CN114320960A - Tail cooling rotor engine - Google Patents

Tail cooling rotor engine Download PDF

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Publication number
CN114320960A
CN114320960A CN202011333870.2A CN202011333870A CN114320960A CN 114320960 A CN114320960 A CN 114320960A CN 202011333870 A CN202011333870 A CN 202011333870A CN 114320960 A CN114320960 A CN 114320960A
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China
Prior art keywords
cylinder
cold flow
annular
channel
wall
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Pending
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CN202011333870.2A
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Chinese (zh)
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李笑一
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Individual
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Individual
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/08—Units comprising pumps and their driving means the working fluid being air, e.g. for ventilation
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/047—Nozzle boxes
    • 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
    • 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
    • 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
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
    • 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
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • 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
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/127—Multi-stage pumps with radially spaced stages, e.g. for contrarotating type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/286—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors multi-stage rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A tail cooling rotor engine is characterized in that a gas compression cavity of a gas compressor A is communicated with a gas collection cavity of an end cover from left to right through a peripheral cold flow channel A of a cold flow tail gas combination, a peripheral cold flow channel B of a jet recoil base and a peripheral cold flow channel C of a main cylinder; the air compression cavity of the air compressor A is communicated with the air collection cavity of the end cover from left to right through the middle cold flow channel A of the cold flow combination, the middle cold flow channel B of the rotor, the middle cold flow channel C of the injection recoil base and the middle cold flow channel D of the main cylinder. The invention has high heat engine efficiency, low requirement on high-temperature performance of blade materials, low rotor rotation speed and large angular momentum, and is suitable for fluid load airplanes and ships and the like.

Description

Tail cooling rotor engine
Technical Field
The invention relates to a tail cooling rotor engine, and belongs to the technical field of gas turbines.
Background
In the gas turbine of the prior art, a main shaft driven by blades generates torque to drive load or output power. Because the structure of the blade determines, the rotational inertia or angular momentum of the main shaft depends on high rotating speed, once the rotating speed is low, the load driving capability or output power of the main shaft is sharply reduced, and even the load cannot be driven. In the prior art gas turbine, the working speed is usually 20000-50000rpm or even higher. However, high speed of rotation inevitably requires high speed gas to drive, and high speed gas requires high temperature and high pressure, so that not only high speed gas flow may bring incomplete conversion of heat engine efficiency and low heat efficiency, but also vane material is required to have excellent high temperature performance, and the vane temperature is even up to 1700 ℃. The high temperature requirements of gas turbines for blade materials are a technical bottleneck that limits the manufacturing and development of gas turbines. Meanwhile, high rotating speed inevitably brings high abrasion and short overhaul period, and the maintenance and use cost of a user is increased.
In the piston type internal combustion engine in the prior art, both a crank connecting rod mechanism and a piston do reciprocating motion, and the engine needs to consume a large amount of energy and has great mechanical loss when overcoming the reciprocating motion of the piston. Therefore, the combined heat engine efficiency of the piston type internal combustion engine is extremely low.
In order to overcome the defect of extremely high internal energy consumption of the piston type internal combustion engine, the prior art has various design cases of rotary engines. For example, in a typical wankel triangular rotary engine, the rotor of the engine is unbalanced, and the maintenance of the unbalanced rotation of the rotor not only consumes a large amount of energy, but also causes incomplete fuel combustion and great pollution to the environment by exhaust gas, so that the combustion efficiency and the thermal cycle efficiency of the engine have great improvement space.
Another typical type of rotary engine is a turbojet or turbofan engine. However, the turbojet or turbofan engine mainly pushes the flight of special vehicles such as airplanes and the like by the reaction force of high-speed jet airflow. When such a rotary engine is used for shaft output, a high-temperature and high-pressure gas flow is discharged by self-expansion between the wide impeller blades by the expansion work of the turbine blades, and a considerable proportion of the gas does not function. In addition, the existing turbojet or turbofan engine is only suitable for a fluid load environment, and has a serious surge phenomenon for land load, so that a high idle speed mode is required to be used for maintaining the stable working state of the engine, the thermal cycle efficiency is low, and the oil consumption is extremely high.
Disclosure of Invention
The invention aims to provide a tail cooling rotor engine which has low requirements on high-temperature performance of blade materials and has low rotating speed and large angular momentum.
