CN110714802A - Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade - Google Patents
Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade Download PDFInfo
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- CN110714802A CN110714802A CN201911188880.9A CN201911188880A CN110714802A CN 110714802 A CN110714802 A CN 110714802A CN 201911188880 A CN201911188880 A CN 201911188880A CN 110714802 A CN110714802 A CN 110714802A
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- discontinuous
- staggered
- cooling
- temperature turbine
- rib structure
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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
Abstract
The invention provides a discontinuous staggered rib structure suitable for cooling the interior of a high-temperature turbine blade, which comprises a cooling channel and staggered ribs, wherein the staggered ribs are placed in the cooling channel, the height of the staggered ribs is half of that of the cooling channel, so that the ribs on the upper wall surface and the lower wall surface are in contact with each other and divide the whole channel into a plurality of grid-type sub-channels, 1-4 discontinuous areas are arranged along the flowing direction of a fluid, and the width of each discontinuous area is constant along the flowing direction. Compared with the traditional staggered ribs, the invention keeps the structures of grid type sub-channels, folding angles and the like, reduces the flow resistance of fluid by arranging the discontinuous areas, reduces the consumption of cooling gas, and improves the comprehensive heat efficiency, thereby improving the efficiency and the power of the gas turbine and the like. The invention can be used for high-temperature turbine stationary vanes and high-temperature turbine movable blades.
Description
Technical Field
The invention relates to a turbine blade cooling technology of a gas turbine, in particular to a discontinuous staggered rib structure suitable for cooling the interior of a high-temperature turbine blade.
Background
The gas turbine is a power machine which converts chemical energy into internal energy and then converts the internal energy into mechanical energy for working, has the advantages of small mass, compact structure, high power output and the like, is widely applied to many fields of aviation industry, ground power generation, ship power and the like, plays an indispensable important role in the aspects of transportation, industrial production, military equipment and the like, is known as 'Mingzhu' in modern industry, and is the centralized embodiment of national comprehensive national strength, scientific and technological level and industrial foundation. In order to solve the bottleneck problem of restricting the industrial development of the gas turbine and the aero-engine for a long time and promote the development of the gas turbine and the aero-engine, the significant special item of the aero-engine and the gas turbine (the special item of 'two machines') is formally established in 2016 in China.
Turbine blade cooling plays an extremely important role in modern gas turbine design, as seen in the brayton cycle, the thermal efficiency and output of the gas turbine increase with increasing initial gas temperature. Research shows that the thrust of the gas turbine can be improved by 10 percent on average for every 55K increase of the temperature of the inlet of the turbine. In the past decades, in order to meet the increasing demands for power and efficiency, the inlet temperature of the turbine is increased year by year, the initial gas temperature of the advanced gas turbine can reach over 1800K at present, and the initial gas temperature of the military aircraft engine reaches 2100K even more, which will result in the severe working environment of the turbine blades, so whether the turbine blades can work safely and reliably is very important for the operation of the gas turbine.
The inlet temperature of high temperature turbines of advanced gas turbines has been far beyond the temperature tolerance limit of the materials and this gap is gradually expanding, studies have shown that the turbine front temperature is on average increased by 22K annually, while the sustainable temperature of the materials is on average increased by 8K annually. Efficient turbine cooling and thermal protection techniques are therefore of paramount importance in order to ensure safe, efficient and long-term operation of the gas turbine. At present, the high-temperature turbine blade of the gas turbine is generally cooled by adopting air compressor bleed air, and a comprehensive cooling scheme consisting of internal cooling, external cooling and a surface heat-insulating coating is basically formed. Since the cooling air is compressed air from the compressor, it is desirable to extract as little cooling air as possible from the compressor to meet the cooling requirements, thereby reducing energy losses and improving gas turbine efficiency.
