exhaust switches; the discharge switch is formed with a rotary plug which opens and seals the worm pressure groove in the rotation of the rotor, and the rotary plug opens the worm pressure groove and discharges the mixed gas with pressure through the exhaust port in an outward guide mode to do work.
According to the rotary turbojet fuel engine with secondary work, the outward exhaust work of the exhaust mechanism is performed in a turbine mode.
According to the rotary turbojet fuel engine with secondary work, the number of the valves is one or two more than twice of the number of the pistons.
According to the rotary turbojet fuel engine doing work for the second time, the jet burner is of a siphon structure and comprises a nozzle and a siphon air port; the jet burner is connected to the end surface of the piston; the injection combustor is provided with a plurality of matching pistons and cavities.
According to the rotary turbojet fuel engine doing work for the second time, the jet burner further comprises a heating device and the ignition device; the heating device is used for heating up the pressure fuel which is introduced for the first time after the gasification engine is started, and the ignition device is used for igniting the pressure fuel which is heated up and gasified by the heating device.
The invention has the beneficial effects that:
the first one is that the structure is changed, and the application mode of rotor and piston rotation work is adopted; the second technical change is that the existing engine can only complete one-time conversion work in one space, and the second technical change is an application mode of performing two-time conversion work in more than two continuous spaces of the engine, and is a technology of performing one-time input and performing two-time conversion work in multiple spaces. The method changes the optimization application of the engine efficiency, and achieves the purposes of real high efficiency, energy conservation and environmental protection.
In the application of the rotary turbojet fuel engine for secondary work, the temperature-pressure mixed pressure gas (pressure mixed gas) obtained by burning the injected pressure fuel can be used for secondary work application. The method is an application mode with high efficiency for energy conversion work, namely, the application of the pressurized mixed gas formed by mixing the pressurized fuel after combustion is distributed into two utilization modes of internal energy; in other words, the pressurized mixed gas obtained by combustion is divided into internal energy of pressure intensity and pressure gas mass, and the internal energy of the turbine can be released to perform application of conversion and work respectively.
Drawings
FIG. 1 is a schematic structural diagram of a preferred embodiment of the present invention;
FIG. 2 is a cross-sectional schematic view of FIG. 1 (with parts hidden);
FIG. 3 is a schematic diagram of the structure of an engine closed cavity;
FIG. 4 is a schematic cross-sectional view of the fuel feed tube engaging the shaft;
FIG. 5 is a schematic view of an injection burner;
reference numerals:
1-shaft, 2-third cavity, 3-rotor, 4-branch pipe, 5-piston, 7-first cavity, 8-second cavity, 9-valve, 10-exhaust hole, 11-exhaust groove, 12-air compression groove, 16-shell, 26-inflation groove, 27-scroll groove, 28-exhaust injection hole, 29-exhaust switch, 38-exhaust hole, 39-rotary plug, 52-second stator, 53-first stator, 61-nozzle, 62-fuel feeding pipeline, 63-heating device, 64-ignition device and 65-air feeding channel.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be readily apparent to those skilled in the art from the disclosure herein.
Please refer to the attached drawings. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions under which the present invention can be implemented, so that the modifications of the structures, the changes of the ratios, or the adjustments of the sizes, which do not affect the effects of the present invention and the purposes achieved by the present invention, should still fall within the scope of the present invention. In addition, the terms "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for clarity of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the terms is not limited to the technical contents of the actual changes.
Example one
Referring to fig. 1-5, the present invention provides a rotary turbojet fuel engine with secondary work, including an engine sealed cavity and stators fixed at two ends of the engine sealed cavity; a rotor 3 supported by a stator is arranged in the closed cavity of the engine in a penetrating way; an annular cavity is formed between the rotor 3 and the engine closed cavity, a plurality of valves 9 are connected to the engine closed cavity, the valves 9 divide the cavity into a plurality of cavities, and the rotor 3 can move in the two cavities; the rotor 3 is matched with a closed cavity of an engine to be connected with a piston 5 rotating along with the rotor 3, one side of the piston 5 is provided with an injection combustor, and the injection combustor is used for injecting gasified pressure fuel to the cavity; the valve 9 is opened and closed to match the pressure fuel injection to drive the piston 5 to rotate, and the pressure fuel is ignited and combusted by an ignition device 64 of the injection combustor to generate temperature pressure gas to drive the piston 5 to drive the rotor 3 to rotate; the nozzle 61 siphons air to burn and generate warm pressure gas during injection; one of the cavities stores the combusted mixed gas with pressure, can do work by opposite impact after the piston 5 leaves the cavity and enters the other cavity, and can exhaust outwards through the exhaust mechanism and do work.
