CN108915868A - gas turbine - Google Patents
gas turbine Download PDFInfo
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- CN108915868A CN108915868A CN201811074861.9A CN201811074861A CN108915868A CN 108915868 A CN108915868 A CN 108915868A CN 201811074861 A CN201811074861 A CN 201811074861A CN 108915868 A CN108915868 A CN 108915868A
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- gas turbine
- shaft
- motor
- turbine
- stator
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 34
- 230000006835 compression Effects 0.000 claims abstract description 23
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- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 4
- 239000012530 fluid Substances 0.000 claims description 7
- 238000004804 winding Methods 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 5
- 230000008878 coupling Effects 0.000 claims description 3
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- 238000010248 power generation Methods 0.000 claims description 3
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- 239000000446 fuel Substances 0.000 description 14
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- 238000012423 maintenance Methods 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 5
- 238000001816 cooling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000001050 lubricating effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 3
- 239000010687 lubricating oil Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
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- 230000001681 protective effect Effects 0.000 description 2
- 229910000976 Electrical steel Inorganic materials 0.000 description 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
- H02K5/163—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields radially supporting the rotary shaft at only one end of the rotor
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/02—Arrangements for cooling or ventilating by ambient air flowing through the machine
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/02—Arrangements for cooling or ventilating by ambient air flowing through the machine
- H02K9/04—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium
- H02K9/06—Arrangements for cooling or ventilating by ambient air flowing through the machine having means for generating a flow of cooling medium with fans or impellers driven by the machine shaft
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K2213/00—Specific aspects, not otherwise provided for and not covered by codes H02K2201/00 - H02K2211/00
- H02K2213/03—Machines characterised by numerical values, ranges, mathematical expressions or similar information
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of gas turbine includes compressor, turbine and combustion chamber.Compressor includes compression impellor and first rotating shaft, and turbine includes turbine wheel and the second shaft.Second shaft is fixedly connected with first rotating shaft to be integrally formed, and the main shaft of gas turbine is formed.Combustion chamber is located at the downstream of compressor and is located at the upstream of turbine.The gas turbine further includes inspiring motor, and the machine shaft of the inspiration motor is connected on main shaft by rod-shaped attachment device.Furthermore the gas turbine operation high reliablity can also prevent the component of gas turbine from damaging because running fluctuation, improve safety.
Description
Technical field
The present invention relates to power device fields, and specifically, the invention discloses a kind of gas turbines.
Background technique
Gas turbine is a kind of internal combustion type motive power machine device.The operation logic of gas turbine is, by fuel combustion products
As working medium, it is made to be continuously flowed into the impeller of gas turbine, impeller rotation, to convert machine for the chemical energy of fuel
Tool energy.
Currently used gas turbine can be divided into heavy duty gas turbine, lightweight gas turbine and micro- according to structure type
Type gas turbine etc., and the gas turbine of these types can be applied to a variety of occasions, such as start as aero-engine, ship
It machine or applies in generating set, etc..The advantages of gas turbine, is, can be easy to carry out the collection of more gas turbines
At dilatation, it is suitable for pluralities of fuel, specific fuel consumption is low, and low noise in operational process, discharge is low, with small vibration, maintenance rate is low, and
And remote control and diagnosis, etc. can be carried out to gas turbine.
Fig. 1 shows the principle schematic diagram of conventional gas turbine.Wherein, the major part of gas turbine 1 includes
Compressor 10, turbine 20 and combustion chamber 30 are connected between the compression impellor of compressor 10 and the turbine wheel of turbine 20 by axis 40
It connects.In the process of running, compressor 10 is started by external power source first, thus compressor 10 is inhaled from the atmosphere of surrounding
Enter air, and compresses it.Compressed air is transported in combustion chamber 30.In this way, in compressed air and penetrating combustion chamber
Fuel occur combustion reaction, generate high-temperature fuel gas.High-temperature fuel gas flows into turbine 20, and expansion work, pushes turbine wheel
Rotation, turbine wheel then pass through axis 40 and compression impellor are driven to rotate together.High-temperature fuel gas after burning is driving the same of compressor
When, there are also output mechanical work of the extra energy as gas turbine.The mechanical work can be used to generate electricity, as aircraft or ship
Propulsive force etc..
