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CN114320960B - A tail-cooled rotary engine - Google Patents

A tail-cooled rotary engine Download PDF

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Publication number
CN114320960B
CN114320960B CN202011333870.2A CN202011333870A CN114320960B CN 114320960 B CN114320960 B CN 114320960B CN 202011333870 A CN202011333870 A CN 202011333870A CN 114320960 B CN114320960 B CN 114320960B
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China
Prior art keywords
cylinder
channel
cold flow
annular
air
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CN202011333870.2A
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Chinese (zh)
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CN114320960A (en
Inventor
李笑一
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Classifications

    • 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 comprises a compressor A, a cold flow tail gas combination body, a cold flow exhaust gas combination body and a cold flow exhaust gas combination body, wherein the cold flow exhaust gas combination body is communicated with an air collecting cavity of an end cover through an outer Zhou Lengliu channel A of the compressor A, an outer Zhou Lengliu cold flow channel B of a jet recoil seat and an outer Zhou Lengliu channel C of a main cylinder body from left to right; 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 body, the middle cold flow channel B of the rotor, the middle cold flow channel C of the jet recoil seat and the middle cold flow channel D of the main cylinder. The heat engine has high efficiency, low requirement on high-temperature performance of blade materials, low rotor speed and large angular momentum, and is suitable for fluid load aircraft ships and the like.

Description

Tail cooling rotor engine
Technical Field
The invention relates to a tail-cooled rotor engine, and belongs to the technical field of gas turbines.
Background
In the prior art, a main shaft driven by blades generates torque to drive load or output power. Due to the structural determination of the blades, the rotational inertia or angular momentum of the main shaft depends on a high rotational speed, and once the rotational speed is low, the capacity of the main shaft to drive a load or the output power drops sharply or even cannot drive the load. The gas turbines of the prior art are usually operated at rotational speeds of 20000-50000rpm and even higher. However, the high-speed gas is driven by high-speed gas, and the high-speed gas needs high temperature and high pressure, so that not only the high-speed gas flow can bring incomplete conversion of heat engine efficiency and low heat efficiency, but also the blade material is required to have excellent high-temperature performance, and the temperature of the blade is even up to 1700 ℃. The high temperature requirements of gas turbines on blade materials are a technical bottleneck restricting the manufacture and development of gas turbines. Meanwhile, high rotation speed inevitably brings high abrasion and short overhaul period, and increases the maintenance and use cost of users.
In the prior art, the crank connecting rod mechanism and the piston of the piston type internal combustion engine have reciprocating motion, so that the engine overcomes the reciprocating motion of the piston, and a great amount of energy is required to be consumed, and the mechanical loss is extremely large. Thus, the overall heat engine efficiency of a piston internal combustion engine is extremely low.
In order to overcome the disadvantage of extremely high internal energy consumption of piston internal combustion engines, various rotary engine designs have been developed in the prior art. For example, a typical wankel triangle rotary engine has unbalanced rotation of a rotor, so that a large amount of energy is consumed for maintaining the unbalanced rotation of the rotor, fuel is incompletely combusted, tail gas has great pollution to the environment, and the combustion efficiency and the thermal cycle efficiency of the engine have great room for improvement.
Another type of typical rotary engine is a turbojet or turbofan engine. However, the turbojet or turbofan engine mainly pushes special vehicles such as an airplane to fly by the reaction force of high-speed jet air flow. When such a rotary engine is used for shaft output, a high-temperature and high-pressure air flow is discharged by self-expansion between the blades of the impeller, which are open, by expansion work of the turbine blades, and a considerable proportion of fuel gas is not allowed to function. Moreover, the existing turbojet or turbofan engine is only suitable for fluid load environments, and serious surge phenomenon exists for land load, so that a high-idle mode is required to be used for maintaining a stable working state, 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 with low requirements on high-temperature performance of blade materials, low rotating speed and large angular momentum.