Regarding the arrangement of the valves 9, one way may specifically be that three valves 9 are connected to the engine sealed cavity, and the three valves 9 separate the cavities into a first cavity 7, a second cavity 8 and a third cavity 2; the valve 9 is opened and closed to drive the piston 5 to rotate in coordination with the injection of the pressure fuel, and the pressure fuel is ignited and combusted by the ignition device 64 to drive the piston 5 to drive the rotor 3 to rotate; the first cavity 7 and/or the second cavity 8 store the combusted mixed gas with pressure, and the piston 5 exhausts outwards through the exhaust mechanism and does work after entering the third cavity 2.
The rotor 3 is connected with a shaft 1, the shaft 1 is a hollow shaft, and a fuel feeding pipeline 62 (in a sleeve form) penetrates through the center of the shaft 1; an air feeding channel 65 is formed between the fuel feeding pipeline 62 and the shaft 1, and the fuel feeding pipeline 62 and the air feeding channel 65 are respectively communicated with the jet burner. Specifically, the fuel feed pipe 62 communicates with the nozzle 61 of the injection burner, and the air feed passage 65 communicates with the siphon air port of the injection burner.
The exhaust mechanism comprises a worm pressure groove 27 arranged on the stator and a pressure air groove 12 arranged on the rotor 3; the compressed air groove 12 is arranged on the end surface of the rotor 3; the mixed gas with pressure in the cavity enters the gas pressing groove 12 and the worm pressure groove 27 during the rotation of the rotor 3, and the mixed gas with pressure is released to press the rotor 3 and drive the rotor to rotate.
In addition, regarding the exhaust mechanism, the rotor 3 is provided with an exhaust groove 11 communicated with a compressed air groove 12, and the compressed air groove 12 and the exhaust groove 11 are arranged in pairs and are positioned on two end faces of the rotor 3; the mixed gas with pressure in the cavity during the rotation of the rotor 3 enters the gas pressing groove 12 and the worm pressure groove 27 through the exhaust groove 11.
The stator is divided into a first stator 53 and a second stator 52; the worm groove 27 is arranged on the first stator 53 and the second stator 52; the first stator 53 and the second stator 52 are formed as end covers, and the housing 16 is disposed between the second stator 52 and the rotor 3 in a fitting manner.
The first stator 53 and the second stator 52 are provided with exhaust ports 38, and the periphery of the rotor 3 positioned in the first stator 53 and the second stator 52 is connected with an exhaust switch 29; the discharge switch 29 is formed with a rotary plug 39 for opening and sealing the scroll groove 27 during rotation of the rotor 3, and the rotary plug 39 opens the scroll groove 27 and guides the discharge of the pressurized mixture to the outside through the discharge port 38. The pilot exhaust may inject work.
The outward exhaust work of the exhaust mechanism is performed in a turbine mode.
The number of said valves 9 is one or two more than twice the number of pistons 5.
The jet burner is of a siphon structure and comprises a nozzle 61 and a siphon air port; the jet burner is connected to the end surface of the piston 5; the injection combustor is provided with a plurality of matching pistons 5 and cavities.
The injection burner further comprises a warming means 63 and the ignition means 64; the heating device 63 is used for heating and gasifying the pressure fuel which is introduced for the first time after the engine is started, and the ignition device 64 is used for igniting the pressure fuel which is heated and gasified by the heating device 63.
The invention of the rotary turbojet fuel engine with high efficiency and secondary work doing can be applied to all occasions needing energy power in implementation.
The application mode of the technology is that in the application of the technology of a pressure gas piston spraying type rotary engine system (with the patent application number of CN2018109947700) applied for doing work twice, fuel gas is directly adopted to generate warm pressure gas so as to supplement a new structure assumption for doing work by conversion. The specific implementation of the method is required to be configured on a product which has a plurality of spaces and is applied for secondary work.
The fundamental conclusion is that the generated pressure gas completes the first work application through the pressure of the gas, and then completes the application of the first part of all work in the second work. Namely, after acting force of pressure intensity and pressure is pushed to the piston 5 by doing work for the first time; then it is determined that the valve 9 in the chamber is open and closed due to the movement of the piston 5; after the valve 9 in the cavity is closed, the cavity stores and stores all the pressure gas fed in; then the air discharge groove 11 and the air compression groove 12 rotate along with the rotor 3, the air compression groove 12 and the air discharge groove 11 discharge air, and the first step of the discharge is the practical application of the design of the invention.