A kind of example for starting the external power supply of gas turbine is external compressed air source, and the compressed air source is to pressure
Mechanism of qi 10 provides compressed air, blows compression impellor rotation.But, the application of this scheme using compressed air source by
To limitation, need to provide compressed air source in its vicinity.
Another way is to be started as shown in Figure 1 using motor 50 is inspired.The inspiration motor 50
Output shaft is connected via speed-changing gear box with compression impellor.When starting gas turbine, at the beginning of inspiring motor 50 to drive compression impellor
It rotates with beginning, outside air is sucked in compressor 10, compressor 10 generates compressed air.But, for inspiring motor mode
Driving source, used inspiration motor can occupy biggish space, and inspire the gear drive between motor and compressor
The efficiency of mechanism is lower, and is prone to wear, so that maintenance cost is relatively high.
In addition, somebody considers that input shaft direct phase of the output shaft of motor with compression impellor will be inspired in the prior art
Even.But compared with gear-box connection type, this mode being directly connected to has lacked buffering between the two, when combustion gas wheel
When the operation of machine is abnormal, such as when the main-shaft torque of gas turbine abnormally rises, inspire motor be easy overload and by
It burns out.
Therefore, in the field of gas turbine, it is desirable to be able at least be partially solved the novel combustion gas wheel of the above problem
Machine.
Summary of the invention
Therefore, the present invention is made to solve the problems of existing gas turbine described above.Of the invention
Purpose is to provide a kind of gas turbine with improvement structure, which can steadily run, and improves gas turbine
Reliability, moreover it is possible to prevent each component in gas turbine, specifically gas turbine from damaging because running fluctuation.
It is of the invention further objective is that providing the inspiration motor for capableing of stable operation for gas turbine.
Gas turbine of the invention includes：
Compressor, the compressor include compression impellor and first rotating shaft, and compression impellor is mounted in first rotating shaft, and can
It is rotated with first rotating shaft；
Turbine, turbine include turbine wheel and the second shaft, and turbine wheel is mounted in the second shaft, and can be with second
Shaft rotation, wherein the second shaft is fixedly connected with first rotating shaft, or is integrally formed with first rotating shaft, to constitute combustion
The main shaft of gas-turbine；
Combustion chamber, combustion chamber are located at the downstream of compressor and are located at the upstream of turbine；And
Motor is inspired, inspiring motor includes machine shaft, rod-shaped attachment device is connected between machine shaft and main shaft,
The rod-shaped attachment device is configured to, when the torque of main shaft exceeds scheduled threshold value, rod-shaped attachment device failure.
Wherein, the exemplary structure of the rod-shaped attachment device includes drive rod, shaft coupling etc..
In the gas turbine with above structure, machine shaft is directly connected to by drive rod and first rotating shaft, is omitted
The complicated transmission mechanism of gear-box etc, so as to improve the operational reliability of gas turbine, and can simplify to combustion
The care and maintenance of gas-turbine.Also, since the drive rod is configured to just be broken when torque is beyond predetermined threshold, thus energy
It is enough to play a protective role to each component of gas turbine, prevent each component of gas turbine due to the torque overload of gas turbine by
Damage, this can be improved the safety in operation of gas turbine entirety.
In further specific structure, which further includes shell, and shell includes：Host casket, host casket at least prop up
Pressure-bearing compressor wheel and turbine wheel, and accommodate combustion chamber；And front housing, front housing bearing inspire motor, wherein front housing
In be provided at least two supporting ribs, one end of supporting rib is connected on the inner peripheral surface of front housing, the other end support inspiration electricity
Machine.
By supporting rib, steadily motor will can be inspired to be fixed in front housing.
Further preferably, the quantity of supporting rib can be two, and the two supporting ribs can be around the longitudinal axis of front housing
It is symmetrically arranged.The setting of two supporting ribs can obtain air inlet area as big as possible for compressor.Certainly, it may also set up other
The supporting rib of quantity can be arranged to equidistant or variation spacing.
In gas turbine of the invention, inspiration motor includes：Stator, the stator include stator core and are wrapped in stator
Stator winding on iron core；Rotor, the rotor include magnet, and magnet is mounted on machine shaft, and can be turned with machine shaft
It is dynamic；And motor cabinet, stator is fixedly supported upon on the motor cabinet, and machine shaft is rotatably supported by least one bearing
On motor cabinet；Wherein, rotor is located at the adjacent one end of machine shaft, and at least one bearing is arranged in machine shaft and turn
Near the opposite other end of son, so that rotor is in cantilever design.