The technical proposal of the invention
A tail-cooled rotor engine comprises a gas compressor A, a rotor machine B, a combustor C, a heat circulation heat exchanger (5) and a preheating air pipe (4); the air compressor A comprises an air inlet cover (1), a bearing A (2), a starting clutch (3), a shell (17), an air compressing 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 an injection recoil seat (6) and a main shaft (10); the burner C comprises a right side structure of the jet recoil seat (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 center of the end cover (9) is penetrated by the main shaft (10) through a bearing D (11); the heat circulation heat exchanger (5) is of a tube array structure and comprises a cold air inlet (5 b) and a tail gas outlet (5 a); the air compressing cavity (17 a) of the air compressor A is communicated with the air collecting cavity (9 a) of the end cover (9) from left to right through the outer Zhou Lengliu channel A (16B) of the cold flow tail gas combination body (16), the outer Zhou Lengliu channel B (6 a) of the jet recoil seat (6) and the outer Zhou Lengliu channel C (7 a) of the main cylinder body (7); the air compressing cavity (17 a) of the air compressor A is communicated with the air collecting cavity (9 a) of the end cover (9) from left to right through the middle cold flow channel A (16C) of the cold flow tail gas combination body (16), the middle cold flow channel B (15 e) of the rotor (15), the middle cold flow channel C (6C) of the jet recoil seat (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 the air inlet hood (1) comprises an outer hood (1 d) and a guide cone (1 c), and an air inlet channel is divided into a peripheral preheating air flow channel (1 a) and a middle cold air channel (1 b); the preheated air outlet of the heat circulation heat exchanger (5) is connected with an outer Zhou Yure airflow channel (1 a) 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 (16 d), the inner wall of the left section of the outer cylinder A (16 d) is connected with a conical flow guide table (16 g) and a flow guide table extension cylinder (16 h), and conical bodies (16 f) are arranged in the conical flow guide table (16 g) and the flow guide table extension cylinder (16 h); the inner wall of the left section of the outer cylinder A (16 d), the left side surface of the conical flow guide table (16 g) and the outer side surface of the conical body are provided with flow guide rib plates (16 e), and the flow guide rib plates (16 e) extend leftwards to the outer side surface of the conical body (16 f) and the flow guide table extension cylinder
(16H) Is provided; the cold flow tail gas combination body (16) is provided with an annular U-shaped groove formed by an inner cylinder A (16 i 1), a middle cylinder A (16 i 2) and a bottom (16 i 3), a heat exchange flat tube (16 j) is connected between an opening of a conical flow guide table (16 g) and an opening of the bottom (16 i 3) of the annular U-shaped groove, and an outer Zhou Lengliu channel A (16 b) of the cold flow tail gas combination body (16) is formed by the opening of the conical flow guide table (16 g), an inner pore canal of the heat exchange flat tube (16 j) and the opening of the annular U-shaped groove; heat exchange plates (16 i 4) are arranged in the annular U-shaped grooves; the cone body
(16F) The outer side surface of the conical flow guide table (16 g), the left side surface of the conical flow guide table and the inner wall of the flow guide table extension cylinder (16 h) are separated by the flow guide rib plate (16 e) to form a middle cold flow channel A (16 c) of the cold flow tail gas combination body (16); the annular channel formed between the inner wall of the inner cylinder A (16 i 1) of the annular U-shaped groove and the outer wall of the guide table extension cylinder (16 h) is a tail gas port (16 a) of the rotor (15), and the tail gas port (16 a) penetrates through the inner side surface of the outer cylinder A (16 d), the outer surface of the heat exchange flat tube (16 j), the right side surface of the conical guide table (16 g) and the outer side surface of the guide table extension cylinder (16 h) to reach the tail gas outlet (5 a).