The volute groove 27 which can be set to be triangular on the stator is discharged through the exhaust groove 11 and the air compression groove 12, and correspondingly, the air compression groove 12 generates reaction force to the rotor 3 to apply work after being fully pressurized; after the worm pressure groove 27 is used for doing work, the pressure gas in the groove is sprayed and discharged outwards, and meanwhile, the surplus work is used, so that the auxiliary work doing effect during the discharge of the pressure gas is increased. And then, releasing the pressure gas to do work by a turbine, wherein the application of the work done by the turbine is the second work defined by us, and can also be a second auxiliary work doing unit.
A gas discharge hole 10 for discharging residual pressure gas is provided at the nearest position on the side of each valve 9, and the gas discharge hole 10 is provided on the rotor 3. After working through the worm grooves 27 of several stators, the pressure in the cavity has already applied a certain amount of pressure volume, but cannot be used up; so if it is desired to evacuate the pressure gas in the corresponding chamber of the piston 5, the pressure gas in the chamber must be evacuated. The piston 5 needs to enter the cavity of the previous valve 9, and pressure gas exists, so that if the pressure gas exists behind the operation of the piston 5, the working efficiency of the piston 5 is influenced; evacuation is one of the necessary things. Determining that there is still pressure gas present behind the piston 5; since this pressure will cause resistance of the piston 5; normal atmospheric pressure is assured behind the piston 5. Therefore, residual pressure gas is designed to be discharged and applied by a rear jet discharge port; the use of such a discharge of the pressurized gas is likewise to give it, via the angled exhaust jet openings 28, additional work for the turbine jet; this work is also defined as the application of the third auxiliary work unit after the second work.
Example two
Referring to fig. 1-5, an embodiment of a rotary turbojet engine with secondary work is provided.
The applicant filed a patent of "pressure gas piston blow-out type rotary engine system for two-time work application" with patent application number CN2018109947700, and filed an international patent application through PCT. The technical scheme of the rotary turbojet fuel engine doing work twice is improved on the technology of a pressure gas piston spraying type rotary engine system applying work twice. The rotary turbojet fuel engine with secondary work doing directly adopts a fuel gas combustion injection technology to realize the application work doing of the secondary work doing as a technical key point. And when doing work for the second time, the pressure gas hedging mode is adopted as the added technical effect of the first work application.
The technology of the rotary turbojet fuel engine doing work for the second time is not supposed and combined in the industry; that is, there is no motivation to apply the internal energy generated by the primary input fuel or gas to the secondary conversion work in two parts, and there is no application technology of continuous rotation work without gap and continuous rotation with the rotation of the rotor shaft concentrically arranged with the piston 5.
In the technology of the rotary turbojet fuel engine doing work for the second time, the conversion work application is that the piston 5 of the engine can push and do work through the pressure intensity and the pressure of the pressure gas, then the pressure gas obtained by combustion is stored in the other space of the cavity due to the multi-space structure built in the engine, and then the second conversion work mode is completed, so that the application of the two conversion work applications is realized.
The key to defining the fuel engine conversion equipment to complete two or more space application technologies is the need to change and improve the application conversion efficiency of the fuel engine.
The rotary turbojet fuel engine with secondary work application changes the structure of a plurality of spaces generated by the structural mode of the fuel engine, so that two synchronous and continuous work applications in two spaces can be completed in the combustion of fuel input once, all low efficiency problems of the original piston working mode are changed, and the improvement is carried out in the technical field of fuel engine equipment which is changed to be applied at present. The applicant's idea is to modify the drawbacks present in fuel engine applications. The applicant finds out in research, development and practical application that the device in the energy fuel application process has the defect of lacking application space technology, namely, the concept of only one application space in all devices using fuel engines and the application of realizing two times of work is unavailable. The applicant considers that the problem of establishing a plurality of space structures of fuel engine application equipment is solved, namely, two or more working application spaces need to be established in a fuel engine conversion application equipment system to complete the energy of mixed pressure gas generated by burning or exploding once input fuel energy so as to generate an application mode for realizing two times of conversion working of the pressure gas.
The invention patent applied by the applicant at this time is a specific application of performing synchronous subsequent second work on the pressure gas stored in the cavity after the fuel engine performs pressure work for the first time in the application of a pressure gas piston injection type rotary engine system applied by two times of work. The subsequent design and application are carried out on the form that the gas pressure (expansion pressure) stored after the first work doing process needs to do work again, so that the first pressure expansion work doing and the pressure of the second pressure gas and the quality of the released (turbine) pressure gas are discharged to fully and completely do work. In the second work doing designed by the applicant, the work doing principle of opposite angle punching of the rectangular triangular groove is adopted to do work under pressure first, and then the worm pressure groove 27 is used for synchronously releasing injection and releasing work doing of the turbine. The applicant defines that the pressure and pressure working application is firstly completed in the process of performing the second step of release (turbine) after the first step of working of the pressure gas generated after the fuel gas is combusted, so that the application that the pressure gas input once can complete more than two times of all working can be completed, and the application can be realized.