The cantilever-designed of rotor makes it is easier to overhaul inspiration motor.Specifically, can easily by
Stator and/or stator are from inspiring motor to remove, to stator and/or stator and other components of motor be inspired to repair
Maintenance.
Preferably, there are two bearings for setting on one end of machine shaft, and it is provided with spring between the two bearings,
Spring applies pretightning force to bearing.The pretightning force that spring provides can help to make that motor is inspired more smoothly to run.
For the inspiration motor of above structure, it is preferred that the first gap is formed between the stator and the rotor, between first
The air inlet runner of gap and compressor is in fluid communication.In this way, a part being sucked into the air-flow in compressor can flow through this
One gap cools down the stator and rotor portion that inspire in motor, and then thus improves the operation stability for inspiring motor.
Further, motor cabinet includes stator supporting part and rotor bearing part, in stator supporting part and rotor branch
The second gap is formed between bearing portion point, wherein the second gap is connected to the first interstitial fluid, and is connected with air inlet runner fluid
It is logical.The air-flow for flowing through the first gap as a result, can also further flow through the second gap, and then flow through the rest part for inspiring motor,
So as to integrally play cooling effect to inspiration motor.
Preferably, inspiration motor of the invention can switch between electric motor mode and generator mode.
Further preferably, inspiring motor to be connected with rechargeable storage battery.In this way, in electric motor mode, the storage
Battery provides electric power to inspiration motor, and in generator mode, inspire electric power generation simultaneously to charge to battery.This hair as a result,
Bright gas turbine can form more independent system, no longer need to be connected with extraneous power source.
It is compact-sized for above-described gas turbine for synthesis, occupy lesser space.For example, the combustion gas
Inspiration motor used in turbine is compared with existing motor, and volume reduces about 75%, and weight can then be reduced about
73% or so.Further, which can be by included power initiation, therefore applicable situation is more extensive.In addition,
Its air for inspiring the structure of motor that can efficiently use into gas turbine is cooled down, and is improved and is inspired motor and gas turbine
Whole operation stability, extends its service life.
Detailed description of the invention
Fig. 1 shows the structure principle chart of the gas turbine of the prior art.
Fig. 2 shows the longitudinal sectional view of the gas turbine of the first embodiment of the present invention, which is along in Fig. 3
Line A-A interception.
The gas turbine that Fig. 3 shows the first embodiment of the present invention is regarded from the end in terms of the left end in its inlet end, i.e. Fig. 2
Figure.
Fig. 4 shows longitudinal sectional structure chart of the inspiration motor in the gas turbine for being mounted on first embodiment.
Fig. 5 shows the longitudinal sectional view of the gas turbine of the second embodiment of the present invention.
Fig. 6 shows the structural schematic diagram of the gas turbine of the third embodiment of the present invention.
Specific embodiment
Below in conjunction with Fig. 2~6, detailed description of the preferred embodiments.It is to be appreciated that institute in attached drawing
What is shown is only presently preferred embodiments of the present invention, and is not construed to limit the scope of the present.Those skilled in the art
Various obvious modifications, modification, equivalence replacement can be carried out to the present invention on the basis of embodiment shown in the drawings, this
It all falls within the scope and spirit of the invention a bit.
<First embodiment>
Fig. 2~4 show the gas turbine 100 of the first embodiment of the present invention.Wherein, Fig. 2 shows be gas turbine
100 longitudinal sectional view, specifically along the cross-sectional view of the line A-A interception in Fig. 3.Fig. 3 then shows first implementation
The end-view that the gas turbine 100 of example is seen from its inlet end (left end in Fig. 2).
As clearly illustrated in Fig. 2, gas turbine 100 mainly includes compressor 110, turbine 120 and combustion chamber 130.
Wherein, along the general air flow direction in gas turbine 100, combustion chamber 130 is located at the downstream of compressor 110 and in turbine 120
Upstream.
It include compression impellor 111 in compressor 110, which is mounted in first rotating shaft 112, first rotating shaft
112 rotation drives compression impellor 111 to rotate.In turn, by the rotation of compression impellor 111, by extraneous air through inlet air flow
Road 113 sucks in compressor 110, and the air sucked by 111 Duis of compression impellor compresses.The air of compression is supplied to combustion
It burns in room 130, to mix combining combustion with the fuel for spraying into combustion chamber 130.