The invention relates to a tail-cooled rotor engine, wherein a rotor (15) comprises a special-shaped curved pipe (15 a), a primary hub (15 b), a secondary hub (15 c), spokes (15 f) and recoil blades (15 d), the sectional area of an expansion ejection opening (15 a 1) of the special-shaped curved pipe (15 a) of the rotor (15) is larger than the sectional area of a fuel gas injection opening (15 a 2), and the sectional area of the fuel gas injection opening (15 a 2) is larger than the sectional area of a necking pipe (15 a 3); the gas injection (15 a 2) of the special-shaped curved pipe (15 a) is distributed on the circumference of the primary hub (15 b), and the expansion ejection opening (15 a 1) is distributed on the circumference of the right section of the secondary hub (15 c); the diameter of the primary hub (15 b) is smaller than that of the secondary hub (15 c), and the primary hub (15 b) and the secondary hub (15 c) are of an integrated structure; the recoil blades (15 d) are distributed on the outer circumference of the left section of the secondary hub (15 c); the circumference of the inner wall of the secondary hub (15 c) is provided with worm-wheel blade-shaped spokes (15 f), and the gap between two adjacent spokes (15 f) and the gap between the outer walls of two adjacent special-shaped curved pipes are communicated to form an intermediate cold flow channel B (15 e) of the rotor (15); the fluid contacting from the outer side to the left of the rotor (15) is high-temperature fuel gas after fuel combustion, and the fluid contacting from the left to the right of the rotor is preheated pressurized air.
The invention relates to a tail-cooling rotor engine, a ring-shaped chassis (6 i) of an injection recoil seat (6) is provided with a clock seat (6 j), a middle cylinder B (6 f) and an outer cylinder B (6 g), the top center of the clock seat (6 j) is provided with a shaft hole (6 e), and the chassis of the left side root of the clock seat (6 j)
(6I) The novel gas-liquid mixing device is characterized in that a diversion recoil pit (6 d) is formed in the upper part, a tangential hollowed-out gas injection hole (6B) is formed in the root of the left side of a clock seat (6 j), a diversion rib (6 h) is formed between the outer wall of the left side of the clock seat (6 j) and the inner wall of a middle cylinder B (6 f), a peripheral cold flow channel B (6 a) is formed in an annular chassis (6 i) between the inner wall of an outer cylinder B (6 g) and the middle cylinder B (6 f), and a middle cold flow channel C (6C) is formed in the periphery of a shaft hole (6 e) in the top of the clock seat (6 j).
The invention relates to a tail-cooling rotor engine, wherein a main cylinder body (7) of a combustor C is provided with an outer cylinder C (7 i), a middle cylinder C (7 j) and an inner cylinder C (7 k) on a right end disc (7 f); the right end disc (7 f) is annularly provided with an installation well (7 e) for assembling the burner (14) and an annular fuel tank (7 g); the annular fuel groove (7 g) of the right end disc (7 f) is embedded into the seal ring (8) and is fixedly formed into an annular fuel channel (8 a) through the assembly hole (8 b), and the annular fuel channel (8 a) is communicated with the fuel feed inlet (7 h); the inner wall pipeline of an inner cylinder C (7 k) of the main cylinder body (7) is a middle cold flow channel D (7 b), and a tubular cavity surrounded by the outer wall of the inner cylinder C (7 k), the left side surface of a right end disc (7 f), the inner wall of the middle cylinder C (7 j) and the right side surface of the jet recoil seat (6) is a combustion chamber (7C); the tubular cavity between the inner wall of the outer cylinder C (7 i) of the main cylinder body (7) and the inner wall of the middle cylinder C (7 j) is communicated with the opening distributed on the outer circumference of the right end disc (7 f) to form an outer Zhou Lengliu channel C (7 a); air channels (7 d) are distributed on the middle circumference of a right end disc (7 f) of the main cylinder body (7).
The tail-cooling rotor engine disclosed by the invention has the advantages that the burner (14) is of a cylinder structure, the periphery of the middle section of the cylinder structure is provided with the annular oil groove (14 f), the annular oil groove (14 f) and an annular cavity formed by surrounding the inner wall of the mounting well (7 e) of the main cylinder body (7) form a fuel oil loop, and the fuel oil loop is communicated with the annular fuel oil channel (8 a) of the main cylinder body (7); the central left section of the burner (14) is a conical duct, the right section of the burner is a circular duct, a cone (14 b) is fixed in the left Duan Zhuixing duct through a bracket, a conical channel between the outer peripheral conical surface of the cone (14 b) and the inner conical surface of the conical duct is an air compressing channel (14 i), and a fuel slit (14 g) is communicated between the air compressing channel (14 i) and the annular oil groove (14 f); an igniter (14 a) is penetrated in the center of the cone body (14 b), and the igniter (14 a) is pressed by a special-shaped nut (14 e); the outer periphery of the left end of the cylinder of the burner (14) is provided with an annular gap (14 h), and the annular gap (14 h) and the inner wall of the mounting well (7 e) of the main cylinder body (7) form a gas-blocking joint for preventing gas backflushing.