Technical scheme of the invention
A tail cooling rotor engine comprises a gas compressor A, a rotor machine B, a combustor C, a heat circulation heat exchanger (5) and a preheated air pipe (4); the compressor A comprises an air inlet cover (1), a bearing A (2), a starting clutch (3), a shell (17), a compressed air impeller (18), a left side structure of a cold flow tail gas combination body (16) and a main shaft (10); the rotor machine B comprises a right side structure of a cold flow tail gas combination body (16), a bearing B (13), a rotor (15), a bearing C (12), a left side structure of a jet recoil base (6) and a main shaft (10); the combustor C comprises a right side structure of a jet recoil base (6), a main cylinder body (7), a burner (14) and an end cover (9); a main shaft (10) is arranged in the middle of the main cylinder body (7), and the main shaft (10) penetrates through the center of the end cover (9) through a bearing D (11); the heat circulation heat exchanger (5) is of a tube array structure and comprises a cold air inlet (5b) and a tail gas outlet (5 a); the air compression cavity (17a) of the compressor A is communicated with the air collection cavity (9a) of the end cover (9) from left to right through the peripheral cold flow channel A (16B) of the cold flow tail gas combination body (16), the peripheral cold flow channel B (6a) of the injection recoil base (6) and the peripheral cold flow channel C (7a) of the main cylinder body (7); the air compression cavity (17a) of the air compressor A is communicated with the air collection cavity (9a) of the end cover (9) from left to right through the middle cold flow channel A (16C) of the cold flow combination body (16), the middle cold flow channel B (15e) of the rotor (15), the middle cold flow channel C (6C) of the injection recoil base (6) and the middle cold flow channel D (7B) of the main cylinder body (7).
The invention relates to a tail cooling rotor engine, wherein an air inlet cover (1) comprises a shell (1d) and a flow guide cone (1d), and an air inlet channel is divided into a peripheral preheating air channel (1a) and a middle cooling air channel (1 b); the preheated air outlet of the heat cycle heat exchanger (5) is connected with the peripheral preheating channel (1a) of the air inlet cover (1) through a preheated air pipe (4).
The invention relates to a tail cooling rotor engine, wherein a cold flow tail gas combination body (16) is provided with an outer cylinder A (16d), the inner wall of the left section of the outer cylinder (16d) is connected with a conical flow guide table (16g) and a flow guide table extension cylinder (16h), and a conical body (16f) is arranged in the conical flow guide table (16g) and the flow guide table extension cylinder (16 h); the inner wall of the left section of the outer cylinder A (16d), the left side surface of the flow guide conical table (16g) and the outer side surface of the conical body are provided with flow guide rib plates (16e), and the flow guide rib plates (16e) extend leftwards to the outer side surface of the conical body (16f) and the inner side surface of the flow guide table extension cylinder (16 h); the cold flow tail gas combination body (16) is provided with an annular U-shaped groove consisting of an inner cylinder A (16i1), a middle cylinder A (16i2) and a bottom (16i3), a heat exchange flat pipe (16j) is connected between an opening of the flow guide conical table (16g) and an opening of the bottom (16i3) of the annular U-shaped groove, and an outer peripheral cold flow channel A (16b) of the cold flow tail gas combination body (16) is formed by the opening of the flow guide conical table (16g), an inner hole of the heat exchange flat pipe (16j) and the openings of the annular U-shaped groove; a heat exchange plate (16i4) is arranged in the annular U-shaped groove; the outer side surface of the conical body (16f), the left side surface of the flow guiding conical table (16g) and the channel of the inner wall of the flow guiding extending cylinder (16h) and separated by the flow guiding rib plate (16e) form an intermediate cold flow channel A (16c) of the cold flow tail gas combination body (16); an annular channel formed between the inner wall of the inner cylinder A (16i1) of the annular U-shaped groove and the outer wall of the flow guide extension cylinder (16h) is a tail gas port (16a) of the rotor (15), and the tail gas port (16a) penetrates through the inner side face of the outer cylinder A (16d), the outer surface of the heat exchange flat tube (16j), the right side face of the flow guide conical table (16g) and the outer side face of the flow guide extension cylinder (16h) to reach a tail gas outlet.
The invention relates to a tail cooling rotor engine, wherein a rotor (15) comprises a special-shaped curved pipe (15a), a primary hub (15b), a secondary hub (15c), spokes (15f) and recoil blades (15d), the sectional area of an expansion ejection port (15a1) of the special-shaped curved pipe (15a) of the rotor (15) is larger than that of a fuel gas ejection port (15a2), and the sectional area of the fuel gas ejection port (15a2) is larger than that of a necking pipe (15a 3); the gas injection ports (15a2) of the special-shaped curved pipe (15a) are distributed on the circumference of the primary hub (15b), and the expansion ejection ports (15a1) are distributed on the circumference of the right section of the secondary hub (15 c); the diameter of the first-stage hub (15b) is smaller than that of the second-stage hub (15c), and the first-stage hub (15b) and the second-stage hub (15c) are of an integral structure; the recoil blades (15d) are distributed on the outer circumference of the left section of the secondary hub (15 c); worm wheel blade-shaped spokes (15f) are distributed on the circumference of the inner wall of the secondary hub (15c), and a gap between two adjacent spokes (15f) and a gap between the outer walls of two adjacent special-shaped curved tubes are communicated to form a middle cold flow channel B (15e) of the rotor (15); the fluid contacting the outer side of the rotor (15) from right to left is high-temperature fuel gas after fuel combustion, and the fluid contacting the inner side from left to right is preheated pressurized air.
