CN111075564B - Turbine rotor engine - Google Patents
Turbine rotor engine Download PDFInfo
- Publication number
- CN111075564B CN111075564B CN201911370745.6A CN201911370745A CN111075564B CN 111075564 B CN111075564 B CN 111075564B CN 201911370745 A CN201911370745 A CN 201911370745A CN 111075564 B CN111075564 B CN 111075564B
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- Prior art keywords
- turbine
- combustion chamber
- stroke combustion
- inlet channel
- stage turbine
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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
- 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
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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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
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
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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)
- Supercharger (AREA)
Abstract
The invention discloses a turbine rotor engine which comprises a shell, a high-speed starter, a front turbine, a one-stroke combustion chamber and a rear-end turbine set, wherein a protective cover is arranged at one side end of the shell, a solid shaft is arranged in the shell, one end of the solid shaft penetrates through the protective cover and is connected with the high-speed starter, the front turbine is arranged on the left side of the solid shaft, which is positioned in the shell, the one-stroke combustion chamber is arranged on the right side of the front turbine, which is positioned on the solid shaft, and the rear-end turbine set is arranged on the right side of the one-stroke combustion chamber, which is positioned on the solid shaft. The turbine rotor engine has the advantages of simple transmission structure, saving of a compression process, improvement of transmission efficiency, sufficient fuel combustion, low manufacturing cost, avoidance of pollutant emission, improvement of working efficiency of the engine, reduction of engine tail gas pollution and belongs to a new energy environment-friendly engine.
Description
Technical Field
The invention relates to an engine, in particular to a turbine rotor engine.
Background
An engine is a machine that can convert other forms of energy into mechanical energy, including, for example, internal combustion engines, external combustion engines, jet engines, electric motors, and the like. Such as internal combustion engines, typically convert chemical energy into mechanical energy. The engine is applicable to both the power generation device and the whole machine including the power device. Engines were first introduced in the united kingdom, and the engine concept is also derived from english, which is meant in its meaning as "power generating machinery".
The existing wheel engine has simple structure and low combustion conversion efficiency, but the common internal combustion engine has more transmission parts, too complex structure, high cost and can produce tail gas pollution. Accordingly, one skilled in the art provides a turbine rotary engine to solve the problems set forth in the background above.
Disclosure of Invention
The object of the present invention is to provide a turbine rotary engine that solves the problems set forth in the background art.
In order to achieve the purpose, the invention provides the following technical scheme:
a turbine rotor engine comprises a shell, a high-speed starter, a front turbine, a one-stroke combustion chamber and a rear-end turbine set, wherein a protective cover is arranged at one side end of the shell, a solid shaft is arranged in the shell, one end of the solid shaft penetrates through the protective cover and is connected with the high-speed starter, the front turbine is arranged on the left side, located inside the shell, of the solid shaft, the one-stroke combustion chamber is arranged on the right side, located on the front turbine, of the solid shaft, and the rear-end turbine set is arranged on the right side, located on the one-stroke combustion chamber, of the solid shaft;
the first-stroke combustion chamber is a 120-degree trisection three-blade circular turbine, the interior of the three-blade circular turbine is of a hollow structure, a second air inlet channel, a high-speed pulse continuous igniter and an exhaust hole are respectively arranged on the first-stroke combustion chamber, and the second air inlet channel comprises an air inlet channel and a hydrogen inlet channel;
the hydrogen intake duct of the intake duct two of a stroke combustion chamber passes through the pipe connection hydrogen basin, the air intake duct passes through pipe connection air cleaner, and the inlet non return ware is installed to one side of nearly air intake duct on the pipeline of air intake duct and air cleaner, spout non return ware is installed to one side of nearly hydrogen intake duct on the pipeline that hydrogen intake duct and hydrogen basin are connected, and be equipped with combustible gas controller, check valve and flame arrester on the pipeline between spout non return ware and the hydrogen basin in proper order, the stroke combustion chamber can be changed into two stroke combustion chambers, three stroke combustion chamber or four stroke combustion chamber.
As a further scheme of the invention: an air exchange passage is arranged between the rear-end turbine group and the shell, and an air inlet passage I is arranged on the protective cover.
As a still further scheme of the invention: the distance between the combustible gas controller, the check valve and the flame retardant device and the hydrogen storage tank is gradually increased.
As a still further scheme of the invention: the two-stroke combustion chamber is a 60-degree six-equal-division six-blade circular turbine.
As a still further scheme of the invention: the three-stroke combustion chamber is a 40-degree nine-equal-division nine-blade circular turbine.
As a still further scheme of the invention: the four-stroke combustion chamber is a 30-degree twelve-equal-division twelve-blade circular turbine.
