CN115585022A - Turbine blade strengthens turbulent flow post cooling structure - Google Patents
Turbine blade strengthens turbulent flow post cooling structure Download PDFInfo
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- CN115585022A CN115585022A CN202211341424.5A CN202211341424A CN115585022A CN 115585022 A CN115585022 A CN 115585022A CN 202211341424 A CN202211341424 A CN 202211341424A CN 115585022 A CN115585022 A CN 115585022A
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- turbine blade
- rib
- cooling structure
- column
- column body
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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
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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 provides a turbine blade reinforced turbulence column cooling structure which comprises a turbulence column body and a rib arranged on the turbulence column body, wherein the rib is spirally wound on the surface of the turbulence column body. The turbine blade reinforced turbulence column cooling structure provided by the invention intervenes the flow of airflow in the channel by using the rib structure, improves the turbulence intensity and the heat exchange area of the airflow in the cooling channel, guides the flow direction of the airflow, and can enhance the heat exchange coefficients of two side wall surfaces where the turbulence column body is located to different degrees under the conditions of not increasing the flow of cold air, not reducing the strength of the blade to a large extent and not changing the manufacturing process to a large extent, namely directionally cooling the wall surface where the turbulence column body is located in a spatially symmetrical or asymmetrical manner, so that the temperature distribution of the turbine blade can be improved more uniformly while the cooling efficiency of the turbine blade is improved.
Description
Technical Field
The invention belongs to the technical field of thermal protection or cooling for turbine blades, and particularly relates to a turbine blade reinforced turbulence column cooling structure of a heavy-duty gas turbine.
Background
The gas turbine is important energy equipment and is widely applied to the fields of ship power, aviation propulsion, land power generation and the like. In order to increase the thermal efficiency and specific work of a gas turbine, the gas temperature in front of the turbine needs to be continuously increased. Currently, the gas temperatures in advance of the turbines of advanced commercial gas turbines have reached over 1650 degrees Celsius, well in excess of the allowable temperatures for the turbine blade metal materials. In order to prolong the service life of the turbine blade and ensure the safe operation of the turbine blade, a plurality of cooling technologies are required to be matched with each other to reduce the temperature of the turbine blade.
Typically, a conventional smooth turbulator array cooling structure is employed within the interior of the turbine blade, particularly in the trailing edge region. The cooling structure is realized by changing the space among the turbulence columns, the number of the turbulence columns and the diameter of the turbulence columns in the aspect of adjusting the internal heat exchange coefficient and the resistance coefficient, and the adjusting mode is single. The heat exchange coefficients of the two side wall surfaces where the turbulence columns are located are spatially symmetrical or similar, the thermal load conditions of different suction surfaces and pressure surfaces of the trailing edge of the turbine blade cannot be fully adapted, the interference effect of the turbulence column body on the airflow cannot be fully exerted, and the space for further improvement is provided.
In order to pursue higher cooling efficiency of the turbine blade, various measures for improving the cooling characteristics of the turbulence columns are proposed at home and abroad, such as adding a concave vortex structure between the turbulence columns, separating the turbulence columns into an upper section and a lower section, changing the vertical arrangement of the turbulence columns into an inclined arrangement, changing the circular section of the turbulence columns into a square shape or a wing shape, and the like. These improvements, while improving cooling efficiency, weaken the strength of the turbine blade to some extent and do not take into account the different thermal loading conditions of the suction side and pressure side of the trailing edge of the turbine blade, nor do they suggest a solution to the non-uniform temperature distribution, which would adversely affect the useful life of the turbine blade.
Therefore, in order to improve the turbine blade cooling efficiency and to improve the temperature distribution of the turbine blade more uniformly, it is necessary to provide a spoiler cooling structure having a simple design structure and directionally performing intensive cooling.
Disclosure of Invention
In order to solve the two problems of non-uniform blade temperature distribution and low cooling efficiency in the existing turbine blade cooling design, the invention aims to provide a spoiler cooling structure with a simple design structure.
In order to achieve the purpose, the invention provides a turbine blade reinforced spoiler column cooling structure which comprises a spoiler column body and a rib arranged on the spoiler column body, wherein the rib is spirally wound on the surface of the spoiler column body.
