CN109578337A - Centrifugal compressor bleed structure and gas-turbine unit - Google Patents
Centrifugal compressor bleed structure and gas-turbine unit Download PDFInfo
- Publication number
- CN109578337A CN109578337A CN201910054519.0A CN201910054519A CN109578337A CN 109578337 A CN109578337 A CN 109578337A CN 201910054519 A CN201910054519 A CN 201910054519A CN 109578337 A CN109578337 A CN 109578337A
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- Prior art keywords
- annular partition
- baffle
- centrifugal impeller
- centrifugal
- rotating
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/662—Balancing of rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to turbogenerator technical field, propose that a kind of centrifugal compressor bleed structure and gas-turbine unit, the bleed structure include centrifugal impeller disk, baffle and annular partition；Baffle and centrifugal impeller disk form rotating-static clearance and back chamber, and rotating-static clearance is connected to back chamber；Annular partition is connected to baffle, and between centrifugal impeller disk and baffle, the through-hole with rotating-static clearance face is provided on annular partition, so that the air-flow of centrifugal impeller outlet can be flowed between annular partition and baffle by rotating-static clearance and through-hole, to form the air-flow around annular partition, and the air current flow direction between centrifugal impeller disk and annular partition is radially outward, coriolis force direction is contrary with air-flow tangential velocity, weaken the influence of centrifugal force caused by air-flow tangential motion, the radial pressure drop of back chamber air-flow can be reduced, increase back chamber average static pressure, to increase the centrifugal impeller disk back forward axial force of chamber.
Description
Technical field
The present invention relates to turbogenerator technical field more particularly to a kind of centrifugal compressor bleed structure and this is installed
The gas-turbine unit of centrifugal compressor bleed structure.
Background technique
In aero-engine operating, to make gas compressor moving blade tip clearance maintain smaller level, guarantees movable vane efficiency, turn
Sub- axial force is typically designed as horizontally forward, and engine must guarantee that rotor axial power is not lightly loaded not when different conditions operate
Reversely, in order to avoid damage bearing, generates harm.
In middle-size and small-size aero gas turbine engine, being designed using centrifugal impeller can be achieved the biggish pressurization of single-stage impeller
Than, but centrifugal impeller itself, there is also very big pneumatic axial force backward, centrifugal impeller carries on the back the size of the axial force of chamber not only
The important function of equilibrium centrifugation impeller aerodynamic force is played, and when engine operates at small state interval, engine rotor axis
Also small to power, the size of centrifugal impeller back chamber axial force can have an important influence on the axial force of engine rotor at this time.Such as Fig. 1
Shown in the prior art centrifugal impeller back chamber generate axial force diagram, centrifugal impeller 1 carry on the back chamber 5 generate axial force the reason of be by
Centrifugal impeller 1 exports the pressure-air that root is drawn and acts directly in the back chamber rotary side of centrifugal impeller 1, thus in the horizontal direction
It is upper to generate forward axial force.
The bleed design diagram of centrifugal impeller back chamber as shown in Figure 2, the rotating-static clearance of root is exported from centrifugal impeller 1
5 bleeds, air-flow, which carries on the back chamber rotary side inward flow by centrifugal impeller 1, can determine coriolis force direction by right-hand rule
Vertical paper is outside, identical as air-flow tangential velocity direction, and back 5 interior air-flow of chamber is more significant by centrifugal forces affect, exacerbates gas
The radial pressure drop of stream reduces centrifugal impeller 1 and carries on the back the forward axial force of chamber 5.Pass through throttling comb tooth together, gas in back 5 bottom of chamber
Stream can be used for the cooling of later stages components and bearing bore is obturaged.
Carrying on the back chamber 5 due to centrifugal impeller 1 is the maximum chamber of magnitude in engine Axial Force Calculating, itself is not only
Play a part of equilibrium centrifugation impeller aerodynamic force, when engine operates at small state interval, also can to Axial Force Calculating result
It has an important influence on.Centrifugal impeller 1 carries on the back chamber 5 and uses radial inward flow bleed design method, exacerbates the shadow of centrifugal force in back chamber 5
It rings, increases the radial pressure drop of back chamber 5, back 5 average pressure of chamber reduces, and the back forward axial force of chamber 5 is caused to reduce.Engine operating
Bearing underloading or load reversal are even less than caused with 1 aerodynamic force of equilibrium centrifugation impeller in small state interval, generated serious
Consequence.
Above- mentioned information disclosed in the background technology part are only used for reinforcing the understanding to background of the invention, therefore it can
To include the information not constituted to the prior art known to persons of ordinary skill in the art.
