CN109139264A - A kind of micro turbine generator for applying annular regenerator - Google Patents
A kind of micro turbine generator for applying annular regenerator Download PDFInfo
- Publication number
- CN109139264A CN109139264A CN201710508180.8A CN201710508180A CN109139264A CN 109139264 A CN109139264 A CN 109139264A CN 201710508180 A CN201710508180 A CN 201710508180A CN 109139264 A CN109139264 A CN 109139264A
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- China
- Prior art keywords
- annular
- regenerator
- power head
- speed motor
- turbine generator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 25
- 238000009413 insulation Methods 0.000 claims abstract description 12
- 230000008878 coupling Effects 0.000 claims abstract description 10
- 238000010168 coupling process Methods 0.000 claims abstract description 10
- 238000005859 coupling reaction Methods 0.000 claims abstract description 10
- 230000006835 compression Effects 0.000 claims description 10
- 238000007906 compression Methods 0.000 claims description 10
- 238000010276 construction Methods 0.000 abstract description 2
- 230000007613 environmental effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001914 calming effect Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Classifications
-
- 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
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- 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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- 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
Abstract
The present invention relates to a kind of micro turbine generators for applying annular regenerator.Including annular air inlet air filter 1, air inlet housing 2, high-speed motor 3, airscoop shroud 4, shaft coupling 5, power head 6, thermal insulation board 7, annular regenerator 8, atomizer 9, combustion chamber 10, heat-insulated wall 11, body fuselage 12；Power head 6 is arranged in the hollow cavity of annular regenerator 8；Annular air inlet air filter 1 is arranged in 3 front end of high-speed motor, and combustion chamber 10 is arranged in 6 rear end of power head；Combustion chamber 10 is arranged in heat-insulated 11 inside cavity of wall；Power head 6, annular regenerator 8, combustion chamber 10, heat-insulated wall 11 are arranged in body fuselage 12.The present invention has fully and rationally used the performance and design feature of annular regenerator and micro turbine generator, and arragement construction is compact, have many advantages, such as small in size, light-weight, low emission, energy-saving and environmental protection, and have very high efficiency of heating- utilization.
Description
Technical field
The invention belongs to micro turbine generator technical fields, and in particular to a kind of miniature turbine for applying annular regenerator
Generator.
Background technique
Micro turbine generator is a kind of small distributed energy system and power generator, has that energy utilization rate is high, ring
The features such as border pollution is small, good in economic efficiency, has good development prospect, and the status for alleviating China's energy shortage has pole
Its important meaning.
Since miniature turbine generating equipment has many advantages, such as, major energy company's research hotspot is had become at present how
Micro turbine generator volume and weight is reduced, improves heat utilization efficiency, it would be highly desirable to develop.
Summary of the invention
The present invention is directed to solve at least to a certain extent it is above-mentioned in the related technology the technical issues of one of.
For this purpose, the object of the present invention is to provide a kind of micro turbine generator for applying annular regenerator, including high speed electricity
Machine, airscoop shroud, power head, thermal insulation board, annular regenerator, atomizer, combustion chamber, heat-insulated wall, body fuselage, the annular backheat
Device is that hollow cavity is formed by regenerator inner wall, and regenerator is arranged on the regenerator inner wall and exchanges blade, hollow
Power head is arranged in cavity.
According to embodiments of the present invention, annular air inlet air filter is arranged in the high-speed motor front end, in high-speed motor and power head
Between location arrangements airscoop shroud, the centre rotational axis front end of power head connects high-speed motor with shaft coupling, and shaft coupling is arranged in
Inside airscoop shroud；Annular air inlet air filter is fixed on air inlet housing, and high-speed motor, airscoop shroud are arranged in air inlet housing.
According to embodiments of the present invention, the combustion chamber placement is in power head rear end；Combustion chamber placement is in heat-insulated wall cavity
Portion；Power head, annular regenerator, combustion chamber, heat-insulated wall are arranged in body fuselage；Atomizer is arranged in body fuselage and burning
Position between room.
According to embodiments of the present invention, the location arrangements thermal insulation board between annular regenerator and power head.
According to embodiments of the present invention, the location arrangements thermal insulation board between power head front end and combustion chamber.
According to embodiments of the present invention, the annular air inlet air filter includes annular air filter filter core, in the annular air filter filter core
Center be equipped with annular air filter exhaust pipe.