The tail-cooling rotor engine disclosed by the invention has the advantages that the compressor A adopts a centrifugal air compressing structure, and can also adopt another compressor in a multi-stage axial flow and radial flow mixed structure.
The invention relates to an air inlet cover, an air compressor shell, a cold flow tail gas combination body, an injection recoil seat, a main cylinder body and an end cover, which are assembled into a whole machine through flange plate assembly or welding.
The working process of the invention
The igniter is electrified to light, 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 fuel is sucked and mixed into fuel-air inflammable mixed gas, and the fuel-air inflammable mixed gas is ignited through the igniter. The high-temperature high-pressure gas after the fuel combustion is sprayed out through the gas spray 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 burner 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 running program.
The invention has the advantages that
1. The rotor is normalized in cold air cooling, the working temperature is relatively low, the high-temperature performance requirement on the rotor blade material is low, and the manufacturing cost is low.
2. The working rotation speed is low, the abrasion is small, the overhaul period is long, and the use cost is low.
3. The rotor is flushly recoiled, and the low flow and high angular momentum output effect can be obtained; meanwhile, the fuel is completely combusted, and the heat efficiency is high.
4. The recoil rotor rotates in a balanced way, so that the defect of high energy consumption caused by reciprocating motion of a piston engine and unbalanced rotation of a Wankel rotor engine is overcome, and the engine is stable in operation, small in vibration and low in noise.
5. The flywheel effect of the large inertia recoil rotor enables the engine to run at low idle speed without surge, and is particularly suitable for a range extender of a ship, a low-speed propeller fan aircraft, a tank, a pure electric vehicle and the like.
Drawings
FIG. 1 is an elevational schematic cross-sectional view of the present invention.
FIG. 2 is a schematic perspective oblique view of an air intake shroud of the present invention.
FIG. 3 is a left side perspective view of the cold flow tail gas combination of the present invention.
FIG. 4 is a schematic cross-sectional left side perspective view of the cold flow tail gas combination of the present invention.
FIG. 5 is a right side perspective view of the cold flow tail gas combination of the present invention.
Fig. 6 is a right side oblique perspective view of the rotor of the present invention.
Fig. 7 is a schematic perspective view of a shaped curved tube in the rotor of the present invention.
Fig. 8 is a left side oblique perspective view of the rotor of the present invention.
Fig. 9 is a left side oblique perspective view of the jet recoil seat of the present invention.
FIG. 10 is a right side perspective view of the jet recoil seat of the present invention.
FIG. 11 is a schematic perspective view of a burner main cylinder of the present invention in cross-section and oblique view.
FIG. 12 is a schematic cross-sectional oblique perspective view of a fuel seal ring of the present invention.
FIG. 13 is a schematic cross-sectional view of a burner of the present invention.