As a still further scheme of the invention: rear end turbine group adopts tertiary turbine group in one-stroke combustion chamber and the two-stroke combustion chamber, and tertiary turbine group includes one-level turbine, second grade turbine and tertiary turbine, and one side of tertiary turbine group is provided with the waste gas import, and the opposite side is equipped with the gas vent, and the outside that just is located one-level turbine, second grade turbine and tertiary turbine still is equipped with the heat dissipation layer.
As a still further scheme of the invention: a five-stage turbine group is adopted in the three-stroke combustion chamber and the four-stroke combustion chamber, the five-stage turbine group is different from the three-stage turbine group in that a four-stage turbine and a five-stage turbine are added, and the rest structures are the same as those of the three-stage turbine group.
As a still further scheme of the invention: the turbine rotor engine can be applied to automobile engines, small and medium-sized ship engines, small aircrafts, helicopters and propeller type airplane engines.
Compared with the prior art, the invention has the beneficial effects that:
the turbine rotor engine has the advantages of simple transmission structure, saving of a compression process, improvement of transmission efficiency, sufficient fuel combustion, low manufacturing cost, avoidance of pollutant emission, improvement of working efficiency of the engine, reduction of engine tail gas pollution and belongs to a new energy environment-friendly engine.
Drawings
Fig. 1 is a schematic structural view of a turbine rotary engine.
Fig. 2 is a schematic view of the internal structure of a one-stroke combustion chamber in a turbine rotary engine.
FIG. 3 is a schematic diagram of a one-stroke combustor in a turbine rotary engine connected to a hydrogen tank and an air filter.
Fig. 4 is a schematic structural view of a two-stroke combustion chamber (a), a three-stroke combustion chamber (b), and a four-stroke combustion chamber (c) in a turbo rotary engine.
Fig. 5 is a schematic structural view of a turbine group of a one-stroke and two-stroke combustion chamber of a rear turbine group in a turbine rotary engine.
Fig. 6 is a schematic structural view of a three-stroke combustion chamber and a turbine group above the three-stroke combustion chamber of a rear turbine group in a turbo rotary engine.
In the figure: 1-a shell; 2-a protective cover; 3-a solid shaft; 4-high speed starter; 5-a front turbine; 6-one-stroke combustion chamber; 7-rear turbine group; 71-a first stage turbine; 72-a two-stage turbine; 73-a three-stage turbine; 74-a four-stage turbine; 75-five stage turbine; 76-a heat dissipation layer; 8-air changing channel; 9-an air inlet channel I; 10, an air inlet channel II; 11-air intake; 12-a hydrogen inlet; 13-high speed pulse continuous igniter; 14-an exhaust port; 15-air vent; 16-a hydrogen storage tank; 17-an air filter; 18-spout backstop; 19-inlet backstop; 20-a combustible gas controller; 21-a check valve; 22-flame arrestor; 23-a two-stroke combustion chamber; 24-a three-stroke combustion chamber; 25-four stroke combustion chamber.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the embodiment of the invention, as shown in fig. 1-2, the turbine rotary engine comprises a shell 1, a high-speed starter 4, a front turbine 5, a one-stroke combustion chamber 6 and a rear-end turbine group 7, wherein a protective cover 2 is arranged at one side end of the shell 1, a solid shaft 3 is arranged in the shell 1, one end of the solid shaft 3 penetrates through the protective cover 2 and is connected with the high-speed starter 4, the front turbine 5 is arranged on the left side of the solid shaft 3 positioned in the shell 1, the one-stroke combustion chamber 6 is arranged on the solid shaft 3 positioned on the right side of the front turbine 5, and the rear-end turbine group 7 is arranged on the solid shaft 3 positioned on the right side of the one-stroke combustion chamber 6;
an air exchange passage 8 is arranged between the rear-end turbine group 7 and the shell 1, and an air inlet passage I9 is arranged on the protective cover 2;
the first-stroke combustion chamber 6 is a 120-degree trisection three-blade circular turbine, the interior of the three-blade circular turbine is of a hollow structure, an air inlet channel II 10, a high-speed pulse continuous igniter 13 and an exhaust hole 15 are respectively arranged on the first-stroke combustion chamber 6, and the air inlet channel II 10 comprises an air inlet channel 11 and a hydrogen inlet channel 12;