According to embodiments of the present invention, the high-speed motor includes high-speed motor shell, is set in the inside of high-speed motor shell
Motor magnetic axis is set, electric motor fan is set in the front end of motor magnetic axis, wind-guiding is set between high-speed motor shell and motor magnetic axis
Grid.
According to embodiments of the present invention, the power head includes turbine, and the turbine front end is compression impellor, the leaf of calming the anger
Compressor airflow fence is arranged in the outer ring of wheel.
According to embodiments of the present invention, the body fuselage includes machine shell outer wall, machine shell inner wall, before body fuselage
End is equipped with the exhaust pipe on body fuselage.
Backheat principle explanation of the invention.
High-speed motor part: fresh cold air enters from annular air filter filter core front end, is entered by the air guiding grid of high-speed motor
Inside high-speed motor；The high speed rotation of electric motor fan makes air quick fluxion strap in the air flue of high-speed motor walk high-speed motor fortune
It changes the line of production raw heat, exhaust gas is discharged to engine body exterior finally by the exhaust pipe among annular air inlet air filter.
Miniature gas turbine part: fresh cold air enters from annular air filter filter core front end, passes through the grid on airscoop shroud
Compression impellor is entered, compression impellor high speed rotation from the compressor airflow fence indentation power head on power head and returns air
Gas chamber between hot device inner wall enters in regenerator heat-exchanger fin and after burning using the air inlet of regenerator inner wall front end
High temperature air carry out heat exchange, then enter combustion chamber by the aperture on burning chamber shell and fuel that atomizer sprays into
Row burning, the high-temperature gas after burning push turbine rotation acting, carry out subsequently into the air before annular regenerator and burning
Heat exchange is discharged to engine body exterior finally by the exhaust pipe on body fuselage.
The beneficial effects of the present invention are: the cavity hollow using annular regenerator, by micro turbine generator section components
Reasonably it is arranged in inside cavity.Performance and the structure for having fully and rationally used annular regenerator and micro turbine generator are special
Point, arragement construction is compact, have many advantages, such as small in size, light-weight, low emission, energy-saving and environmental protection, and have very high heat utilization
Efficiency.
Detailed description of the invention
Fig. 1 is a kind of micro turbine generator structural plan for applying annular regenerator.
Fig. 2 is that a kind of micro turbine generator air-flow of annular regenerator of application moves towards schematic diagram.
Fig. 3 is annular air inlet air filter structural schematic diagram, and wherein Fig. 3 (a) is side view, and Fig. 3 (b) is front view.
Fig. 4 is high-speed motor structural schematic diagram, and wherein Fig. 4 (a) is front view, and Fig. 4 (b) is left view.
Fig. 5 is power head structure schematic diagram.
Fig. 6 is annular regenerator structure schematic diagram.
Fig. 7 is body fuselage structural schematic diagram.
In figure: 1- annular air inlet air filter；2- air inlet housing；3- high-speed motor；4- airscoop shroud；5- shaft coupling；6- power head；
7- thermal insulation board 8- regenerator；9- atomizer；The combustion chamber 10-；The heat-insulated wall of 11-；12- body fuselage；13- annular air filter filter core；
14- annular air filter exhaust pipe；15- high-speed motor shell；16- air guiding grid；17- motor magnetic axis；18- electric motor fan；19- calms the anger leaf
Wheel；20- compressor airflow fence；21- turbine；22- regenerator heat-exchanger fin；23- regenerator inner wall；On 24- body fuselage
Exhaust pipe；25- body fuselage outer wall；26- body fuselage inner wall.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings.Below with reference to
The embodiment of attached drawing description is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.
As shown in Figure 1, a kind of micro turbine generator for applying annular regenerator, including annular air inlet air filter 1, airscoop shroud
Shell 2, high-speed motor 3, airscoop shroud 4, shaft coupling 5, power head 6, thermal insulation board 7, annular regenerator 8, atomizer 9, combustion chamber 10, every
Hot wall 11, body fuselage 12；Power head 6 is arranged in the hollow cavity of annular regenerator 8.
Annular air inlet air filter 1, the location arrangements air inlet between high-speed motor 3 and power head 6 are arranged in 3 front end of high-speed motor
The centre rotational axis front end of cover 4, power head 6 connects high-speed motor 3 with shaft coupling 5, and shaft coupling 5 is arranged in inside airscoop shroud 4；Ring
Shape air inlet air filter 1 is fixed on air inlet housing 2, and high-speed motor 3, airscoop shroud 4 are arranged in air inlet housing 2.
