CN116771434A - Working medium driven micro turbine power generation device - Google Patents
Working medium driven micro turbine power generation device Download PDFInfo
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- CN116771434A CN116771434A CN202111451679.2A CN202111451679A CN116771434A CN 116771434 A CN116771434 A CN 116771434A CN 202111451679 A CN202111451679 A CN 202111451679A CN 116771434 A CN116771434 A CN 116771434A
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- 238000010248 power generation Methods 0.000 title claims abstract description 12
- 230000005540 biological transmission Effects 0.000 claims abstract description 21
- 230000005611 electricity Effects 0.000 claims abstract description 7
- 230000001172 regenerating effect Effects 0.000 claims description 17
- 238000011084 recovery Methods 0.000 claims description 15
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 238000004804 winding Methods 0.000 claims description 6
- 230000008929 regeneration Effects 0.000 claims description 4
- 238000011069 regeneration method Methods 0.000 claims description 4
- 230000001105 regulatory effect Effects 0.000 claims description 4
- 239000000126 substance Substances 0.000 claims 2
- 239000007921 spray Substances 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 140
- 238000001816 cooling Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
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- 239000007858 starting material Substances 0.000 description 1
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Abstract
The invention relates to a micro turbine power generation device driven by working medium, which comprises a turbine engine, wherein a gas collecting device is arranged in a casing at a cold air outlet of a diffuser of the turbine engine; a heat returning device is communicated with the tail nozzle of the turbine engine; the gas collecting device is communicated with the heat returning device through the gas guide pipe, the heat returning device exchanges heat between the high-pressure cold gas entering the heat returning device and the high-pressure hot gas in the tail spray pipe, the exchanged high-pressure hot gas is transmitted to the inner cavity of the volute of the generator through the working medium transmission pipe, and the high-pressure hot gas gathered in the volute drives the turbine of the generator to rotate, so that the generator is driven to operate. The invention adopts the high-energy working medium of the miniature gas turbine engine to drive the power turbine, thereby driving the generator to generate electricity, leading the rotation speed of the generator to get rid of the limit of the engine, leading the layout freedom degree of the generator to be higher, and being capable of designing the generator and the power turbine according to the most efficient and suitable rotation speed.
Description
Technical Field
The invention relates to the technical field of aviation power, in particular to a turbine power generation device.
Background
The miniature turbine generator is a small-sized power generation device, has the characteristics of high energy utilization rate, small environmental pollution, good economic benefit and the like, and has good development prospects in multiple fields. The existing miniature gas turbine generator mainly comprises a turbine, a gas compressor, a combustion chamber and a generator, and mainly comprises the working processes that air is compressed by the gas compressor and then heated in the combustion chamber to obtain high-temperature and high-pressure gas, and the gas enters the turbine to expand and do work so as to drive a rotor and simultaneously drive the generator to work for generating electricity.
In order to improve the overall thermal efficiency of a micro gas turbine engine, for example, when an aircraft auxiliary power device is used, a regenerator is generally used for recovering heat of turbine exhaust gas to heat gas at an outlet of a compressor, so that the shape and the size of the regenerator need to be matched with those of the compressor and a combustion chamber, and the size of the regenerator is limited due to the limitation of the overall size of the micro gas turbine engine, so that the regenerative efficiency is lower.