The tail cooling rotor engine is characterized in that a ring-shaped chassis (6i) of an injection recoil base (6) is provided with a clock base (6j), a middle cylinder B (6f) and an outer cylinder B (6g), the center of the top of the clock base (6j) is provided with a shaft hole (6e), the chassis (6i) at the root of the left side of the clock base (6j) is provided with a flow guide recoil pit (6d), the root of the left side of the clock base (6j) is provided with a tangential hollow gas injection hole (6B), a flow guide rib (6h) is arranged between the outer wall of the left side of the clock base (6j) and the inner wall of the middle cylinder B (6f), an outer periphery cold flow channel B (6a) is arranged on the chassis (7f) between the inner wall of the outer cylinder B (6g) and the middle cylinder B (6g), and a middle cold flow channel C (6C) is arranged around the shaft hole (6e) at the top of the clock base (6 j).
The invention relates to a tail cooling rotary engine, wherein a main cylinder (7) of a combustor C is provided with an outer cylinder C (7i), a middle cylinder C (7j) and an inner cylinder C (7k) on a right end disc (7 f); a mounting trap (7e) for mounting a burner (14) and an annular fuel groove (7g) are annularly distributed on the right end disc (7 f); an annular fuel oil groove (7g) of the right end disc (7f) is embedded into the seal ring (8) and is fixed through an assembly hole (8b) to form an annular fuel oil channel (8a), and the annular fuel oil channel (8a) is communicated with a fuel oil feed port (7 h); the inner wall pipeline of an inner cylinder C (7k) of the main body cylinder (7) is a middle cold flow channel D (7b), and a tubular cavity enclosed by the outer wall of the inner cylinder C (7k), the left side surface of a right end disc (7f), the inner wall of a middle cylinder C (7j) and the right side surface of the injection recoil seat (6) is a combustion chamber (7C); a tubular cavity between the inner wall of the outer cylinder C (7i) of the main body cylinder (7) and the inner wall of the middle cylinder (7j) is communicated with openings distributed on the outer circumference of the right end disc (7f) to form a peripheral cold flow channel C (7 a); and air channels (7d) are distributed on the middle circumference of the right end disc (7f) of the main cylinder body (7).
The tail cooling rotor engine is characterized in that the burner (14) is of a cylinder structure, an annular oil groove (14f) is formed in the periphery of the middle section of the cylinder, the annular oil groove (14f) and an annular cavity enclosed by the inner wall of a mounting trap (7e) of the main cylinder body (7) form a fuel oil annular channel, and the fuel oil annular channel is communicated with a fuel oil channel (8a) of the main cylinder body (7); the left section of the center of the burner (14) is a conical duct, the right section of the center of the burner is a circular duct, a cone (14b) is fixed in the left section of the center duct through a support, a conical passage between the outer peripheral conical surface of the cone (14b) and the inner conical surface of the conical duct is an air compression passage (14i), and a fuel slit (14g) is communicated between the air compression passage (14i) and the annular oil groove (14 f); an igniter (14a) penetrates through the center of the cone body (14b), and the igniter (14a) is pressed through a special-shaped nut (14 e); the periphery of the left end of the cylinder of the burner (14) is provided with an annular notch (14h), and the annular notch (14h) and the inner wall of the mounting well (7e) of the main body cylinder (8) form a choke joint for preventing gas from backflushing.
The air compressor A of the tail cooling rotor engine provided by the invention adopts a centrifugal air compressor structure, and can also adopt another air compressor with a multi-stage axial flow and radial flow mixed structure.
The invention relates to an air inlet cover, a compressor shell, a cold flow tail gas combination body, a jet recoil base, a main cylinder body and an end cover, which are assembled into a whole machine through flange plate assembly or welding.
Working process of the invention
The igniter is electrified to be lighted, a starting motor (not shown) is started and drives the air compressing impeller and the rotor to rotate, the air compressing impeller and the rotor spokes press air into the air collecting cavity, the air is injected into the combustion chamber through the conical air injection channel of the burner, and simultaneously, the fuel is sucked to be mixed into fuel-air combustible mixed gas which is ignited through the igniter. The high-temperature and high-pressure fuel gas after the fuel combustion is sprayed out through the fuel gas spraying hole to drive the rotor to rotate. When the rotating speed of the rotor is greater than that of the starting motor and the temperature of the combustor reaches about 600 ℃, the igniter is closed, the starting motor stops working and is separated from the main shaft of the engine, and the engine enters a normal operation program.