Furthermore, the rotary turbojet fuel engine doing work for the second time is an application for improving the structure of the original engine in a pressure gas piston spraying type rotary engine system applying work for the second time, and the pressure gas is sent to be converted to do work and is changed into the temperature and pressure gas generated by directly burning fuel gas and supplied to the engine to do work for the second time. It is known that the combustion of fuel can mix air and then thermally expand the mixed air to generate warm-pressure gas (P1 × V1)/T1 ═ P2 × V2)/T2; the pressure of the injected fuel determines the pressure of the gas generated later (for example, in a turbojet); however, pressurizing the fuel is a relatively small energy requirement, so application modes are identified in which high efficiency conversion can be achieved.
The rotary turbojet fuel engine with secondary work application comprises a piston structure body consisting of one or more groups of pistons 5, and the piston structure body is matched with an engine sealed cavity. The rear portion of the piston 5 heats the pressurized fuel supplied through the fuel supply pipe 62 by the nozzle 61 and then performs injection combustion to form a mixed warm pressurized gas, and the pressure of the generated pressurized gas is determined by the pressure of the injected fuel. The piston 5 is pushed to rotate by the pressure thrust of the injection pressure of the nozzle 61 and the pressure of the warm pressure gas generated behind the piston 5. Under the action of a valve 9 (closed) behind the piston 5, the piston 5 does work for the first time under the pressure of pressure gas, and the conversion work-doing mode technology is that the end face of the piston 5 on the rotor 3 of the engine is provided with the valve 9, and the pressure gas generated by injection is subjected to the resistance of the valve 9 to enable the piston 5 to be subjected to the pressure to do rotary movement. The piston 5 on the rotor 3 is designed to work normally under the condition of over-torque load, so the pressure of fuel gas determines the height of the pressure gas and determines the variable torque of the piston 5 to perform rotary movement. Thus, the first work flow of the piston 5 is determined, and then it is determined that gas which is remained in the cavity due to the torque resistance of the piston 5 and has pressure exists in the moving process of a group of pistons 5, so that the gas volume which is obtained after the piston 5 rotates and has the basic original pressure in the cavity due to the torque resistance of the piston 5 is determined, and the energy which is stored in the cavity and exists under the torque resistance of the piston 5 is the energy of all pressure gas. It can be seen from fig. 2 that when the moving piston 5 moves out of the valve 9 into the second chamber 8. The pressure gas which pushes the piston 5 to move at the back is stored in the cavity (the first cavity 7), then when the moving piston 5 moves through the second valve 9 at the back and is closed, the piston 5 can continuously do continuous jet combustion and continuously do work as before, then the pressure gas can be continuously introduced into the cavity (the third cavity 2) at the back, and then all the pressure gas stored due to input is generated in the cavity (the first cavity 7 and the second cavity 8) between the two valves 9. The main aspect of the invention is to carry out two work applications on the injection combustion synthesized temperature-pressure gas formed after fuel gas combustion, and the design realizes two work processes in the range of the second work, namely, the second conversion work application is carried out on the stored pressure gas after the first conversion work; in the second work, the first work application process adopts the hedging pressure to perform conversion work, the second step is the release turbine conversion work application of the pressure gas discharged after the hedging work, and the second work application process is the two-step conversion work application process for performing the second work.