Summary of the invention
It is an object of the invention to overcome the shortcomings of that the forward axial force of the centrifugal impeller of above-mentioned prior art back chamber reduces,
A kind of centrifugal impeller back chamber centrifugal compressor bleed structure that forward axial force increases is provided and the centrifugal compressor is installed
The gas-turbine unit of bleed structure.
Additional aspect and advantage of the invention will be set forth in part in the description, and partly will be from description
It is apparent from, or can practice through the invention and acquistion.
According to one aspect of the disclosure, a kind of centrifugal compressor bleed structure is provided, comprising:
Centrifugal impeller disk；
Baffle forms rotating-static clearance and back chamber with the centrifugal impeller disk, and the rotating-static clearance is connected to the back chamber；
Annular partition is connected to the baffle, and between the centrifugal impeller disk and the baffle, it is described annular every
The through-hole with the rotating-static clearance face is provided on plate, so that the air-flow of centrifugal impeller outlet can pass through the rotating-static clearance
And the through-hole flows into the rear inflow annular partition and the centrifugal impeller disk between the annular partition and the baffle
Between.
In a kind of exemplary embodiment of the disclosure, the baffle includes:
First connecting cylinder forms rotating-static clearance with the centrifugal impeller disk；
First annular connecting plate is connected to first connecting cylinder, the first annular connecting plate and the centrifugal impeller
Disk forms back chamber.
In a kind of exemplary embodiment of the disclosure, the outer ring surface of the annular partition is interior with first connecting cylinder
Cylinder face is fixed.
In a kind of exemplary embodiment of the disclosure, the through-hole is set as multiple.
In a kind of exemplary embodiment of the disclosure, multiple through-holes are distributed in the annular partition.
In a kind of exemplary embodiment of the disclosure, being provided on one side for the close baffle of the annular partition is more
A connecting column, the multiple connecting column are connect with the baffle.
In a kind of exemplary embodiment of the disclosure, the outer diameter of the annular partition is less than the interior of first connecting cylinder
Diameter is so that the inner ring surface of the outer ring surface of the annular partition and the baffle forms the through-hole.
In a kind of exemplary embodiment of the disclosure, the internal diameter of the annular partition is greater than or equal to its outer diameter very
Six and be less than or equal to its outer diameter 8/10ths.
In a kind of exemplary embodiment of the disclosure, the rotating-static clearance is located at the root of the outlet of the centrifugal impeller
Portion.
According to one aspect of the disclosure, a kind of gas-turbine unit is provided, comprising:
Centrifugal compressor bleed structure described in above-mentioned any one.
As shown from the above technical solution, the present invention has at least one of following advantages and good effect:
Centrifugal compressor bleed structure of the invention, baffle form the rotating-static clearance being connected to and back chamber with centrifugal impeller disk,
Annular partition is connected on baffle, annular partition is provided with and is turned between centrifugal impeller disk and baffle, on annular partition
The through-hole of quiet gap face so that the air-flow of centrifugal impeller outlet can be flowed by rotating-static clearance and through-hole annular partition with
It is flowed between the annular partition and the centrifugal impeller disk after between baffle.Air-flow keeps diameter between annular partition and baffle
Inwardly flow it is constant, the air-flow a part flowed out between annular partition and baffle for downstream components cooling obturage, another portion
It is diverted between annular partition and centrifugal impeller disk, between annular partition and centrifugal impeller, by centrifugal impeller Effect of Rotation, gas
The flow direction of stream radially outward, by right-hand rule, can determine that coriolis force direction is that vertical paper is inside, tangential with air-flow
Directional velocity can reduce centrifugal impeller rotation sidewind on the contrary, weaken the influence of centrifugal force caused by air-flow tangential velocity
Radial pressure drop, increase centrifugal impeller carry on the back chamber average static pressure, thus increase centrifugal impeller back the forward axial force of chamber.Realize from
While heart impeller outlet air-entraining function, the underloading of engine rotor rotor axial power when small state interval operates is also improved
And inverse problem.The centrifugal impeller disk carries on the back the design of chamber bleed structure, while meeting that downstream components are cooling to obturage demand,
Realize the needs of engine rotor axial force adjusting.
Detailed description of the invention
Its example embodiment is described in detail by referring to accompanying drawing, above and other feature of the invention and advantage will become
It is more obvious.
