CN204552947U - A kind of aeroengine afterheat generating system - Google Patents
A kind of aeroengine afterheat generating system Download PDFInfo
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- CN204552947U CN204552947U CN201520187420.5U CN201520187420U CN204552947U CN 204552947 U CN204552947 U CN 204552947U CN 201520187420 U CN201520187420 U CN 201520187420U CN 204552947 U CN204552947 U CN 204552947U
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- decompressor
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Abstract
The utility model belongs to aero engine technology field, particularly relate to a kind of aeroengine afterheat generating system, propose a kind of power supply system being applicable to aircraft turbine engine based on organic Rankine bottoming cycle, it mainly comprises vaporizer, decompressor, condenser, working medium pump, generator.Wherein, vaporizer and condenser are all obtain in conjunction with turbine engine components carries out transforming, by the design to native system, obviously can not only increase the output work of airplane engine, improve workmanship effect rate of airplane engine, the problem that airplane engine leading portion incoming flow easily freezes when temperature is lower can also be solved, and casing temperature can be reduced, extend the materials'use life-span.
Description
Technical field
The invention belongs to aero engine technology field, particularly relate to a kind of aeroengine afterheat generating 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 equipment that generates electricity.
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.But, instrumentations numerous on aircraft and electrical equipment institute subfam. Spiraeoideae can be able to not maintain only by storage battery, in 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, this reduces the efficiency of turbogenerator.
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.
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 aeroengine afterheat generating system; by the utilization to aeroengine waste heat and the design to system architecture; a kind of type aircraft power supply mode is provided; aeroplane engine engine efficiency is improved; condenser described in invention is that the structure by changing turbogenerator suction port front end nozzle ring realizes condensation effect, engine material is also played to the effect of cooling protection.
The technical solution that the utility model adopts is a kind of aeroengine afterheat generating system, comprise vaporizer, decompressor, condenser, working medium pump and generator, described vaporizer, decompressor, condenser are connected with input end successively with working medium delivery side of pump, the input end of described generator is connected with the output terminal of decompressor, described condenser is nozzle ring, described vaporizer adopts the tubular heat exchanger of air cooling form, is 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.
Compared with prior art, the beneficial effect that the present invention has is: utilize Rankine cycle power generation system that the waste heat outside airplane engine firing chamber is transformed into electric energy, 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, by the improvement to nozzle ring structure, can carry out preheating, also can prevent the generation of the icing phenomenon when air is lower to incoming air.Therefore utilize afterheat generating system, obviously can improve the acting ability of airplane engine, realize the maximization of using energy source.Engine exhaust heat power generation system provided by the present invention is not only 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.
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.
1. nozzle rings, 2. fan, 3. gear-box, 4. low pressure compressor, 5. high pressure compressor in figure, 6. firing chamber, 7. evaporator coil, 8. high-pressure turbine, 9. low-pressure turbine, 10. air, 11. high-temperature gases, 12. solid shafts, 13. outer disks, 14. blades, 15. guide plates.
Embodiment
Embodiment 1:
As shown in Figure 1: a kind of aeroengine afterheat generating system, comprise vaporizer, decompressor, condenser, working medium pump and generator, described vaporizer, decompressor, condenser are connected with input end successively with working medium delivery side of pump, the input end of described generator is connected with the output terminal of decompressor, described condenser is nozzle ring 1, described vaporizer adopts the tubular heat exchanger of air cooling form, is arranged between casing and firing chamber 6.
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, reduces heat loss.Wherein decompressor 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 expander plant of multikilowatt in the market, be applicable to, needed for native system, can business buying.Wherein working medium pump is mainly the saturated working medium pressurization carrying out condenser, saturated working medium is made to become the supercooled liquid of high pressure by working medium pump pressurization, thus heat absorption becomes the gas of High Temperature High Pressure in vaporizer, promote decompressor acting, according to the thermodynamic properties of organic working medium, the working pressure of working medium pump is at 1 MPa-2MPa, and lift is that about 150m can meet native system requirement.