as shown in fig. 3, fig. 3 is a schematic structural diagram of the connection of the one-stroke combustion chamber with a hydrogen storage tank and an air filter, a hydrogen inlet channel 12 of a second inlet channel 10 of the one-stroke combustion chamber 6 is connected with the hydrogen storage tank 16 through a pipeline, the air inlet channel 11 is connected with the air filter 17 through a pipeline, an inlet check device 19 is installed on one side, close to the air inlet channel 11, of the pipeline of the air inlet channel 11 and the air filter 17, a spout check device 18 is installed on one side, close to the hydrogen inlet channel 12, of the pipeline of the hydrogen inlet channel 12 connected with the hydrogen storage tank 16, a combustible gas controller 20, a check valve 21 and a flame retardant device 22 are sequentially arranged on the pipeline between the spout check device 18 and the hydrogen storage tank 16, and the distances between the combustible gas controller 20, the check valve 21 and the flame retardant device 22 and the hydrogen storage tank 16 are sequentially gradually increased;
as shown in fig. 4, fig. 4 is a schematic structural diagram of the two-stroke combustion chamber 23, the three-stroke combustion chamber 24 and the four-stroke combustion chamber 25, wherein the two-stroke combustion chamber 23 is a six-blade circular turbine with 60 degrees and six equal divisions; the three-stroke combustion chamber 24 is a 40-degree nine-equal-division nine-blade circular turbine; the four-stroke combustion chamber 25 is a 30-degree twelve-equal-division twelve-blade circular turbine;
the first-stroke combustion chamber 6, the second-stroke combustion chamber 23, the three-stroke combustion chamber 24 and the four-stroke combustion chamber 25 are used for air intake mixing, ignition and exhaust when working, and the process is repeated in this way;
as shown in fig. 5, fig. 5 is a schematic structural diagram of the rear end turbine group 7 used in the one-stroke combustion chamber 6 and the two-stroke combustion chamber 23, the rear end turbine group 7 adopts a three-stage turbine group, which includes a first-stage turbine 71, a second-stage turbine 72 and a third-stage turbine 73, and one side of the three-stage turbine group is provided with an exhaust gas inlet, the other side is provided with an exhaust port 14, and a heat dissipation layer 76 is further disposed outside the first-stage turbine 71, the second-stage turbine 72 and the third-stage turbine 73;
as shown in fig. 6, fig. 6 is a schematic structural diagram of the rear turbine group 7 in the three-stroke combustion chamber 24, the four-stroke combustion chamber 25 and the combustion chamber above the four-stroke combustion chamber, which is a five-stage turbine group, and is different from the three-stage turbine group in that a four-stage turbine 74 and a five-stage turbine 75 are added, and the rest of the structure is the same as that of the three-stage turbine group.
The hydrogen storage tank 16 in the turbine rotor engine stores hydrogen which is the best fuel, other fuels can also but need to have explosion property and can be mixed with air to form explosive mixed gas or mixture, the hydrogen reacts with oxygen to generate water, other combustible substances react with the oxygen to possibly generate pollutants, tail gas treatment is needed, and the hydrogen-oxygen combustion reactant can be directly discharged without treatment;
the hydrogen flows out from a hydrogen storage tank 16, enters a first stroke combustion chamber 6 (a two/three/four stroke combustion chamber) through a combustible gas controller 20, a check valve 21, a flame retardant device 22 and a nozzle check device 18, air enters the first stroke combustion chamber 6 (the two/three/four stroke combustion chamber) through an air filter 17 and an inlet check device 19, the hydrogen and the oxygen are mixed, the high-speed starter 3 starts when the initial start is carried out, the turbine rotates to a high-speed pulse continuous igniter 13 for ignition, high-temperature waste gas at an exhaust hole 15 enters a rear end turbine group 7, secondary combustion is carried out with heated fresh air sucked by a front turbine 5 through an air inlet channel I9, insufficient combustion is prevented, the waste gas is discharged through a first-stage turbine to a fifth-stage turbine, and the process is repeated.