Fig. 1 is the axial force diagram that centrifugal impeller back chamber generates in the prior art；
Fig. 2 is the bleed design diagram of centrifugal impeller back chamber in the prior art；
Fig. 3 is the partial structural diagram of one embodiment of centrifugal compressor bleed structure of the present invention；
Fig. 4 is that the centrifugal compressor of the prior art carries on the back intracavitary average static pressure computer simulation schematic diagram；
Fig. 5 is that centrifugal compressor of the present invention carries on the back intracavitary average static pressure computer simulation schematic diagram；
The reference numerals are as follows for main element in figure:
1, centrifugal impeller；11, centrifugal impeller disk；
2, baffle；21, the first connecting cylinder；22, first annular connecting plate；23, the second connecting cylinder；24, the second annular connection
Plate；25, third connecting cylinder；
3, annular partition；31, through-hole；
4, rotating-static clearance；5, chamber is carried on the back.
Specific embodiment
Example embodiment is described more fully with reference to the drawings.However, example embodiment can be with a variety of shapes
Formula is implemented, and is not understood as limited to embodiment set forth herein；On the contrary, thesing embodiments are provided so that the present invention will
Fully and completely, and by the design of example embodiment comprehensively it is communicated to those skilled in the art.Identical attached drawing in figure
Label indicates same or similar structure, thus the detailed description that will omit them.
Present invention firstly provides a kind of centrifugal compressor bleed structures, referring to centrifugal compressor bleed knot shown in Fig. 3
The partial structural diagram of structure, the bleed structure may include centrifugal impeller disk 11, baffle 2 and annular partition 3；Baffle 2 with
Centrifugal impeller disk 11 forms rotating-static clearance 4 and back chamber 5, and rotating-static clearance 4 is connected to back chamber 5；Annular partition 3 is connected to baffle 2, and
Between centrifugal impeller disk 11 and baffle 2, the through-hole 31 with 4 face of rotating-static clearance is provided on annular partition 3, so that centrifugation
Described in the air-flow that impeller 1 exports flows into after capable of being flowed between annular partition 3 and baffle 2 by rotating-static clearance 4 and through-hole 31
Between annular partition 3 and the centrifugal impeller disk 11.
In this example embodiment, baffle 2 may include the first connecting cylinder 21, first connect with the first connecting cylinder 21
Annular connecting plate 22, the second connecting cylinder 23 connecting with the inner ring of first annular connecting plate 22 are connect with the second connecting cylinder 23
Second annular connecting plate 24, the third connecting cylinder 25 being connect with the inner ring of the second annular connecting plate 24.Centrifugal impeller 1 may include
Centrifugal impeller disk 1.The root of the outlet of centrifugal impeller 1, the first connecting cylinder 21 and centrifugal impeller disk is arranged in first connecting cylinder 21
11 form rotating-static clearance 4, the outlet face setting of rotating-static clearance 4 and centrifugal impeller 1；Baffle 2 and centrifugal impeller disk 11, which are formed, to be carried on the back
Chamber 5.
In this example embodiment, annular partition 3 is set as circular, and annular partition 3 has inner ring surface and outer ring surface.
The outer ring surface of annular partition 3 and the inner cylinder face of the first connecting cylinder 21 can be bolted, can also be solid by welding manner
It is fixed.Multiple through-holes 31 can be set on annular partition 3, multiple through-holes 31 are circumferentially laid on annular partition 3, and multiple
Through-hole 31 is distributed in annular partition 3, and the pore size of through-hole 31, which is subject to, to be realized and do not throttle to air-flow.
In this example embodiment, the internal diameter of annular partition 3 is 7/10ths of the outer diameter of annular partition 3, annular every
The outer diameter of plate 3 is identical as the internal diameter of the first connecting cylinder 21.The inner ring surface of annular partition 3 is not connect with centrifugal impeller disk 11, i.e.,
It is formed with airflow channel between the inner ring surface and centrifugal impeller disk 11 of annular partition 3, in order between annular partition and baffle
The air-flow of outflow flows between annular partition 3 and centrifugal impeller disk 11.Certainly, the size of annular partition 3 is not limited to foregoing description,
As long as the internal diameter of annular partition 3 is greater than or equal to 6/10ths of its outer diameter and is less than or equal to 8/10ths of its outer diameter
It can.