The staggered ribs are a special internal heat exchange enhancing turbulence rib structure which is designed and used by the former Soviet Union, and the flow heat exchange mechanism and the design idea of the structure are greatly different from those of a snake-shaped channel and a column rib channel which are generally adopted. The upper and lower layers of fins are contacted with each other to divide the whole channel into a plurality of grid-type sub-channels, and the fluid in the channel can only flow along the sub-channels or grids among the sub-channels. The airflow flows along each sub-channel after entering the channel, and after reaching the bent angle of the channel, the airflow collides with the wall and turns over, the airflow meanders in the channel to increase the flowing distance of the airflow in the channel, and meanwhile, because the deflection of the bent angle of the airflow generates impact and disturbance, the turbulence degree of the airflow is increased, and the heat exchange coefficient is also increased; on the other hand, the addition of a plurality of fins results in a substantial increase in the actual effective heat exchange area, and therefore the amount of heat exchange in the interleaved rib channels is much greater relative to smooth channels and conventional rib channels. Besides, the airflow flows along each sub-channel in the channel, and the airflow also irregularly flows among each grid, so that the formation and development of boundary layers are damaged by the mixing and disturbance, and the generated strong secondary flow is also beneficial to enhancing the heat exchange. However, the staggered rib channels increase the heat exchange amount and also increase the flow resistance of the channels, which increases the pressure loss. Therefore, there is a need for an efficient and low resistance method of organizing the staggered ribs to improve the level of gas-thermal design of the staggered rib channel.
Disclosure of Invention
The invention aims to provide a discontinuous staggered rib structure suitable for cooling the interior of a high-temperature turbine blade in order to enhance the heat exchange performance of the turbine blade, reduce pressure loss and improve comprehensive heat efficiency.
The purpose of the invention is realized as follows: staggered fins are arranged in a cooling channel inside the blade and are formed by two layers of staggered fins, the staggered fins divide the inside of the blade into grid runners, at least one discontinuous area is arranged on the staggered fins, and the discontinuous area is arranged along the airflow direction. The invention also includes such structural features:
1. the number of the discontinuous areas is one or two, and the discontinuous areas are arranged close to the side wall surface of the blade.
2. The length of the discontinuous area is L, the length of the cooling channel is L, and the following requirements are met: l is more than or equal to 0.5L and less than or equal to L.
3. The length of the discontinuous region is W, the length of the cooling channel is W, and the following conditions are met: w is more than or equal to 0.015W and less than or equal to 0.125W.
4. The staggered fins on the end face of the discontinuous area are provided with turning angles.
Compared with the prior art, the invention has the beneficial effects that: the discontinuous staggered ribs of the invention keep the structures of grid type sub-channels, folding angles and the like of the traditional staggered ribs; compared with the traditional staggered ribs, the flow resistance of the fluid is reduced by arranging the discontinuous areas, the using amount of cooling gas is reduced, and the comprehensive heat efficiency is improved, so that the efficiency and the power of the gas turbine are improved.
Drawings
FIG. 1 is a schematic view of the structure of example 1 of the present invention after the top wall surface is removed;
FIG. 2 is a top view of example 1 of the present invention with the top wall removed;
FIG. 3 is a left side view of example 1 of the present invention with the top wall removed;
FIG. 4 is a schematic structural view of example 2 of the present invention after the top wall has been removed;
FIG. 5 is a schematic view of the structure of example 3 of the present invention after the top wall surface is removed;
fig. 6 is a schematic structural view of embodiment 4 of the present invention after the top wall surface is removed.
In the figure: 1. the cooling structure comprises a left side wall surface, a right side wall surface, a bottom wall surface, a gap area, a rib, a grid type sub-channel, a folding angle, a cooling channel internal flow direction length, a gap area flow direction length, a cooling channel internal width, a gap area width, a cooling channel internal height and a rib height, wherein the gap area is a square, the rib is a square, and the rib height is h.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The invention relates to a discontinuous staggered rib structure suitable for cooling the interior of a high-temperature turbine blade, which comprises a cooling channel with the internal dimension of length L, width W and height H and staggered ribs with the height H of H/2, wherein the staggered ribs are placed in the cooling channel, and the discontinuous staggered rib structure is characterized in that the staggered ribs are discontinuous along the gas flowing direction, namely, the staggered ribs are provided with discontinuous areas along the gas flowing direction. The width of the interruption zone is constant in the flow direction. The number of the discontinuous areas is 1-4. The length L of the discontinuous area is 0.5-1L. The width W of the discontinuous area is 0.015-0.125W. For example, three or four discontinuous regions may be provided on the side wall surfaces, and the remaining one or two discontinuous regions may be provided between the two regions at equal intervals.
