CN110714803B - Cooling heat insulation plate and turbine heat insulation structure - Google Patents
Cooling heat insulation plate and turbine heat insulation structure Download PDFInfo
- Publication number
- CN110714803B CN110714803B CN201910816360.1A CN201910816360A CN110714803B CN 110714803 B CN110714803 B CN 110714803B CN 201910816360 A CN201910816360 A CN 201910816360A CN 110714803 B CN110714803 B CN 110714803B
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- Prior art keywords
- cooling
- flow passage
- spiral
- heat insulation
- casing
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- 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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Classifications
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
- F01K7/32—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or overcritical pressure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a cooling heat insulation plate and a turbine heat insulation structure. A cooling insulation tray comprising: the block-shaped body is provided with a shaft hole for the rotor to pass through; a cooling flow passage is formed in the block-shaped body, and two ends of the cooling flow passage are communicated with an external cooling auxiliary device to form circulation; the cooling flow passage comprises a spiral flow passage which is in a spiral shape and is positioned on the same plane. The turbine heat insulation structure comprises the cooling heat insulation disc, wherein the cooling heat insulation disc is arranged between the volute and the casing, and the rotor penetrates through the shaft hole. The cooling heat-insulating disk has the cooling flow passage, so that the cooling heat-insulating disk can play a role in heat insulation and cooling when a cooling medium is introduced into the cooling flow passage, and when the cooling heat-insulating disk is arranged between the volute and the casing, the temperature at the casing is prevented from being higher than the highest working temperature of the sealing assembly, and the service life of the sealing assembly is prolonged.
Description
Technical Field
The invention relates to the field of cooling structure design of turbines, in particular to a cooling heat insulation plate and a turbine heat insulation structure.
Background
The supercritical carbon dioxide Brayton cycle power generation technology is a closed cycle turbine power generation technology adopting supercritical carbon dioxide as a working medium, and is a leading edge technology which is rapidly developed in recent years. The high density characteristic of supercritical carbon dioxide can greatly reduce the size of the compressor and the turbine, so that the structure of the impeller mechanical component is compact, but because the temperature of the supercritical carbon dioxide is higher, the temperature of the volute is also higher, if heat is transferred to the adjacent casing, the temperature of the casing exceeds the limit temperature of the normal operation of the sealing assembly in the casing, and the service life of the sealing assembly is further reduced.
Disclosure of Invention
The invention aims to provide a cooling heat insulation plate and a turbine heat insulation structure, wherein the cooling heat insulation plate is applied between a volute and a casing of a turbine, reduces heat transfer from the volute to the casing, ensures that the casing is at a proper working temperature, ensures that the temperature at the volute does not drop too much, and ensures the performance of the whole unit. The service life of the sealing component is longer and the performance of the whole unit is better.
The technical scheme provided by the invention is as follows:
a cooling insulating tray comprising: the block-shaped body is provided with a shaft hole for the rotor to pass through; a cooling flow passage is formed in the block-shaped body, and two ends of the cooling flow passage are communicated with an external cooling auxiliary device to form circulation; the cooling flow path includes a spiral flow path that is spiral.
In the above-mentioned structure, through setting up into cooling channel in the cubic body, and the cooling runner includes spiral runner of spiral, when cooling auxiliary device lets in coolant in to the cooling runner, the cold volume can be transmitted to the cubic body from the cooling runner, and then when this cooling heat-proof dish sets up between spiral case and the receiver of turbine, can take away the partial heat of coming from spiral case department transfer to guarantee that the temperature of receiver department is in seal assembly's the highest operating temperature, guarantee seal assembly's normal work, extension seal assembly's life.
Preferably, the helical flow passage is tapered in a perpendicular distance from the axis of the rotor along the extending direction thereof.
Preferably, the spiral flow channels lie on the same plane.
Preferably, the cooling flow passage further comprises an inlet flow passage through which the first end of the spiral flow passage communicates with an external cooling aid.
Preferably, the inlet flow channel is on the same plane as the spiral flow channel.
Preferably, the cooling flow passage further comprises an outlet flow passage, the second end of the spiral flow passage is communicated with an external cooling auxiliary device through the outlet flow passage, the outlet flow passage is linear, and the outlet flow passage and the spiral flow passage are not on the same plane.
