CN204729142U - A kind of aeroengine heat recovery cogeneration system - Google Patents
A kind of aeroengine heat recovery cogeneration system Download PDFInfo
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- CN204729142U CN204729142U CN201520428316.0U CN201520428316U CN204729142U CN 204729142 U CN204729142 U CN 204729142U CN 201520428316 U CN201520428316 U CN 201520428316U CN 204729142 U CN204729142 U CN 204729142U
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- vaporizer
- steam chest
- working medium
- aeroengine
- heat recovery
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/14—Combined heat and power generation [CHP]
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Abstract
The utility model belongs to aero engine technology field, particularly relate to a kind of aeroengine heat recovery cogeneration system, comprise the first vaporizer, the second vaporizer, decompressor, condenser, working medium pump, generator, liquid container, feed tank and steam chest.Utilize Rankine cycle power generation system that the waste heat outside airplane engine firing chamber is changed into electric energy and interior energy, directly cold water is heated by steam, change on current aircraft and adopt electrically heated mode, enough drinking and domestic water can be provided for passenger and flight crew, decrease the useful work sharing out drive electrical generators from turbine shaft.Compared with designing with conventional airplane electricity generating device, the design adds the acting ability of airplane engine, improves the Economy of aircraft fuel oil; Therefore the heat recovery cogeneration system of this patent, effectively can realize the maximization of using energy source.
Description
Technical field
The utility model belongs to aero engine technology field, particularly relates to a kind of aeroengine heat recovery cogeneration system.
Background technique
Along with the lifting of people's living standard, the raising of quality of life, the consciousness of people to energy-saving and emission-reduction is also constantly strengthened.The utilization of residual heat resources receives the concern of more and more people, and these heat energy are of a great variety, comprises the new energy such as solar energy, geothermal power and various remaining (giving up) heat etc.The quantity of middle-low temperature heat is extremely huge, the a large amount of middle-low temperature heats produced in the industry production processes such as iron and steel, cement, petrochemical industry, comprise hot water, low-grade flue gas and steam etc., these amount of heat are large, grade is low, substantially can not be recycled by production process, to the recycling of this part waste heat, not only can reduce the pollution to environment, more can increase the Appropriate application of resource, reach the effect of energy-saving and emission-reduction.Propose herein a kind of utilize aircraft turbine engine to burn after waste heat carry out the cogeneration equipment recycled.
At present, the power generating equipment on aircraft mainly contains three sources: (1) is carried out drive electrical generators by motor and generated electricity; (2) at the afterbody of aircraft, a small-sized turbogenerator and generator are housed, it is auxiliary power unit (APU).The effect of this mini engine, just in order to drive APU generator, the power of its generator is larger than the power of other 2 generators on machine; (3) for modern passenger aircraft, being also provided with DC system, utilizing large-capacity battery when generator normally works, by current transformer for aircraft provides direct current, and is that charge in batteries is as reserve battery.The third generation mode only just can be entrusted with a mission at a critical and difficult moment under all inoperable extreme case of above three kinds of generators, and generated energy is also limited.
At present, on aircraft, the mode of hot water and heat food is the electrical equipment such as electric heater or microwave oven.Instrumentations numerous on aircraft and electrical equipment institute subfam. Spiraeoideae can be able to not maintain only by storage battery, in above-mentioned first two generation mode, making the motor of the drive electrical generators that the accessory drive casing that is mechanically connected is installed with engine turbine axle, no matter working efficiency is much, they all can share the useful work being used for promoting turbine greatly, and the efficiency that this reduces turbogenerator reduces the Economy of aircraft fuel oil.
For turbogenerator, the temperature of firing chamber is usually very high, and can reach more than 1000K, even if the temperature outside firing chamber also can reach more than 600K, this part heat is not only fully utilized and is wasted on the contrary.Burning outdoor temperature is too high also can propose higher requirement to the material of casing, and working life greatly reduces, and the design is exactly by utilizing this part waste heat externally to export heat energy and electric energy and by to start and the design of structure improves engine performance.
