CN115013075A - Anti-slip pattern-shaped turbulence rib and turbine blade - Google Patents
Anti-slip pattern-shaped turbulence rib and turbine blade Download PDFInfo
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- CN115013075A CN115013075A CN202210953293.XA CN202210953293A CN115013075A CN 115013075 A CN115013075 A CN 115013075A CN 202210953293 A CN202210953293 A CN 202210953293A CN 115013075 A CN115013075 A CN 115013075A
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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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- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/80—Technologies aiming to reduce greenhouse gasses emissions common to all road transportation technologies
- Y02T10/82—Elements for improving aerodynamics
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- 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
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an anti-skid pattern-shaped turbulence rib and a turbine blade, wherein the turbulence rib comprises four blade-shaped ribs and a circular groove rib, the four blade-shaped ribs and the circular groove rib are the same in structural appearance, the four blade-shaped ribs are symmetrically distributed on the upper side and the lower side of the circular groove rib, and the four blade-shaped ribs and the circular groove rib form an anti-skid pattern-shaped structure. The anti-skid pattern-shaped turbulence rib is formed by matching a plurality of flow distribution ribs, secondary longitudinal vortexes generated by the oblique planes are utilized among the flow distribution blade type ribs to strengthen fluid near a disturbance wall surface, meanwhile, the secondary longitudinal vortexes generate guidance on the flow in the transverse direction of the flow to promote the transverse diffusion and mixing of the fluid, disturbance similar to Karman vortexes is formed, the disturbance is propagated downstream to achieve the purpose of strengthening heat transfer, the high heat transfer strength is obtained, the flow loss is well considered, and the comprehensive heat transfer performance of the anti-skid pattern-shaped turbulence rib is 21.2% higher than that of a common two-dimensional straight rib structure within the range of the Re number of 11000 and 29000.
Description
Technical Field
The invention belongs to the technical field of turbine blades of aero-engines, and particularly relates to an anti-slip pattern-shaped turbulence rib and a turbine blade.
Background
Increasing the turbine inlet temperature is an effective way to increase the thrust and efficiency of an aircraft engine, but the increased turbine inlet temperature can subject the turbine blades to greater thermal loads, and excessive temperatures and thermal stresses can cause the turbine blades to fail to operate properly. The turbine inlet gas temperature of modern high-performance aircraft engines far exceeds the temperature resistance limit of the used materials, and a complex cooling technology must be adopted to ensure the normal operation of the turbine under the high-temperature condition. Currently, many efforts have been made to develop efficient internal cooling technology, wherein the provision of turbulator ribs is one of the effective measures for internal cooling of turbine blades.
The most widely used of turbine blades are common two-dimensional straight rib structures with rectangular cross sections, such as straight ribs, diagonal ribs, V-shaped ribs, etc. The common two-dimensional straight rib structure is one of the commonly used heat transfer enhancement structures in the internal cooling of the blade, and can increase the turbulence degree of cooling air flow and increase the heat exchange area of a cooling channel, thereby effectively enhancing the heat exchange capacity of the channel. Conventional two-dimensional straight rib structures are typically arranged in a plurality of combinations within the chord region interior passage of the turbine blade. When cooling gas flows through the common two-dimensional straight rib structure, the cooling gas can generate boundary layer separation, so that the heat exchange effect between the gas and the solid wall surface is enhanced, and the purpose of cooling the turbine blade is achieved. In summary, the enhanced cooling of the common two-dimensional straight rib structure is realized by repeatedly arranging the turbulence ribs to generate flow separation, and then re-attaching a new boundary layer to the heat transfer surface, so as to enhance the internal heat exchange strength; in addition, the separated boundary layer enhances the mixing of the wall surface fluid and the main flow, and the heat from the wall surface can be more effectively transferred to the main flow, so that the heat exchange effect is further enhanced.
Therefore, from the view point of flow and heat exchange, the conventional common two-dimensional straight rib structure mainly has the following defects that the flow resistance generated by gas is larger because the cooling gas can generate a boundary layer separation phenomenon on the surface of the common two-dimensional straight rib and a wake area behind the common two-dimensional straight rib structure has obvious flow separation and vortex shedding phenomena. In other words, the benefit of the enhanced heat transfer of the common two-dimensional straight rib structure is obtained at the cost of increasing the flow loss, so that the comprehensive heat exchange performance of the common two-dimensional straight rib structure is poor.
