CN113605992B - Gas turbine cooling blade with internal micro-channels - Google Patents
Gas turbine cooling blade with internal micro-channels Download PDFInfo
- Publication number
- CN113605992B CN113605992B CN202110991406.0A CN202110991406A CN113605992B CN 113605992 B CN113605992 B CN 113605992B CN 202110991406 A CN202110991406 A CN 202110991406A CN 113605992 B CN113605992 B CN 113605992B
- Authority
- CN
- China
- Prior art keywords
- blade
- cooling
- rib
- channels
- air flow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 66
- 238000005192 partition Methods 0.000 claims abstract description 41
- 239000002826 coolant Substances 0.000 claims description 6
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine cooling blade with an internal micro-channel, which comprises a blade body, a blade root platform, a cooling cavity, a partition plate channel, a turbulent rib inner channel, an airflow outflow structure and the like. The novel cooling structure increases the local cooling strengthening of the positions of the baffle plates and the turbulent flow ribs, so that the surface temperature of the blade is more uniform, the local temperature gradient of the surface of the blade is further reduced, and meanwhile, the longitudinal collecting channel conveys cooling airflow to the blade top, so that the temperature of the blade top can be reduced, and the leakage flow of the blade top is weakened.
Description
Technical Field
The present invention relates to a gas turbine blade, and in particular to a gas turbine cooling blade having internal microchannels.
Background
The enhanced heat exchange of the spoiler is that the spoiler on the wall surface disturbs the fully developed boundary layer, so that the thickness of the thermal boundary layer is reduced, and the convection heat exchange coefficient is increased. The turbulent fin is the most classical turbulent structure in the intensified heat exchange, and the fin turbulent generator not only increases the effective heat exchange area of the blade cooling channel, but also causes the strong mixing of fluids in different areas inside the channel, and the development of a turbulent boundary layer so as to improve the heat exchange effect. The heat exchange efficiency can be enhanced by arranging the fins in the channels, but the flow resistance of the cold air is increased simultaneously along with the insertion of the fins, and the development of a novel turbulent rib structure with better comprehensive cooling and flow characteristics has important theoretical research significance and engineering application value.
Disclosure of Invention
The object of the present invention is to provide a gas turbine cooling blade having internal micro-channels which improves the cooling effect at the turbulator and baffle by opening the inlet at the intermediate baffle wall while establishing cooling channels in the baffle and turbulator ribs as the cooling air entering from the inlet at the lower part of the blade root flows through the substantially platform location.
The invention is realized by adopting the following technical scheme:
The utility model provides a gas turbine cooling blade with inside microchannel, includes integrated into one piece's blade body and blade root platform, and the inside of blade body is provided with inside cooling chamber, and cooling chamber is by pressure side and suction side of blade body, and leading edge and trailing edge enclose to establish and form, and has offered a plurality of leading edge air film cooling holes on the leading edge, has offered a plurality of trailing edge ventholes on the trailing edge, and the top of blade body is provided with the roof, has offered a plurality of top of blade air film cooling holes on the roof;
The inner surface of the blade body pressure surface is connected with the inner surface of the suction surface through a plurality of partition boards which are longitudinally arranged at intervals, and the first partition board arranged in the cooling cavity divides the air inlet at the lower part of the blade root platform into a plurality of parts which are arranged according to the number of the air inlets at the bottom of the blade; other baffles defining airflow channel areas and travelling paths are arranged between the first baffle and the leading edge and between the first baffle and the trailing edge; the forefront baffle plate is provided with impact holes, and air flow enters the forefront chamber through the impact holes and then enters the main flow through the front air film holes;
A first partition passage for conveying the cooling medium towards the front edge and a second partition passage for conveying the cooling medium towards the tail edge are arranged in the first partition;
A plurality of turbulence ribs which are arranged in parallel are arranged on the inner surface of the blade body pressure surface and the inner surface of the suction surface between the two adjacent clapboards and between the rightmost clapboards and the tail edge; the inside of the turbulence rib is of a hollow structure, the channels in the rib and the baffle channels are of a communication structure, and the other baffles except the first baffle are provided with third baffle channels for connecting the channels in the turbulence ribs at two sides of the baffle; the air flow in the turbulent rib enters a longitudinal air flow collecting channel arranged from bottom to top after passing through the last row of turbulent rib in the direction close to the front edge, and enters the main flow from the top of the blade; after passing through the last row of turbulence ribs in the direction close to the trailing edge, the air enters a longitudinal air flow collecting channel arranged from bottom to top, and enters the main flow from the top of the blade.