Summary of the invention
The defect that the utility model exists to overcome prior art, the purpose of this utility model is to provide a kind of aeroplane engine engine efficiency and is improved, and engine material is also played to the aeroengine heat recovery cogeneration system of the effect of cooling protection.
The technical solution that the utility model adopts is a kind of aeroengine heat recovery cogeneration system, comprise the first vaporizer, second vaporizer, decompressor, condenser, working medium pump, generator, liquid container, feed tank and steam chest, the first described vaporizer, second vaporizer is arranged in airplane engine, the organic working medium output terminal of the first described vaporizer is connected with the input end of decompressor, the organic working medium output terminal of described decompressor is connected with the input end of condenser, the output terminal of condenser is connected with the input end of liquid container, organic working medium is inputed to the organic working medium input end of the first vaporizer by liquid container by working medium pump, the input end of described generator is connected with the output terminal of decompressor, the working medium input end of the second described vaporizer is connected with the output terminal of steam chest, the steam input end of described steam chest is connected with the working medium output terminal of the second vaporizer, and the cold water output terminal of described feed tank is connected with the feed-water end of steam chest, described condenser is nozzle ring, and the first described vaporizer, the second vaporizer adopt the tubular heat exchanger of air cooling form, are arranged between casing and firing chamber.
Described vaporizer, decompressor, adopt resistant to elevated temperatures metallic conduit to connect between condenser and working medium pump, described pipeline external is provided with thermal insulation layer.
Described nozzle ring is arranged on the outside of turbogenerator fan in casing, nozzle ring comprises blade, outer disk and solid shaft, described solid shaft two ends are bolted on blade, described blade is fixedly connected with outer disk, described nozzle ring outer disk and casing are weldingly fixed on casing, be provided with guide plate in described blade, described guide plate in blade by S-type for working medium passage setting.
Described vaporizer adopts one group of oval coil pipe, and described coil pipe firing chamber outer surface is arranged along air-flow direction in the shape of a spiral.
Described feed tank, also pneumatic tube is comprised between steam chest and the second vaporizer, return pipe, first control valve, second control valve, water-level gauge conduit, hot water box, safety valve, sealing cover, thermometer conduit, gas bleeder valve, inlet valve, cold valves, heat water valve, described steam chest top and feed tank joint are provided with the second control valve, steam chest inside is provided with hot water box, inlet valve is provided with feed tank joint above hot water box, safety valve and gas bleeder valve is also provided with above hot water box, thermometer conduit is provided with in safety valve side, described thermometer conduit and joint, hot water box top are provided with sealing cover, the heat water valve that drain water piping connects water fountain is provided with bottom hot water box, return pipe is arranged on the bottom of steam chest, the return pipe of described steam chest is connected with the input end of the 3rd heat exchanger, described pneumatic tube is located at the bottom of vaporizer, the pneumatic tube of described steam chest is connected with the output terminal of the 3rd heat exchanger, is provided with the first control valve, is provided with water-level gauge conduit in described steam chest in described pneumatic tube.
Described pneumatic tube, muffler all adopt bolt by flange respectively the outlet end of working medium cold with heater and entrance point be connected, accompanies red copper pad in the middle of described flange plate, ensure the sealing after connecting, pneumatic tube and return pipe all adopt 304 stainless steel pipes.
The height of described water fountain will lower than the height of steam chest.
Described hot water box and steam chest all adopt stainless steel material, and steam chest outside rubber asbestos gasket is heat insulation, shockproof and be fixed on vehicle tail end motor side.
Compared with prior art, the beneficial effect that the utility model has is: utilize Rankine cycle power generation system that the waste heat outside airplane engine firing chamber is changed into electric energy and interior energy, directly cold water is heated by steam, change on current aircraft and adopt electrically heated mode, enough drinking and domestic water can be provided for passenger and flight crew, decrease the useful work sharing out drive electrical generators from turbine shaft.Heating Cyclic and potable water circulation separate completely, ensure that the sanitation and hygiene of potable water.By the improvement to airflow fence structure, preheating can be carried out to incoming air, also can prevent the generation of the icing phenomenon when air is lower.Compared with designing with conventional airplane electricity generating device, the design adds the acting ability of airplane engine, improves the Economy of aircraft fuel oil; Therefore the heat recovery cogeneration system of this patent, effectively can realize the maximization of using energy source.