Description of the embodiments
Example 1
As shown in fig. 1-13, a tail-cooled rotary engine comprises a compressor A, a rotor machine B, a combustor C, a heat circulation heat exchanger 5 and a preheating air pipe 4; the air compressor A comprises an air inlet cover 1, a bearing A2, a starting clutch 3, a shell 17, an air compressing 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 side structure of a cold flow tail gas combination body 16, a bearing B13, a rotor 15, a bearing C12, a left side structure of an injection recoil seat 6 and a main shaft 10; the burner C comprises a right side structure of the jet recoil seat 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 center of the end cover 9 is provided with a main shaft 10 penetrating through a bearing D11; the heat circulation heat exchanger 5 is of a tube array structure and comprises a cold air inlet 5b and a tail gas outlet 5a; the air compressing cavity 17a of the air compressor A is communicated with the air collecting cavity 9a of the end cover 9 from left to right through an outer Zhou Lengliu channel A16B of the cold flow tail gas combination body 16, an outer Zhou Lengliu channel B6a of the jet recoil seat 6 and an outer Zhou Lengliu channel C7a of the main cylinder 7; the air compressing cavity 17a of the air compressor A is communicated with the air collecting cavity 9a of the end cover 9 from left to right through the middle cold flow channel A16C of the cold flow tail gas combination body 16, the middle cold flow channel B15e of the rotor 15, the middle cold flow channel C6C of the jet recoil seat 6 and the middle cold flow channel D7B of the main cylinder 7.
Example 2
As shown in fig. 1 and 2, the tail-cooled rotor engine of the invention, the intake hood 1 comprises an outer cover 1d and a guide cone 1c, and the intake passage is divided into a peripheral preheating airflow passage 1a and a middle cold air passage 1b; the preheated air outlet of the heat circulation heat exchanger 5 is connected with the outer Zhou Yure airflow 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 tail-cooling rotor engine of the invention is characterized in that the cold flow tail gas combination 16 is provided with an outer cylinder a16d, the inner wall of the left section of the outer cylinder a16d is connected with a conical guide table 16g and a guide table extension cylinder 16h, and conical bodies 16f are arranged in the conical guide table 16g and the guide table extension cylinder 16 h; the inner wall of the left section of the outer cylinder A16d, the left side surface of the conical guide table 16g and the outer side surface of the conical body are provided with guide rib plates 16e, and the guide rib plates 16e extend leftwards to the outer side surface of the conical body 16f and the inner side surface of the guide table extension cylinder 16 h; the cold flow tail gas combination body 16 is provided with an annular U-shaped groove formed by 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 conical flow guide table 16g and an opening of the bottom 16i3 of the annular U-shaped groove, and an opening of the conical flow guide table 16g, an inner pore canal of the heat exchange flat tube 16j and an opening of the annular U-shaped groove form an outer Zhou Lengliu channel A16b of the cold flow tail gas combination body 16; heat exchange plates 16i4 are arranged in the annular U-shaped grooves; the outer side surface of the conical body 16f, the left side surface of the conical flow guide table 16g and the inner wall of the flow guide table extension cylinder 16h are partitioned by the flow guide rib plate 16e to form a middle cold flow channel A16c of the cold flow tail gas combination body 16; the 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 table extension cylinder 16h is a tail gas port 16a of the rotor 15, and the tail gas port 16a penetrates through the inner side surface of the outer cylinder A16d, the outer surface of the heat exchange flat tube 16j, the right side surface of the conical guide table 16g and the outer side surface of the guide table extension cylinder 16h to reach the tail gas outlet 5a.
Example 4
As shown in fig. 1 and 6-8, the tail-cooled rotor engine according to the present invention, the rotor 15 includes a profiled curved tube 15a, a primary hub 15b, a secondary hub 15c, spokes 15f and a recoil blade 15d, wherein the cross-sectional area of the expansion ejection port 15a1 of the profiled curved tube 15a of the rotor 15 is larger than the cross-sectional area of the gas injection port 15a2, and the cross-sectional area of the gas injection port 15a2 is larger than the cross-sectional area of the 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 integrated structure; the recoil blades 15d are distributed on the outer circumference of the left section of the secondary hub 15 c; the circumference of the inner wall of the secondary hub 15c is provided with worm-wheel blade-shaped spokes 15f, and the gap between two adjacent spokes 15f and the 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 the outer side to the left of the rotor 15 is high-temperature fuel gas after fuel combustion, and the fluid contacting from the left to the right of the inner side is preheated pressurized air.