The invention relates to a structural mode for applying pressure gas obtained after fuel gas is injected and combusted to perform first conversion work, then storing the pressure gas and performing second work. The technical requirement of the structure is that in the pressure gas piston spraying type rotary engine system applied by two-time work, the nozzle 61 for fuel gas spraying and feeding sprays the input pressure fuel gas, mixes air to perform spraying combustion and generate pressure gas so as to perform first work through the piston 5 on the rotor 3, then stores the pressure gas in the cavity, and then discharges and sprays the pressure gas in the cavity to realize second conversion work application of opposite impact and turbine release. The first work application is a simple working process, namely the pressure of fuel gas is applied and then injection is carried out. Because of the need for mixed air to be combusted during the injection process; then after combustion, because the combustion has the function of expanding air, a combustion discharge pressure determined by the pressure of the fuel is generated; this creates a combustion warm pressure gas having a pressure. The first work of the piston 5 is the movement work under the pushing of the pressure. Because of the rotation movement of the rotor 3, the exhaust groove 11 on the rotor 3 synchronizes the work that the piston 5 enters the next step position, namely the rotor 3 is sprayed and applied to the pressure gas in the space of the cavity through the inclined plane nozzle on the exhaust groove 11 in the rotation process, and then is applied to the punching work for the first time through the worm groove 27; the first step is a pressure and pressure opposite impact pressure application mode for applying work for the second time after the first work is done, and the first step is to apply work for gas pressure by adopting a mode that the worm pressure groove 27 corresponds to the gas pressing groove 12 on the rotor 3. That is, by the rotation of the rotor 3, the pressure gas in the cavity between the rotor 3 and the stator is discharged from the inclined plane nozzle through the plurality of volute grooves 27 on the stator corresponding to the pressure groove 12 to apply the inclined angle pressure, and the thrust pressure is generated to make the rotor 3 rotate by an acting force of pressure. The rotary fuel engine of the invention has more than two working application spaces, so two independent working application modes can be completed, namely two completely independent spaces are provided, so that two or more independent conversion working applications can be completed. According to research, volume compression is the reality of high-efficiency conversion work; therefore, the air groove is designed in a mode that the pressure air needs to be discharged to complete the first-step opposite-impact work application. The design is that a plurality of symmetrical rectangular worm pressure grooves 27 are fully distributed on stators on two sides, two exhaust grooves 11 with the same size and specification are also arranged on the end face of the rotor 3, two air pressure grooves 12 with the same size and two spaced rectangular air charging grooves 26 are also arranged on the end face of the rotor 3, the air charging grooves 26 can correspond to the plurality of rectangular worm pressure grooves 27 arranged on the stators, the pressure jet discharge and the worm pressure pushing work of the worm pressure grooves 27 are realized one by one in the rotation of the rotor 3, the work doing concept is that the end face area of the worm pressure grooves 27 of the stators corresponds to the pressure acting force of the areas of the rotors 3 and the cavities through the air pressure grooves 12 of the rotor 3, and the magnitude of the two punching reaction forces determines the magnitude of the work doing acting pressure through the end face plane area in the worm pressure grooves 27 and the size area of the notches of the air pressure grooves 12. This forms two reactive forces that the cavity (gas pressure) produced that can inflate the pressure for rotor 3 and stator, cavity, lets the pressure gas that discharges carry out the first step work application of second: a plurality of worm pressure grooves 27 with rectangular shapes can be arranged on the whole stator; the rotor 3 is also provided with a compressed air groove 12 with the same size as the stator and two rectangular air-filling grooves 26 separated at intervals; when the rotor 3 rotates, the exhaust grooves 11 on the rotor 3 can be punched into the worm pressure groove 27 for multiple times, and then the exhaust grooves 11 on the end surfaces of the two sides of the rotor 3 discharge pressure gas to the worm pressure groove 27 to generate reaction force for the stator, so that the application of acting on the impact pressure is realized. Similarly, after each work application, the pressure in the cavity is simultaneously reduced, because the rotor 3 is rotated, the pressure in the volute pressure groove 27 is determined to be discharged and inflated through a plurality of steps, then the discharge switch 29 of the rotor 3 is also rotated, the discharge switch 29 is opened and closed to discharge the pressure gas in the volute pressure groove 27 through the exhaust port 38, and the exhaust groove of the exhaust switch is designed to be an inclined surface in the discharging process; so that the same effect can be done to assist in releasing the work of the turbine when the turbine pressure groove 27 is discharged. After venting, because the volute 27 and the chamber volume have a volume asymmetry, the pressurized gas is still present in the chamber and has a reduced pressurized gas volume after the course of several pressurized work flow applications. The pressure gas in the volute groove 27 is discharged through the exhaust port 38 along with the rotation of the discharge switch 29 driven by the rotor 3, so that the pressure gas in the cavity tends to be reduced; the chamber is in a state where the input pressure is discharged to achieve a relative reduction by one degree. However, a part of residual pressure gas exists in the cavity, and after the residual pressure gas is pressurized and discharged for multiple times through the air compressing groove 12 to output work, the residual pressure gas still exists in the cavity, because the work design is that the cavity is used for completing pressure-pressure conversion work under higher pressure. The conversion work application is used as the first step, so that the conversion work is performed in the first part; the pressure gas exists in the cavity continuously, and after the first pressure gas groove 12 is applied to work by the worm pressure groove 27, the gas needs to be sprayed and discharged to work by the worm pressure groove 27 through the discharge switch 29 and the exhaust port 38. The residual pressure gas still existing in the cavity after the first discharge is designed to be placed on the cover plate of the stator to be subjected to evacuation treatment on the cavity through the angular exhaust injection hole 28 which plays a final discharge role, so that the residual pressure gas in the cavity is discharged through the air compression groove 12 of the rotor 3 and the exhaust injection hole 28 of the stator corresponding to the turbine blade, and the application of conversion work is performed on the impulse and mass release turbine of the turbine blade, namely the application mode for performing the second step of work. The application mode of the pressure gas exhausted under the condition of using the high-pressure gas is an application mode of angular jet to the steam turbine. The rotation of the rotor 3 is determined to discharge the multiple injections of the volute 27 through the dischargeable discharge switch 29, and if the high-pressure gas is adopted for use, the pressure gas discharge with pressure is determined to also enter the application mode of the steam turbine so as to perform work application of angular injection release (turbine). This turbine work is defined and described in the above patent application; and is provided with a drawing; we will not describe the mode of application of work to the turbine.