Accompanying drawing explanation
Fig. 1 is the utility model structure and schematic diagram;
Fig. 2 is aeroengine afterheat generating system sectional drawing;
Fig. 3 is condenser front view;
Fig. 4 is the sectional view of nozzle ring blade;
Fig. 5 is system evaporator plan view;
Fig. 6 is system evaporator plan view;
Fig. 7 is system evaporator side view;
Fig. 8 is aeroengine heating system schematic diagram.
1 airplane engine in figure, 2 condensers, 3 first vaporizers, 4 second vaporizers, 5 decompressors,
6 liquid containers, 7 working medium pumps, 8 generators, 9 feed tanks, 10 steam chests, 11 pneumatic tubes,
12 return pipes, 13 first control valves, 14 water-level gauge conduits, 15 hot water boxs, 16 safety valves,
17 sealing covers, 18 thermometer conduits, 19 gas bleeder valves, 20 inlet valves, 21 second control valves,
22 cold valves, 23 heat water valves, 24 air, 25 fans, 26 low pressure compressors,
27 high pressure compressors, 28 gear-boxes, 29 firing chambers, 30 high-pressure turbines, 31 low-pressure turbines,
32 high-temperature gases, 33 solid shafts, 34 outer disks, 35 blades, 36 guide plates.
Embodiment
Embodiment 1:
As shown in Figure 1: a kind of aeroengine afterheat generating system, by airplane engine 1 as thermal source, comprise the first vaporizer 3, second vaporizer 4, decompressor 5, condenser 2, working medium pump 7, generator 8, liquid container 6, feed tank 9 and steam chest 10, the first described vaporizer 3, second vaporizer 4 is arranged in airplane engine 1, the organic working medium output terminal of the first described vaporizer 3 is connected with the input end of decompressor 5, the organic working medium output terminal of described decompressor 5 is connected with the input end of condenser 2, the output terminal of condenser 2 is connected with the input end of liquid container 6, organic working medium is inputed to the organic working medium input end of the first vaporizer 3 by liquid container 6 by working medium pump 7, the input end of described generator 8 is connected with the output terminal of decompressor 5, the working medium input end of the second described vaporizer 4 is connected with the output terminal of steam chest 10, the steam input end of described steam chest 10 is connected with the working medium output terminal of the second vaporizer 4, and the cold water output terminal of described feed tank 9 is connected with the feed-water end of steam chest 10, described condenser 2 is nozzle ring, and the first described vaporizer 3, second vaporizer 4 adopts the tubular heat exchanger of air cooling form, is arranged between casing and firing chamber 29.
Described vaporizer, decompressor 5, adopt resistant to elevated temperatures metallic conduit to connect between condenser 2 and working medium pump 7, described pipeline external is provided with thermal insulation layer, reduces heat loss.Wherein decompressor 5 is the important motivity parts in aeroengine afterheat generating system, by the interior a kind of novel power output part that can be converted into mechanical energy by the gas expansion for doing work of High Temperature High Pressure, existing other decompressor 5 equipment of multikilowatt in the market, be applicable to, needed for native system, can business buying.Wherein working medium pump 7 is mainly the saturated working medium pressurization carrying out condenser 2, saturated working medium is made to become the supercooled liquid of high pressure by working medium pump 7 pressurization, thus heat absorption becomes the gas of High Temperature High Pressure in vaporizer, promote decompressor 5 to do work, according to the thermodynamic properties of organic working medium, the working pressure of working medium pump 7 is at 1 MPa-2MPa, and lift is that about 150m can meet native system requirement.Vaporizer needs two, and one flows through working medium is Rankine cycle organic working medium, and one flows through working medium is water.Generator 8: generator 8 is be electric energy vitals by changes mechanical energy in the present system, generator 8 technology the application of China developed enough ripe.Those skilled in the art can carry out according to the scale of prior art and system the generator 8 selecting and arrange various model.Because condenser in native system 2 and vaporizer need not consider the impact of heat dissipation problem on system, so connect with resistant to elevated temperatures metallic conduit in casing inside.Liquid container 6, working medium pump 7, decompressor 5, generator 8 are arranged on casing, also connect with metallic conduit, but will add thermal insulation layer at pipeline external, reduce heat loss.