Example 5
As shown in fig. 1 and 9-10, in the tail-cooling rotor engine of the invention, a clock seat 6j, a middle cylinder B6f and an outer cylinder B6g are arranged on an annular chassis 6i of the injection recoil seat 6, a shaft hole 6e is arranged in the center of the top of the clock seat 6j, a diversion recoil pit 6d is arranged on the chassis 6i of the left root of the clock seat 6j, a tangential hollowed-out fuel gas injection hole 6B is arranged on the root of the left side of the clock seat 6j, a diversion rib 6h is arranged between the left outer wall of the clock seat 6j and the inner wall of the middle cylinder B6f, a peripheral cold flow channel B6a is arranged on the annular chassis 6i between the inner wall of the outer cylinder B6g and the middle cylinder B6f, and a middle cold flow channel C6C is arranged around the shaft hole 6e at the top of the clock seat 6 j.
Example 6
As shown in fig. 1 and 11-13, the main cylinder 7 of the combustor C of the tail-cooled rotary engine of the present invention has an outer cylinder C7i, a middle cylinder C7j and an inner cylinder C7k on a right end disk 7 f; the right end disc 7f is annularly provided with a mounting well 7e for assembling a burner 14 and an annular fuel groove 7g; the annular fuel groove 7g of the right end disc 7f is embedded into the seal ring 8 and is fixed through the assembly hole 8b to form an annular fuel channel 8a, and the annular fuel channel 8a is communicated with the fuel feed inlet 7 h; the inner wall pipeline of the inner cylinder C7k of the main cylinder 7 is a middle cold flow channel D7b, and a tubular cavity surrounded 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 jet recoil seat 6 is a combustion chamber 7C; the tubular cavity between the inner wall of the outer cylinder C7i of the main cylinder 7 and the inner wall of the middle cylinder C7j is communicated with the opening distributed on the outer circumference of the right end disc 7f to form an outer Zhou Lengliu channel C7a; the middle circumference of the right end disk 7f of the main cylinder 7 is distributed with air channels 7d.
Example 7
As shown in fig. 1 and 13, the tail-cooling rotor engine of the invention has a cylindrical structure, the outer periphery of the middle section of the cylindrical structure is provided with an annular oil groove 14f, 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 loop, and the fuel oil loop is communicated with an annular fuel oil channel 8a of the main cylinder 7; the central left section of the burner 14 is a conical duct, the right section of the burner is a circular duct, a cone 14b is fixed in the left Duan Zhuixing duct through a bracket, a conical channel between the outer peripheral conical surface of the cone 14b and the inner conical surface of the conical duct is a compressed air channel 14i, and a fuel slit 14g is communicated between the compressed air channel 14i and the annular oil groove 14 f; an igniter 14a is penetrated in the center of the cone 14b, and the igniter 14a is pressed by a special-shaped nut 14 e; the outer 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 cylinder 7 form a gas-blocking joint for preventing gas backflushing.
Example 8
The tail-cooling rotor engine disclosed by the invention has the advantages that the compressor A adopts a centrifugal air compressing structure, and can also adopt another compressor in a multi-stage axial flow and radial flow mixed structure.
The invention relates to an air inlet cover, an air compressor shell, a cold flow tail gas combination body, an injection recoil seat, a main cylinder body and an end cover, which are assembled into a whole machine through flange plate assembly or welding.
The tail-cooled rotary engine provided by the invention is described in detail above. The description of the specific embodiments is only intended to aid in understanding the method of the present invention and its core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.