The invention has the advantages that
1. The rotor is in cold air cooling in a normalized state, the working temperature is relatively low, the requirement on the high-temperature performance of the rotor blade material is low, and the manufacturing cost is low.
2. Low working speed, small abrasion, long overhaul period and low use cost.
3. The rotor is not smoothly recoiled, and the output effects of low flow and high angular momentum can be obtained; meanwhile, the fuel is completely combusted, and the heat efficiency is high.
4. The recoil rotor rotates in a balanced manner, the defect of high energy consumption of reciprocating motion of a piston engine and unbalanced rotation of a Wankel triangle rotor engine is overcome, and the engine is stable in operation, small in vibration and low in noise.
5. The flywheel function of the large inertia recoil rotor enables the engine to run at low idle speed without surge, and is particularly suitable for range extenders of ships, low-speed propeller aircrafts, tanks and pure electric vehicles.
Drawings
FIG. 1 is a schematic cross-sectional elevation view of the present invention.
Fig. 2 is a perspective oblique view schematic diagram of the intake shroud of the present invention.
FIG. 3 is a schematic perspective view of the cold flow tail gas combination of the present invention from the left.
FIG. 4 is a schematic view of the cold flow tail gas combination of the present invention with a cross-sectional left side view.
FIG. 5 is a schematic perspective view of the cold flow tail gas combination of the present invention from the right.
Fig. 6 is a perspective view of the right side of the rotor of the present invention.
Fig. 7 is a perspective view of a modified curved tube in the rotor of the present invention.
Fig. 8 is a left side perspective view of the rotor of the present invention.
Fig. 9 is a left side perspective view of the jet recoil base of the present invention.
Fig. 10 is a perspective view of the right side of the jet recoil base of the present invention.
FIG. 11 is a schematic perspective sectional view of the burner main body of the present invention.
FIG. 12 is a schematic cross-sectional oblique perspective view of the fuel seal ring of the present invention.
Fig. 13 is a schematic cross-sectional view of a burner of the present invention.
Detailed description of the preferred embodiments
Example 1
As shown in the attached figures 1-13, a tail cooling rotary engine comprises a gas compressor A, a rotary engine B, a combustor C, a heat circulation heat exchanger 5 and a preheated air pipe 4; the compressor A comprises an air inlet cover 1, a bearing A2, a starting clutch 3, a shell 17, a compressor impeller 18, a left side structure of a cold flow tail gas combination 16 and a main shaft 10; the rotor machine B comprises a right structure of a cold flow tail gas combination 16, a bearing B13, a rotor 15, a bearing C12, a left structure of a jet recoil base 6 and a main shaft 10; the combustor C comprises a right structure of the injection recoil base 6, a main cylinder 7, a burner 14 and an end cover 9; a main shaft 10 is arranged in the middle of the main cylinder 7, and the main shaft 10 penetrates through the center of the end cover 9 through a bearing D11; the heat circulation heat exchanger 5 is of a tubular structure and comprises a cold air inlet 5b and a tail gas outlet 5 a; the air compression cavity 17a of the compressor A is communicated with the air collection cavity 9a of the end cover 9 from left to right through the outer peripheral cold flow channel A16B of the cold flow tail gas combination body 16, the outer peripheral cold flow channel B6a of the injection recoil base 6 and the outer peripheral cold flow channel C7a of the main cylinder 7; the air compression cavity 17a of the compressor A passes through the middle cold flow channel A16C of the cold flow combination 16, the middle cold flow channel B15e of the rotor 15, the middle cold flow channel C6C of the injection recoil base 6 and the middle cold flow channel D7B of the main cylinder 7 from left to right, and is communicated with the air collection cavity 9a of the end cover 9.
Example 2
As shown in fig. 1 and 2, the air intake cover 1 of the tail cooling rotary engine of the present invention includes a housing 1d and a flow guiding cone 1d, and an air intake passage is divided into an outer circumference preheating air passage 1a and a middle cooling air passage 1 b; the preheated air outlet of the heat circulation heat exchanger 5 is connected with the peripheral preheating channel 1a of the air inlet cover 1 through a preheated air pipe 4.