Nozzle ring as described in as shown in Fig. 2-Fig. 7 is arranged on the outside of turbogenerator fan 25 in casing, nozzle ring comprises blade 35, outer disk 34 and solid shaft 33, described solid shaft 33 two ends are bolted on blade 35, described blade 35 is fixedly connected with outer disk 34, described nozzle ring outer disk 34 is weldingly fixed on casing with casing, be provided with guide plate 36 in described blade 35, described guide plate 36 in blade 35 by S-type for working medium passage setting.Condenser 2 described in model utility is obtained by the structure changing turbogenerator suction port front end airflow fence, in order to save turbogenerator material therefor, alleviating aircraft weight, the structure of turbine vane grid being redesigned in design.The structure of airflow fence takes centre to be provided with the design of guide plate 36 hollow, and working medium flows into from the conduit of nozzle ring front portion, and dependence internal diversion plate 36 is S-type in nozzle ring to be flow through, and such design increases the heat exchange area of working medium, improves exchange efficiency.
Described vaporizer adopts one group of oval coil pipe, and described coil pipe firing chamber 29 outer surface is arranged along air-flow direction in the shape of a spiral.The diameter of coil pipe is less, more intensive, evaporation area will be larger, evaporation effect is also better, in turbogenerator, intensive thin coil pipe, from the continuous rearwardly flow at high speed of leading portion, is fixed on the space between firing chamber 29 and casing by air stream, the just Air-cooled Heat Exchanger of a composition forced convection, the coil direction of coil pipe is along air-flow direction.
The utility model is as follows in the specific works process of turbogenerator inside: working medium absorbs the heat distributed from outside, firing chamber 29 in coils, and the temperature outside current combustion room 29 reaches more than 600K usually, and coil pipe is arranged along air-flow direction in the shape of a spiral.After saturated liquid working substance in coil pipe absorbs certain heat, the steam being transformed into High Temperature High Pressure is transported to the decompressor 5 on casing, promote decompressor 5 do work after the working medium gas that becomes temperature relatively high low pressure enter into the nozzle ring being positioned at motor leading portion along pipeline.Due to aircraft high-speed flight, the temperature of engine intake is very low, is condensed after high-temperature gas passes through in nozzle ring, becomes the liquid of low-temp low-pressure.Vaporizer is entered after by the working medium pump 7 that is arranged on casing outside the liquid pressing from nozzle ring being become the liquid of saturated high pressure, complete a circulation of doing manual work, and the generator 8 be connected with decompressor 5 output terminal continually will send electric energy, on machine, power distribution network is various load distribution.
Native system also needs electrical energy drive, powers so should be provided with a power supply line for native system in power distribution unit.The electric energy that power supply line provides mainly is used for regulating working medium pump 7 rotating speed to realize power generation system generated energy.The selection of described power supply line and be set to the state of the art, those skilled in the art can carry out selecting and arranging according to prior art.The engine exhaust heat power generation system that the design's model utility provides not only is adapted to gas turbine engine, and the waste heat that the motor for other types produces also can absorb, and is a kind of energy-efficient power generation system.