The turbine blade enhanced turbulent column cooling structure provided by the invention is also characterized in that the cross section of the rib is in a shape comprising one or more combinations selected from polygons and arcs. The disturbance of the polygonal cross section to the airflow is severe, the disturbance of the arc cross section to the airflow is mild, the turbulence intensity and the heat exchange area caused by the cross sections of different shapes are different, and further the influence on the heat exchange coefficient and the resistance coefficient is different. To avoid the problem of stress concentration in the blade, the cross section of the rib may be more curved.
The turbine blade reinforced spoiler column cooling structure provided by the invention is also characterized in that the rib is spirally wound on the surface of the spoiler column body in any one of the modes of equal cross-sectional area change or unequal cross-sectional area change, wherein the ratio of the cross-sectional area of the rib to the cross-sectional area of the spoiler column body is 0.001-0.1. Since the cross-sectional area of the rib has a large influence on both the heat exchange coefficient and the drag coefficient of the turbulator column, and considering that the turbulence intensity and the vortex system are continuously developed upstream and downstream of the airflow, the region with different thermal load conditions can be adapted by changing the cross-sectional area of the rib. In the downstream region of the cooling channel, the cross-sectional area of the ribs shown can be increased appropriately for improving the downstream cooling effect and enhancing the uniformity of the temperature distribution. When the ratio of the cross section area of the rib to the cross section area of the turbulent flow column body is smaller, the enhancement effect of the heat exchange coefficient is not obvious; when the ratio is large, the resulting drag coefficient is large.
The turbine blade reinforced spoiler column cooling structure provided by the invention is also characterized in that the contact point of the rib and the surface of the spoiler column body is continuous or in a segmented continuous mode. The advantage is that the surface of the spoiler column body does not have to be completely used with the ribs, which may be arranged in a stepwise continuous manner, when the thermal loads on the pressure and suction sides of the turbine blade are different. When the thermal load of the suction surface of the turbine blade is higher, the number of the ribs is increased, and vice versa, so that the local thermal load of the turbine blade is better adapted, namely, the local wall surface temperature is directionally reduced, and the aim of enabling the temperature distribution of the blade to be more uniform is fulfilled.
The turbine blade reinforced turbulence column cooling structure provided by the invention is also characterized in that the included angle between the rib in the pass direction and the central line of the turbulence column body ranges from 0 degree to 90 degrees, namely the range of the helical angle ranges from 0 degree to 90 degrees. When the helical angle is 0 degree, the heat exchange coefficient distribution of the two side wall surfaces where the turbulence columns are located has spatial symmetry, and the method is suitable for the condition that the thermal loads of the suction surface and the pressure surface of the turbine blade are uniform; when the helical angle is larger than 0 degree and smaller than 90 degrees, the heat exchange coefficient distribution of the two side wall surfaces where the turbulence columns are located is not symmetrical any more, and the turbulence columns are suitable for the condition that the thermal loads of the suction surface and the pressure surface of the turbine blade are uneven or the condition that the turbine blade rotates; when the helix angle is 90 deg., the heat transfer coefficient distribution again possesses spatial symmetry. Therefore, the flow direction of the air flow is guided by adjusting the helical angle, the purpose of adjusting the local heat exchange coefficient can be achieved, and the temperature of the local wall surface is further reduced in a directive manner, so that the temperature distribution of the blades is more uniform.
The turbine blade reinforced spoiler column cooling structure provided by the invention is also characterized in that the spiral winding comprises a spiral winding mode selected from spiral winding of which the rib protrudes towards the outer side of the surface of the spoiler column body or spiral winding of which the rib is sunken towards the inner side of the surface of the spoiler column body. The reason is that when the air flow contacts the ribs which are convex outwards and the ribs which are concave inwards, the local flowing directions of the air flow on the surface of the spoiler column body are different, and the vortex system and the turbulence intensity caused by the air flow and the spoiler column body are different, so that the heat exchange coefficient and the resistance coefficient are different.