A further improvement of the invention is that the air flow enters the first baffle channel and the second baffle channel through a first orifice inlet and a second orifice inlet that are at an acute angle to the direction of the air flow.
The invention is further improved in that the turbulence ribs are ribs with a set included angle with the flow direction of the air flow, and the included angle ranges from 30 degrees to 45 degrees.
The invention is further improved in that the turbulence ribs are W-shaped ribs.
A further development of the invention is that the spoiler ribs are V-shaped ribs.
A further development of the invention is that the spoiler ribs are discontinuous V-shaped ribs.
The invention is further improved in that the turbulence rib is arranged along the rib height direction according to the drawing direction, the connection part with the inner wall surface of the blade is rounded, and the top of the turbulence rib is rounded.
When the blade root cooling device is in operation, after cooling air flow enters from the air inlet at the lower part of the blade root, part of the cooling air flow is conveyed to the top of the blade through the longitudinally arranged internal passage of the middle partition plate, and is diffused towards the front edge and the tail edge respectively through the internal passage of the turbulence rib connected with the internal passage of the middle partition plate, so that the partition plate and the vicinity of the turbulence rib are cooled again.
The invention has at least the following beneficial technical effects:
According to the gas turbine cooling blade with the internal micro-channels, the micro-cooling channels are arranged in the inner partition plates and the turbulent ribs of the blade, part of cooling air flow can flow through each turbulent rib after entering from the air inlet of the middle partition plate, and finally enters the main flow from the front edge and the tail edge respectively, so that the local cooling strengthening of the partition plates and the turbulent ribs is increased, the surface temperature of the blade is more uniform, and the local temperature gradient of the surface of the blade is further reduced.
The longitudinal cooling air flow collecting channels arranged on the leading edge and the trailing edge collect and introduce the cooling air flow from the channels in the turbulence ribs into the blade tip, and can also play a role in cooling the blade tip and blocking leakage flow of the blade tip.
Drawings
FIG. 1 is a longitudinal cross-sectional view of a gas turbine cooling blade having internal microchannels according to the present invention;
FIG. 2 is a three-dimensional schematic view of a gas turbine cooling blade collection channel having internal microchannels according to the present invention;
FIG. 3 is a schematic view of a leading edge collection channel of a gas turbine cooling blade having internal microchannels in accordance with the present invention;
FIG. 4 is a schematic view of a gas turbine cooling blade trailing edge collection channel having internal microchannels according to the present invention;
FIG. 5a is a schematic illustration of one turbulator rib arrangement of a gas turbine cooling blade having an internal microchannel of the present invention, the turbulator rib being a discontinuous V-shaped rib;
FIG. 5b is a schematic view of a turbulator rib arrangement of a gas turbine cooling blade having an internal microchannel of the present invention, the turbulator rib being a V-shaped rib;
FIG. 5c is a schematic view of one turbulator rib arrangement of a gas turbine cooling blade having internal microchannels according to the present invention, the turbulator rib being a W-shaped rib.
Detailed Description
The invention is described in further detail below with reference to the attached drawing figures:
as shown in fig. 1, the gas turbine cooling blade with an internal micro-channel provided by the invention comprises an integrally formed blade body 1 and a blade root platform 2, wherein an internal cooling cavity 3 is arranged in the blade body 1, the cooling cavity 3 is formed by surrounding a pressure surface and a suction surface of the blade body 1, a front edge 4 and a tail edge 5, a plurality of front edge air film cooling holes 401 are formed in the front edge 4, a plurality of tail edge air outlet holes 501 are formed in the tail edge 5, a top plate 6 is arranged at the top of the blade body 1, and a plurality of blade top air film cooling holes 601 are formed in the top plate 6.