As shown in Figure 8: described feed tank 9, pneumatic tube 11 is also comprised between steam chest 10 and the second vaporizer 4, return pipe 12, first control valve 13, second control valve 21, water-level gauge conduit 14, hot water box 15, safety valve 16, sealing cover 17, thermometer conduit 18, gas bleeder valve 19, inlet valve 20, cold valves 22, heat water valve 23, described steam chest 10 top and feed tank 9 joint are provided with the second control valve 21, steam chest 10 inside is provided with hot water box 15, inlet valve 20 is provided with feed tank 9 joint above hot water box 15, safety valve 16 and gas bleeder valve 19 is also provided with above hot water box 15, thermometer conduit 18 is provided with in safety valve 16 side, described thermometer conduit 18 is provided with sealing cover 17 with joint, hot water box 15 top, the heat water valve 23 that drain water piping connects water fountain is provided with bottom hot water box 15, return pipe 12 is arranged on the bottom of steam chest 10, the return pipe 12 of described steam chest 10 is connected with the input end of the 3rd heat exchanger, described pneumatic tube 11 is located at the bottom of vaporizer, the pneumatic tube 11 of described steam chest 10 is connected with the output terminal of the 3rd heat exchanger, the first control valve 13 is provided with in described pneumatic tube 11, water-level gauge conduit 14 is provided with in described steam chest 10.
Described pneumatic tube 11, muffler all adopt bolt, and by flange, the outlet end of working medium cold with heater and entrance point are connected respectively, red copper pad is accompanied in the middle of described flange plate, ensure the sealing after connecting, pneumatic tube 11 and return pipe 12 all adopt 304 stainless steel pipes.
The height of described water fountain will lower than the height of steam chest 10.
Described hot water box 15 and steam chest 10 all adopt stainless steel material, and steam chest 10 outside rubber asbestos gasket is heat insulation, shockproof and be fixed on vehicle tail end motor side.
Heat supplying process is as follows: the cold water of feed tank 9 enters hot water box 15 by inlet valve 20, portion of cold water enters steam chest 10 by the second control valve 21, when hot water is needed, open the first control valve 13, cold water in steam chest 10 enters the second vaporizer 4 by return pipe 12, become water vapor through the cool water heating of the second vaporizer 4 and get back to steam chest 10 by pipeline, cold water in steam heating hot water box 15 in steam chest 10, after heat release, steam-condensation is bottom liquid water stream to steam chest 10, then enters the second vaporizer 4 by return pipe 12 and complete heating process.
More than show and describe basic principle of the present utility model, major character and advantage of the present utility model.The technician of the industry should understand; the utility model is not restricted to the described embodiments; what describe in above-described embodiment and specification just illustrates principle of the present utility model; under the prerequisite not departing from the utility model spirit and scope, the utility model also has various changes and modifications, and these changes and improvements all fall within the scope of claimed the utility model.The claimed scope of the utility model is defined by appending claims and equivalent thereof.
Claims (8)
1. an aeroengine heat recovery cogeneration system, it is characterized in that: comprise the first vaporizer, second vaporizer, decompressor, condenser, working medium pump, generator, liquid container, feed tank and steam chest, the first described vaporizer, second vaporizer is arranged in airplane engine, the organic working medium output terminal of the first described vaporizer is connected with the input end of decompressor, the organic working medium output terminal of described decompressor is connected with the input end of condenser, the output terminal of condenser is connected with the input end of liquid container, organic working medium is inputed to the organic working medium input end of the first vaporizer by liquid container by working medium pump, the input end of described generator is connected with the output terminal of decompressor, the working medium input end of the second described vaporizer is connected with the output terminal of steam chest, the steam input end of described steam chest is connected with the working medium output terminal of the second vaporizer, and the cold water output terminal of described feed tank is connected with the feed-water end of steam chest, described condenser is nozzle ring, and the first described vaporizer, the second vaporizer adopt the tubular heat exchanger of air cooling form, are arranged between casing and firing chamber.
2. aeroengine heat recovery cogeneration system according to claim 1, is characterized in that: described vaporizer, decompressor, adopt resistant to elevated temperatures metallic conduit to connect between condenser and working medium pump, and described pipeline external is provided with thermal insulation layer.