Combustion chamber 130 includes the combustion space crossed by burner inner liner 131, and multiple holes are provided on the burner inner liner 131 or are opened
Mouth (being not shown), the compressed air from compressor 110 enter the combustion of burner inner liner 131 through this some holes or opening
It burns in space.It is additionally provided at least one in combustion chamber 130, preferably multiple fuel nozzles 132, the fuel such as fuel oil can be via
The fuel nozzle 132 sprays into combustion chamber 130.After igniting, fired into the compressed air of combustion chamber 130 and fuel interreaction
It burns, generates high temperature, high-pressure gas.
Turbine 120 is located at the downstream of combustion chamber 130, and including turbine wheel 121, which is mounted on second
In shaft 122.Second shaft 122 is connected with first rotating shaft 112, or as shown in the picture, first rotating shaft 112 and second
Shaft 122 is integrally formed, to constitute the main shaft of gas turbine 100.
Burn in combustion chamber 130 high temperature of generation, high-pressure gas flows into turbine 120, and turbine wheel 121 is pushed to rotate,
And then turbine wheel 121 drives the rotation of the second shaft 122.Since the second shaft 122 is connected or at one with first rotating shaft 112
Body, therefore into the high temperature of turbine 120, high-pressure gas compression impellor can be also driven while pushing turbine wheel 121 to rotate
111 rotations, thus sustainably provide compressed air from compression impellor 111 to combustion chamber 130.
In the present invention, when starting to start gas turbine 100, in order to be provided initially to the compression impellor 111 of compressor 110
Power, enlightening motor 200 is set.Inspire motor 200 that there is stator 211 and rotor 212.Stator 211 and rotor 212 are respective
Structure be all conventional structure.That is, stator 211 includes stator core (being preferably made of silicon steel sheet), in stator core
On be wound with coil, to form stator winding.Rotor 212 then include at least one, preferably a plurality of magnet (such as permanent magnet),
And rotor 212 is mounted on the machine shaft 213 for inspiring motor 200.
Machine shaft 213 is connected with the main shaft of gas turbine 100, such as first with compressor 110 shown in figure
Shaft 112 is connected.When the winding of stator 211 is powered, it is powered to the magnet of the rotor 212 faced by winding with the winding
The effect in generated magnetic field starts pushing motor shaft 213 and rotates, and then first rotating shaft 112 is driven to rotate, to start pressure
Mechanism of qi 110 is run.
Inspiring motor 200 further includes motor cabinet 214, for fixing or supporting stator 211 and rotor 212.Specifically, such as
Shown in Fig. 4, motor cabinet 214 includes stator supporting part 222 and rotor bearing part 223.Stator 211 is fixedly mounted on stator branch
In bearing portion point 222, the machine shaft 213 for being equipped with rotor 212 is then rotatably supported in rotor bearing part by bearing 220
On 223.
Gas turbine 100 further includes shell, to accommodate above-mentioned compressor 110, turbine 120, combustion chamber 130 and inspire motor
200.The shell includes front housing 171, and the bearing of front housing 171 inspires motor 200.Specifically, as shown in figure 3, in front housing 171
On be provided at least two supporting ribs 173, one end of the supporting rib 173 is connected on the inner peripheral surface of front housing 171, and the other end is then
It is connected on motor support 174, wherein motor support 174 is connect with motor cabinet 214, stator supporting part 222 and motor cabinet
214 connections, so that motor 200 will be inspired to be supported in the front housing 171.Also, inspire motor 200 preferably with front housing
171 are coaxially arranged.Herein, the components such as front housing 171, supporting rib 173, motor cabinet 214, stator supporting part 222 can be
The individual components for manufacturing and fitting together respectively are also possible to integrally formed component, alternatively, being also possible to wherein several shapes
Be integrally formed molding component, and fitted together with other components being individually formed, these can according to actual processing and
Installation requirements design.
Two supporting ribs 173 shown in Fig. 3 are symmetrically arranged around the longitudinal axis of front housing 171.That is, as shown in Figure 3
Ground is spaced from 180 degree.The set-up mode of two supporting ribs 173 shown in Fig. 3 can obtain maximum air inlet for compressor 110
Area.
Certainly, in order to increase to inspire motor 200 support stability, three or more also settable supporting ribs 173.This
A little supporting ribs can also be arranged to interval variation as needed around inspiring the circumferential direction of motor 200 to be evenly spaced apart to arrange.