Combustion chamber 10 is arranged in 6 rear end of power head；Combustion chamber 10 is arranged in heat-insulated 11 inside cavity of wall；Power head 6, ring
Shape regenerator 8, combustion chamber 10, heat-insulated wall 11 are arranged in body fuselage 12；Atomizer 9 is arranged in body fuselage 12 and combustion chamber
Position between 10；Location arrangements thermal insulation board 7 between annular regenerator 8 and power head 6；In 6 front end of power head and burning
Location arrangements thermal insulation board 7 between room 10.
As shown in figure 3, annular air inlet air filter 1 includes annular air filter filter core 13, at the center of the annular air filter filter core 13
Equipped with annular air filter exhaust pipe 14.
As shown in figure 4, high-speed motor 3 includes high-speed motor shell 15, motor is arranged in intermediate in high-speed motor shell 15
Magnetic axis 17 is arranged electric motor fan 18 in the front end of motor magnetic axis 17, is arranged between high-speed motor shell 15 and motor magnetic axis 17
Air guiding grid 16.
As shown in figure 5, power head 6 includes turbine 21,21 front end of turbine is compression impellor 19, the compression impellor 19
Outer ring be arranged compressor airflow fence 20.
As shown in fig. 6, the body fuselage 12 includes machine shell outer wall 25, machine shell inner wall 26, in body fuselage 12
Front end is equipped with the exhaust pipe 24 on body fuselage.
As shown in fig. 7, body fuselage 12 includes machine shell outer wall 25, machine shell inner wall 26, in the front end of body fuselage 12
Equipped with the exhaust pipe 24 on body fuselage.
Annular air inlet air filter 1: high-speed motor 3 and miniature gas turbine air inlet are via annular air inlet air filter 1, annular air inlet
Air filter 1 is filtered dust, gravel, moisture and the various impurity in air, guarantees to enter the pure of internal body air, drop
The abrasion of low body.
Air inlet housing 2: it is used for stationary annular air inlet air filter 1, and guarantees that filtered air is isolated with outside air.
High-speed motor 3: when miniature gas turbine starts, high-speed motor 3 is rotated as powered belt turn dynamic component, makes air
Flow at high speed；When miniature gas turbine does work, it is defeated that the kinetic energy that high-speed motor sends miniature gas turbine is converted into electric energy
Out.
Airscoop shroud 4: for connecting the mechanical fastener between high-speed motor and power head, it is provided with grid above, makes gas
Enter compression impellor 19.
Shaft coupling 5: the central axis rotated for connecting high-speed motor 3 and power head 6.
Power head 6: mechanical kinetic energy rotation acting is converted by the thermal energy after burning.
Thermal insulation board 7: unburned air is isolated with the high temperature air after burning.
Annular regenerator 8: the high-temperature gas after making unburned air and burning carries out heat exchange, improves the thermal efficiency.
Atomizer 9: being made of oil atomizing device and igniter, makes fuel atomization and ignition.
Combustion chamber 10: being mixed and burned fuel inside it with air, generates energy.
Heat-insulated wall 11: the gas before burning and the high-temperature gas after burning are isolated, central structure is exhaust pipe, with turbine
The connection of 21 gas outlets, the tail gas after burning is exported.
Body fuselage 12: inside it by the airframe components such as regenerator package, and guarantee internal body and engine body exterior temperature
Degree isolation, design have air passage structure, tail gas are exported engine body exterior.
As shown in Fig. 2, high-speed motor part: fresh cold air enters from annular 13 front end of air inlet air filter filter core, by high speed
The air guiding grid 16 of motor 3 enters inside high-speed motor.The high speed rotation of high-speed motor fan 18 makes air in the gas of high-speed motor 3
Quick fluxion strap walks the heat that high-speed motor operating generates in road, and exhaust gas is discharged to machine finally by annular air filter exhaust pipe 14
Outside body.