3. aeroengine heat recovery cogeneration system according to claim 1, it is characterized in that: described nozzle ring is arranged on the outside of turbogenerator fan in casing, nozzle ring comprises blade, outer disk and solid shaft, described solid shaft two ends are bolted on blade, described blade is fixedly connected with outer disk, described nozzle ring outer disk and casing are weldingly fixed on casing, be provided with guide plate in described blade, described guide plate in blade by S-type for working medium passage setting.
4. aeroengine heat recovery cogeneration system according to claim 1, is characterized in that: described vaporizer adopts one group of oval coil pipe, and described coil pipe firing chamber outer surface is arranged along air-flow direction in the shape of a spiral.
5. aeroengine heat recovery cogeneration system according to claim 1, is characterized in that: described feed tank, also pneumatic tube is comprised between steam chest and the second vaporizer, return pipe, first control valve, second control valve, water-level gauge conduit, hot water box, safety valve, sealing cover, thermometer conduit, gas bleeder valve, inlet valve, cold valves, heat water valve, described steam chest top and feed tank joint are provided with the second control valve, steam chest inside is provided with hot water box, inlet valve is provided with feed tank joint above hot water box, safety valve and gas bleeder valve is also provided with above hot water box, thermometer conduit is provided with in safety valve side, described thermometer conduit and joint, hot water box top are provided with sealing cover, the heat water valve that drain water piping connects water fountain is provided with bottom hot water box, return pipe is arranged on the bottom of steam chest, the return pipe of described steam chest is connected with the input end of the 3rd heat exchanger, described pneumatic tube is located at the bottom of vaporizer, the pneumatic tube of described steam chest is connected with the output terminal of the 3rd heat exchanger, is provided with the first control valve, is provided with water-level gauge conduit in described steam chest in described pneumatic tube.
6. aeroengine heat recovery cogeneration system according to claim 5, it is characterized in that: described pneumatic tube, muffler all adopt bolt the outlet end of working medium cold with heater and entrance point are connected respectively by flange, red copper pad is accompanied in the middle of described flange plate, ensure the sealing after connecting, pneumatic tube and return pipe all adopt 304 stainless steel pipes.
7. aeroengine heat recovery cogeneration system according to claim 5, is characterized in that: the height of described water fountain will lower than the height of steam chest.
8. aeroengine heat recovery cogeneration system according to claim 5, is characterized in that: described hot water box and steam chest all adopt stainless steel material, and steam chest outside rubber asbestos gasket is heat insulation, shockproof and be fixed on vehicle tail end motor side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520428316.0U CN204729142U (en) | 2015-06-22 | 2015-06-22 | A kind of aeroengine heat recovery cogeneration system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520428316.0U CN204729142U (en) | 2015-06-22 | 2015-06-22 | A kind of aeroengine heat recovery cogeneration system |
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| CN204729142U true CN204729142U (en) | 2015-10-28 |
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| CN201520428316.0U Expired - Fee Related CN204729142U (en) | 2015-06-22 | 2015-06-22 | A kind of aeroengine heat recovery cogeneration system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104912609A (en) * | 2015-06-22 | 2015-09-16 | 沈阳航空航天大学 | Waste heat recovery combined heat and power system of aero-engine |
| CN110905689A (en) * | 2018-09-17 | 2020-03-24 | 高荣江 | Open water cooling split-flow engine |
-
2015
- 2015-06-22 CN CN201520428316.0U patent/CN204729142U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104912609A (en) * | 2015-06-22 | 2015-09-16 | 沈阳航空航天大学 | Waste heat recovery combined heat and power system of aero-engine |
| CN104912609B (en) * | 2015-06-22 | 2016-10-26 | 沈阳航空航天大学 | Aero-engine waste heat recovery cogeneration system |
| CN110905689A (en) * | 2018-09-17 | 2020-03-24 | 高荣江 | Open water cooling split-flow engine |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151028 Termination date: 20180622 |
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| CF01 | Termination of patent right due to non-payment of annual fee |