Has the beneficial effects that:
the turbine blade reinforced turbulence column cooling structure provided by the invention intervenes the flow of airflow in the channel by using the rib structure, improves the turbulence intensity and the heat exchange area of the airflow in the cooling channel, guides the flow direction of the airflow, and can enhance the heat exchange coefficients of two side wall surfaces where the turbulence column body is located to different degrees under the conditions of not increasing the flow of cold air, not reducing the strength of the blade to a large extent and not changing the manufacturing process to a large extent, namely directionally cooling the wall surface where the turbulence column body is located in a spatially symmetrical or asymmetrical manner, so that the temperature distribution of the turbine blade can be improved more uniformly while the cooling efficiency of the turbine blade is improved.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings required to be used in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of a turbine blade enhanced turbulent flow column cooling structure provided by the present invention;
FIG. 2 isbase:Sub>A cross-sectional view taken along line A-A of FIG. 1;
FIG. 3 is a diagram illustrating an exemplary application of the cooling structure provided by the present invention to a double-walled cooling blade of a turbine;
FIG. 4 is a comparison graph of dimensionless spanwise average Nussel numbers of the wall surfaces on which the turbulence columns of the conventional cooling structure and the cooling structure of the embodiment of the invention are located under the condition of the Reynolds numbers of the same inlet channels;
FIG. 5 is a cross-sectional view of a rib of a rectangular shape having a helical angle of approximately 90 degrees;
FIG. 6 is a cross-sectional view of a rib of a rectangular cross-section having a helix angle of approximately 0 degrees;
FIG. 7 is a schematic view of the combination of the cooling structure and the separation gap structure provided by the present invention.
In the figure: the structure comprises 1-a turbulence column body, 2-ribs, 3-helical angles, 4-rib cross sections, 5-a turbine blade double-wall structure, 6-a turbulence column provided by the invention, 7-a turbulence column provided by the invention with separation gaps, and 8-a reinforced turbulence column array.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement objects and the functions of the invention easy to understand, the following embodiments are specifically explained for the turbine blade provided by the invention with reference to the attached drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central," "longitudinal," "transverse," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are only for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1, the embodiment provides a turbine blade enhanced spoiler column cooling structure, which includes a spoiler column body 1 and a rib 2 provided on the spoiler column body 1. The ribs 2 are attached to the surface of the spoiler column body 1 in a spirally wound manner. The ribs 2 reach the other end of the spoiler column body 1 from one end of the spoiler column body 1 in a spiral angle 3 and an outward convex spiral winding mode, and the spiral angle 3 is equal to 30 degrees. In fig. 1, there are 12 ribs 2, and each rib 2 is arranged at equal intervals in a manner of rotating around the center line of the spoiler body 1.
In some embodiments, as shown in fig. 2, the cross-section 4 of the rib 2 is arc-shaped, and the ratio of the area of the cross-section 4 of the rib 2 to the cross-sectional area of the spoiler body 1 is 0.003.
In some embodiments, as shown in fig. 3, the turbulator cooling structure 6 provided by the present invention is applied in the gap of the turbine blade double-walled cooling structure 5, and the airflow flows into the double-walled gap through the impact holes, and then passes through the interference effect of the enhanced turbulator cooling structure, so as to bring a better internal heat exchange effect. In addition to turbine double-wall cooling blades, the trailing edge cleft of a turbine blade may also use the enhanced turbulent column cooling structure.
In some embodiments, as shown in FIG. 4, under the condition that the Reynolds number of the inlet channel is 10 ten thousand, the data of the dimensionless spanwise Nussel number of the cooling channels distributed along the flow direction of the turbulent flow column array can be obtained, wherein Nu w Nu is the Nu number of the wall surface on which the turbulence column is located 0 The area ratio AR =0 represents the traditional smooth turbulence column, and the rest area ratios are the turbulence columns provided by the invention, and the parameters are as follows: the cross section of each rib is arc-shaped, the spiral angle is 0 degree, the number of the ribs is 8, and the ribs are distributed on the surface of the turbulent flow column body at equal intervals. As can be seen from fig. 4, the knoop number of the downstream area of the cooling channel is obviously increased after the cooling channel is provided with the enhanced turbulent flow column cooling structure provided by the invention.
For the internal cooling of the turbine blade, the problem of improving the temperature distribution of the turbine blade cannot be completely solved by enhancing the heat exchange coefficient of the cooling channel of the turbulent flow column, because the suction surface and the pressure surface of the turbine blade bear different heat loads, and the local temperature is higher. According to the result shown in fig. 4, the ribs 2 can enhance the heat exchange coefficient of the wall surface where the spoiler pillar body 1 is located, and the heat exchange coefficient tends to be gradually enhanced along with the increase of the flow direction distance, which means that the cold air takes away more heat from the downstream wall surface, which is more beneficial to make the temperature on the wall surface of the turbine blade more uniform.