As being clearly shown in Fig. 2, in gas turbine 100 of the invention, the machine shaft 213 of motor 200 is inspired
It is connected in the first rotating shaft 112 of compressor 110 by drive rod 230.The drive rod 230 is configured to, when gas turbine 100
Main shaft (i.e. the first and second shafts 112,122) torque exceed scheduled threshold value when, the drive rod 230 fracture or plasticity become
The failure such as shape.Wherein, the threshold value is specifically configured to the corresponding torque of turbine turns strength of parts load.
Specifically, when opening alternator failure locking, machine shaft 213 etc. can stop rotating, and then make combustion gas wheel
The main shaft of machine also stops rotating.At this point, since the revolving speed of gas turbine main shaft is typically up to thousands of to tens of thousands of turns, if gas turbine
Turn high speed from thousands of to tens of thousands of is reduced to 0 turn to main shaft suddenly in a short time, and the component of gas turbine can be used because of huge rotation
It measures and receives badly damaged.Therefore, need to be when inspiring 200 locking of motor, turbine turns component still keeps rotating, and gradually
Stop, without being damaged because rotary inertia is excessive.By the way that drive rod 230 is arranged, can break down locking etc. in motor 200
When situation, due to torque sharply raising and make drive rod 230 that fracture or plastic deformation occur to failing, electricity can be disconnected in this way
Drive connection between machine 200 and gas turbine main shaft, to play the role of protecting gas turbine.
Certainly, other than the above single drive rod 230 as shown in the figure, other types of rod-shaped connection dress can also be used
It sets to connect machine shaft 213 and first rotating shaft 112, such as shaft coupling etc. can be connected between them.
In several ways drive rod 230 can be set to fail under scheduled torque threshold, for example, can incite somebody to action
The sectional dimension of drive rod 230 is set smaller than the sectional dimension of machine shaft 213 and/or first rotating shaft 112；In drive rod
Weak point (such as groove, hollow part) is set on 230, so that drive rod 230 can be thin at this when torque exceeds scheduled threshold value
It is broken or is plastically deformed first at weak portion；Alternatively, drive rod 230 can be by more compared with machine shaft 213 and first rotating shaft 112
Easy fracture or the material of plastic deformation are made；Etc..
Machine shaft 213 and first rotating shaft 112 are connected by using drive rod 230, compared to existing gear
The connection of case, the operational reliability and service life of gas turbine 100 can be improved greatly.Meanwhile when the fortune of gas turbine 100
Row occur it is abnormal and when leading to the too fast rising of load, drive rod 230 can be also broken before inspiring motor 200 to be burned, and be played
Protective effect to motor 200 is inspired, to also ensure the safety in operation of gas turbine 100.
In said structure, drive rod 230, first rotating shaft 112 and machine shaft 213 are come as component independent
Description.Certainly, these shaft members are also possible to integrally formed component.For example, drive rod 230 can be with first rotating shaft 112 1
It is body formed；Drive rod 230 can be integrally formed with machine shaft 213；Or drive rod 230, first rotating shaft 112 and machine shaft
213 are all integrally formed together.
Further, it in gas turbine 100 of the invention, also improves to some extent to the structure for inspiring motor 200.Specifically may be used
See Fig. 4, which schematically illustrates the unique textures of inspiration motor 200 of the invention.It is electronic with routine in the prior art
Machine is different, and in inspiration motor 200 of the invention, rotor 212, each magnet for specifically forming rotor 212 are arranged in electricity
The adjacent one end of machine shaft 213, such as the adjacent one end of the separate compression impellor 111 in machine shaft 213, and in machine shaft
At least one bearing 220, two bearings being spaced from preferably as shown in Figure 4 are nearby arranged in 213 other end
220, machine shaft 213 is supported on the rotor bearing part 223 of motor cabinet 214 by the bearing 220.
Through this structure, rotor 212 is supported in cantilevered fashion, and facing to being fixedly supported upon stator supporting part
Divide the stator 211 on 222.The bearing of this cantilevered fashion of rotor 212 can be easily installed and safeguard and inspire motor 200.Specifically
For, it can easily only need to be from and in maintenance by the front end for the air inlet for inspiring motor 200 be mounted on compressor 110
The front end of air inlet removes rotor 212 and/or stator 211, can carry out maintenance guarantor to other components in inspiration motor 200
It supports.