The gas that multiple through-holes 31 are exported with 4 face of rotating-static clearance, centrifugal impeller 1 after annular partition 3 is mounted on baffle 2
Then stream can be flowed between annular partition 3 and baffle 2 by rotating-static clearance 4 by through-hole 31.In annular partition 3 and baffle 2
Between air-flow keep radial inward flow it is constant, the fraction flowed out between annular partition 3 and baffle 2 can pass through airflow channel
It flows between annular partition 3 and centrifugal impeller disk 11, between annular partition 3 and centrifugal impeller disk 11, is rotated by centrifugal impeller 1
It influencing, the flow direction of air-flow is that radially outward, by right-hand rule, can determine that coriolis force direction is that vertical paper is inside,
It is contrary with air-flow tangential velocity, the influence of centrifugal force caused by air-flow tangential velocity is weakened, centrifugal impeller 1 can be reduced
The radial pressure drop of sidewind is rotated, increases centrifugal impeller 1 and carries on the back 5 average static pressure of chamber, so that it is forward to increase the back chamber 5 of centrifugal impeller 1
Axial force.Be conducive to improve the underloading and inverse problem of engine rotor rotor axial power when small state interval operates.
The connection type of annular partition 3 and baffle 2 is not limited to foregoing description, for example, can be in the close gear of annular partition 3
Multiple connecting columns are arranged in the one side of plate 2, and multiple connecting columns are connect with baffle 2.The outer diameter of annular partition 3 is less than the first connecting cylinder 21
Internal diameter, the outer ring surface of annular partition 3 and the inner ring surface of baffle 2 form above-mentioned through-hole, which is annular through-hole.
Intracavitary average static pressure computer simulation signal is carried on the back referring to the centrifugal compressor bleed structure of the prior art shown in Fig. 4
Figure, available 5 average static pressure of back chamber is 571.6kPa from figure.Centrifugal compressor bleed knot of the present invention referring to Figure 5
Structure carries on the back intracavitary average static pressure computer simulation schematic diagram, and available 5 average static pressure of back chamber is 605.1kPa from figure.Carry on the back chamber 5
Average static pressure improves 6% ((605.1-571.6)/571.6 ≈ 6%).According to formula: axial force=average static pressure * is centrifuged leaf
Wheel disc axial projective area, available is about 180kgf to the adjustment amplitude of axial force in the small state operating of engine, foot
Enough improve the underloading and inverse problem under the small state of engine.
Further, this example embodiment additionally provides a kind of gas-turbine unit, which can
To include centrifugal compressor bleed structure described in any of the above-described example embodiment.Due to combustion gas whirlpool in this example embodiment
In each example embodiment of centrifugal compressor bleed structure and above-mentioned centrifugal compressor bleed structure that turbine uses
Centrifugal compressor bleed structure is identical, and therefore, the two can solve identical technical problem, and reach identical technical effect,
Details are not described herein.
Above-mentioned described feature, structure or characteristic can be incorporated in one or more embodiment party in any suitable manner
In formula, if possible, it is characterized in discussed in each embodiment interchangeable.In the above description, it provides many specific thin
Section fully understands embodiments of the present invention to provide.It will be appreciated, however, by one skilled in the art that this can be practiced
The technical solution of invention, or can be using other methods, component, material without one or more in the specific detail
Material etc..In other cases, known features, material or operation are not shown in detail or describe to avoid each side of the invention is obscured
Face.
The term of " about " " about " is used to be generally represented within the 20% of a given value or range in this specification, preferably
It is within 10%, and is more preferably within 5%.Given quantity is quantity about herein, implies that the feelings in not certain illustrated
Under condition, " about " " about " " substantially " meaning of " general " can be still implied.
Although the term of relativity, such as "upper" "lower" is used to describe a component of icon for another in this specification
The relativeness of one component, but these terms are in this manual merely for convenient, for example, with reference to the accompanying drawings described in show
The direction of example.It is appreciated that, if making it turn upside down the device overturning of icon, the component described in "upper" will
As the component in "lower".Term of other relativities, such as "inner" "outside" etc. also make have similar meaning.When certain structure is at it
When its structure "upper", it is possible to refer to that certain structural integrity is formed in other structures, or refer to that certain structure is " direct " and be arranged other
In structure, or refer to that certain structure is arranged in other structures by the way that another structure is " indirect ".
In this specification, term "one", " one ", "the" and " described " be to indicate that there are one or more elements/groups
At part/etc.；Term "comprising", " comprising " and " having " to indicate the open meaning being included and refer in addition to
The element/component part/listed also may be present except waiting other element/component part/etc.；Term " first ", " second " and
" third " etc. is only used as label, is not the quantity limitation to its object.
It should be appreciated that the present invention is not limited in its application to the detailed construction and arrangement of the component of this specification proposition
Mode.The present invention can have other embodiments, and can realize and execute in many ways.Aforesaid deformation form and
Modification is fallen within the scope of the present invention.It should be appreciated that this disclosure and the present invention of restriction extend in text
And/or it is mentioned in attached drawing or all alternative combinations of two or more apparent independent features.It is all these different
Combination constitutes multiple alternative aspects of the invention.Embodiment described in this specification illustrates to become known for realizing the present invention
Best mode, and will enable those skilled in the art using the present invention.