Utilization of the combustion heat energy temperature: according to the law of thermal energy, the energy generated in the fuel combustion process can be divided into a plurality of parts, and the utilization of the heat energy in the whole work-doing system is designed to be the subsidiary application of liquefied pressure gas; the applied structure adopts the matching application of the technology of a pressure gas piston spraying type rotary engine system applied by two-time work; that is to say "a pressurized gas piston injection type rotary engine system for two work applications" may be included as part of the content of this patent application. From the above information on this patent, i can understand that the engine has very high efficiency; so we can use this heat energy for utilization; all the energy of the engine is fully utilized; the conversion efficiency of the system is improved.
The rotary turbojet fuel engine with secondary work doing changes the application that the prior engine can only complete primary work doing on the hot-pressing gas generated by combustion/explosion in one space, and achieves the purpose of completing secondary work doing on the hot-pressing gas generated by combustion in two spaces. The structure of the rotary turbojet fuel engine with secondary work application is changed, for example, the reciprocating motion of the piston 5 engine is changed into direct rotary motion, so that the application of converting work application in a mode that the piston 5 continuously applies work in multiple spaces (annular cavities) is realized. The rotary turbojet fuel engine doing work for the second time has the advantages that all combustion jet mixed temperature and pressure gas remained after the piston 5 rotates after the piston 5 does work for the first time is used for doing work again for the second time. The technology is to realize the application of twice conversion and work application in multiple spaces (a first cavity 7, a second cavity 8 and a third cavity 2). The working mode is that the temperature-pressure mixed pressure gas generated by the combustion injection of the pressurized fuel at the first time does the first pressure work; the pressure gas stored in the space before rotation then performs a second pressure gas mass turbine work release. In conclusion, the rotary turbojet fuel engine with secondary work application has the function of changing the structure of the fuel engine to generate structural changes of a plurality of spaces, so that the fuel input for one time can burn internal energy, and the application of synchronous continuous secondary work application in the two spaces is completed.
The technical points of the rotary turbojet fuel engine doing work for the second time are as follows, and can be used as a supplement to the technical scheme.
1. The method is characterized in that one-time injection of combustion temperature-pressure mixed air to generate pressure gas is completed on the same system device (fuel engine), and two-time work application can be synchronously and continuously completed in two spaces, namely the device stores the pressure gas after the first work application and then applies the work again for the second time. A fuel gas with variable pressure is fed into the piston 5 in the closed cavity of the engine through a fuel feeding pipeline 62, the fuel gas is sprayed, combusted and mixed into a mixed gas with pressure and containing air, the mixed gas is sprayed out to form the piston 5 and then has the energy of pressure intensity for pushing the piston 5 to rotate and move and do work rotationally, after the rotor 3 and the piston 5 are pushed to rotate and transfer out of the cavity of the first valve 9, because the position of the piston 5 is changed among a plurality of valves 9 in the cavity, the piston 5 continues to burn and spray in the cavity after entering the cavity corresponding to the second valve 9 to finish continuous work, the piston 5 burns and sprays mixed pressure gas to obtain the storage of the pressure gas in the cavity corresponding to the first valve 9 due to the moment resistance of the piston 5, and then the stored pressure gas is converted into two conversion work of second pressure and release injection.
2. The reciprocating motion of the piston 5 is changed into the rotary continuous work-doing motion mode of the piston 5. The design adopts more than two spaces and is an application mode capable of continuously doing work, and the flow of secondary work is designed into a working mode of synchronously operating and doing work on the same equipment so as to realize the high-efficiency full-energy utilization of fuel gas.