In some embodiments, the included angle between the rib 2 and the central line of the spoiler column body 1 along the pass direction ranges from 0 to 90 degrees, and the included angle between the rib and the central line of the spoiler column body along the pass direction is the spiral angle 3. According to the size of the helix angle 3, the cooling structure of the reinforced turbulent flow column can be divided into a transverse spiral winding turbulent flow column shown in fig. 5, namely a winding mode that the helix angle 3 is close to 90 degrees, and a longitudinal spiral winding turbulent flow column shown in fig. 6, namely a winding mode that the helix angle 3 is close to 0 degrees. In fig. 5 and 6, the cross-section 4 of the rib is rectangular in shape. The two configurations shown in fig. 5 and 6 have different heat exchange effects on the air flow in the cooling passage due to the difference in the spiral winding manner of the ribs 2. When the ratio of the area of the cross section 4 of the rib 2 to the cross-sectional area of the spoiler column body is smaller, the number of the ribs 2 can be increased, and the turbulence of the reinforced spoiler column cooling structure on the air flow in the cooling channel is stronger. In order to ensure the resistance coefficient and the processing and manufacturing, the ratio of the area of the cross section 4 of the rib 2 to the cross section area of the spoiler column body is not less than 0.001, otherwise, the processing and manufacturing are difficult, and not more than 0.1, otherwise, the resistance coefficient is too large.
In addition, the number, the length and the positions of the ribs 2 coiled on the surface of each spoiler column body 1 can be different, and the purpose of regulating and controlling the heat exchange coefficient of a local area in the cooling channel can be achieved through different combination modes and different array modes. As shown in fig. 7, the ribs are arranged on the surface of the turbulators 7 with the separation gaps, that is, contact points of the ribs and the surface of the turbulators are continuous in a segmented manner, and then the turbulators are arranged in an array alternating manner to obtain a reinforced turbulator array 8, so that the cooling performance can be further improved. Therefore, the turbulence column provided by the invention has the capability of further enhancing the cooling by combining with other cooling structures.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (6)
1. The utility model provides a turbine blade reinforces vortex post cooling structure which characterized in that, cooling structure includes vortex post body and the rib of setting on the vortex post body, the rib spiral is coiled on the surface of vortex post body.
2. The turbine blade enhanced turbulence column cooling structure of claim 1, wherein a cross-sectional shape of the rib includes one or more combinations selected from a polygon and an arc.
3. The turbine blade enhanced spoiler column cooling structure according to claim 1, wherein the rib is spirally wound on the surface of the spoiler column body in any one of a uniform cross-sectional area variation or a non-uniform cross-sectional area variation, wherein a ratio of a cross-sectional area of the rib to a cross-sectional area of the spoiler column body ranges from 0.001 to 0.1.
4. The turbine blade enhanced turbulator column cooling structure of claim 1, wherein a contact point of the rib with the surface of the turbulator column body is any one of continuous or piecewise continuous.
5. The turbine blade enhanced turbulator column cooling structure of claim 1, wherein an angle between the rib in the in-pass direction and a centerline of the turbulator column body is in a range of 0 ° to 90 °.
6. The turbine blade enhanced turbulator column cooling structure of claim 1, wherein the helical winding comprises a helical winding selected from a helical winding in which the rib is convex to an outside of the surface of the turbulator column or a helical winding in which the rib is concave to an inside of the surface of the turbulator column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211341424.5A CN115585022A (en) | 2022-10-28 | 2022-10-28 | Turbine blade strengthens turbulent flow post cooling structure |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211341424.5A CN115585022A (en) | 2022-10-28 | 2022-10-28 | Turbine blade strengthens turbulent flow post cooling structure |
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| CN115585022A true CN115585022A (en) | 2023-01-10 |
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| CN202211341424.5A Pending CN115585022A (en) | 2022-10-28 | 2022-10-28 | Turbine blade strengthens turbulent flow post cooling structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116950724A (en) * | 2023-09-20 | 2023-10-27 | 中国航发四川燃气涡轮研究院 | Internal cooling structure applied to turbine blade trailing edge and design method thereof |
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2022
- 2022-10-28 CN CN202211341424.5A patent/CN115585022A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116950724A (en) * | 2023-09-20 | 2023-10-27 | 中国航发四川燃气涡轮研究院 | Internal cooling structure applied to turbine blade trailing edge and design method thereof |
| CN116950724B (en) * | 2023-09-20 | 2024-01-09 | 中国航发四川燃气涡轮研究院 | Internal cooling structure applied to turbine blade trailing edge and design method thereof |
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