Example 3
As shown in fig. 1 and 3-5, the cold flow and tail gas combination 16 of the tail-cooling rotary engine of the present invention has an outer cylinder a16d, a conical diversion table 16g and a diversion table extension cylinder 16h are connected to the inner wall of the left section of the outer cylinder 16d, and a conical body 16f is arranged in the conical diversion table 16g and the diversion table extension cylinder 16 h; the inner wall of the left section of the outer cylinder A16d, the left side surface of the flow guiding conical table 16g and the outer side surface of the conical body are provided with flow guiding rib plates 16e, and the flow guiding rib plates 16e extend leftwards to the outer side surface of the conical body 16f and the inner side surface of the flow guiding table extension cylinder 16 h; the cold flow tail gas combination 16 is provided with an annular U-shaped groove consisting of an inner cylinder A16i1, a middle cylinder A16i2 and a bottom 16i3, a heat exchange flat tube 16j is connected between an opening of the flow guide conical table 16g and an opening of the bottom 16i3 of the annular U-shaped groove, and an outer peripheral cold flow channel A16b of the cold flow tail gas combination 16 is formed by the opening of the flow guide conical table 16g, an inner hole of the heat exchange flat tube 16j and the opening of the annular U-shaped groove; the annular U-shaped groove is internally provided with heat exchange fins 16i 4; the middle cold flow channel A16c of the cold flow tail gas combination 16 is formed by the channels which are formed by the outer side surface of the conical body 16f, the left side surface of the flow guiding conical table 16g and the inner wall of the flow guiding extension cylinder 16h and are separated by the flow guiding rib plate 16 e; an annular channel formed between the inner wall of the inner cylinder A16i1 of the annular U-shaped groove and the outer wall of the guide extension cylinder 16h is a tail gas port 16a of the rotor 15, and the tail gas port 16a penetrates through the inner side face of the outer cylinder A16d, the outer surface of the heat exchange flat tube 16j, the right side face of the guide conical table 16g and the outer side face of the guide extension cylinder 16h to reach a tail gas outlet.
Example 4
As shown in fig. 1, 6-8, the rotor 15 of the tail cooling rotary engine of the present invention includes a special-shaped curved tube 15a, a primary hub 15b, a secondary hub 15c, spokes 15f and recoil vanes 15d, wherein the sectional area of an expansion ejection port 15a1 of the special-shaped curved tube 15a of the rotor 15 is larger than the sectional area of a gas injection port 15a2, and the sectional area of a gas injection port 15a2 is larger than the sectional area of a necking tube 15a 3; the gas injection ports 15a2 of the special-shaped curved pipe 15a are distributed on the circumference of the primary hub 15b, and the expansion ejection ports 15a1 are distributed on the circumference of the right section of the secondary hub 15 c; the diameter of the primary hub 15b is smaller than that of the secondary hub 15c, and the primary hub 15b and the secondary hub 15c are of an integral structure; the recoil blades 15d are distributed on the outer circumference of the left section of the secondary hub 15 c; worm-wheel blade-shaped spokes 15f are distributed on the circumference of the inner wall of the secondary hub 15c, and a gap between two adjacent spokes 15f and a gap between the outer walls of two adjacent special-shaped curved pipes are communicated to form a middle cold flow channel B15e of the rotor 15; the fluid contacting from right to left on the outer side of the rotor 15 is high-temperature fuel gas after fuel combustion, and the fluid contacting from left to right on the inner side is preheated pressurized air.
Example 5
As shown in fig. 1 and 9-10, in the tail cooling rotary engine of the present invention, a ring-shaped chassis 6i of the injection recoil base 6 is provided with a bell base 6j, a middle cylinder B6f and an outer cylinder B6g, the top center of the bell base 6j is provided with a shaft hole 6e, the chassis 6i at the left root of the bell base 6j is provided with a flow guiding recoil pit 6d, the root at the left side of the bell base 6j is provided with a tangential hollow gas injection hole 6B, a flow guiding rib 6h is arranged between the left outer wall of the bell base 6j and the inner wall of the middle cylinder B6f, a chassis 7f between the inner wall of the outer cylinder B6g and the middle cylinder B6g is provided with an outer peripheral cold flow channel B6a, and a middle cold flow channel C6C is arranged around the shaft hole 6e at the top of the bell base 6 j.
Example 6
As shown in fig. 1, 11-13, the main cylinder 7 of the burner C of the tail cooling rotary engine of the present invention has an outer cylinder C7i, an intermediate cylinder C7j and an inner cylinder C7k on a right end disk 7 f; the right end disk 7f is annularly provided with a mounting trap 7e and an annular fuel tank 7g which are provided with a burner 14; the annular fuel oil groove 7g of the right end disc 7f is embedded into the seal ring (8) and is fixed through the assembling hole 8b to form an annular fuel oil channel 8a, and the annular fuel oil channel 8a is communicated with the fuel oil feed opening 7 h; the inner wall pipeline of the inner cylinder C7k of the main body cylinder 7 is a middle cold flow channel D7b, and a tubular cavity enclosed by the outer wall of the inner cylinder C7k, the left side surface of the right end disc 7f, the inner wall of the middle cylinder C7j and the right side surface of the injection recoil seat 6 is a combustion chamber 7C; a tubular cavity between the inner wall of the outer cylinder C7i of the main body cylinder 7 and the inner wall of the middle cylinder 7j is communicated with openings distributed on the outer circumference of the right end disc 7f to form a peripheral cold flow channel C7 a; and air channels 7d are distributed on the middle circumference of the right end disc 7f of the main cylinder 7.