3. The fuel gas with variable pressure is fed to feed the combustible materials into the nozzle 61 in a gas vortex spraying mode for combustion injection, and the piston 5 generates pressure gas to push the piston 5 to rotate and move due to the combustion injection and the air sucked in by a siphon. The valves 9 include a first valve, a second valve, and a third valve. After the piston 5 passes through a space position formed by the first valve 9 and the second valve 9, the piston 5 moves to a position between the second valve 9 and the third valve 9 to continuously combust and spray and carry air to generate mixed pressure gas to push the piston 5 to continuously rotate to do work, after the piston 5 completes a continuous movement work doing mode, the gas with pressure mixed by combustion and spraying is stored in a cavity corresponding to the first valve 9 and the second valve 9 behind the piston 5 because of the moment resistance of the piston 5, the stored pressure gas performs the second work doing, the second work doing can be defined as a two-part work doing mode, namely, the expansion work of oblique angle of pressure of the pressure gas to pressure, and the injection conversion work of pressure gas mass release (of a steam turbine) is completed after the work doing the work to pressure expansion is completed.
4. The piston 5 is arranged on the rotor 3, and the designed piston 5 is of a rectangular structure; the designed piston 5 can be a structure which can be flexibly applied in two directions so as to adapt to the axial deviation generated by combustion and the delayed damping action of combustion impact force, the number of the pistons 5 is designed according to the size of the rotor 3 so as to determine the configuration number, the pressure gas input into the cavity from the combustion jet mixed air exists between the two valves 9, and the fuel feeding pipeline 62 adopts a one-way input anti-backfire structure; the number of nozzles 61 which burn on the piston 5 structure is configured according to the actual calculation application. The rotor 3 is provided with exhaust grooves 11 and air compression grooves 12 which are arranged at equal intervals according to the same number of the configured pistons 5.
5. The input mixed fuel gas is designed to be input through the inside of the center of one end of the rotor 3. The method is that fuel gas and pressure air are simultaneously input into a closed cavity of the engine through a shaft 1 port at one end of the engine by adopting a sleeve process, a fuel feeding pipeline 62 and an air feeding channel 65 inside the closed cavity feed the fuel and combustion-supporting air to a nozzle 61 on a piston 5, and the nozzle 61 is mixed by spraying siphon air and jointly fed into the cavity. The warming device 63 and the ignition device 64, as well as the automatic control combustion device, can be designed to effectively complete the working process of the piston 5 in the cavity which can do work.
6. The cavity is a closed annular cavity formed by the stator and the rotor 3, the valve 9 and the piston 5, and a plurality of application spaces which are matched and established according to the number of the pistons 5 and can allow the pistons 5 to move and apply work are designed in the cavity. The number of the valves 9 is the number of the pistons 5 multiplied by two plus one or two, the valves 9 separate the cavity, and the valves 9 are arranged on an application structure of an engine closed cavity to establish a plurality of application spaces. The working process of each piston 5 is designed and established to have two or more than two working application spaces.
7. When the pressure fuel gas is injected and combusted in the nozzle 61, the cavity has pressure, so that air at the mixing periphery must be introduced into the cavity during injection. Since oxygen is required for combustion and at the same time expanding the air entering the chamber, a gas under pressure behind the piston 5 is generated in the chamber and can then push the piston 5 to move.
8. When the second work is applied, three work applying modes are designed; the first work doing is the opposite punching work of pressure intensity and pressure intensity on the punching worm pressure groove 27, and then the releasing jet work of the pressure gas discharging quality in the worm pressure groove 27; the third is the work applied by the release impulse of the residual pressure gas mass in the cavity. The specific working mode is that triangular bevel cutting grooves are processed on stators on two sides, a pressure air groove 12 is designed at the opposite position of a rotor 3, an exhaust switch 29 rotating along with the rotor 3 is designed in the stator, the pressure air working mode of the exhaust switch 29 is a jet working design, and exhaust jet holes 28 communicated with the last residual air in a cavity are designed on two end face covers of the stator so as to exhaust all residual pressure air existing in the cavity at last and complete the impulse release turbine working application of a steam turbine.