Since a balance between flow loss and enhanced heat transfer is often required when designing a turbine blade cooling structure. Therefore, the development and innovation of the turbulence rib structure with more efficient comprehensive heat exchange performance are important measures for ensuring the stable work of the turbine blade.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide an anti-slip rib and a turbine blade, so as to solve the problem of large flow loss of the two-dimensional straight rib structure in the prior art, and obtain high heat transfer strength while considering flow loss well.
In order to achieve the above object, the present invention provides an anti-skid patterned spoiler rib, which includes four blade ribs having the same structural shape and a circular groove rib 5, wherein the four blade ribs include a first splitter rib 1, a second splitter rib 2, a first collector rib 3 and a second collector rib 4, the first splitter rib 1 and the second splitter rib 2 are horizontally and symmetrically distributed on two sides directly above the circular groove rib 5, the first collector rib 3 and the second collector rib 4 are horizontally and symmetrically distributed on two sides directly below the circular groove rib 5, and the first splitter rib 1, the second splitter rib 2, the first collector rib 3, the second collector rib 4 and the circular groove rib 5 form an anti-skid patterned structure.
The anti-skid patterned turbulence rib provided by the invention is also characterized in that the top of the circular groove rib 5 is provided with a circular groove, the diameter D of the circular groove rib 5 is 1.0-2.0mm, the height H of the circular groove rib 5 is 1.2-2.5mm, the depth of the circular groove is 0.15-0.35H, and the diameter of the circular groove is 0.6-0.9D.
The anti-skid pattern-shaped turbulence rib is also characterized in that the cross section of the bottom surface of the blade-shaped rib is of a streamline blade shape, the cross section of the bottom surface is divided into three areas which are sequentially and smoothly connected, the three areas comprise a semi-elliptical area 8 arranged at the front section, a middle section circular arc area 9 arranged at the middle section and a rear section circular arc area 10 arranged at the rear section, the long axis a of the semi-ellipse is 2.65-3.85 times of the short axis b, the radius R of the circular arc section of the middle section circular arc area 9 is 1.82 a-2.65 a, and the central angle theta of the middle section circular arc area 9 is 28-39 degrees.
The anti-skid patterned turbulence rib provided by the invention is also characterized in that the blade profile rib is of a chamfered structure, and the maximum height H of the blade profile rib max 0.9-1.2H, minimum height H of the blade profile rib min Is 0.4-0.55H.
The rib provided by the invention also has the characteristics that the horizontal distance S1 between the center point O1 of the first turbulence rib and the center point O2 of the second turbulence rib is 2.5-3.5, and the included angle beta 1 between the center lines of the first turbulence rib 1 and the second turbulence rib 2 is 82-96 degrees.
The anti-skid patterned turbulence rib provided by the invention is also characterized in that the vertical distance H1 between the center point O1 of the first turbulence rib and the center point O of the circular groove rib is 1.35-1.65.
The rib provided by the invention also has the characteristics that the horizontal distance S2 between the center point O3 of the first converging blade-shaped rib and the center point O4 of the second converging blade-shaped rib is 2.5-3.5, and the included angle beta 2 between the center lines of the first diversion rib 1 and the second diversion rib 2 is 88-105 degrees.
The anti-skid patterned spoiler rib provided by the invention is also characterized in that the vertical distance H2 between the center point O3 of the first converging blade type rib and the center point O of the circular groove rib is 1.05H 1-1.25H 1.
Another object of the present invention is to provide a turbine blade provided with the above-described rib structure.
The turbine blade provided by the invention is also characterized in that a plurality of anti-skid pattern-shaped turbulence ribs are arranged in the middle chord area of the turbine blade in an array mode, the distance S3 between every two adjacent anti-skid pattern-shaped turbulence ribs in the airflow flowing direction is 4-10mm, and the chordwise distance S4 between every two adjacent anti-skid pattern-shaped turbulence ribs perpendicular to the airflow flowing direction is 3.5-12 mm.