Nozzle ring 1 as described in as shown in Fig. 2-Fig. 7 is arranged on the outside of turbogenerator fan 2 in casing, nozzle ring 1 comprises blade 14, outer disk 13 and solid shaft 12, described solid shaft 12 two ends are bolted on blade 14, described blade 14 is fixedly connected with outer disk 13, described nozzle ring 1 outer disk 13 is weldingly fixed on casing with casing, be provided with guide plate 15 in described blade 14, described guide plate 15 in blade 14 by S-type for working medium passage setting.Condenser described in invention 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 1 being redesigned in design.The structure of airflow fence takes centre to be provided with the design of guide plate 15 hollow, and working medium flows into from the conduit of nozzle ring 1 front portion, and dependence internal diversion plate 15 is S-type in nozzle ring 1 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 6 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 6 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 present invention is as follows in the specific works process of turbogenerator inside: working medium absorbs the heat distributed from outside, firing chamber 6 in coils, and the temperature outside current combustion room 6 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 on casing, and the gas that after promoting decompressor acting, working medium becomes temperature relatively high low pressure enters into the nozzle ring 1 being positioned at motor leading portion along pipeline.Due to aircraft high-speed flight, the temperature of engine intake is very low, and high-temperature gas is condensed after passing through in nozzle ring 1, becomes the liquid of low-temp low-pressure.Vaporizer is entered after by the working medium pump that is arranged on casing outside the liquid pressing from nozzle ring 1 being become the liquid of saturated high pressure, complete a circulation of doing manual work, and the generator be connected with decompressor 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 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.
More than show and describe basic principle of the present invention, major character and advantage of the present invention.The technician of the industry should understand; the present invention is not restricted to the described embodiments; what describe in above-described embodiment and specification just illustrates principle of the present invention; the present invention also has various changes and modifications without departing from the spirit and scope of the present invention, and these changes and improvements all fall in the claimed scope of the invention.Application claims protection domain is defined by appending claims and equivalent thereof.
Claims (4)
1. an aeroengine afterheat generating system, it is characterized in that: comprise vaporizer, decompressor, condenser, working medium pump and generator, described vaporizer, decompressor, condenser are connected with input end successively with working medium delivery side of pump, the input end of described generator is connected with the output terminal of decompressor, described condenser is nozzle ring, described vaporizer adopts the tubular heat exchanger of air cooling form, is arranged between casing and firing chamber.
2. aeroengine afterheat generating 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 afterheat generating 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, are provided with guide plate in described blade, described guide plate in blade by S-type for working medium passage setting.
4. aeroengine afterheat generating 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.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520187420.5U CN204552947U (en) | 2015-03-31 | 2015-03-31 | A kind of aeroengine afterheat generating system |
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| CN201520187420.5U CN204552947U (en) | 2015-03-31 | 2015-03-31 | A kind of aeroengine afterheat generating system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104763533A (en) * | 2015-03-31 | 2015-07-08 | 沈阳航空航天大学 | Aero-engine waste heat power generation system |
| CN107253528A (en) * | 2017-06-21 | 2017-10-17 | 深圳市雷凌广通技术研发有限公司 | A kind of unmanned plane with function of energy reclaiming |
| US10544705B2 (en) | 2018-03-16 | 2020-01-28 | Hamilton Sundstrand Corporation | Rankine cycle powered by bleed heat |
| CN114370336A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
-
2015
- 2015-03-31 CN CN201520187420.5U patent/CN204552947U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104763533A (en) * | 2015-03-31 | 2015-07-08 | 沈阳航空航天大学 | Aero-engine waste heat power generation system |
| CN107253528A (en) * | 2017-06-21 | 2017-10-17 | 深圳市雷凌广通技术研发有限公司 | A kind of unmanned plane with function of energy reclaiming |
| US10544705B2 (en) | 2018-03-16 | 2020-01-28 | Hamilton Sundstrand Corporation | Rankine cycle powered by bleed heat |
| CN114370336A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
| CN114370336B (en) * | 2022-01-07 | 2023-08-18 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
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