In addition, between the rotor 212 and stator 211 of cantilevered fashion, there are the first gaps 215.First gap 215 and pressure
The air inlet runner 113 of mechanism of qi 110 is in fluid communication, in this way, being sucked into compressor 110 during inspiring motor 200 to run
In air-flow in a part can flow through the first gap 215, to play cooling effect to stator 211 and rotor 212.And
And bearing 220 concentrates on that adjacent one end of the close compression impellor 111 of machine shaft 213, close to the profit of front housing 171
Near the mist of oil chamber of lubricating oil, so as to which easily bearing 220 is cooled down and lubricated, motor bearing 174 passes through air inlet runner
113 pairs of lubricating oil are cooling, inspire such as stator 211 of motor 200 and the other parts of rotor 212 etc without influencing whether.
Further, the second gap is also preferably provided between stator supporting part 222 and rotor bearing part 223
216, second gap 216 and the first gap 215 are in fluid communication, and also connect with 113 fluid of air inlet runner of compressor 110
It is logical.It is formed as a result, and cooling air-flow is carried out to inspiration motor 200.
Preferably, spring 221 can be set between the two bearings 220 there are two in the case where bearing 220 in setting,
The spring 221 applies pretightning force to bearing 220.In this way, the effect of the pretightning force by spring 221, in the process of running, bearing
220 can more smoothly operate.
Bearing 220 can be the bearing suitable for high-speed rotation, such as ceramic bearing, electric power bearing, hydrodynamic journal liquid polymers, liquid
Body hydrodynamic bearing, aerostatic bearing, aero dynamic bearing, sliding bearing etc..
In addition, motor 200 of the invention can also switch between two kinds of operational modes.Specifically, when starting combustion gas
When turbine 100, motor 200 is inspired using being driven by electricity, rotates its rotor 212, and then drives first rotating shaft 112 and installation
Compression impellor 111 in first rotating shaft 112 rotates, and inspires motor 200 to run with electric motor mode at this time.Opening in the present invention
The driving voltage of generator 200 is substantially in 12~24V.And when the turbine wheel of gas turbine 100 121 reaches certain revolving speed,
Stop to inspiring motor 200 to supply electric power, at this point, turbine wheel 121 will be rotated via the second shaft 122 and first rotating shaft 112
Movement sends compression impellor 111 to, and then drives rotor 212 to rotate via drive rod 230, at this point, inspiring motor 200 to generate electricity
Machine mode operation.It is of the invention inspire motor 200 as generator generating voltage range between 14~30V.In addition to having
Except above-mentioned driving voltage and the inspiration motor 200 of generating voltage, can also select according to actual needs has other driving electricity
Press the motor of range and generating voltage range as inspiration motor 200.
Preferably, rechargeable storage battery can be connected on inspiring motor 200.When inspiration motor 200 is with motor mould
When formula is run, battery is powered to inspiration motor 200, and when inspiring motor 200 to run with generator mode, inspire motor
200 power generations are simultaneously charged to battery.
Gas turbine 100 may also include other auxiliary systems of common gas turbine, control system as shown in Figure 2
300, fuel system 400 and lubricating system 500 etc..Wherein, control system 300 passes through wired or wireless form and gas turbine
100 other parts (such as inspiration motor 200, fuel system 400, lubricating system 500 etc.) connection, to control these parts
Operation.Fuel system 400 then controls the fuel nozzle 132 of combustion chamber 130, to supply fuel oil, and lubricating system to combustion chamber 130
500 portions to the bearing 220 for such as inspiring motor 200, the bearing for supporting first rotating shaft 112 and/or the second shaft 122 etc
Part provides lubricating oil.
<Second embodiment>
Fig. 5 shows the structure of the second embodiment of the present invention.Wherein, it is identical with the first embodiment or corresponding features
It point is indicated with same or similar appended drawing reference, and mainly description is different from the first embodiment in disclosure below
Feature, without being described in detail again to identical feature.Unless there are opposite description, feature described in first embodiment is same
Suitable for second embodiment.
As shown in figure 5, inspiring the machine shaft 213 of motor 200 to pass through magnetic in the gas turbine 100 of second embodiment
Suspension bearing 220 ' is supported on motor cabinet 214.The magnetic suspension bearing 220 ' can be the magnetic suspension bearing electrically activated, with electricity
Source connection generates magnetic field, so that machine shaft 213 be made to be suspended in the magnetic suspension shaft when being powered to magnetic suspension bearing 220 '
It holds in 220 '.