9. The invention relates to a conversion work application that can install two sets of devices in the same system equipment, namely, the heat generated in the fuel gas combustion process is utilized by work, the design can be matched with the same equipment according to the heat generated by an engine, and the auxiliary synchronous work application of liquefied pressure gas is adopted, and the applied structural mode is the technology of a pressure gas piston spraying type rotary engine system which adopts the twice work application; the patent application number is CN 2018109947700.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (10)
1. A rotary turbojet fuel engine doing work for the second time is characterized by comprising an engine sealed cavity and stators fixed at two ends of the engine sealed cavity; a rotor supported by a stator is arranged in the engine closed cavity in a penetrating manner; an annular cavity is formed between the rotor and the engine closed cavity, a plurality of valves are connected to the engine closed cavity, and the valve separation cavity is a plurality of cavities; the rotor is matched with an engine sealed cavity to be connected with a piston rotating along with the rotor, and one side of the piston is provided with an injection combustor which is used for injecting gasified pressure fuel to the cavity; the valve is opened and closed to drive the piston to rotate in coordination with the injection of the pressure fuel, and the pressure fuel is ignited and combusted by an ignition device of the injection combustor in coordination with the injection of the pressure fuel to drive the piston to drive the rotor to rotate; one of the cavities stores the combusted mixed gas with pressure, and the piston leaves the cavity and enters the other cavity to be exhausted outwards through the exhaust mechanism and do work.
2. The rotary turbojet fuel engine performing secondary work according to claim 1, wherein the rotor is connected with a shaft, and a fuel feeding pipeline penetrates through the center of the shaft; an air feeding channel is formed between the fuel feeding pipeline and the shaft, and the fuel feeding pipeline and the air feeding channel are respectively communicated with the jet burner.
3. The rotary turbojet fuel engine performing secondary work according to claim 1, wherein the exhaust mechanism comprises a scroll groove formed in the stator and a compression groove formed in the rotor; the air compression groove is arranged on the end surface of the rotor; the pressurized mixed gas in the cavity during the rotation of the rotor enters the gas pressing groove and the worm pressure groove, and the pressurized mixed gas is released to punch the rotor and drive the rotor to rotate.
4. The rotary turbojet fuel engine doing work twice as recited in claim 3, wherein the rotor is provided with exhaust grooves communicated with the air compression grooves, and the air compression grooves and the exhaust grooves are arranged in pairs and are located on two end faces of the rotor; the pressurized mixed gas in the cavity during the rotation of the rotor enters the gas pressing groove and the worm pressure groove through the exhaust groove.
5. The rotary turbojet fuel engine performing secondary work according to claim 3 or 4, wherein the stator is divided into a first stator and a second stator; the worm pressure groove is arranged on the first stator and the second stator; the first stator and the second stator form end face covers, and a shell is arranged between the second stator and the rotor in a matched mode.
6. The rotary turbojet fuel engine doing work twice as recited in claim 5, wherein the first stator and the second stator are provided with exhaust ports, and the periphery of the rotor in the first stator and the second stator is connected with an exhaust switch; the discharge switch is formed with a rotary plug which opens and seals the worm pressure groove in the rotation of the rotor, and the rotary plug opens the worm pressure groove and discharges the mixed gas with pressure through the exhaust port in an outward guide mode to do work.
7. The secondary work rotary turbojet fuel engine of claim 1 wherein outward exhaust work of the exhaust mechanism is performed in a turbine mode.
8. The secondary work-producing rotary turbojet fuel engine of claim 1 wherein the number of valves is one or two more than twice the number of pistons.
9. The rotary turbojet fuel engine performing secondary work according to claim 1, wherein the jet burner is of a siphon construction and includes a nozzle and a siphon air port; the jet burner is connected to the end surface of the piston; the injection combustor is provided with a plurality of matching pistons and cavities.
10. The secondary work-doing rotary turbojet fuel engine of claim 1 or 9, wherein the injection burner further comprises a warming device and the ignition device; the heating device is used for heating up the pressure fuel which is firstly introduced after the gasification engine is started, and the ignition device is used for igniting the pressure fuel which is heated up and gasified by the heating device.
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| CN202010719427.2A CN113969836A (en) | 2020-07-23 | 2020-07-23 | Rotary turbojet fuel engine doing work secondarily |
| PCT/CN2020/112942 WO2022016666A1 (en) | 2020-07-23 | 2020-09-02 | Rotary turbojet fuel engine capable of performing work two times |
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| CN202010719427.2A CN113969836A (en) | 2020-07-23 | 2020-07-23 | Rotary turbojet fuel engine doing work secondarily |
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| CN102121402A (en) * | 2010-01-08 | 2011-07-13 | 郭文清 | Steam engine |
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| CN1282833A (en) * | 2000-08-01 | 2001-02-07 | 黄有文 | Split-type compression ignited rotor engine |
| RU2006122366A (en) * | 2006-06-22 | 2008-01-10 | Олег Аполлосович Айзуппе (RU) | METHOD OF WORK OF THE HEAT ENGINE AND ITS DEVICE |
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Application publication date: 20220125 |