The generator rotating shaft in the micro turbine generator is generally required to be connected with the rotor of the turbine engine, the generator has to work at an extremely high rotating speed, the mechanical load of the generator is extremely high, the iron loss of the generator is also increased sharply due to the high rotating speed of the generator, the total length of the shaft after connection is long due to the fact that the generator is directly connected with the turbine engine shaft, flexible vibration of the shaft is easy to cause, stable work of the turbine engine is affected, the whole rotor of the micro turbine generator is overlong, the optimal design rotating speed is difficult to achieve, and the vibration control difficulty of the rotor is high.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide the working medium-driven micro turbine power generation device which can enable the rotating speed of a generator to break away from the limit of an engine and adopts the high-energy working medium of a micro gas turbine engine to drive a generator power turbine so as to drive the generator to generate power.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: a miniature turbine generating set driven by working medium comprises a turbine engine, wherein a compressor and a diffuser are coaxially arranged in a casing at a cold air inlet of the turbine engine in sequence along the cold air direction, and a gas collecting device is arranged in the casing at a cold air outlet of the diffuser; a centripetal turbine and a rectifying cone are sequentially arranged in a casing at a high-pressure hot gas outlet of a combustion chamber of the turbine engine along the hot gas direction, and a heat returning device is communicated with a tail nozzle at the hot gas outlet direction of the rectifying cone; the gas collecting device is communicated with the heat recovery device through a gas guide pipe, the gas collecting device is used for collecting part of high-pressure cold gas entering the turbine engine and guiding the high-pressure cold gas to a cold gas inlet of the heat recovery device, and the heat recovery device is used for exchanging heat between the high-pressure cold gas entering the heat recovery device and the high-pressure hot gas in the tail nozzle and transmitting the exchanged high-pressure hot gas to the generator through a working medium transmission pipe;
one end of the working medium transmission pipe is communicated with a high-pressure hot gas outlet of the heat regeneration device, the other end of the working medium transmission pipe is communicated with a volute inner cavity of the generator, a turbine of the generator is arranged in the volute, and high-pressure hot gas gathered in the volute drives the turbine of the generator to rotate, so that the generator is driven to operate.
Further, the gas collecting device comprises a gas collecting ring which is provided with an annular cavity and is U-shaped in section, at least four gas guide pipes are uniformly communicated on the same annular surface of the gas collecting ring, regulating valves are arranged on the gas guide pipes, and the gas collecting ring is communicated with a cold air inlet of the heat regenerating device through the gas guide pipes;
the U-shaped opening of the gas collecting ring is positioned on the inner ring surface of the gas collecting ring, the gas collecting ring is fixedly connected and communicated with the casing through two side walls at the U-shaped opening, so that the gas collecting ring and the casing jointly form an outer ring channel of the outlet air flow of the gas compressor, the outlet air flow channel of the gas compressor is an inner ring channel, cold air flowing in from the outer ring channel enters the heat recovery device through the gas collecting ring and the air guide pipe, and cold air flowing in from the inner ring channel enters the cold air input end of the combustion chamber.
Further, the heat regenerating device comprises an annular air inlet pipe and an annular air outlet pipe, and a plurality of inlet air collecting transverse pipes are arranged on the same annular surface of the annular air inlet pipe in a circumferential direction; a plurality of outlet gas collecting transverse pipes are arranged on the same annular surface of the annular gas outlet pipe in the circumferential direction; the inlet gas-collecting horizontal pipe is communicated with the outlet gas-collecting horizontal pipe through a heat exchange pipe row;
the gas collecting device is communicated with the annular gas inlet pipe through a gas guide pipe, the collected cold gas is led into the annular gas inlet pipe by the gas collecting device, so that the cold gas sequentially enters the inlet gas collecting transverse pipe and the heat exchange pipe row, the cold gas in the heat exchange pipe row exchanges heat with the high-pressure hot gas at the outlet end of the centripetal turbine and the rectifying cone hot gas, and the exchanged hot gas is led into the annular gas outlet pipe through the outlet gas collecting transverse pipe and is led into the working medium transmission pipe through the annular gas outlet pipe.
Further, the annular diameter of the annular air inlet pipe is smaller than that of the annular air outlet pipe, so that an annular cavity is formed between the inlet gas collecting transverse pipe and the outlet gas collecting transverse pipe, the heat exchange pipe row is arranged in the annular cavity, and the heat exchange pipe row consists of a plurality of pipelines circumferentially arranged along the annular cavity;
and the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine and the rectifying cone passes through the gaps of the heat exchange tube rows, and meanwhile, the cold gas entering from the inlet gas collecting transverse tube flows through the heat exchange tube rows from inside to outside in the annular cavity, so that efficient heat exchange is realized.
Furthermore, the heat exchange tube row is composed of at least one row of pipelines which are arranged side by side, and a row of parallel pipelines which are axially distributed are arranged in the annular cavity in an Archimedes spiral way in a gradually outwards extending way by taking the inner diameter of the annular cavity as a starting point.