Example 7
As shown in fig. 1 and 13, in the tail cooling rotary engine of the present invention, the burner 14 is a cylinder structure, an annular oil groove 14f is formed on the periphery of the middle section of the cylinder, the annular oil groove 14f and an annular cavity surrounded by the inner wall of the mounting well 7e of the main cylinder 7 form a fuel oil ring, and the fuel oil ring is communicated with the fuel oil channel 8a of the main cylinder 7; the left section of the center of the burner 14 is a conical duct, the right section of the center of the burner is a circular duct, a cone 14b is fixed in the left section of the center duct through a bracket, a conical channel between the peripheral conical surface of the cone 14b and the inner conical surface of the conical duct is an air compressing channel 14i, and a fuel slit 14g is communicated between the air compressing channel 14i and the annular oil groove 14 f; an igniter 14a penetrates through the center of the cone 14b, and the igniter 14a is pressed by a special-shaped nut 14 e; the burner 14 is provided with an annular gap 14h at the periphery of the left end of the cylinder, and the annular gap 14h and the inner wall of the mounting trap 7e of the main body cylinder 8 form a choke joint for preventing gas from backflushing.
Example 8
The air compressor A of the tail cooling rotor engine adopts a centrifugal air compressor structure and also adopts another air compressor with a multi-stage axial flow and radial flow mixed structure.
The invention relates to an air inlet cover, a compressor shell, a cold flow tail gas combination body, a jet recoil base, a main cylinder body and an end cover, which are assembled into a whole machine through flange plate assembly or welding.
The tail cooling rotary engine provided by the invention is described in detail above. The description of the specific embodiments is only intended to facilitate an understanding of the method of the invention and its core ideas. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made to the present invention, and these improvements and modifications also fall into the protection scope of the claims of the present invention.

Claims (7)

1. A tail cooling rotor engine comprises a gas compressor A, a rotor machine B, a combustor C, a heat circulation heat exchanger (5) and a preheated air pipe (4); the compressor A comprises an air inlet cover (1), a bearing A (2), a starting clutch (3), a shell (17), a compressed air impeller (18), a left side structure of a cold flow tail gas combination body (16) and a main shaft (10); the rotor machine B comprises a right side structure of a cold flow tail gas combination body (16), a bearing B (13), a rotor (15), a bearing C (12), a left side structure of a jet recoil base (6) and a main shaft (10); the combustor C comprises a right side structure of a jet recoil base (6), a main cylinder body (7), a burner (14) and an end cover (9); a main shaft (10) is arranged in the middle of the main cylinder body (7), and the main shaft (10) penetrates through the center of the end cover (9) through a bearing D (11); the heat circulation heat exchanger (5) is of a tube array structure and comprises a cold air inlet (5b) and a tail gas outlet (5 a); the method is characterized in that:
a gas compression cavity (17a) of the compressor A is communicated with a gas collection cavity (9a) of the end cover (9) from left to right through a peripheral cold flow channel A (16B) of a cold flow tail gas combination body (16), a peripheral cold flow channel B (6a) of the injection recoil base (6) and a peripheral cold flow channel C (7a) of the main cylinder body (7);
the air compression cavity (17a) of the air compressor A is communicated with the air collection cavity (9a) of the end cover (9) from left to right through the middle cold flow channel A (16C) of the cold flow combination body (16), the middle cold flow channel B (15e) of the rotor (15), the middle cold flow channel C (6C) of the injection recoil base (6) and the middle cold flow channel D (7B) of the main cylinder body (7).
2. The tail-cooled rotary engine of claim 1, wherein:
the air inlet cover (1) comprises a shell (1d) and a flow guide cone (1d), and an air inlet channel is divided into a peripheral preheating air channel (1a) and a middle cooling air channel (1 b); the preheated air outlet of the heat cycle heat exchanger (5) is connected with the peripheral preheating channel (1a) of the air inlet cover (1) through a preheated air pipe (4).