Embodiments of the invention are given below with reference to the accompanying drawings:
example 1:
with reference to fig. 1-3, the present embodiment provides an interrupted staggered rib structure suitable for cooling inside a high-temperature turbine blade, including a cooling channel and staggered ribs, where two layers of ribs 5 are staggered in the cooling channel, dividing the whole cooling channel into a plurality of grid-type sub-channels 6, and providing 2 interrupted regions 4 near the left side wall 1 and the right side wall 2, where the interrupted regions 4 penetrate through the whole cooling channel, and after entering the cooling channel from an inlet, a part of the cooling gas flows into the interrupted regions 4, and another part of the cooling gas flows into the sub-channels 6 along the ribs, and after mixing with the surrounding walls and the ribs 5 to exchange heat, the cooling gas in the sub-channels 6 directly flows out of the cooling channel, and there is no strong impact with the walls and the ribs, so the flow resistance is much lower than that of an uninterrupted staggered rib structure, meanwhile, the heat exchange capacity is not greatly reduced, the other part of cooling gas flows along the sub-channels 6 in a winding mode or flows in grids among the sub-channels 6, after reaching the turning angle 7, the collision wall is overturned to generate longitudinal vortex for enhancing heat exchange at the downstream, the characteristic of strong heat exchange capacity of the traditional staggered ribs is kept, and on the whole, the discontinuous area 4 is arranged to facilitate reducing flow resistance, keep heat exchange capacity and improve comprehensive heat efficiency.
Example 2:
with reference to fig. 4, the present embodiment provides an interrupted staggered rib structure suitable for cooling inside a high-temperature turbine blade, including a cooling channel and staggered ribs, where two layers of ribs 5 are staggered in the cooling channel, the whole cooling channel is divided into a plurality of grid-type sub-channels 6, 1 interrupted region 4 is provided at a position close to a right side wall surface 2, the interrupted region 4 penetrates through the whole cooling channel, after cooling gas enters the cooling channel from an inlet, a part of the cooling gas flows into the interrupted region 4, and another part of the cooling gas flows into the sub-channels 6 along the ribs, and most of the cooling gas flowing into the interrupted region 4 directly flows out of the cooling channel after being mixed with surrounding wall surfaces and the ribs 5 for heat exchange, and does not generate strong impact with the wall surfaces and the ribs, so that the flow resistance is far lower than that of an uninterrupted staggered rib structure, and the heat exchange capability is not greatly reduced, and the other part of cooling gas flows along the sub-channels 6 in a winding way or flows in a grid way among the sub-channels 6, and after reaching the turning angle 7, the cooling gas collides with the wall and turns over to generate longitudinal vortex to enhance heat exchange at the downstream, so that the characteristic of strong heat exchange capability of the traditional staggered ribs is kept, and on the whole, the provided discontinuous area 4 is favorable for reducing flow resistance, keeping heat exchange capability and improving comprehensive heat efficiency.
Example 3:
with reference to fig. 5, the present embodiment provides a discontinuous staggered rib structure suitable for cooling inside a high-temperature turbine blade, which includes a cooling channel and staggered ribs, the ribs 5 are arranged in two layers in a staggered manner in the cooling channel, the whole cooling channel is divided into a plurality of grid-type sub-channels 6, 1 interrupted area 4 is arranged at the position close to the right side wall surface 2, the length L of the interrupted area 4 is smaller than the length L of the interior of the cooling channel, cooling gas firstly flows in the sub-channel 6 along the fins 5 at the inlet and can only flow into the interrupted area 4 after a section of flow, the cooling gas flowing into the interrupted area 4 can flow out along the interrupted area or can flow into other sub-channels 6 through the interrupted area 4, the complexity of the flow is enhanced, and on the whole, the arrangement of the discontinuous area 4 is beneficial to reducing the flow resistance, retaining the heat exchange capacity and improving the comprehensive heat efficiency.
Example 4:
with reference to fig. 6, the present embodiment provides a discontinuous staggered rib structure suitable for cooling inside a high-temperature turbine blade, which includes a cooling channel and staggered ribs, wherein the ribs 5 are arranged in two layers in a staggered manner in the cooling channel, dividing the entire cooling channel into a plurality of grid-type sub-channels 6, 2 discontinuous areas 4 are arranged at the positions close to the left side wall surface 1 and the right side wall surface 2, the length L of the discontinuous area 4 is less than the length L in the cooling channel, cooling gas firstly flows in the sub-channel 6 along the fins 5 at the inlet and can only flow into the discontinuous area 4 after a section of flow, the cooling gas flowing into the discontinuous area 4 can flow out along the discontinuous area or can flow into other sub-channels 6 through the discontinuous area 4, the complexity of the flow is enhanced, and on the whole, the arrangement of the discontinuous area 4 is beneficial to reducing the flow resistance, retaining the heat exchange capacity and improving the comprehensive heat efficiency.