Furthermore, the gas collecting device is also communicated with pipelines of an air source system and an engine starting system of the airplane through a gas-guiding pipe, a gas-guiding valve is arranged on the gas-guiding pipe, and the gas-guiding pipe is communicated with at least one gas-guiding pipe of the gas collecting device.
Further, the generator also comprises a generator shell, a generator shaft, a generator rotor and a generator stator winding, wherein the generator rotor and the generator stator winding are arranged in the generator shell, and the generator shaft and the turbine shaft of the generator turbine are coaxially arranged; the hot gas in the volute drives a turbine shaft of a turbine of the generator to rotate so as to drive the generator shaft to rotate for generating electricity.
The beneficial effects of the invention are as follows: the invention adopts a working medium transmission mode to transmit high-energy working medium generated by an energy source to a power generation device for power generation, specifically adopts a miniature gas turbine engine to generate compressed air through internal thermodynamic cycle, collects the compressed air through a high-energy working medium collecting device, recovers heat discharged after a turbine by a heat regenerating device, and transmits the heat to a power turbine volute through a working medium transmission pipe to drive the power turbine to drive the power generator to generate power. The high working medium transmission pipe is generally a high thermal resistance and low resistance working medium transmission pipe. Meanwhile, the generator is separated from the driving shaft of the engine, so that the generator can automatically select the working rotating speed, and the power turbine can be designed according to the selected rotating speed.
On one hand, the working medium based on the transmission of the working medium drives the small engine of the auxiliary power device of the airplane, so that the rotating speed of the generator is free from the limit of the engine, the layout freedom degree of the generator is higher, and the design of the generator and the power turbine can be carried out according to the most efficient and suitable rotating speed of the generator;
the heat recovery device can improve the overall heat efficiency of the engine of the auxiliary power device of the airplane, and the design of the heat recovery device can be free from the design of the shape and the size of the internal parts of the engine of the auxiliary power device of the airplane, so that higher heat exchange efficiency can be realized. Meanwhile, the heat regeneration device uses a spiral case technology and a capillary heat exchange technology: the spiral case is a hollow shell wrapped outside the centripetal turbine, and guide vanes are arranged in the spiral case and used for collecting external airflow and guiding the airflow into the centripetal turbine to push the centripetal turbine to do work.
The capillary heat exchange technology is that a cluster of axially distributed parallel tube bundles takes the inner diameter of a heat regenerator as a starting point, gradually extends outwards in an Archimedes spiral form, and an inlet at the inner side and an outlet at the outer side are connected with a gas collecting tube to form a heat regenerator module; a plurality of identical heat regenerator modules are uniformly distributed along the circumferential direction, and gas collecting pipes at the inlet and the outlet of all the heat regeneration units are respectively connected with two gas collecting rings; the inner gas collecting ring is connected with the outlets of the four gas guide pipes, compressed air flows from inside to outside in the tube bundle, and exhaust gas flows inwards along the outer diameter of the tube, so that the heat exchange area inside and outside the tube is increased in a limited space.
When the invention is applied to the auxiliary power device of the airplane, the load air compressor device in the traditional auxiliary power device of the airplane is removed, the air compressor of the auxiliary power device of the airplane is directly used for generating a compressed air source, and the compressed air source is provided for starting an aeroengine through the bleed valve of the auxiliary power device of the airplane. Meanwhile, the heat regenerator is added, and the heat regenerator can be positioned behind the engine of the auxiliary power device of the aircraft, so that the design difficulty of the heat regenerator is reduced, the heat regenerator can fully improve the heat exchange efficiency, and the auxiliary power device of the aircraft has a more flexible and compact structure.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic structural view of the turbine engine of the present invention;
FIG. 3 is a schematic structural view of the generator of the present invention;
FIG. 4 is a schematic view of the structure of the gas collecting device of the present invention;
FIG. 5 is a schematic view of a partially cut-away structure of a gas collecting apparatus of the present invention;
fig. 6 is a schematic view of an axial side structure of the regenerator of the present invention;
fig. 7 is a schematic view of a front view of a regenerator according to the present invention;
FIG. 8 is a schematic structural view of the turbine engine of example 2;
fig. 9 is a schematic view of the structure of a gas collecting apparatus in embodiment 2;
fig. 10 is a schematic view showing the arrangement of an auxiliary power unit for an aircraft in embodiment 2.