Claims (10)
1. a kind of centrifugal compressor bleed structure characterized by comprising
Centrifugal impeller disk；
Baffle forms rotating-static clearance and back chamber with the centrifugal impeller disk, and the rotating-static clearance is connected to the back chamber；
Annular partition is connected to the baffle, and between the centrifugal impeller disk and the baffle, on the annular partition
Be provided with the through-hole with the rotating-static clearance face so that the air-flow of centrifugal impeller outlet can by the rotating-static clearance and
The through-hole flows between the annular partition and the centrifugal impeller disk after flowing between the annular partition and the baffle.
2. centrifugal compressor bleed structure according to claim 1, which is characterized in that the baffle includes:
First connecting cylinder forms rotating-static clearance with the centrifugal impeller disk；
First annular connecting plate is connected to first connecting cylinder, the first annular connecting plate and the centrifugal impeller dish type
At back chamber.
3. centrifugal compressor bleed structure according to claim 2, which is characterized in that the outer ring surface of the annular partition with
The inner cylinder face of first connecting cylinder is fixed.
4. centrifugal compressor bleed structure according to claim 3, which is characterized in that the through-hole is set as multiple.
5. centrifugal compressor bleed structure according to claim 4, which is characterized in that multiple through-holes are distributed in described
Annular partition.
6. centrifugal compressor bleed structure according to claim 2, which is characterized in that the annular partition close to described
Baffle is provided with multiple connecting columns on one side, and the multiple connecting column is connect with the baffle.
7. centrifugal compressor bleed structure according to claim 6, which is characterized in that the outer diameter of the annular partition is less than
The internal diameter of first connecting cylinder is so that the inner ring surface of the outer ring surface of the annular partition and the baffle forms the through-hole.
8. centrifugal compressor bleed structure according to claim 1, which is characterized in that the internal diameter of the annular partition is greater than
Or 6/10ths equal to its outer diameter and 8/10ths less than or equal to its outer diameter.
9. centrifugal compressor bleed structure according to claim 1, which is characterized in that the rotating-static clearance be located at it is described from
The root of heart impeller outlet.
10. a kind of gas-turbine unit characterized by comprising
Centrifugal compressor bleed structure described in any one of claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910054519.0A CN109578337B (en) | 2019-01-21 | 2019-01-21 | Centrifugal compressor air entraining structure and gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910054519.0A CN109578337B (en) | 2019-01-21 | 2019-01-21 | Centrifugal compressor air entraining structure and gas turbine engine |
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| Publication Number | Publication Date |
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| CN109578337A true CN109578337A (en) | 2019-04-05 |
| CN109578337B CN109578337B (en) | 2020-10-09 |
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| CN201910054519.0A Active CN109578337B (en) | 2019-01-21 | 2019-01-21 | Centrifugal compressor air entraining structure and gas turbine engine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110454436A (en) * | 2019-07-29 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed |
| CN112576377A (en) * | 2020-12-07 | 2021-03-30 | 中国航发沈阳发动机研究所 | Aeroengine bearing seals bleed structure |
| CN113357189A (en) * | 2021-06-23 | 2021-09-07 | 中国航发湖南动力机械研究所 | Radial outflow impeller back cavity air-entraining structure and gas turbine engine |
| CN115324911A (en) * | 2022-10-12 | 2022-11-11 | 中国核动力研究设计院 | Supercritical carbon dioxide compressor and coaxial power generation system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110454436A (en) * | 2019-07-29 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of short flexure type eddy plate applied to aero-engine compressor high position bleed |
| CN112576377A (en) * | 2020-12-07 | 2021-03-30 | 中国航发沈阳发动机研究所 | Aeroengine bearing seals bleed structure |
| CN113357189A (en) * | 2021-06-23 | 2021-09-07 | 中国航发湖南动力机械研究所 | Radial outflow impeller back cavity air-entraining structure and gas turbine engine |
| CN115324911A (en) * | 2022-10-12 | 2022-11-11 | 中国核动力研究设计院 | Supercritical carbon dioxide compressor and coaxial power generation system |
| CN115324911B (en) * | 2022-10-12 | 2023-08-22 | 中国核动力研究设计院 | Supercritical carbon dioxide compressor and coaxial power generation system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109578337B (en) | 2020-10-09 |
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