The inner surface of the pressure surface and the inner surface of the suction surface of the blade body 1 are connected through a plurality of partition boards which are longitudinally arranged at intervals, and the first partition board 7 arranged in the cooling cavity 3 divides the air inlet at the lower part of the blade root platform 2 into a plurality of parts which are arranged according to the number of the air inlets at the bottom of the blade; other partitions defining an airflow passage area and a traveling path are provided between the first partition 7 and the leading edge 4 and the trailing edge 5; the foremost partition plate is provided with an impact hole 9, air flow enters the foremost cavity 10 through the impact hole 9 and then enters the main flow through the front edge air film hole 401, a first partition plate channel 701 for conveying cooling medium towards the front edge direction and a second partition plate channel 702 for conveying cooling medium towards the tail edge are arranged in the first partition plate 7, and a plurality of turbulence ribs 8 which are arranged in parallel are arranged on the inner surface of the pressure surface and the inner surface of the suction surface of the blade body 1 between the two adjacent partition plates and between the rightmost partition plate and the tail edge 5; the inside of the turbulence rib 8 is of a hollow structure, the channels in the rib and the baffle channels are of a communication structure, and the other baffles except the first baffle are provided with third baffle channels 705 for connecting the channels in the turbulence ribs at the two sides of the baffle; the air flow in the turbulence ribs 8 enters the longitudinal air flow collecting channel 12 arranged from bottom to top after passing through the last row of turbulence ribs in the direction close to the front edge 4, and enters the main flow from the top of the blade; after passing through the last row of turbulence ribs in the direction close to the trailing edge 5, the air enters a longitudinal air flow collecting channel 13 arranged from bottom to top, and enters the main flow from the top of the blade.
After the blade cooling scheme of the invention is adopted, after cooling air flow enters from the air inlet at the lower part of the blade root, part of the air flow is conveyed to the top of the blade through the longitudinally arranged internal passage of the middle partition plate near the height of the blade root platform, and is diffused towards the front edge and the tail edge respectively through the internal passage of the turbulence rib connected with the internal passage of the middle partition plate, so that the partition plate and the vicinity of the turbulence rib are cooled again.
Preferably, the air flow enters the first diaphragm channel 701 and the second diaphragm channel 702 through a first orifice inlet 703 and a second orifice inlet 704 that are at an acute angle to the direction of the air flow.
Preferably, the turbulence ribs 8 are ribs having an angle to the direction of flow of the air flow, the angle being in the range of 30 ° to 45 °.
Preferably, the spoiler rib 8 is a W-shaped rib or a V-shaped rib or an intermittent V-shaped rib.
Preferably, the turbulence rib 8 is arranged along the rib height direction according to the drawing direction, and is rounded at the connection with the inner wall surface of the blade, and is rounded at the top of the turbulence rib.
Fig. 1 is only one form of the designed internal structure, and other types of internal structures are possible without departing from the intention of the invention, and the internal structure is not limited to only two cooling chambers inside the blade, and when other cooling chambers exist, a partition internal channel air inlet is also arranged at the position, close to the platform height, of an air inlet channel of each cooling chamber, so that the air flow of the partition channel is conveyed upwards to each adjacent turbulence rib. Fig. 2 to fig. 4 are schematic views of collecting channels of the internal micro-channels, and in practical application, cooling air flow collecting channels are arranged on the pressure surface and the suction surface. The turbulence ribs may also have a shape which is only three of the variations shown in figures 5a, 5b and 5 c.
When introducing elements of various embodiments of the present invention, the articles "a," "an," "the," and "said" are intended to mean that there are one or more of the elements, be "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements other than the listed elements.
The embodiments described in the present invention are only intended to be examples, and should not be construed as limiting the scope of the invention, and other equivalent variations according to the invention fall within the scope of the invention.