Claims (7)

1. A tail-cooled rotor engine comprises a gas compressor A, a rotor machine B, a combustor C, a heat circulation heat exchanger (5) and a preheating air pipe (4); the air compressor A comprises an air inlet cover (1), a bearing A (2), a starting clutch (3), a shell (17), an air compressing 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 an injection recoil seat (6) and a main shaft (10); the burner C comprises a right side structure of the jet recoil seat (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 center of the end cover (9) is penetrated by the main shaft (10) through a bearing D (11); the heat circulation heat exchanger (5) is of a tube array structure and comprises a cold air inlet (5 b) and a tail gas outlet (5 a); the method is characterized in that:
The air compressing cavity (17 a) of the air compressor A is communicated with the air collecting cavity (9 a) of the end cover (9) from left to right through an outer Zhou Lengliu channel A (16B) of the cold flow tail gas combination body (16), an outer Zhou Lengliu channel B (6 a) of the jet recoil seat (6) and an outer Zhou Lengliu channel C (7 a) of the main cylinder body (7);
the air compressing cavity (17 a) of the air compressor A is communicated with the air collecting cavity (9 a) of the end cover (9) from left to right through the middle cold flow channel A (16C) of the cold flow tail gas combination body (16), the middle cold flow channel B (15 e) of the rotor (15), the middle cold flow channel C (6C) of the jet recoil seat (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 an outer cover (1 d) and a guide cone (1 c), and the air inlet channel is divided into a peripheral preheating airflow channel (1 a) and a middle cold air channel (1 b); the preheated air outlet of the heat circulation heat exchanger (5) is connected with an outer Zhou Yure airflow channel (1 a) 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 (16 d), the inner wall of the left section of the outer cylinder A (16 d) is connected with a conical flow guide table (16 g) and a flow guide table extension cylinder (16 h), and conical bodies (16 f) are arranged in the conical flow guide table (16 g) and the flow guide table extension cylinder (16 h);
The inner wall of the left section of the outer cylinder A (16 d), the left side surface of the conical guide table (16 g) and the outer side surface of the conical body are provided with guide rib plates (16 e), and the guide rib plates (16 e) extend leftwards to the outer side surface of the conical body (16 f) and the inner side surface of the guide table extension cylinder (16 h);
The cold flow tail gas combination body (16) is provided with an annular U-shaped groove formed by an inner cylinder A (16 i 1), a middle cylinder A (16 i 2) and a bottom (16 i 3), a heat exchange flat tube (16 j) is connected between an opening of a conical flow guide table (16 g) and an opening of the bottom (16 i 3) of the annular U-shaped groove, and an outer Zhou Lengliu channel A (16 b) of the cold flow tail gas combination body (16) is formed by the opening of the conical flow guide table (16 g), an inner pore canal of the heat exchange flat tube (16 j) and the opening of the annular U-shaped groove; heat exchange plates (16 i 4) are arranged in the annular U-shaped grooves;
The outer side surface of the conical body (16 f), the left side surface of the conical guide table (16 g) and the channel of the inner wall of the guide table extension cylinder (16 h) separated by the guide rib plate (16 e) form a middle cold flow channel A (16 c) of the cold flow tail gas combination body (16);
The annular channel formed between the inner wall of the inner cylinder A (16 i 1) of the annular U-shaped groove and the outer wall of the guide table extension cylinder (16 h) is a tail gas port (16 a) of the rotor (15), and the tail gas port (16 a) penetrates through the inner side surface of the outer cylinder A (16 d), the outer surface of the heat exchange flat tube (16 j), the right side surface of the conical guide table (16 g) and the outer side surface of the guide table extension cylinder (16 h) to reach the tail gas outlet (5 a).
4. The tail-cooled rotary engine of claim 1, the rotor (15) comprising a profiled curved tube (15 a), a primary hub (15 b), a secondary hub (15 c), spokes (15 f) and recoil vanes (15 d), characterized in that:
the sectional area of an expansion ejection port (15 a 1) of the special-shaped curved pipe (15 a) of the rotor (15) is larger than the sectional area of a fuel gas ejection port (15 a 2), and the sectional area of the fuel gas ejection port (15 a 2) is larger than the sectional area of the necking pipe (15 a 3);
The gas injection ports (15 a 2) of the special-shaped curved pipe (15 a) are distributed on the circumference of the primary hub (15 b), and the expansion ejection ports (15 a 1) are distributed on the circumference of the right section of the secondary hub (15 c);
the diameter of the primary hub (15 b) is smaller than that of the secondary hub (15 c), and the primary hub (15 b) and the secondary hub (15 c) are of an integrated structure;
The recoil blades (15 d) are distributed on the outer circumference of the left section of the secondary hub (15 c);
the circumference of the inner wall of the secondary hub (15 c) is provided with worm-wheel blade-shaped spokes (15 f), and the gap between two adjacent spokes (15 f) and the gap between the outer walls of two adjacent special-shaped curved pipes are communicated to form an intermediate cold flow channel B (15 e) of the rotor (15);
The fluid contacting from the outer side to the left of the rotor (15) is high-temperature fuel gas after fuel combustion, and the fluid contacting from the left to the right of the rotor is preheated pressurized air.