Advantageous effects
The anti-skid pattern-shaped turbulence rib provided by the invention is formed by matching a plurality of flow dividing ribs, wherein the flow dividing blade type ribs are used for strengthening the fluid near a disturbance wall surface by utilizing secondary longitudinal vortexes generated by the inclined planes and simultaneously generating guidance on the flow in the transverse direction of the flow to promote the transverse diffusion and mixing of the fluid to form disturbance similar to Karman vortexes, the disturbance is propagated downstream to achieve the purpose of strengthening heat transfer, the high heat transfer strength is obtained while the flow loss is well considered, and the comprehensive heat transfer performance of the anti-skid pattern-shaped turbulence rib is 21.2 percent higher than that of a common two-dimensional straight rib structure within the range of the Re number of 11000 and 29000.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings needed to be used in the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present disclosure, 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 two-dimensional schematic view of an arrangement of anti-slip pattern-shaped turbulence ribs in an embodiment of the invention;
FIG. 2 is a two-dimensional schematic view of a cross-section of a base of a profile rib according to an embodiment of the present invention;
FIG. 3 is a schematic three-dimensional structure of a single airfoil rib in an embodiment of the invention;
FIG. 4 is a schematic view of a turbine turning vane with rib shaped like an anti-slip pattern according to the present invention;
FIG. 5 is a vector diagram of the velocity of the gas flow inside a turbine blade with turbulator ribs in the form of a slip-resistant pattern according to an embodiment of the present invention;
wherein, 1: a first shunting rib; 2, second shunting blade profile ribs; 3: a first blade rib; 4: a second blade rib; 5: a circular groove rib; 6: a turbine blade; 7: anti-slip pattern-shaped turbulence ribs; 8: a semi-elliptical region; 9: a middle arc-shaped area; 10: a rear arc-shaped area; 11: a chamfered structure; o: a circular groove rib center point; o1: a first shunting rib center point; o2: a second splitter vane profile rib center point; o3: a first blade profile rib center point; o4: a second blade rib center point.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not intended to limit the present invention, and those skilled in the art should understand that the functional, methodological, or structural equivalents of these embodiments or substitutions may be included in the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present 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 to 4, an anti-slip pattern-shaped turbulence rib 7 is provided, the turbulence rib includes four blade ribs having the same structural shape and a circular groove rib 5, the four blade ribs include a first splitting turbulence rib 1, a second splitting blade rib 2, a first converging blade rib 3 and a second converging blade rib 4, the first splitting turbulence rib 1 and the second splitting blade rib 2 are horizontally and symmetrically distributed on two sides right above the circular groove rib 5, the first converging blade rib 3 and the second converging blade rib 4 are horizontally and symmetrically distributed on two sides right below the circular groove rib 5, and the first splitting turbulence rib 1, the second splitting blade rib 2, the first converging blade rib 3, the second converging blade rib 4 and the circular groove rib 5 form an anti-slip pattern-shaped structure.
In some embodiments, the circular groove rib 5 is provided with a circular groove at the top, and the diameter D of the circular groove rib 5 is 1.0-2.0mm, the height H of the circular groove rib 5 is 1.2-2.5mm, the depth of the circular groove is 0.15-0.35H, and the diameter of the circular groove is 0.6-0.9D.
In some embodiments, the cross section of the bottom surface of the blade profile rib is a streamline blade profile, the cross section of the bottom surface is divided into three regions which are sequentially and smoothly connected, the three regions comprise a semi-elliptical region 8 arranged at the front section, a middle section circular arc region 9 arranged at the middle section and a rear section circular arc region 10 arranged at the rear section, the major axis a of the semi-ellipse is 2.65-3.85 times of the minor axis b, the radius R of the circular arc region of the middle section circular arc region 9 is 1.82 a-2.65 a, and the central angle θ of the middle section circular arc region 9 is 28-39 degrees. As shown in FIG. 2, the closed curve A-B-C-G-E-F-A is a schematic cross-sectional view of the bottom surface of the blade rib, the symmetry axis of the bottom surface interface is an AG straight line, the curve of the section F-A-B is a semi-elliptical area 8, and M is the center of the semi-ellipse; the two sections of arcs B-C/F-E are arc-shaped areas arranged in the middle section of the middle section, and the two sections of arcs are respectively tangent to the point B and the point F with the semi-elliptical area 8; the point P is the center of the arc of the section B-C and is on the extension line of the section B-M-F; the C-G-E sections form a rear section circular arc shaped area 10 arranged at the rear section.
In some embodiments, the profile rib is a chamfered structure 11, the maximum height Hmax of the profile rib is 0.9-1.2H, and the minimum height Hmin of the profile rib is 0.4-0.55H.