In summary, an object of the present invention is to provide a discontinuous staggered rib structure suitable for cooling inside a high temperature turbine blade, including a cooling channel and staggered ribs, where the staggered ribs are placed in the cooling channel, and the height of the staggered ribs is half of the height of the cooling channel, so that the ribs on the upper and lower wall surfaces are in contact with each other and divide the entire channel into a plurality of grid-type sub-channels, and 1-4 discontinuous regions are opened along the fluid flow direction, and the width of all the discontinuous regions is constant along the flow direction. Compared with the traditional staggered ribs, the invention keeps the structures of grid type sub-channels, folding angles and the like, reduces the flow resistance of fluid by arranging the discontinuous areas, reduces the consumption of cooling gas, and improves the comprehensive heat efficiency, thereby improving the efficiency and the power of the gas turbine and the like. The invention can be used for high-temperature turbine stationary vanes and high-temperature turbine movable blades.
Claims (9)
1. The utility model provides a crisscross rib structure of discontinuous type suitable for high temperature turbine blade internal cooling which characterized in that: staggered fins are arranged in a cooling channel inside the blade and are formed by two layers of staggered fins, the staggered fins divide the inside of the blade into grid runners, at least one discontinuous area is arranged on the staggered fins, and the discontinuous area is arranged along the airflow direction.
2. The interrupted staggered rib configuration for internal cooling of a high temperature turbine blade of claim 1, wherein: the number of the discontinuous areas is one or two, and the discontinuous areas are arranged close to the side wall surface of the blade.
3. A discontinuous staggered rib structure suitable for internal cooling of high temperature turbine blades according to claim 1 or 2, wherein: the length of the discontinuous area is L, the length of the cooling channel is L, and the following requirements are met: l is more than or equal to 0.5L and less than or equal to L.
4. A discontinuous staggered rib structure suitable for internal cooling of high temperature turbine blades according to claim 1 or 2, wherein: the length of the discontinuous region is W, the length of the cooling channel is W, and the following conditions are met: w is more than or equal to 0.015W and less than or equal to 0.125W.
5. A discontinuous staggered rib structure adapted for high temperature turbine blade internal cooling as claimed in claim 3, wherein: the length of the discontinuous region is W, the length of the cooling channel is W, and the following conditions are met: w is more than or equal to 0.015W and less than or equal to 0.125W.
6. A discontinuous staggered rib structure suitable for internal cooling of high temperature turbine blades according to claim 1 or 2, wherein: the staggered fins on the end face of the discontinuous area are provided with turning angles.
7. A discontinuous staggered rib structure adapted for high temperature turbine blade internal cooling as claimed in claim 3, wherein: the staggered fins on the end face of the discontinuous area are provided with turning angles.
8. A discontinuous staggered rib structure adapted for high temperature turbine blade internal cooling as claimed in claim 4, wherein: the staggered fins on the end face of the discontinuous area are provided with turning angles.
9. A discontinuous staggered rib structure adapted for high temperature turbine blade internal cooling as claimed in claim 5, wherein: the staggered fins on the end face of the discontinuous area are provided with turning angles.
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| CN201911188880.9A CN110714802B (en) | 2019-11-28 | 2019-11-28 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
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| CN201911188880.9A CN110714802B (en) | 2019-11-28 | 2019-11-28 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
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| CN110714802B CN110714802B (en) | 2022-01-11 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111305906A (en) * | 2020-03-31 | 2020-06-19 | 哈尔滨工程大学 | Area is disconnected straight rib and is half split joint cooling structure between suitable for high temperature turbine blade |
| CN112392550A (en) * | 2020-11-17 | 2021-02-23 | 上海交通大学 | Turbine blade trailing edge pin fin cooling structure and cooling method and turbine blade |
| CN113623011A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111305906A (en) * | 2020-03-31 | 2020-06-19 | 哈尔滨工程大学 | Area is disconnected straight rib and is half split joint cooling structure between suitable for high temperature turbine blade |
| CN112392550A (en) * | 2020-11-17 | 2021-02-23 | 上海交通大学 | Turbine blade trailing edge pin fin cooling structure and cooling method and turbine blade |
| CN112392550B (en) * | 2020-11-17 | 2021-09-28 | 上海交通大学 | Turbine blade trailing edge pin fin cooling structure and cooling method and turbine blade |
| CN113623011A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
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