In the figure: 1. a turbine engine; 11. a compressor; 12. a diffuser; 13. a combustion chamber; 14. a centripetal turbine; 15. a rectifying cone; 16. a tail nozzle; 17. a casing; 2. a gas collecting device; 21. a gas collecting ring; 22. an air duct; 23. a regulating valve; 24. an air-introducing pipe; 25. a bleed valve; 3. a heat returning device; 31. an annular air inlet pipe; 32. an inlet gas collection transverse pipe; 33. an annular air outlet pipe; 34. an outlet gas collection transverse pipe; 35. a heat exchange tube row; 4. a working medium transmission pipe; 5. a generator; 51. a generator turbine; 52. a volute; 53. a motor housing; 54. a motor rotor; 55. stator windings; 56. a generator shaft.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
Example 1: a miniature turbine generating set driven by working medium comprises a turbine engine 1, wherein a compressor 11 and a diffuser 12 are coaxially arranged in a casing 17 at a cold air inlet of the turbine engine 1 in sequence along the cold air direction, and a gas collecting device 2 is arranged in the casing 17 at a cold air outlet of the diffuser 12; a centripetal turbine 14 and a rectifying cone 15 are sequentially arranged in a casing 17 at a high-pressure hot gas outlet of a combustion chamber 13 of the turbine engine 1 along the hot gas direction, and a heat recovery device 3 is communicated with a tail nozzle 16 at the hot gas outlet direction of the rectifying cone 15; the gas collecting device 2 is communicated with the heat regenerating device 3 through a gas guide pipe 22, the gas collecting device 2 is used for collecting part of high-pressure cold gas entering the turbine engine 1 and guiding the high-pressure cold gas to a cold gas inlet of the heat regenerating device 3, the heat regenerating device 3 is used for exchanging heat between the high-pressure cold gas entering the heat regenerating device 3 and the high-pressure hot gas in the tail nozzle 16 and transmitting the exchanged high-pressure hot gas to the generator 5 through a working medium transmission pipe 4; one end of the working medium transmission pipe 4 is communicated with a hot gas outlet of the heat recovery device 3, the other end of the working medium transmission pipe 4 is communicated with the inner cavity of the volute 52 of the generator 5, the turbine 51 of the generator 5 is arranged in the volute 52, and high-pressure hot gas gathered in the volute 52 drives the turbine 51 of the generator to rotate, so that the generator 5 is driven to operate; the generator 5 further comprises a generator shell 53, a generator shaft 56, and a generator rotor 54 and a generator stator winding 55 which are arranged in the generator shell 53, wherein the generator shaft 56 is coaxially arranged with a turbine shaft of the generator turbine 51; the hot gas in the volute 52 drives the turbine shaft of the generator turbine 51 to rotate, thereby driving the generator shaft 56 to rotate for generating electricity.
The gas collecting device 2 comprises a gas collecting ring 21 with a ring-shaped cavity and a U-shaped section, at least four gas guide pipes 22 are uniformly distributed and communicated on the same ring surface of the gas collecting ring 21, regulating valves 23 are arranged on the gas guide pipes 22, and the gas collecting ring 21 is communicated with a cold air inlet of the heat regenerating device 3 through the gas guide pipes 22; the U-shaped opening of the gas collecting ring 21 is positioned on the inner ring surface of the gas collecting ring 21, the gas collecting ring 21 is fixedly connected and communicated with the casing 17 through two side walls at the U-shaped opening, so that the gas collecting ring 21 and the casing 17 jointly form an outer ring channel of the outlet air flow of the gas compressor 11, an outlet air flow channel of the gas compressor 11 is an inner ring channel, cold air flowing in from the outer ring channel enters the heat recovery device 3 through the gas collecting ring 21 and the air guide pipe 22, and cold air flowing in from the inner ring channel enters the cold air input end of the combustion chamber 13.