Preferably, a plurality of cooling flow passages are arranged in the block-shaped body, and the plurality of cooling flow passages are arranged along the axial direction of the shaft hole.
In the above-described structure, the heat insulating effect of the cooling heat insulating disk can be improved by providing the plurality of cooling flow passages in the block-shaped body.
Preferably, the cooling flow channel comprises a plurality of spiral flow channels, the plurality of spiral flow channels are located in the same plane, and all the spiral flow channels are communicated at least two by two.
A turbine heat insulation structure comprising the cooling heat insulation plate is arranged between a volute and a casing, and a rotor passes through a shaft hole.
The cooling heat-insulating disc is arranged between the volute and the casing, so that heat at the volute can be prevented from flowing into the casing through the cooling heat-insulating disc, the temperature at the casing is ensured to be within the highest working temperature of the sealing assembly, the normal working of the sealing assembly is ensured, and the service life of the sealing assembly is prolonged.
Preferably, the volute, the cooling heat insulation plate and the casing are detachably connected through bolts.
The volute, the cooling heat insulation plate and the casing are detachably connected, so that the replacement and the maintenance are convenient.
The cooling heat insulation plate and the turbine heat insulation structure provided by the invention can bring the following beneficial effects:
the cooling heat-insulating disk has the cooling flow passage, so that the cooling heat-insulating disk can play a role in heat insulation and cooling when a cooling medium is introduced into the cooling flow passage, and when the cooling heat-insulating disk is arranged between the volute and the casing, the temperature at the casing can be prevented from being higher than the highest working temperature of the sealing assembly, and the service life of the sealing assembly is prolonged.
Drawings
The above-mentioned features, technical features, advantages and implementation of the cooling insulation disk and turbine insulation structure will be further described in a clear and understandable manner by describing preferred embodiments with reference to the accompanying drawings.
FIG. 1 is a cross-sectional view of a cooling insulation tray taken along a direction perpendicular to an axis;
FIG. 2 is a front view of a cooling flow path;
FIG. 3 is a side view of FIG. 2;
FIG. 4 is a schematic structural view of a turbine insulation structure.
Reference numerals illustrate:
the device comprises a spiral casing, a 1 a-fixed counter bore, a 2-casing, a 2 a-second fixed hole, a 3-cooling heat insulation disc, a 3 a-shaft hole, a 3 b-first fixed hole, a 4-cooling runner, a 4 a-spiral runner, a 4 b-inlet runner and a 4 c-outlet runner.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will explain the specific embodiments of the present invention with reference to the accompanying drawings. It is evident that the drawings in the following description are only examples of the invention, from which other drawings and other embodiments can be obtained by a person skilled in the art without inventive effort.
For simplicity of the drawing, only the parts relevant to the present invention are schematically shown in each drawing, and they do not represent the actual structure thereof as a product.
[ example 1 ]
As shown in fig. 1 to 3, embodiment 1 discloses a specific embodiment of a cooling insulation tray, comprising: the block-shaped body is provided with a shaft hole 3a for the rotor to pass through.
As shown in fig. 1, a cooling flow passage 4 is provided in the block-shaped body, the cooling flow passage 4 is wound on the outer side of the shaft hole 3a, and both ends of the cooling flow passage 4 are communicated with an external cooling auxiliary device to form a circulation. As shown in fig. 2 to 3, the cooling flow path 4 includes a spiral flow path 4a having a spiral shape, an inlet flow path 4b and an outlet flow path 4c, the spiral flow path 4a is located on the same plane, the vertical distance between the spiral flow path 4a and the axis of the rotor along the extending direction thereof is gradually reduced, the first end of the spiral flow path 4a is communicated with an external cooling auxiliary device through the inlet flow path 4b, and the inlet flow path 4b is located on the same plane as the spiral flow path 4 a. The second end of the spiral flow channel 4a is communicated with an external cooling auxiliary device through an outlet flow channel 4c, the outlet flow channel 4c is linear, and the outlet flow channel 4c and the spiral flow channel 4a are not on the same plane.