Claims (6)
1. The utility model provides a gas turbine cooling blade with inside microchannel, a serial communication port, including integrated into one piece's blade body (1) and blade root platform (2), the inside of blade body (1) is provided with inside cooling chamber (3), cooling chamber (3) are enclosed by pressure face and suction face of blade body (1), and leading edge (4) and trailing edge (5) and establish, and set up a plurality of leading edge air film cooling hole (401) on leading edge (4), set up a plurality of trailing edge ventholes (501) on trailing edge (5), the top of blade body (1) is provided with roof (6), set up a plurality of top air film cooling hole (601) on roof (6);
The inner surface of the pressure surface and the inner surface of the suction surface of the blade body (1) are connected through a plurality of partition plates which are longitudinally arranged at intervals, and a first partition plate (7) arranged in the cooling cavity (3) divides an air inlet at the lower part of the blade root platform (2) into a plurality of parts which are arranged according to the number of air inlets at the bottom of the blade; other partitions defining an airflow passage area and a traveling path are arranged between the first partition (7) and the leading edge (4) and the trailing edge (5); the forefront partition plate is provided with an impact hole (9), and air flow enters the forefront chamber (10) through the impact hole (9) and then enters the main flow through the front air film hole (401);
A first partition passage (701) for conveying the cooling medium in the direction of the leading edge and a second partition passage (702) for conveying the cooling medium to the trailing edge are arranged in the first partition (7);
A plurality of turbulence ribs (8) which are arranged in parallel are arranged on the inner surface of the pressure surface and the inner surface of the suction surface of the blade body (1) between two adjacent partition boards and between the rightmost partition board and the tail edge (5); the inside of the turbulence rib (8) is of a hollow structure, the channels in the rib and the baffle channels are of a communication structure, and the other baffles except the first baffle are provided with third baffle channels (705) for connecting the inner channels of the turbulence ribs on two sides of the baffle; the air flow in the turbulence ribs enters a longitudinal air flow collecting channel (12) arranged from bottom to top after passing through the last row of turbulence ribs in the direction close to the front edge (4), and enters the main flow from the top of the blade; after passing through the last row of turbulence ribs in the direction close to the tail edge (5), the air enters a longitudinal air flow collecting channel (13) arranged from bottom to top, and enters the main flow from the top of the blade;
the air flow enters the first partition board channel (701) and the second partition board channel (702) through a first hole inlet (703) and a second hole inlet (704) which form an acute angle with the air flow direction;
When the cooling device works, after cooling air flow enters from the air inlet at the lower part of the blade root, part of the cooling air flow is conveyed to the top of the blade through the inner channel of the middle partition plate which is longitudinally arranged near the height of the blade root platform, and is diffused towards the front edge and the tail edge respectively through the inner channel of the turbulence rib which is connected with the cooling air flow, so that the cooling device is used for cooling the partition plate and the vicinity of the turbulence rib again.
2. A gas turbine cooling blade with internal micro-channels according to claim 1, characterized in that the turbulence ribs (8) are ribs with a set angle to the flow direction of the gas flow, which angle is in the range of 30 ° to 45 °.
3. A gas turbine cooling blade with internal micro-channels according to claim 1, characterized in that the turbulator rib (8) is a W-shaped rib.
4. A gas turbine cooling blade with internal micro-channels according to claim 1, characterized in that the turbulator rib (8) is a V-shaped rib.
5. A gas turbine cooling blade with internal micro-channels according to claim 1, characterized in that the turbulating ribs (8) are intermittent V-shaped ribs.