In some embodiments, the horizontal distance S1 between the center point O1 of the first spoiler rib and the center point O2 of the second spoiler rib is 2.5 × D to 3.5 × D, and the included angle β 1 between the center lines of the first spoiler rib 1 and the second spoiler rib 2 is 82 ° to 96 °.
In some embodiments, the first turbulator rib center point O1 is a vertical distance H1 from the circular groove rib center point O of 1.35 × D-1.65 × D. The vertical distance between the center point O2 of the second splitter vane rib and the center point O of the circular groove rib is equal to H1.
In some embodiments, the horizontal distance S2 between the center point O3 of the first converging blade-shaped rib and the center point O4 of the second converging blade-shaped rib is 2.5 × D-3.5 × D, and the included angle β 2 between the center lines of the first and second splitter flow ribs 1 and 2 is 88 ° to 105 °.
In some embodiments, the first manifold rib center point O3 is a vertical distance H2 from the circular groove rib center point O of 1.05 × H1-1.25 × H1. The vertical distance between the center point O4 of the second bus blade type rib and the center point O of the circular groove rib is equal to H2.
In some embodiments, a turbine blade 6 is provided, the turbine blade 6 being provided with a plurality of the above-described rib strips 7.
In some embodiments, the plurality of rib strips 7 are arranged in a matrix in the chord region of the turbine blade, and the distance S3 between two adjacent rib strips along the airflow direction is 4-10mm, and the chord distance S4 between two adjacent rib strips perpendicular to the airflow direction is 3.5-12 mm.
The reinforced heat transfer mechanism of the anti-skid pattern-shaped turbulence ribs provided by the embodiment of the invention is as follows:
1) the first flow-dividing turbulence rib 1 and the second flow-dividing blade-shaped rib 2 not only utilize secondary longitudinal vortexes generated by the oblique planes to strengthen fluid near the turbulence wall surface and destroy the flow boundary layer of the wall surface, but also have obvious guiding effect on the flow in the transverse direction of the flow, so that the fluid generates flow-dividing effect to two sides and the transverse diffusion and mixing of the fluid are promoted.
2) The circular groove rib 5 is relatively complex in disturbance on fluid formation, a horseshoe vortex effect is generated at the root of the front edge of the groove rib, a back step effect is generated at the top of the circular groove rib 5, a karman vortex street effect is generated at the rear part of the circular groove rib 5, and finally a larger channel vortex which flows forwards in a spiral mode is generated in the channel along the wall surface normal direction, so that two additional effects are caused: on one hand, the fluid can form a certain scouring effect on the wall surface of the channel, so that the effect of enhancing heat transfer is achieved; on the other hand, the fluid in the central area of the channel can be brought to the heat transfer wall surface, so that more fluid in the channel has the opportunity of contacting with the heat transfer wall surface, and the heat transfer is enhanced.
3) The first and second converging blade- shaped ribs 3 and 4 mainly have the function of obviously converging the flow in the transverse direction of the flow, so that the fluid on two sides is continuously gathered to the middle area, on one hand, the range of a swirl area at the rear part of the circular groove rib 5 can be weakened, and on the other hand, more airflow on two sides can be gathered to generate an impact effect on the downstream circular groove rib 5 to strengthen the heat exchange strength.
As shown in fig. 5, a velocity vector diagram of the gas flow inside the turbine blade with the anti-slip pattern-shaped turbulence ribs provided by the embodiment of the present application is provided, compared with a common two-dimensional straight rib, the disturbance effect is weaker in the front and back step of the anti-slip pattern-shaped turbulence ribs, and mainly has a disturbance effect on the flow in the transverse direction of the flow to form disturbance similar to karman vortex, and the disturbance propagates downstream, so that a certain purpose of enhancing heat transfer is achieved. The reinforced heat transfer mechanism of the anti-skid pattern-shaped turbulence ribs is different from that of the two-dimensional straight ribs to a certain extent, and the transverse disturbance and mixing of the fluid are mainly promoted in the flowing process.