The cooling auxiliary device is respectively communicated with the inlet runner 4b and the outlet runner 4c, the cooling auxiliary device can convey cooling medium to the inlet runner 4b, then the cooling medium flows through the spiral runner 4a and enters the outlet runner 4c, then the outlet runner 4c flows back to the cooling auxiliary device again to form circulation, and the flowing direction of the cooling medium can be shown by arrows in fig. 1-2. Naturally, the cooling medium in the cooling aid can also enter through the outlet flow channel 4c and then exit through the inlet flow channel 4b, with the same effect.
Note that the shapes of the outlet flow passage 4c and the inlet flow passage 4b are not limited to this example, as long as the spiral flow passage 4a can circulate the cooling medium, and the others are not limited.
[ example 2 ]
As shown in fig. 1, in embodiment 2, on the basis of embodiment 1, 2 cooling flow channels 4 are provided in the block-shaped body of embodiment 2, the cooling flow channels 4 are wound on the outer side of the shaft hole 3a, and the 2 cooling flow channels 4 are arranged along the axial direction of the shaft hole 3a, and the inlet flow channel 4b and the outlet flow channel 4c of each cooling flow channel 4 are all communicated with an external cooling auxiliary device, wherein the flow directions of the cooling mediums in the two cooling flow channels 4 can be the same or opposite, the heat insulation cooling effect of the cooling heat insulation disc 3 can be realized, and compared with the technical scheme of embodiment 1 with only 1 cooling flow channel, the heat insulation effect of the cooling heat insulation disc 3 of this embodiment is better.
In other embodiments, the number of the cooling channels 4 in the block-shaped body can be other, and the larger the number is, the better the heat insulation effect is, and the selection can be made according to practical situations.
[ example 3 ]
Example 3 discloses another embodiment of a cooling insulating tray comprising: the block-shaped body is provided with a shaft hole for the rotor to pass through.
The cooling channel is arranged in the block-shaped body, the cooling channel is wound on the outer side of the shaft hole, and two ends of the cooling channel are communicated with an external cooling auxiliary device to form circulation. The cooling flow channel comprises 2 spiral flow channels, 1 inlet flow channel and 2 outlet flow channels, wherein the 2 spiral flow channels are all positioned on the same plane, the first end of the 1 st spiral flow channel is communicated with an external cooling auxiliary device through the inlet flow channel, and the inlet flow channel and the 1 st spiral flow channel are positioned on the same plane. The second end of the 1 st spiral flow passage is communicated with an external cooling auxiliary device through the 1 st outlet flow passage, the outlet flow passage is linear, and the outlet flow passage and the 1 st spiral flow passage are not on the same plane.
The first end of the 2 nd spiral flow passage is communicated with the 1 st spiral flow passage, so that the first end of the 2 nd spiral flow passage is communicated with the cooling auxiliary device through the 1 st spiral flow passage and the inlet flow passage of the 1 st spiral flow passage, and the second end of the 2 nd spiral flow passage is communicated with the 2 nd outlet flow passage and is communicated with the cooling auxiliary device through the 2 nd outlet flow passage.
The cooling auxiliary device can convey cooling medium to the inlet flow channel, then the cooling medium flows through the spiral flow channel and then enters the outlet flow channel, and then the outlet flow channel flows back to the cooling auxiliary device to form circulation. Naturally, the cooling medium in the cooling aid can also enter through the outlet flow channel 4c and then flow out through the inlet flow channel, with the same effect.
It should be noted that the shapes of the outlet flow passage and the inlet flow passage are not limited to this example, as long as the spiral flow passage can circulate the cooling medium, and the others are not limited.
In other specific embodiments, the number of spiral channels may be multiple, and all the spiral channels may be two-to-two, three-to-three, two-to-three, etc., so that the multiple spiral channels are located in the same plane, which is not described herein.
[ example 4 ]
As shown in fig. 1 to 4, embodiment 4 discloses a turbine heat insulation structure including any one of the cooling heat insulation plates 3 of the foregoing embodiments 1 to 3.
Specifically, as shown in fig. 4, the cooling and heat insulating disk 3 is provided between the scroll 1 and the casing 2 and the rotor passes through the shaft hole 3a. The spiral case 1, the cooling heat insulation plate 3 and the casing 2 are detachably connected through a plurality of bolts or screws, and the bolts or screws can be uniformly distributed along the circumferential direction of the cooling heat insulation plate 3, so that the relative fixation of the three is realized. Namely, a fixed counter bore 1a is arranged on the volute 1, a first fixed hole 3b is arranged on the block-shaped body, a second fixed hole 2a is arranged on the casing 2, and bolts sequentially pass through the second fixed hole 2a and the first fixed hole 3b and are fixedly connected with the fixed counter bore 1 a.