For the situation for using magnetic suspension bearing 220 ', machine shaft 213 during rotation with other components all
It does not contact, there is no need to the parts to magnetic suspension bearing 220 ' to be lubricated.Further, for rotatably supporting first
The bearing of shaft 112 and/or the second shaft 122 is also possible to magnetic suspension bearing.In this way, in the gas turbine of second embodiment
In 100, it is convenient to omit lubricating system, as shown in Figure 5.
<3rd embodiment>
Fig. 6 shows the structure of the third embodiment of the present invention.Wherein, identical or corresponding with the first and second embodiments
Characteristic is indicated with same or similar appended drawing reference, and mainly description and first and second in disclosure below
The different feature of embodiment, without being described in detail again to identical feature.Implement unless there are opposite description, first and second
Feature described in example is equally applicable to second embodiment.
Two combustions being connected in parallel of the structure using first embodiment above and second embodiment are shown in Fig. 6
Gas-turbine 100, they share an inspiration motor 200.Wherein, inspiring motor 200 is both ends output type, and rotor 212 is located at
The centre of machine shaft 213, the both ends of machine shaft 213 are supported by bearing 220 respectively.Also, the both ends of machine shaft 213 point
It is not connected on gas turbine 100-1 and gas turbine 100-2, is had by the first drive rod 230-1 and the second drive rod 230-2
Body it is attached to main shaft (first rotating shaft 112 of compressor 110 and/or the second shaft of turbine 120 of each gas turbine 100
122) on.Simultaneously according to actual needs, two gas turbines 100 can be set to, after reaching scheduled speed, is disengaged
Linkage between two respective main shafts of gas turbine 100, so that the two gas turbines 100 can be run each independently.
Some preferable embodiments of the invention are had been described in detail above.On this basis, art technology
Personnel can obviously be modified, modification and the combination of the various features in different embodiments, these are all in this hair
Within the scope of bright.
Claims (10)
1. a kind of gas turbine, which is characterized in that the gas turbine includes：
Compressor, the compressor include compression impellor and first rotating shaft, and the compression impellor is mounted in the first rotating shaft,
And it can be rotated with the first rotating shaft；
Turbine, the turbine include turbine wheel and the second shaft, and the turbine wheel is mounted in second shaft, and energy
It is enough to be rotated with second shaft, wherein second shaft is fixedly connected with the first rotating shaft, or with described first turn
Axis is integrally formed, to constitute the main shaft of the gas turbine；
Combustion chamber, the combustion chamber are located at the downstream of the compressor and are located at the upstream of the turbine；And
Motor is inspired, the inspiration motor includes machine shaft, and the machine shaft is connected to described by rod-shaped attachment device
Main shaft, the rod-shaped attachment device are configured to, when the torque of the first rotating shaft and/or second shaft is beyond scheduled
When threshold value, the rod-shaped attachment device failure.
2. gas turbine as described in claim 1, which is characterized in that the rod-shaped attachment device is drive rod or shaft coupling.
3. gas turbine as claimed in claim 1 or 2, which is characterized in that the compressor further includes shell, the shell packet
It includes：
Host casket, the host casket at least supports the compressor impeller and the turbine wheel, and accommodates the combustion chamber；With
And
Front housing, the front housing support the inspiration motor, wherein at least two supporting ribs are provided in the front housing,
One end of the supporting rib is connected on the inner peripheral surface of the front housing, and the other end supports the inspiration motor.
4. gas turbine as claimed in claim 3, which is characterized in that be provided in the front housing around the vertical of the front housing
Two supporting ribs of axisymmetrical setting.
5. gas turbine as claimed in claim 1 or 2, which is characterized in that the inspiration motor includes：
Stator, the stator include stator core and the stator winding that is wrapped on the stator core；
Rotor, the rotor include magnet, and the magnet is mounted on the machine shaft, and can be turned with the machine shaft
It is dynamic；And
Motor cabinet, the stator are fixedly supported upon on the motor cabinet, and the machine shaft can be turned by least one bearing
It is supported on the motor cabinet dynamicly；
Wherein, the rotor is located at the adjacent one end of the machine shaft, and at least one described bearing is arranged in the motor
Near the other end opposite with the rotor of shaft, so that the rotor is in cantilever design.