Miniature gas turbine part: fresh cold air enters from annular 13 front end of air inlet air filter filter core, passes through airscoop shroud 4
On grid enter compression impellor 19,19 high speed rotation of compression impellor, by air from the compressor airflow fence 20 on power head 6
The gas chamber being pressed between power head 6 and regenerator inner wall 23, the air inlet using 23 front end of regenerator inner wall enter regenerator
Heat exchange is carried out with the high temperature air after burning in heat-exchanger fin 22, is then entered by the aperture on 10 shell of combustion chamber
The fuel that combustion chamber 10 is sprayed with atomizer 9 burns, and high-temperature gas after burning pushes the rotation acting of turbine 21, then into
Enter annular regenerator 8 and carry out heat exchange with the air before burning, is discharged to outside body finally by the exhaust pipe 24 on body fuselage
Portion.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
"front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside", " axial direction ", " radial direction ", " circumferential direction " etc.；
The orientation or positional relationship of instruction is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of the description present invention and letter
Change description, rather than the device or element of indication or suggestion meaning must have a particular orientation, with specific orientation construct and
Operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include at least one this feature.In the description of the present invention, the meaning of " plurality " is at least two, such as two, three
It is a etc., unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be mechanical connect
It connects, is also possible to be electrically connected or can communicate each other；It can be directly connected, can also indirectly connected through an intermediary, it can be with
It is the interaction relationship of the connection or two elements inside two elements, unless otherwise restricted clearly.For this field
For those of ordinary skill, the specific meanings of the above terms in the present invention can be understood according to specific conditions.
In the present invention unless specifically defined or limited otherwise, fisrt feature in the second feature " on " or " down " can be with
It is that the first and second features directly contact or the first and second features pass through intermediary mediate contact.Moreover, fisrt feature exists
Second feature " on ", " top " and " above " can be fisrt feature and be directly above or diagonally above the second feature, or only table
Show that first feature horizontal height is higher than second feature.Fisrt feature can be under the second feature " below ", " below " and " below "
Fisrt feature is directly under or diagonally below the second feature, or is merely representative of first feature horizontal height less than second feature.
In the description of this specification, reference term " embodiment ", " specific embodiment ", " example " or " specific example " etc.
Description mean particular features, structures, materials, or characteristics described in conjunction with this embodiment or example be contained in it is of the invention extremely
In few one embodiment or example.In the present specification, schematic expression of the above terms are necessarily directed to identical
Embodiment or example.Moreover, particular features, structures, materials, or characteristics described can in any one or more embodiments or
It can be combined in any suitable manner in example.In addition, without conflicting with each other, those skilled in the art can illustrate this
The feature of different embodiments or examples and different embodiments or examples described in book is combined.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, modifies, replacement and variant.
Claims (9)
1. a kind of micro turbine generator for applying annular regenerator, including high-speed motor (3), airscoop shroud (4), power head (6),
Thermal insulation board (7), annular regenerator (8), atomizer (9), combustion chamber (10), heat-insulated wall (11), body fuselage (12), feature exists
It is that hollow cavity is formed by regenerator inner wall (23) in the annular regenerator (8), is set on the regenerator inner wall (23)
Regenerator exchange blade (22) is set, arranges power head (6) in hollow cavity.
2. a kind of micro turbine generator for applying annular regenerator according to claim 1, it is characterised in that the height
Annular air inlet air filter (1), the location arrangements airscoop shroud between high-speed motor (3) and power head (6) are arranged in speed motor (3) front end
(4), the centre rotational axis front end of power head (6) connects high-speed motor (3) with shaft coupling (5), and shaft coupling (5) is arranged in airscoop shroud
(4) internal；Annular air inlet air filter (1) is fixed on air inlet housing (2), and high-speed motor (3), airscoop shroud (4) are arranged in airscoop shroud
In shell (2).
3. a kind of micro turbine generator for applying annular regenerator according to claim 1, it is characterised in that the combustion
It burns room (10) and is arranged in power head (6) rear end；Combustion chamber (10) is arranged in heat-insulated wall (11) inside cavity；Power head (6), annular
Regenerator (8), combustion chamber (10), heat-insulated wall (11) are arranged in body fuselage (12)；Atomizer (9) is arranged in body fuselage
(12) position between combustion chamber (10).
4. a kind of micro turbine generator for applying annular regenerator according to claim 3, it is characterised in that in annular
Location arrangements thermal insulation board (7) between regenerator (8) and power head (6).
5. a kind of micro turbine generator for applying annular regenerator according to claim 3, it is characterised in that in power
Location arrangements thermal insulation board (7) between head (6) front end and combustion chamber (10).
6. a kind of micro turbine generator for applying annular regenerator according to claim 2, it is characterised in that the ring
Shape air inlet air filter (1) includes annular air filter filter core (13), is equipped with annular air filter row at the center of the annular air filter filter core (13)
Tracheae (14).