The heat regenerating device 3 comprises an annular air inlet pipe 31 and an annular air outlet pipe 33, and a plurality of inlet air collecting transverse pipes 32 are arranged on the same annular surface of the annular air inlet pipe 31 in a circumferential direction; a plurality of outlet gas collecting transverse pipes 34 are arranged on the same annular surface circumference of the annular gas outlet pipe 33; the inlet gas-collecting cross pipes 32 are communicated with the outlet gas-collecting cross pipes 34 through heat exchange pipe rows 35; the gas collecting device 2 is communicated with the annular gas inlet pipe 31 through the gas guide pipe 22, the gas collecting device 2 guides the collected cold gas into the annular gas inlet pipe 31, so that the cold gas sequentially enters the inlet gas collecting transverse pipe 32 and the heat exchange pipe row 35, the cold gas in the heat exchange pipe row 35 exchanges heat with the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine 14 and the rectifying cone 15, the exchanged hot gas is guided into the annular gas outlet pipe 33 through the outlet gas collecting transverse pipe 34, and the hot gas is guided into the working medium transmission pipe 4 through the annular gas outlet pipe 33; the annular diameter of the annular air inlet pipe 31 is smaller than the annular diameter of the annular air outlet pipe 33, so that an annular cavity is formed between the inlet gas collecting transverse pipe 32 and the outlet gas collecting transverse pipe 34, the heat exchange pipe row 35 is formed by at least one row of pipelines arranged side by side, and a row of parallel pipelines which are axially distributed takes the inner diameter of the annular cavity as a starting point and is gradually and outwards arranged in the annular cavity in an Archimedes spiral manner; the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine 14 and the rectifying cone 15 passes through the gaps of the heat exchange tube row 35, and meanwhile, the cold gas entering from the inlet gas collecting transverse tube 32 flows through the heat exchange tube row 35 from inside to outside in the annular cavity, so that efficient heat exchange is realized.
The compressor 11 of the turbine engine 1 sucks in the incoming cold air and compresses the incoming cold air, the compressed cold air is divided into two at the output end of the compressor 11, one air flow enters the heat recovery device 3 from the gas collecting ring 21, the other compressed cold air flow enters the combustion chamber 13 of the turbine engine and is mixed with fuel to burn to form high-temperature and high-pressure fuel gas, the fuel gas expands and works in the centripetal turbine 14, the high-temperature tail gas after the centripetal turbine 14 flows to the heat recovery device 3 through the rectifying cone 15 to exchange heat with the air in the heat exchange tube row 35 of the heat recovery device 3, the air flow enters the heat exchange tube row 35 through the inlet gas collecting transverse tube 32 connected with the annular air inlet tube 31, and the hot fuel gas flows between gaps of the heat exchange tube 35 to exchange heat with the compressed air in the heat exchange tube row 25.
The hot air after heat exchange passes through the outlet gas collection transverse pipe 34 and reaches the inlet of the working medium transmission pipe 4 through the annular gas outlet pipe 33 of the hot air outlet. The compressed air with high temperature and high pressure enters the volute 52 of the generator 5 from the working medium transmission pipe 4, the volute 52 pushes the air with high temperature and high pressure into the generator turbine 51, the generator turbine 51 converts expansion work of the air with high temperature and high pressure into shaft work, and the generator rotor 54 is driven to operate through the generator shaft 56. The generator rotor 54 interacts with stator windings 55 to generate electricity.
Example 2: as shown in fig. 8 to 10, the same as in example 1 is different in that: the air collecting device 2 is also communicated with pipelines of an air source system and an engine starting system of the airplane through an air bleed pipe 24, an air bleed valve 25 is arranged on the air bleed pipe 24, and the air bleed pipe 24 is communicated with at least one air guide pipe 22 of the air collecting device 2.
In this example, the turbine engine is a single rotor aircraft auxiliary power unit engine. The air collected by the air collecting ring 21 is transmitted to the annular air inlet pipe 31 of the heat recovery device 3 through the air guide pipe 22, wherein the air in one air guide pipe 22 is divided into two parts, and the other compressed air is used for providing an air source for the starting of the main engine of the aircraft through the air guide pipe 24 and the air guide valve 25 of the auxiliary power device of the aircraft.