6. gas turbine as claimed in claim 5, which is characterized in that be provided with two on described one end of the machine shaft
A bearing, and spring is provided between the two described bearings, the spring applies pretightning force to the bearing.
7. gas turbine as claimed in claim 5, which is characterized in that be formed with first between the stator and the rotor
The air inlet runner of gap, first gap and the compressor is in fluid communication.
8. gas turbine as claimed in claim 7, which is characterized in that the motor cabinet includes stator supporting part and rotor branch
Bearing portion point is formed with the second gap between the stator supporting part and the rotator abutment point, wherein between described second
Gap is connected to first interstitial fluid, and is in fluid communication with the air inlet runner.
9. gas turbine as claimed in claim 3, which is characterized in that the inspiration motor can be in electric motor mode and power generation
Switch between machine mode.
10. gas turbine as claimed in claim 9, which is characterized in that be connected with chargeable electric power storage in the inspiration motor
Pond.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811074861.9A CN108915868A (en) | 2018-09-14 | 2018-09-14 | gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811074861.9A CN108915868A (en) | 2018-09-14 | 2018-09-14 | gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108915868A true CN108915868A (en) | 2018-11-30 |
Family
ID=64409168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811074861.9A Pending CN108915868A (en) | 2018-09-14 | 2018-09-14 | gas turbine |
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| CN110529252A (en) * | 2019-09-25 | 2019-12-03 | 江苏恒军动力科技有限公司 | A kind of microturbine generators |
| CN110864900A (en) * | 2019-12-23 | 2020-03-06 | 至玥腾风科技集团有限公司 | Bearing detection method, bearing detection system, gas turbine starting method and gas turbine starting system |
| CN111156180A (en) * | 2020-01-19 | 2020-05-15 | 至玥腾风科技集团有限公司 | Gas compressor, rotor system and micro gas turbine |
| WO2022100088A1 (en) * | 2020-11-13 | 2022-05-19 | 至玥腾风科技集团有限公司 | Cooling, heating and power supply-combined system of micro-combustion turbine in building |
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| DE102010063270A1 (en) * | 2010-12-16 | 2012-06-21 | Siemens Aktiengesellschaft | Electric-propelled traction vehicle has auxiliary fan that is arranged at exhaust air-side end of stator laminated core |
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| CN110529252A (en) * | 2019-09-25 | 2019-12-03 | 江苏恒军动力科技有限公司 | A kind of microturbine generators |
| CN110864900A (en) * | 2019-12-23 | 2020-03-06 | 至玥腾风科技集团有限公司 | Bearing detection method, bearing detection system, gas turbine starting method and gas turbine starting system |
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| JP2022537587A (en) * | 2019-12-23 | 2022-08-26 | 永旭▲騰▼▲風▼新能源▲動▼力科技（北京）有限公司 | Bearing detection method, detection system, gas turbine starting method, starting system |
| JP7224709B2 (en) | 2019-12-23 | 2023-02-20 | 永旭▲騰▼▲風▼新能源▲動▼力科技（北京）有限公司 | Bearing detection method, detection system, gas turbine starting method, starting system |
| CN111156180A (en) * | 2020-01-19 | 2020-05-15 | 至玥腾风科技集团有限公司 | Gas compressor, rotor system and micro gas turbine |
| WO2021143417A1 (en) * | 2020-01-19 | 2021-07-22 | 至玥腾风科技集团有限公司 | Gas compressor, rotor system, and micro gas turbine |
| JP2022544153A (en) * | 2020-01-19 | 2022-10-17 | 至▲ユエ▼▲騰▼▲風▼科技集▲団▼有限公司 | Compressors, rotor systems and micro gas turbines |
| WO2022100088A1 (en) * | 2020-11-13 | 2022-05-19 | 至玥腾风科技集团有限公司 | Cooling, heating and power supply-combined system of micro-combustion turbine in building |
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Effective date of registration: 20220928 Address after: No. 17517, Weijiao Road, Fangzi District, Weifang City, Shandong Province, 261200 (100 meters west of the intersection of Weijiao Road and Zhengtai Road) Applicant after: Weifang Yunshen Machinery Technology Co.,Ltd. Address before: No.233, Jiaozhou West Road, zhongyun sub district office, Jiaozhou City, Qingdao City, Shandong Province 266300 Applicant before: QINGDAO YUNSHEN POWER TECHNOLOGY Co.,Ltd. |
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Application publication date: 20181130 |