Compared with a four-stroke gasoline and diesel engine, the turbine rotor engine of the invention has the advantages that: the structure is simple, the compression process is omitted, the transmission parts such as a crankshaft, a connecting rod and the like are simplified, the transmission process is simple, the transmission efficiency is improved, and the emission of pollutants such as hydrocarbon and the like is avoided;
compared with a rotary engine: the structure of the triangular rotor and the combustion chamber of the rotor engine causes uneven combustion, the structure is simple, the combustion efficiency is low, the structure of the turbine rotor engine is relatively complex, the structure and the combustion efficiency of the combustion chamber are better than those of the rotor engine, and pollutant emission is avoided;
compared with a turboprop engine: the structure is simple, a front high-pressure turbine group and a combustion chamber are omitted, the manufacturing cost is low, and pollutant emission is avoided;
the turbine rotor engine can be applied to automobile engines, small and medium-sized ship engines, small aircraft, helicopters, propeller type airplane engines and the like.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (7)
1. A turbine rotor engine is characterized by comprising a shell (1), a high-speed starter (4), a front turbine (5), a one-stroke combustion chamber (6) and a rear-end turbine set (7), wherein a protective cover (2) is arranged at one side end of the shell (1), a solid shaft (3) is arranged in the shell (1), one end of the solid shaft (3) penetrates through the protective cover (2) and is connected with the high-speed starter (4), the front turbine (5) is arranged on the left side, located inside the shell (1), of the solid shaft (3), the one-stroke combustion chamber (6) is arranged on the right side, located on the front turbine (5), of the solid shaft (3), and the rear-end turbine set (7) is arranged on the right side, located on the one-stroke combustion chamber (6), of the solid shaft (3);
the one-stroke combustion chamber (6) is a 120-degree trisection three-blade circular turbine, the interior of the three-blade circular turbine is of a hollow structure, an air inlet channel II (10), a high-speed pulse continuous igniter (13) and an exhaust hole (15) are respectively arranged on the one-stroke combustion chamber (6), and the air inlet channel II (10) comprises an air inlet channel (11) and a hydrogen inlet channel (12);
a hydrogen inlet channel (12) of an inlet channel II (10) of the one-stroke combustion chamber (6) is connected with a hydrogen storage tank (16) through a pipeline, the air inlet channel (11) is connected with an air filter (17) through a pipeline, an inlet non-return device (19) is arranged on one side, close to the air inlet channel (11), of the pipeline of the air inlet channel (11) and the air filter (17), a spout non-return device (18) is arranged on one side, close to the hydrogen inlet channel (12), of the pipeline of the hydrogen inlet channel (12) and the hydrogen storage tank (16), a combustible gas controller (20), a check valve (21) and a flame retardant device (22) are sequentially arranged on the pipeline between the spout non-return device (18) and the hydrogen storage tank (16), and the one-stroke combustion chamber (6) can be replaced by a two-stroke combustion chamber (23), a three-stroke combustion chamber (24) or a four-stroke combustion chamber (25);
a rear end turbine group (7) in the first-stroke combustion chamber (6) and the two-stroke combustion chamber (23) adopts a three-stage turbine group, the three-stage turbine group comprises a first-stage turbine (71), a second-stage turbine (72) and a third-stage turbine (73), one side of the three-stage turbine group is provided with a waste gas inlet, the other side of the three-stage turbine group is provided with an exhaust port (14), and a heat dissipation layer (76) is arranged on the outer sides of the first-stage turbine (71), the second-stage turbine (72) and the third-stage turbine (73);
a five-stage turbine group is adopted in the three-stroke combustion chamber (24) and the four-stroke combustion chamber (25), the five-stage turbine group is different from the three-stage turbine group in that a four-stage turbine (74) and a five-stage turbine (75) are added, and the rest structure is the same as that of the three-stage turbine group.
2. A turbo-rotor engine according to claim 1, characterized in that a scavenging duct (8) is provided between the rear turbine group (7) and the casing (1), and the first inlet duct (9) starts on the shroud (2).
3. A turbine rotor engine according to claim 1, characterised in that the combustible gas controller (20), the non-return valve (21) and the flame arrester (22) are located at successively greater distances from the hydrogen storage tank (16).
4. A turbine rotor engine according to claim 1, characterised in that the two-stroke combustion chamber (23) is a 60 degree six-lobed circular turbine.
5. A turbo-rotor engine according to claim 1, characterized in that said three-stroke combustion chamber (24) is a 40 degree nine-lobed circular turbine.
6. A turbo-rotor engine according to claim 1, characterized in that said four-stroke combustion chamber (25) is a 30 degree twelve-segment ten-two-blade circular turbine.
7. The turbine rotor engine as claimed in claim 1, wherein the turbine rotor engine is applicable to automobile engines, small and medium sized ship engines, small aircraft, helicopters, and propeller type aircraft engines.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911370745.6A CN111075564B (en) | 2019-12-27 | 2019-12-27 | Turbine rotor engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911370745.6A CN111075564B (en) | 2019-12-27 | 2019-12-27 | Turbine rotor engine |
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| CN111075564A CN111075564A (en) | 2020-04-28 |
| CN111075564B true CN111075564B (en) | 2022-10-28 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113898470A (en) * | 2020-07-07 | 2022-01-07 | 韩培洲 | Rotor supercharged gas turbine |
| CN111998387A (en) * | 2020-08-18 | 2020-11-27 | 中国空气动力研究与发展中心 | Method and device for promoting scramjet engine to realize starting ignition |
| CN111963313A (en) * | 2020-08-21 | 2020-11-20 | 韩培洲 | Rotor supercharging gas turbine |
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| CN111075564A (en) | 2020-04-28 |
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