The aircraft auxiliary power unit 100 described in this example refers to a main power unit on an aircraft, such as a small auxiliary power unit that can independently output compressed air or supply power outside an engine. The function of the auxiliary power unit is to provide power and compressed air (and some only power) independently to the aircraft, and a small number of auxiliary power units may provide additional thrust to the aircraft. The engine of the auxiliary power unit of the aircraft is positioned at the tail part of the aircraft body, is generally arranged in the tail cone at the last section of the aircraft body, is provided with an air inlet at the upper part of the aircraft body and near the vertical tail, and exhaust is directly discharged from an exhaust port at the rear end of the tail cone, as shown in fig. 10. The front end of the engine of the auxiliary power device of the airplane is provided with a load compressor besides a normal compressor, and the load compressor is used for conveying high-temperature compressed air to an air conditioning assembly at the front part of the airplane body so as to ensure that an air conditioning system of the airplane cabin works and simultaneously drive a generator, and can send out 115V three-phase current to an airplane power grid.
The aircraft auxiliary power unit has its own individual electric starter powered by a separate battery with a separate additional gearbox, lubrication system, cooling system and fire protection. The engine of the auxiliary power device of the airplane mainly comprises an air inlet device, a compressor, a load compressor on the same shaft with the compressor, a combustion chamber, a turbine, an accessory gearbox, a lubricating oil pump, a fuel pump and a cooling fan, wherein the cooling fan is used for providing cooling air, a generator and an exhaust device for the generator and the lubricating oil cooler of the auxiliary power device of the airplane.
The main working process of the auxiliary power device of the aircraft is that air enters a compressor of the auxiliary power device of the aircraft from an air inlet valve of the auxiliary power device of the aircraft through an air inlet pipeline, is heated in a combustion chamber after being compressed by the compressor to obtain high-temperature and high-pressure gas, the gas enters a turbine to expand and do work so as to drive the compressor and a load compressor of the auxiliary power device of the aircraft, meanwhile, an accessory gearbox is driven, the gearbox drives accessories in the gearbox after reducing the torque of a high rotating speed of a power part, for example, a generator is driven to work for generating electricity, a cooling fan, a lubricating oil pump, a fuel pump and the like, and finally, the air enters an exhaust device to be discharged into the atmosphere.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (7)
1. The miniature turbine generating device driven by working media is characterized by comprising a turbine engine (1), wherein a compressor (11) and a diffuser (12) are coaxially arranged in a casing at a cold air inlet of the turbine engine (1) in sequence along the cold air direction, and a gas collecting device (2) is arranged in a casing (17) at a cold air outlet of the diffuser (12); a centripetal turbine (14) and a rectifying cone (15) are sequentially arranged in a casing (17) at a high-pressure hot gas outlet of a combustion chamber (13) of the turbine engine (1) along the hot gas direction, and a heat recovery device (3) is communicated with a tail nozzle (16) at the hot gas outlet direction of the rectifying cone (15); the gas collecting device (2) is communicated with the heat regenerating device (3) through a gas guide pipe (22), the gas collecting device (2) is used for collecting part of high-pressure cold gas entering the turbine engine (1) and guiding the high-pressure cold gas to a cold gas inlet of the heat regenerating device (3), the heat regenerating device (3) is used for exchanging heat between the high-pressure cold gas entering the heat regenerating device (3) and the high-pressure hot gas in the tail nozzle (16) and transmitting the exchanged high-pressure hot gas to the generator (5) through a working medium transmission pipe (4);
one end of the working medium transmission pipe (4) is communicated with a high-pressure hot gas outlet of the heat regenerating device (3), the other end of the working medium transmission pipe (4) is communicated with an inner cavity of a volute (52) of the generator (5), a turbine (51) of the generator (5) is arranged in the volute (52), and high-pressure hot gas gathered in the volute (52) drives the generator turbine (51) to rotate, so that the generator (5) is driven to operate.
2. The working medium driven micro turbine generating device according to claim 1, wherein the gas collecting device (2) comprises a gas collecting ring (21) with a ring-shaped cavity and a U-shaped section, at least four gas guide pipes (22) are uniformly communicated on the same ring surface of the gas collecting ring (21), regulating valves (23) are arranged on the gas guide pipes (22), and the gas collecting ring (21) is communicated with a cold air inlet of the heat regenerating device (3) through the gas guide pipes (22);
the U-shaped opening of the gas collecting ring (21) is positioned on the inner ring surface of the gas collecting ring (21), the gas collecting ring (21) is fixedly connected and communicated with the casing (17) through two side walls at the U-shaped opening, so that the gas collecting ring (21) and the casing (17) jointly form an outer ring channel of the outlet airflow of the compressor (11), an outlet airflow channel of the compressor (11) is an inner ring channel, cold air flowing in from the outer ring channel enters the heat regenerating device (3) through the gas collecting ring (21) and the air duct (22), and cold air flowing in from the inner ring channel enters the cold air input end of the combustion chamber (13).