7. a kind of micro turbine generator for applying annular regenerator according to claim 1, it is characterised in that the height
Speed motor (3) includes high-speed motor shell (15), motor magnetic axis (17) is arranged in the inside of high-speed motor shell (15), in motor
Electric motor fan (18) are arranged in the front end of magnetic axis (17), and air guiding grid is arranged between high-speed motor shell (15) and motor magnetic axis (17)
(16)。
8. a kind of micro turbine generator for applying annular regenerator according to claim 1, it is characterised in that described dynamic
Power head (6) includes turbine (21), and turbine (21) front end is compression impellor (19), and the outer ring of the compression impellor (19) is arranged
Compressor airflow fence (20).
9. a kind of micro turbine generator for applying annular regenerator according to claim 1, it is characterised in that the machine
Body case (12) includes machine shell outer wall (25), machine shell inner wall (26), is equipped with body fuselage in the front end of body fuselage (12)
On exhaust pipe (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710508180.8A CN109139264A (en) | 2017-06-28 | 2017-06-28 | A kind of micro turbine generator for applying annular regenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710508180.8A CN109139264A (en) | 2017-06-28 | 2017-06-28 | A kind of micro turbine generator for applying annular regenerator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109139264A true CN109139264A (en) | 2019-01-04 |
Family
ID=64803052
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710508180.8A Pending CN109139264A (en) | 2017-06-28 | 2017-06-28 | A kind of micro turbine generator for applying annular regenerator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109139264A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021144002A1 (en) * | 2020-01-13 | 2021-07-22 | Bladon Jets Holdings Limited | Monolithic rotor and compressor wheel |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5497615A (en) * | 1994-03-21 | 1996-03-12 | Noe; James C. | Gas turbine generator set |
| CN1196107A (en) * | 1995-09-08 | 1998-10-14 | 本田技研工业株式会社 | Gas-turbine engine |
| CN1277343A (en) * | 1999-06-11 | 2000-12-20 | 联合讯号公司 | Generating system for small turbomachine |
| US6308513B1 (en) * | 1999-04-23 | 2001-10-30 | Takefumi Hatanaka | Turbine and gas turbine |
| US20020195821A1 (en) * | 2000-12-19 | 2002-12-26 | Joel Wacknov | Microturbine/capacitor power distribution system |
| US20040118101A1 (en) * | 2002-12-23 | 2004-06-24 | Dewis David W. | Recuperator configuration |
| US20050089392A1 (en) * | 2003-10-28 | 2005-04-28 | Daniel Lubell | Rotor and bearing system for a turbomachine |
| CN102900533A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Micro gas turbine generating device |
| CN104246177A (en) * | 2012-02-21 | 2014-12-24 | 巴布科克·博西格·施泰因米勒有限公司 | Micro gas turbine system with a pipe-shaped recuperator |
| CN207080290U (en) * | 2017-06-28 | 2018-03-09 | 武汉迈科特微型涡轮机有限责任公司 | A kind of micro turbine generator for applying annular regenerator |
-
2017
- 2017-06-28 CN CN201710508180.8A patent/CN109139264A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5497615A (en) * | 1994-03-21 | 1996-03-12 | Noe; James C. | Gas turbine generator set |
| CN1196107A (en) * | 1995-09-08 | 1998-10-14 | 本田技研工业株式会社 | Gas-turbine engine |
| US6308513B1 (en) * | 1999-04-23 | 2001-10-30 | Takefumi Hatanaka | Turbine and gas turbine |
| CN1277343A (en) * | 1999-06-11 | 2000-12-20 | 联合讯号公司 | Generating system for small turbomachine |
| US20020195821A1 (en) * | 2000-12-19 | 2002-12-26 | Joel Wacknov | Microturbine/capacitor power distribution system |
| US20040118101A1 (en) * | 2002-12-23 | 2004-06-24 | Dewis David W. | Recuperator configuration |
| US20050089392A1 (en) * | 2003-10-28 | 2005-04-28 | Daniel Lubell | Rotor and bearing system for a turbomachine |
| CN104246177A (en) * | 2012-02-21 | 2014-12-24 | 巴布科克·博西格·施泰因米勒有限公司 | Micro gas turbine system with a pipe-shaped recuperator |
| CN102900533A (en) * | 2012-10-24 | 2013-01-30 | 哈尔滨东安发动机（集团）有限公司 | Micro gas turbine generating device |
| CN207080290U (en) * | 2017-06-28 | 2018-03-09 | 武汉迈科特微型涡轮机有限责任公司 | A kind of micro turbine generator for applying annular regenerator |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021144002A1 (en) * | 2020-01-13 | 2021-07-22 | Bladon Jets Holdings Limited | Monolithic rotor and compressor wheel |
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