6. A gas turbine cooling blade with internal micro-channels according to claim 1, characterized in that the turbulator rib (8) is set up in the rib height direction according to the draft direction and rounded at the connection with the inner wall surface of the blade and rounded at the top of the turbulator rib.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110991406.0A CN113605992B (en) | 2021-08-26 | 2021-08-26 | Gas turbine cooling blade with internal micro-channels |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110991406.0A CN113605992B (en) | 2021-08-26 | 2021-08-26 | Gas turbine cooling blade with internal micro-channels |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113605992A CN113605992A (en) | 2021-11-05 |
| CN113605992B true CN113605992B (en) | 2024-08-27 |
Family
ID=78309459
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110991406.0A Active CN113605992B (en) | 2021-08-26 | 2021-08-26 | Gas turbine cooling blade with internal micro-channels |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113605992B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114961874A (en) * | 2022-04-22 | 2022-08-30 | 上海大学 | Aeroengine air cooling turbine blade reinforced cooling structure |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN215633158U (en) * | 2021-08-26 | 2022-01-25 | 华能国际电力股份有限公司 | Turbine cooling blade of gas turbine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS62271902A (en) * | 1986-01-20 | 1987-11-26 | Hitachi Ltd | Cooled blade for gas turbine |
| CH700321A1 (en) * | 2009-01-30 | 2010-07-30 | Alstom Technology Ltd | Cooled vane for a gas turbine. |
| CN104791020B (en) * | 2015-04-23 | 2016-06-15 | 华能国际电力股份有限公司 | Gas turbine blade with longitudinal crossed rib cooling structure |
| CN205876398U (en) * | 2016-07-07 | 2017-01-11 | 张雯 | Gas turbine blade with vertical crossing rib cooling structure |
| CN113236370B (en) * | 2021-05-25 | 2023-04-25 | 杭州汽轮动力集团有限公司 | Cooling structure of high-pressure moving blade of gas turbine |
-
2021
- 2021-08-26 CN CN202110991406.0A patent/CN113605992B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN215633158U (en) * | 2021-08-26 | 2022-01-25 | 华能国际电力股份有限公司 | Turbine cooling blade of gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113605992A (en) | 2021-11-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104791020B (en) | Gas turbine blade with longitudinal crossed rib cooling structure | |
| CN103967621B (en) | There is the refrigerating unit of small diagonal rib-depression composite structure | |
| EP2616641B1 (en) | Turbine component cooling channel mesh with intersection chambers | |
| CN104617352B (en) | Heat radiation method and device for built-in electromobile battery pack | |
| CN215633158U (en) | Turbine cooling blade of gas turbine | |
| CN1318735C (en) | Pulsing impact cooling blade for gas turbine engine | |
| CN111764967A (en) | Turbine blade trailing edge cooling structure | |
| CN113513372B (en) | Double-wall turbine guide blade with small air guiding amount | |
| CN112177681B (en) | Fractal intermittent rib structure suitable for internal cooling of turbine blade | |
| CN113605992B (en) | Gas turbine cooling blade with internal micro-channels | |
| CN202023597U (en) | Shrouded cooling blade of gas turbine | |
| CN109751090A (en) | Guide vane and nozzle ring with it | |
| CN114109515B (en) | Turbine blade suction side cooling structure | |
| CN208380634U (en) | Gas turbine blade with large and small rib alternative cooling structure | |
| CN114109514B (en) | Turbine blade pressure surface cooling structure | |
| CN209354202U (en) | A kind of low-pressure turbine guide vane | |
| CN204609950U (en) | Gas turbine blade with longitudinal crossed rib cooling structure | |
| CN216204482U (en) | High-efficient heat exchanger that phase transition cooling system used | |
| CN216642214U (en) | High-blockage-ratio finned laminate cooling structure for middle chord area of turbine blade | |
| CN114922734B (en) | Uniform temperature rectification support plate hot gas anti-icing structure based on rib column partition turbulence | |
| CN216204483U (en) | Phase-change cooling heat exchanger | |
| CN216788487U (en) | Air film hole turbine blade with flow guide structure | |
| CN114382553A (en) | High-blockage-ratio rib laminate cooling structure and cooling method for middle chord area of turbine blade | |
| CN112746872B (en) | Through continuous folded plate structure suitable for tail edge part of turbine blade | |
| CN113624042A (en) | Phase-change cooling heat exchanger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |