CN112177681A - Fractal intermittent rib structure suitable for internal cooling of turbine blade - Google Patents
Fractal intermittent rib structure suitable for internal cooling of turbine blade Download PDFInfo
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- CN112177681A CN112177681A CN202010992833.6A CN202010992833A CN112177681A CN 112177681 A CN112177681 A CN 112177681A CN 202010992833 A CN202010992833 A CN 202010992833A CN 112177681 A CN112177681 A CN 112177681A
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- discontinuous
- fractal
- ribs
- cooling
- interrupted
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- 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
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a fractal interrupted rib structure suitable for cooling the interior of a turbine blade, belonging to the technical field of cooling of high-temperature turbine blades of gas turbines; fractal intermittent ribs are arranged in the cooling channel in the blade, and each fractal intermittent rib comprises a plurality of fractal periods which are uniformly distributed along the length direction of the wall surface at the bottom of the cooling channel; each fractal period consists of four rows of interrupted ribs, and each row of interrupted ribs consists of interrupted ribs and interrupted areas; the number of the discontinuous ribs and the discontinuous areas of each row of the discontinuous ribs gradually increases along the airflow direction in a fractal period. The discontinuous ribs can reduce the blockage rate of the fluid and reduce the pressure loss in the channel; secondly, the discontinuous area of the discontinuous rib can generate transverse vortex, the turbulent flow effect on the air flow is enhanced, the mixing of the main flow and the boundary layer fluid is enhanced, the turbulence degree of the fluid is increased, and thus the heat exchange is enhanced; and thirdly, transverse vortexes induced by the discontinuous areas appear in the downstream areas of the fins, so that a backflow area behind the fins is reduced, and heat exchange is enhanced.
Description
Technical Field
The invention belongs to the technical field of cooling of high-temperature turbine blades of gas turbines, and particularly relates to a fractal intermittent rib structure suitable for cooling the interior of a turbine blade.
Background
The gas turbine is a thermal power device, is widely applied to the fields of aviation propulsion, ship power, land power generation, industrial driving, distributed energy supply and the like by virtue of a series of advantages of small volume, high power, high efficiency, cleanness, good economy and the like, and plays a vital role in national economy and safety. With the high-speed development of national socioeconomic, the gas turbine has huge market potential, and the vigorous development of the gas turbine industry not only has obvious influence on the basic industry and high-end manufacturing industry of China, but also has important significance on enhancing the economic strength, the scientific and technological strength, the national defense strength and the national cohesion of China.
The thermal efficiency and output power of a gas turbine are important indexes for evaluating the working performance of the gas turbine, and with the wide application of the gas turbine, the improvement of the thermal efficiency and output power of the gas turbine becomes more urgent. To increase the efficiency and stability of a gas turbine, increasing the turbine front inlet gas temperature is one of the key indices to improve gas turbine performance. Research shows that the thrust of the gas turbine can be improved by 8 to 13 percent and the cycle efficiency can be improved by 2 to 4 percent when the temperature of the gas at the front inlet of the turbine is improved by 56 ℃. However, the two requirements of increasing the turbine front inlet gas temperature and extending the turbine blade service time are conflicting. The gas temperature of the turbine front inlet of the modern advanced gas turbine is up to 2000K, which far exceeds the melting point of the high-temperature material for manufacturing the turbine blade. In addition, turbine forward port gas temperatures have increased year by year as the gas turbine service performance requirements have increased. Although the heat resistance of the material is gradually excellent along with the development of material science, the improvement of the gas inlet temperature of the gas turbine can not be compensated. Therefore, it is imperative to develop efficient turbine blade cooling techniques to reduce blade temperatures and extend their service life.
Internal convection cooling is the primary cooling means for the internal passages of the turbine blade. The fins are main heat exchange strengthening structures applied to the internal channels, and the fins can increase the heat transfer area, reduce the heat resistance of convective heat transfer and enhance the heat exchange performance. Interrupted ribs have been widely studied and used because of their ability to reduce the pressure loss of the continuous rib channels. Through the search of prior art documents, Chinese patent application No. 201910344045.3, patent publication date 2019, 7 and 23 days, patent name: the utility model provides an interrupted rib internal cooling structure for gas turbine blade, this patent sets up U type fork wall at blade major structure, all sets up between lateral wall and U type fork wall and is interrupted the rib to it sets up in pairs to be interrupted the rib. The disturbance generated by the cooling mode to the gas flow is enhanced, so that the separation degree generated by the gas flow is increased, the turbulence degree of the fluid is enhanced, the heat exchange is enhanced, and the pressure loss is reduced. However, because the discontinuous ribs are arranged in pairs in the structure, the fluid in the middle area of the inner channel is not disturbed, so that a low heat exchange area is formed in the middle of the channel, and the uniformity of heat exchange in the channel is reduced.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides the fractal intermittent rib structure suitable for cooling the interior of the turbine blade, and the fractal intermittent rib is arranged in the cooling channel, and the layout of the intermittent rib is optimized, so that the structure has high and uniform convection heat exchange performance, low pressure loss and high overall thermal performance.
The technical scheme of the invention is as follows: a fractal interrupted rib structure suitable for internal cooling of turbine blades is characterized in that: fractal intermittent ribs are arranged in the cooling channel in the blade, and each fractal intermittent rib comprises a plurality of fractal periods which are uniformly distributed along the length direction of the wall surface at the bottom of the cooling channel; each fractal period consists of four rows of interrupted ribs, each row of interrupted ribs consists of interrupted fins and interrupted areas, and the interrupted areas are gaps between two adjacent interrupted fins; the number of the discontinuous ribs and the discontinuous areas of each row of the discontinuous ribs gradually increases along the airflow direction in a fractal period.
The further technical scheme of the invention is as follows: two ends of each row of the interrupted ribs are respectively attached to the side wall surface of the cooling channel by the interrupted fins, and the interrupted areas are positioned in the cooling channel.
The further technical scheme of the invention is as follows: the discontinuous regions of four rows of discontinuous ribs of the fractal cycle form a fractal structure along the airflow direction, and the number of the discontinuous regions of the four rows of discontinuous ribs is 20 and 2 in sequence1，22，23。
The further technical scheme of the invention is as follows: the total lengths of the discontinuous ribs in each row of discontinuous ribs in the fractal cycle are equal, and the total lengths of the discontinuous areas in each row of discontinuous ribs are equal.
The further technical scheme of the invention is as follows: the total length of the discontinuous region of each row of discontinuous ribs in the fractal cycle is L, the width of the cooling channel is W, and L is more than or equal to 0.2W and less than or equal to 0.5W.
The further technical scheme of the invention is as follows: the section of each intermittent rib is in any shape, and each row of intermittent ribs is perpendicular to the wall surface of the right side in the cooling channel or forms an included angle of 30-90 degrees.
The further technical scheme of the invention is as follows: the height of the interrupted rib is e, the distance between two adjacent rows of interrupted ribs along the flow direction is P, and the requirement that P/e is more than or equal to 8 and less than or equal to 15 is met.
The further technical scheme of the invention is as follows: when the internal height of the cooling channel is H, the requirement that e/H is more than or equal to 0.1 and less than or equal to 0.3 is met.
Advantageous effects
The invention has the beneficial effects that: firstly, the discontinuous ribs can reduce the blockage rate of fluid and reduce the pressure loss in the channel; secondly, the discontinuous area of the discontinuous rib can generate transverse vortex, the turbulent flow effect on the air flow is enhanced, the mixing of the main flow and the boundary layer fluid is enhanced, the turbulence degree of the fluid is increased, and thus the heat exchange is enhanced; thirdly, transverse vortexes induced by the discontinuous areas appear in the downstream areas of the fins, so that a backflow area behind the fins is reduced, and heat exchange is enhanced; most importantly, compared with the prior art documents, chinese patent application No. 201910344045.3, patent publication date 2019, 7 and 23, patent name: compared with an internal cooling structure of an interrupted rib for a turbine blade of a gas turbine, the internal cooling structure of the interrupted rib for the turbine blade of the gas turbine adopts a fractal principle to arrange the interrupted rib, four rows of interrupted ribs are used as a fractal period, the number of interrupted areas is set in an exponential increasing mode, and on the premise of ensuring that the processing is easy, continuous disturbance can be generated on fluid along the flow direction, and the heat exchange of a channel is strengthened. In addition, the total length of the interrupted ribs of each row of interrupted ribs is equal, and the total length of the interrupted areas is equal, so that the cooling channel can be ensured to have better temperature uniformity. The total length L of the discontinuous region of each row of discontinuous ribs meets the range that L is more than or equal to 0.2W and less than or equal to 0.5W, and the heat exchange of the channel can be strengthened on the premise of reducing the pressure loss in the channel. Therefore, the fractal intermittent rib structure suitable for cooling the interior of the turbine blade has the advantages of high and uniform convection heat exchange performance, low pressure loss, high overall thermal performance and the like.
Drawings
FIG. 1 is a schematic view of the structure of example 1 of the present invention with the top wall removed;
FIG. 2 is a top view of example 1 of the present invention with the top wall removed;
FIG. 3 is a front view of embodiment 1 of the present invention with the right side wall removed;
FIG. 4 is a front view of embodiment 2 of the present invention with the right side wall removed;
FIG. 5 is a top view of example 3 of the present invention with the top wall removed;
description of reference numerals: in the figure: 1. the cooling structure comprises a left side wall face, a right side wall face, a bottom wall face, a 4-discontinuous area, 5-discontinuous ribs, 6-fractal period, W, width of a cooling channel and total length of each row of discontinuous areas, wherein L is more than or equal to 0.2W and less than or equal to 0.5W, P is a distance between two adjacent rows of discontinuous ribs along the flowing direction, e is the height of the discontinuous ribs, P/e is more than or equal to 8 and less than or equal to 15, H is the internal height of the cooling channel, and e/H is more than or equal to 0.1 and less than or equal to 0.3.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
The invention provides a fractal interrupted rib structure suitable for internal cooling of a turbine blade, wherein a cooling channel in the blade comprises a top wall surface, a left side wall surface 1, a right side wall surface 2 and a bottom wall surface 3, the fractal interrupted rib comprises a plurality of interrupted ribs 5 and a plurality of interrupted areas 4, and the interrupted ribs are placed in the internal cooling channel with the width W and the height H. Wherein the height of the interrupted rib is e, and the interval between every two adjacent rows of interrupted ribs is P along the flow direction.
All the intermittent ribs are arranged in the inner cooling channel in a fractal cycle 6 mode, each fractal cycle comprises four rows of intermittent ribs, specifically, in the flowing direction of the fluid, a first row of intermittent ribs has 20 intermittent areas and is positioned in the center of the channel, and a second row of intermittent ribs has 21A third row of interrupted ribs having 22A fourth row of interrupted ribs having 23A discontinuous region. The total length of each row of the discontinuous regions is L, and L is more than or equal to 0.2W and less than or equal to 0.5W, and the discontinuous regions of the four rows of discontinuous ribs form a fractal structure.
Fig. 1 to 3 show embodiment 1 of the present invention. In this embodiment, the cross-sectional shape of the interrupted rib is square, and the width of the interrupted rib is equal to the height e of the interrupted rib. After the cold fluid enters the internal channel, one part of the cold fluid flows into the discontinuous area, two sides of the discontinuous area respectively form a transverse vortex to be attached to the rear parts of the two discontinuous ribs, the other part of the cold fluid flows through the fins, backflow areas are generated at the upstream and the downstream of the fins, and the reattachment phenomenon is generated between two adjacent rows of fins. Due to the existence of the discontinuous area, the flow resistance of the fluid is reduced, and the transverse vortex induced by the discontinuous area not only increases the turbulence degree of the fluid and strengthens the mixing of the main flow in the boundary layer fluid, but also is attached to the rear part of the rib, so that the backflow area behind the rib is reduced, the heat exchange is strengthened, and the overall thermal performance of the channel is improved. In addition, the discontinuous ribs are arranged in a fractal structure mode in the flow direction, continuous disturbance is caused to the incoming flow, and the continuously increased discontinuous areas are beneficial to improving the uniformity of channel heat exchange. The experimental results show that when the cold fluid Reynolds number is 20000, the pressure loss of the embodiment is reduced by 27.59%, the heat exchange is increased by 0.1% and the overall thermal performance is improved by 38.21% relative to the pressure loss of the straight rib channel.
Fig. 4 shows example 2 of the present invention. In this embodiment, the cross-sectional shape of the interrupted rib is an isosceles right triangle with a side length of e, and the right-angle side of the rib faces the incoming flow direction. The cold fluid enters the internal channel, a part of the cold fluid flows into the discontinuous area, a transverse vortex is formed on two sides of the discontinuous area and attached to the rear of the two discontinuous ribs, the other part of the cold fluid flows through the fins, and backflow areas are formed on the upstream and the downstream of the fins. Due to the existence of the discontinuous region, the flow resistance of the fluid is reduced, the turbulence degree of the fluid is increased by the transverse vortex induced by the discontinuous region, the mixing of the main flow and the fluid of the boundary layer is enhanced, the heat exchange is enhanced, and the overall thermal performance of the channel is improved. In addition, the discontinuous ribs are arranged in a fractal structure mode in the flow direction, continuous disturbance is caused to the incoming flow, and the continuously increased discontinuous areas are beneficial to improving the uniformity of channel heat exchange. The experimental results show that when the cold fluid Reynolds number is 20000, the pressure loss of the embodiment is reduced by 12.66%, the heat exchange is increased by 5.46% and the overall thermal performance is improved by 20.74% relative to the pressure loss of the straight rib channel.
Fig. 5 shows example 3 of the present invention. In this embodiment, the sectional shape of the intermittent rib is a square with a side length e, and the intermittent rib is obliquely placed in the cooling passage to form an inclination angle of 75 ° with the right side wall surface. The length of the discontinuous area of each row of discontinuous ribs is kept unchanged, and the fins are obliquely placed in the cooling channel, so that the heat exchange area can be further increased, and the channel heat exchange is strengthened. Due to the existence of the discontinuous region, the flow resistance of the fluid is reduced, the turbulence degree of the fluid is increased by the transverse vortex induced by the discontinuous region, the mixing of the main flow and the fluid of the boundary layer is enhanced, the heat exchange is enhanced, and the overall thermal performance of the channel is improved. In addition, the discontinuous ribs are arranged in a fractal structure mode in the flow direction, continuous disturbance is caused to the incoming flow, and the continuously increased discontinuous areas are beneficial to improving the uniformity of channel heat exchange.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (8)
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010992833.6A CN112177681B (en) | 2020-09-21 | 2020-09-21 | A Fractal Interrupted Rib Structure Suitable for Internal Cooling of Turbine Blades |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010992833.6A CN112177681B (en) | 2020-09-21 | 2020-09-21 | A Fractal Interrupted Rib Structure Suitable for Internal Cooling of Turbine Blades |
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| CN112177681A true CN112177681A (en) | 2021-01-05 |
| CN112177681B CN112177681B (en) | 2022-03-15 |
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Cited By (6)
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| CN113404548A (en) * | 2021-07-09 | 2021-09-17 | 中国联合重型燃气轮机技术有限公司 | Blade, turbine and gas turbine |
| CN113847102A (en) * | 2021-10-10 | 2021-12-28 | 西北工业大学 | Structure of structural truncated rib for enhancing integral thermal performance |
| CN114649284A (en) * | 2022-05-13 | 2022-06-21 | 中国人民解放军海军工程大学 | A rib-row bionic structure microchannel radiator |
| CN116191713A (en) * | 2022-09-09 | 2023-05-30 | 扬州大学 | Full-through-flow pump rotor with heat dissipation and self-cleaning functions and design method thereof |
| CN117418906A (en) * | 2023-12-19 | 2024-01-19 | 哈尔滨工业大学 | Turbine internal cold air structure based on fractal theory |
| EP4450760A1 (en) * | 2023-04-18 | 2024-10-23 | RTX Corporation | Layout for asymmetric trip strips, layout for asymmetric trip strips for a component for a gas turbine engine and process for managing a fluid flow through a flow passage having asymmetric trip strips for a gas turbine engine component |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113404548A (en) * | 2021-07-09 | 2021-09-17 | 中国联合重型燃气轮机技术有限公司 | Blade, turbine and gas turbine |
| CN113847102A (en) * | 2021-10-10 | 2021-12-28 | 西北工业大学 | Structure of structural truncated rib for enhancing integral thermal performance |
| CN114649284A (en) * | 2022-05-13 | 2022-06-21 | 中国人民解放军海军工程大学 | A rib-row bionic structure microchannel radiator |
| CN114649284B (en) * | 2022-05-13 | 2022-07-29 | 中国人民解放军海军工程大学 | A rib-row bionic structure microchannel radiator |
| CN116191713A (en) * | 2022-09-09 | 2023-05-30 | 扬州大学 | Full-through-flow pump rotor with heat dissipation and self-cleaning functions and design method thereof |
| CN116191713B (en) * | 2022-09-09 | 2024-01-26 | 扬州大学 | Full-through-flow pump rotor with heat dissipation and self-cleaning functions and design method thereof |
| EP4450760A1 (en) * | 2023-04-18 | 2024-10-23 | RTX Corporation | Layout for asymmetric trip strips, layout for asymmetric trip strips for a component for a gas turbine engine and process for managing a fluid flow through a flow passage having asymmetric trip strips for a gas turbine engine component |
| CN117418906A (en) * | 2023-12-19 | 2024-01-19 | 哈尔滨工业大学 | Turbine internal cold air structure based on fractal theory |
| CN117418906B (en) * | 2023-12-19 | 2024-03-22 | 哈尔滨工业大学 | A cooling air structure inside the turbine based on fractal theory |
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