5. The tail-cooled rotary engine of claim 1, wherein:
The jet backflushing seat is characterized in that a clock seat (6 j), a middle cylinder B (6 f) and an outer cylinder B (6 g) are arranged on an annular chassis (6 i) of the jet backflushing seat (6), a shaft hole (6 e) is arranged in the center of the top of the clock seat (6 j), a diversion backflushing pit (6 d) is arranged on the chassis (6 i) at the left root of the clock seat (6 j), a tangential hollowed-out gas jet hole (6B) is arranged at the left root of the clock seat (6 j), a diversion rib (6 h) is arranged between the left outer wall of the clock seat (6 j) and the inner wall of the middle cylinder B (6 f), a peripheral cold flow channel B (6 a) is arranged on the annular chassis (6 i) between the inner wall of the outer cylinder B (6 g) and the middle cylinder B (6 f), and an intermediate cold flow channel C (6C) is arranged around the shaft hole (6 e) at the top of the clock seat (6 j).
6. The tail-cooled rotary engine of claim 1, wherein: the main cylinder body (7) of the burner C is provided with an outer cylinder C (7 i), a middle cylinder C (7 j) and an inner cylinder C (7 k) on a right end disc (7 f); the right end disc (7 f) is annularly provided with an installation well (7 e) for assembling the burner (14) and an annular fuel tank (7 g);
the annular fuel groove (7 g) of the right end disc (7 f) is embedded into the seal ring (8) and is fixedly formed into an annular fuel channel (8 a) through the assembly hole (8 b), and the annular fuel channel (8 a) is communicated with the fuel feed inlet (7 h);
The inner wall pipeline of an inner cylinder C (7 k) of the main cylinder body (7) is a middle cold flow channel D (7 b), and a tubular cavity surrounded by the outer wall of the inner cylinder C (7 k), the left side surface of a right end disc (7 f), the inner wall of the middle cylinder C (7 j) and the right side surface of the jet recoil seat (6) is a combustion chamber (7C);
The tubular cavity between the inner wall of the outer cylinder C (7 i) of the main cylinder body (7) and the inner wall of the middle cylinder C (7 j) is communicated with the opening distributed on the outer circumference of the right end disc (7 f) to form an outer Zhou Lengliu channel C (7 a);
Air channels (7 d) are distributed on the middle circumference of a right end disc (7 f) of the main cylinder body (7).
7. The tail-cooled rotary engine of claim 6, wherein:
The burner (14) is of a cylindrical structure, an annular oil groove (14 f) is formed in the periphery of the middle section of the cylindrical structure, an annular cavity formed by the annular oil groove (14 f) and the inner wall of an installation well (7 e) of the main cylinder body (7) forms a fuel oil loop, and the fuel oil loop is communicated with an annular fuel oil channel (8 a) of the main cylinder body (7);
The central left section of the burner (14) is a conical duct, the right section of the burner is a circular duct, a cone (14 b) is fixed in the left Duan Zhuixing duct through a bracket, a conical channel between the outer peripheral conical surface of the cone (14 b) and the inner conical surface of the conical duct is an air compressing channel (14 i), and a fuel slit (14 g) is communicated between the air compressing channel (14 i) and the annular oil groove (14 f);
an igniter (14 a) is penetrated in the center of the cone body (14 b), and the igniter (14 a) is pressed by a special-shaped nut (14 e);
the outer periphery of the left end of the cylinder of the burner (14) is provided with an annular notch (14 h), and the annular notch (14 h) and the inner wall of the mounting well (7 e) of the main cylinder body (7) form a gas-barrier joint for preventing gas backflushing.
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