In other embodiments, the spiral case 1, the casing 2 and the cooling insulation plate 3 may be fixedly connected by welding, which is not described herein.
During practical application, the cooling auxiliary device is used for introducing cooling medium into the cooling flow channel 4 in the cooling heat insulation disc 3, so that the cooling heat insulation disc 3 has heat insulation and cooling functions, heat at the volute 1 is reduced and transferred to the casing 2, the temperature at the casing 2 is prevented from being higher, the temperature of the casing 2 is kept below the highest working temperature of the sealing assembly in the casing 2, and the service life of the sealing assembly is prolonged.
It should be noted that the above embodiments can be freely combined as needed. The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.
Claims (5)
1. A cooling insulation tray for a turbine, wherein heat transfer between a volute and a gate at the volute is reduced to the gate, comprising:
the block-shaped body is provided with a shaft hole for the rotor to pass through;
a cooling flow passage is formed in the block-shaped body, and two ends of the cooling flow passage are communicated with an external cooling auxiliary device to form circulation;
the cooling flow channel comprises a spiral flow channel which is spiral; a plurality of cooling flow channels are arranged in the block-shaped body, and are distributed along the axial direction of the shaft hole;
the cooling flow passage further comprises an inlet flow passage, and the first end of the spiral flow passage is communicated with an external cooling auxiliary device through the inlet flow passage; the inlet flow channel and the spiral flow channel are on the same plane; the cooling runner further comprises an outlet runner, the second end of the spiral runner is communicated with an external cooling auxiliary device through the outlet runner, the outlet runner is linear and the outlet runner and the spiral runner are not on the same plane.
2. The cooling insulation tray of claim 1, wherein:
the spiral flow passage is gradually reduced in a perpendicular distance from the axis of the rotor along the extending direction thereof.
3. The cooling insulation tray of claim 1, wherein:
the spiral flow channels are located on the same plane.
4. A turbine insulation structure comprising the cooling insulation tray according to any one of claims 1 to 3, characterized in that:
the cooling heat insulation disc is arranged between the volute and the casing, and the rotor penetrates through the shaft hole.
5. The turbine insulation structure of claim 4, wherein:
the spiral case, the cooling heat insulation plate and the casing are detachably connected through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910816360.1A CN110714803B (en) | 2019-08-30 | 2019-08-30 | Cooling heat insulation plate and turbine heat insulation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910816360.1A CN110714803B (en) | 2019-08-30 | 2019-08-30 | Cooling heat insulation plate and turbine heat insulation structure |
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| Publication Number | Publication Date |
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| CN110714803A CN110714803A (en) | 2020-01-21 |
| CN110714803B true CN110714803B (en) | 2023-08-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910816360.1A Active CN110714803B (en) | 2019-08-30 | 2019-08-30 | Cooling heat insulation plate and turbine heat insulation structure |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113804045A (en) * | 2020-06-15 | 2021-12-17 | 拓荆科技股份有限公司 | Temperature control device with reducing flow channel and semiconductor production equipment |
| CN114810228B (en) * | 2022-03-18 | 2024-07-02 | 哈尔滨工业大学 | A compact high-temperature fuel cracking gas power generation turbine seal cooling structure |
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| JPH0932761A (en) * | 1995-07-19 | 1997-02-04 | Tokico Ltd | Scroll type fluid machinery |
| JPH10153678A (en) * | 1996-11-25 | 1998-06-09 | Hitachi Ltd | Reactor isolation cooling system |
| US7544044B1 (en) * | 2006-08-11 | 2009-06-09 | Florida Turbine Technologies, Inc. | Turbine airfoil with pedestal and turbulators cooling |
| CN101050727A (en) * | 2007-05-09 | 2007-10-10 | 韩培洲 | Medium cooling isobaric backheating gas turbine |
| CN102611223A (en) * | 2012-03-20 | 2012-07-25 | 中科盛创（青岛）电气有限公司 | Water cooling structure of axial magnetic flux permanent-magnet wind driven generator |
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| CN110714803A (en) | 2020-01-21 |
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