3. The tail-cooled rotary engine of claim 1, wherein:
the cold flow tail gas combination body (16) is provided with an outer cylinder A (16d), the inner wall of the left section of the outer cylinder (16d) is connected with a conical flow guide table (16g) and a flow guide table extension cylinder (16h), and a conical body (16f) is arranged in the conical flow guide table (16g) and the flow guide table extension cylinder (16 h);
the inner wall of the left section of the outer cylinder A (16d), the left side surface of the flow guide conical table (16g) and the outer side surface of the conical body are provided with flow guide rib plates (16e), and the flow guide rib plates (16e) extend leftwards to the outer side surface of the conical body (16f) and the inner side surface of the flow guide table extension cylinder (16 h);
the cold flow tail gas combination body (16) is provided with an annular U-shaped groove consisting of an inner cylinder A (16i1), a middle cylinder A (16i2) and a bottom (16i3), a heat exchange flat pipe (16j) is connected between an opening of the flow guide conical table (16g) and an opening of the bottom (16i3) of the annular U-shaped groove, and an outer peripheral cold flow channel A (16b) of the cold flow tail gas combination body (16) is formed by the opening of the flow guide conical table (16g), an inner hole of the heat exchange flat pipe (16j) and the openings of the annular U-shaped groove; a heat exchange plate (16i4) is arranged in the annular U-shaped groove;
the outer side surface of the conical body (16f), the left side surface of the flow guiding conical table (16g) and the channel of the inner wall of the flow guiding extending cylinder (16h) and separated by the flow guiding rib plate (16e) form an intermediate cold flow channel A (16c) of the cold flow tail gas combination body (16);
an annular channel formed between the inner wall of the inner cylinder A (16i1) of the annular U-shaped groove and the outer wall of the flow guide extension cylinder (16h) is a tail gas port (16a) of the rotor (15), and the tail gas port (16a) penetrates through the inner side face of the outer cylinder A (16d), the outer surface of the heat exchange flat tube (16j), the right side face of the flow guide conical table (16g) and the outer side face of the flow guide extension cylinder (16h) to reach a tail gas outlet.
4. An exhaust cooled rotary engine according to claim 1, the rotor (15) comprising a shaped curved tube (15a), a primary hub (15b), a secondary hub (15c), spokes (15f) and recoil blades (15d), characterized in that:
the sectional area of an expansion ejection port (15a1) of a special-shaped curved pipe (15a) of the rotor (15) is larger than that of a fuel gas injection port (15a2), and the sectional area of the fuel gas injection port (15a2) is larger than that of a neck pipe (15a 3);
the gas injection ports (15a2) of the special-shaped curved pipe (15a) are distributed on the circumference of the primary hub (15b), and the expansion ejection ports (15a1) are distributed on the circumference of the right section of the secondary hub (15 c);
the diameter of the first-stage hub (15b) is smaller than that of the second-stage hub (15c), and the first-stage hub (15b) and the second-stage hub (15c) are of an integral structure;
the recoil blades (15d) are distributed on the outer circumference of the left section of the secondary hub (15 c);
worm wheel blade-shaped spokes (15f) are distributed on the circumference of the inner wall of the secondary hub (15c), and a gap between two adjacent spokes (15f) and a gap between the outer walls of two adjacent special-shaped curved tubes are communicated to form a middle cold flow channel B (15e) of the rotor (15);
the fluid contacting the outer side of the rotor (15) from right to left is high-temperature fuel gas after fuel combustion, and the fluid contacting the inner side from left to right is preheated pressurized air.
5. The tail-cooled rotary engine of claim 1, wherein:
the annular base plate (6i) of the injection recoil base (6) is provided with a clock base (6j), a middle cylinder B (6f) and an outer cylinder B (6g), the center of the top of the clock base (6j) is provided with a shaft hole (6e), the base plate (6i) at the root part of the left side of the clock base (6j) is provided with a flow guide recoil pit (6d), the root part of the left side of the clock base (6j) is provided with a tangential hollow gas injection hole (6B), a flow guide rib (6h) is arranged between the outer wall of the left side of the clock base (6j) and the inner wall of the middle cylinder B (6f), the base plate (7f) between the inner wall of the outer cylinder B (6g) and the middle cylinder B (6g) is provided with an outer peripheral cold flow channel B (6a), and a middle cold flow channel C (6C) is arranged around the shaft hole (6e) at the top of the clock base (6 j).
6. The tail-cooled rotary engine of claim 1, wherein: the main cylinder (7) of the combustor C is provided with an outer cylinder C (7i), a middle cylinder C (7j) and an inner cylinder C (7k) on a right end disc (7 f); a mounting trap (7e) for mounting a burner (14) and an annular fuel groove (7g) are annularly distributed on the right end disc (7 f);
an annular fuel oil groove (7g) of the right end disc (7f) is embedded into the seal ring (8) and is fixed through an assembly hole (8b) to form an annular fuel oil channel (8a), and the annular fuel oil channel (8a) is communicated with a fuel oil feed port (7 h);
the inner wall pipeline of an inner cylinder C (7k) of the main body cylinder (7) is a middle cold flow channel D (7b), and a tubular cavity enclosed by the outer wall of the inner cylinder C (7k), the left side surface of a right end disc (7f), the inner wall of a middle cylinder C (7j) and the right side surface of the injection recoil seat (6) is a combustion chamber (7C);
a tubular cavity between the inner wall of the outer cylinder C (7i) of the main body cylinder (7) and the inner wall of the middle cylinder (7j) is communicated with openings distributed on the outer circumference of the right end disc (7f) to form a peripheral cold flow channel C (7 a);
and air channels (7d) are distributed on the middle circumference of the right end disc (7f) of the main cylinder body (7).
7. The tail-cooled rotary engine of claim 1, wherein:
the burner (14) is of a cylindrical structure, an annular oil groove (14f) is formed in the periphery of the middle section of the cylinder, the annular oil groove (14f) and an annular cavity surrounded by the inner wall of a mounting trap (7e) of the main cylinder (7) form a fuel oil annular channel, and the fuel oil annular channel is communicated with a fuel oil channel (8a) of the main cylinder (7);
the left section of the center of the burner (14) is a conical duct, the right section of the center of the burner is a circular duct, a cone (14b) is fixed in the left section of the center duct through a support, a conical passage between the outer peripheral conical surface of the cone (14b) and the inner conical surface of the conical duct is an air compression passage (14i), and a fuel slit (14g) is communicated between the air compression passage (14i) and the annular oil groove (14 f);
an igniter (14a) penetrates through the center of the cone body (14b), and the igniter (14a) is pressed through a special-shaped nut (14 e);
the periphery of the left end of the cylinder of the burner (14) is provided with an annular notch (14h), and the annular notch (14h) and the inner wall of the mounting well (7e) of the main body cylinder (8) form a choke joint for preventing gas from backflushing.
CN202011333870.2A 2020-07-01 2020-11-22 Tail cooling rotor engine Pending CN114320960A (en)

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2627161A (en) * 1947-04-03 1953-02-03 Jarvis C Marble Elastic fluid power system utilizing a rotary engine with cooled rotors
GB1091621A (en) * 1965-03-29 1967-11-22 Vlastimir Davidovic High efficiency regeneratively cooled gas turbine engines
CN103216333A (en) * 2013-04-08 2013-07-24 南京理工大学 Countercurrent tangential type micro turbojet engine
CN108104977A (en) * 2017-10-09 2018-06-01 李钢坤 A kind of vortex-spraying type is without stroke rotary engine
CN108952964A (en) * 2018-07-13 2018-12-07 南昌航空大学 A kind of gas-turbine unit of single composite impeller
CN109404250A (en) * 2018-10-17 2019-03-01 安徽工业大学 A kind of fuel gas injection engine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6966174B2 (en) * 2002-04-15 2005-11-22 Paul Marius A Integrated bypass turbojet engines for air craft and other vehicles
AU2003233159A1 (en) * 2002-06-26 2004-01-19 R-Jet Engineering Ltd. Orbiting combustion nozzle engine
US8147178B2 (en) * 2008-12-23 2012-04-03 General Electric Company Centrifugal compressor forward thrust and turbine cooling apparatus
CN101832154B (en) * 2009-03-11 2013-03-27 中国科学院工程热物理研究所 Method for cooling air film of turbine blade of aircraft engine
CN105626266B (en) * 2016-01-12 2017-09-08 中国科学院工程热物理研究所 A kind of gas turbine anti-surge deflation energy recovery utilizing system
US20180355887A1 (en) * 2016-12-09 2018-12-13 Frontline Aerospace, Inc. Centrifugal compressor cooling
CN110273782A (en) * 2019-07-12 2019-09-24 南昌航空大学 A kind of Micro Turbine Jet Engine of two-sided NEW TYPE OF COMPOSITE impeller

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2627161A (en) * 1947-04-03 1953-02-03 Jarvis C Marble Elastic fluid power system utilizing a rotary engine with cooled rotors
GB1091621A (en) * 1965-03-29 1967-11-22 Vlastimir Davidovic High efficiency regeneratively cooled gas turbine engines
CN103216333A (en) * 2013-04-08 2013-07-24 南京理工大学 Countercurrent tangential type micro turbojet engine
CN108104977A (en) * 2017-10-09 2018-06-01 李钢坤 A kind of vortex-spraying type is without stroke rotary engine
CN108952964A (en) * 2018-07-13 2018-12-07 南昌航空大学 A kind of gas-turbine unit of single composite impeller
CN109404250A (en) * 2018-10-17 2019-03-01 安徽工业大学 A kind of fuel gas injection engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
蒋庄德;王久洪;卢德江;: "微型旋转冲压发动机设计与分析", 机械工程学报, no. 11, 15 November 2008 (2008-11-15) *

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