3. The working medium driven micro turbine power generation device according to claim 1, wherein the heat regeneration device (3) comprises an annular air inlet pipe (31) and an annular air outlet pipe (33), and a plurality of inlet air collection transverse pipes (32) are arranged on the same annular surface of the annular air inlet pipe (31) in a circumferential direction; a plurality of outlet gas collecting transverse pipes (34) are arranged on the same annular surface of the annular gas outlet pipe (33); the inlet gas-collecting horizontal pipe (32) is communicated with the outlet gas-collecting horizontal pipe (34) through a heat exchange pipe row (35);
the gas collecting device (2) is communicated with the annular gas inlet pipe (31) through the gas guide pipe (22), the gas collecting device (2) guides the collected cold gas into the annular gas inlet pipe (31), so that the cold gas in the inlet gas collecting transverse pipe (32) and the heat exchange pipe row (35) sequentially enter the heat exchange pipe row (35), the cold gas in the heat exchange pipe row (35) exchanges heat with the high-pressure hot gas at the hot gas outlet end of the centripetal turbine (14) and the rectifying cone (15), and the exchanged hot gas is guided into the annular gas outlet pipe (33) through the outlet gas collecting transverse pipe (34) and is guided into the working medium transmission pipe (4) through the annular gas outlet pipe (33).
4. A working medium driven micro turbine power generation device according to claim 3, wherein the annular diameter of the annular air inlet pipe (31) is smaller than the annular diameter of the annular air outlet pipe (33), so that an annular cavity is formed between the inlet gas collecting transverse pipe (32) and the outlet gas collecting transverse pipe (34), the heat exchange pipe row (35) is arranged in the annular cavity, and the heat exchange pipe row (35) is composed of a plurality of pipelines circumferentially arranged along the annular cavity;
the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine (14) and the rectifying cone (15) passes through the gaps of the heat exchange tube rows (35), and meanwhile, the high-pressure cold gas entering from the inlet gas collecting transverse tube (32) flows through the annular cavity from inside to outside along the heat exchange tube rows (35) to realize efficient heat exchange.
5. The working-medium-driven microturbine power generation device of claim 4, wherein the heat exchange tube row (35) is composed of at least one row of tubes arranged side by side, and a row of axially-distributed parallel tubes is arranged in the annular cavity in an archimedes spiral form by gradually extending outwards from the inner diameter of the annular cavity.
6. A working substance driven microturbine power generation device as claimed in claim 1, characterized in that the gas collection device (2) is also in communication with the air supply system of the aircraft and the conduits of the engine starting system via bleed air pipes (24), a bleed air valve (25) being provided on the bleed air pipes (24), the bleed air pipes (24) being arranged in communication with at least one air duct (22) of the gas collection device (2).
7. A working substance driven micro turbine power plant according to any of claims 1-6, characterized in that the generator (5) further comprises a generator housing (53), a generator shaft (56) and a generator rotor (54) and a generator stator winding (55) arranged in the generator housing (53), the generator shaft (56) being arranged coaxially with the turbine shaft of the generator turbine (51); the hot gas in the volute (52) drives a turbine shaft of the generator turbine (51) to rotate so as to drive a generator shaft (56) to rotate for generating electricity.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111451679.2A CN116771434A (en) | 2021-12-01 | 2021-12-01 | Working medium driven micro turbine power generation device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111451679.2A CN116771434A (en) | 2021-12-01 | 2021-12-01 | Working medium driven micro turbine power generation device |
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| CN202111451679.2A Pending CN116771434A (en) | 2021-12-01 | 2021-12-01 | Working medium driven micro turbine power generation device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5497615A (en) * | 1994-03-21 | 1996-03-12 | Noe; James C. | Gas turbine generator set |
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