In some embodiments, a ribbed wall surface flat plate channel model is designed by combining structural parameters of a certain type of engine turbine guide vane and cold air flow parameters, comparison research on the flow state and the heat exchange performance of internal cooling air is carried out on a common two-dimensional straight rib structure and the anti-skid pattern-shaped turbulence rib of the invention through three-dimensional numerical simulation on the basis, in order to comprehensively compare the heat exchange performance of two types of ribs, the invention defines a comprehensive heat exchange performance parameter eta which represents the heat transfer intensity corresponding to unit pressure drop, and the specific formula of the comprehensive heat transfer performance index parameter eta is as follows:
in the formula (f) 0 =0.507*Re -0.3 ，f=Δp/(0.5*ρ*U 2 )。f 0 The coefficient of pressure loss of the common two-dimensional straight rib structure is shown, and f is the coefficient of pressure loss of the anti-skid pattern turbulence rib.
Wherein the dimensionless Knudsen number is defined as follows:
in the formula, h is a heat exchange coefficient, D is a characteristic length, lambda is a heat conduction coefficient, Re is an inlet Reynolds number, and Pr is a Plantt number.
The three-dimensional simulation calculation result shows that the comprehensive heat exchange performance of the anti-skid patterned turbulence rib is 21.2 percent higher than that of the common two-dimensional straight rib (rectangular cross section) structure in the range of the Re number of 11000-29000.
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 (10)
1. An anti-skid patterned turbulence rib is characterized in that the turbulence rib comprises four blade-shaped ribs with the same structure and appearance and a circular groove rib (5), the four blade profile ribs comprise a first diversion turbulence rib (1), a second diversion blade profile rib (2), a first converging blade profile rib (3) and a second converging blade profile rib (4), the first shunting turbulence rib (1) and the second shunting blade profile rib (2) are horizontally and symmetrically distributed at two sides right above the circular groove rib (5), the first confluence blade-shaped rib (3) and the second confluence blade-shaped rib (4) are horizontally and symmetrically distributed on two sides right below the circular groove rib (5), and the first diversion turbulence rib (1), the second diversion blade-shaped rib (2), the first confluence blade-shaped rib (3), the second confluence blade-shaped rib (4) and the circular groove rib (5) form an anti-skid patterned structure.
2. Rib according to claim 1, characterized in that the top of the rib (5) is provided with circular grooves, and the diameter D of the rib (5) is 1.0-2.0mm, the height H of the rib (5) is 1.2-2.5mm, the depth of the grooves is 0.15-0.35H, and the diameter of the grooves is 0.6D-0.9D.
3. The rib as claimed in claim 1, wherein the cross section of the bottom surface of the rib is a streamlined blade shape, the cross section of the bottom surface is divided into three regions smoothly connected in sequence, the three regions include a semi-elliptical region (8) disposed at the front section, a middle arc region (9) disposed at the middle section, and a rear arc region (10) disposed at the rear section, the major axis a of the semi-ellipse is 2.65 to 3.85 times the minor axis b, the radius R of the arc region of the middle section (9) is 1.82 a to 2.65 a, and the central angle θ of the middle section (9) is 28 ° to 39 °.
4. The rib of claim 2, wherein the airfoil rib is a chamfered structure, and a maximum height H of the airfoil rib is max 0.9-1.2H, minimum height H of the blade profile rib min Is 0.4-0.55H.
5. The rib of claim 2, wherein the horizontal distance S1 between the center point (O1) of the first rib and the center point (O2) of the second rib is 2.5 × D to 3.5 × D, and the included angle β 1 between the center lines of the first rib (1) and the second rib (2) is 82 ° to 96 °.
6. The rib of claim 2, wherein the vertical distance H1 between the center point (O1) of the first turbulator rib and the center point (O) of the circular groove rib is 1.35 x D to 1.65 x D.
7. Rib according to claim 2, characterized in that the horizontal distance S2 between the center point (O3) of the first and second rib (O4) is 2.5 to 3.5, and the angle β 2 between the centre lines of the first and second ribs (1, 2) is 88 ° to 105 °.
8. The rib of claim 2, wherein the vertical distance H2 between the center point (O3) of the first blade rib and the center point (O) of the circular groove rib is 1.05H 1-1.25H 1.
9. A turbine blade provided with a plurality of the above-described rib structures as claimed in any one of claims 1 to 8.
10. The turbine blade as in claim 9, wherein the plurality of rib arrays are arranged in a chord region of the turbine blade, and a distance S3 between two adjacent ribs in the airflow direction is 4-10mm, and a chord-wise distance S4 between two adjacent ribs perpendicular to the airflow direction is 3.5-12 mm.
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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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