Laminate cooling structure with V-shaped turbulent flow ribs

Abstract

The invention belongs to the technical field of aero-engine turbine blade cooling, and particularly relates to a laminate cooling structure with V-shaped turbulent flow ribs, which comprises an impact pore plate and an air film pore plate, and a cold flow cavity is formed between the impact pore plate and the air film pore plate; one side of the cold flow cavity is communicated with the cold flow channel, and the other side of the cold flow cavity is communicated with the fuel gas channel; a plurality of turbulent flow units are arranged between the impact pore plate and the gas film pore plate; each turbulent flow unit comprises a plurality of air film holes formed in the air film hole plate, and a plurality of V-shaped turbulent flow ribs and a plurality of turbulent flow columns which are fixedly arranged with the air film hole plate; a plurality of impact holes are formed in the impact hole plate, and the impact holes and the air film holes are arranged in a staggered manner; the impact holes are located between every two adjacent turbulent flow units. The center of the impact hole and the connecting line of the centers of the two adjacent air film holes are coplanar; and the turbulent flow column is fixed with the impact pore plate. The structural design has the advantages of being simple in structure, convenient to machine and good in cooling effect.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine turbine blade cooling technology, and particularly relates to a layered cooling structure with V-shaped ribs. Background Technology

[0002] Aero engines are the powerhouse of the modern aviation industry. Currently, the turbine inlet temperature of advanced aero engines under development both domestically and internationally exceeds 2100K, far exceeding the maximum allowable temperature of 1370K for the most advanced third-generation single-crystal high-temperature alloys. Even with the protection of thermal barrier coatings, efficient cooling technologies are still required for heat dissipation. Therefore, turbine blade cooling technology is a crucial technology for ensuring the safety and performance of aero engines.

[0003] Laminate cooling technology, as one of the most advanced turbine blade cooling technologies, integrates cooling technologies such as impact cooling, internal enhanced heat transfer, and film cooling. It has high cooling efficiency and is now widely used in the design of cooling schemes for next-generation aero engines.

[0004] Generally speaking, the greater the airflow rate, the better the cooling effect on hot-end components. However, the airflow rate of an aero-engine is limited, and excessive consumption of cooling air will lead to a decrease in engine thrust and overall efficiency. Therefore, how to achieve better cooling effect with less cooling air consumption remains a significant technical challenge in aero-engine design.

[0005] Studies have shown that among various internal cooling structures for turbine blades, the fringe structure offers the best overall cooling performance and is the most widely used. Given the high heat transfer and low loss performance exhibited by the fringe structure, applying it to the optimized design of laminated cooling structures can further enhance the flow heat transfer between the cooling airflow within the laminated cooling structure's cavity and the film cooling plate, thereby improving the cooling performance of the laminated structure without increasing the amount of cooling air required.

[0006] Therefore, we propose a laminated cooling structure with V-shaped fringe ribs. Summary of the Invention

[0007] The purpose of this invention is to provide a layered cooling structure with V-shaped baffles to solve the above-mentioned problems.

[0008] To achieve the above objectives, the present invention provides the following solution:

[0009] A layered cooling structure with V-shaped baffles, comprising:

[0010] An impact orifice plate and a film gas orifice plate are provided, with a cold flow cavity formed between the impact orifice plate and the film gas orifice plate.

[0011] One side of the cold flow chamber is connected to the cold flow channel, and the other side of the cold flow chamber is connected to the gas flow channel;

[0012] Several turbulence units are provided between the impact perforated plate and the air film perforated plate;

[0013] The turbulence unit includes a plurality of air film holes formed on the air film perforated plate, and a plurality of V-shaped turbulence ribs and a plurality of turbulence columns fixedly disposed with the air film perforated plate.

[0014] Each pair of V-shaped ribs and one air film hole constitute a turbulence section. Within the same turbulence section, two V-shaped ribs are symmetrically arranged on both sides of the air film hole and the tips of the two V-shaped ribs face opposite directions.

[0015] The impact plate has a plurality of impact holes, which are staggered with the air film holes.

[0016] The impact hole is located between two adjacent turbulence units;

[0017] The center of the impact hole is coplanar with the line connecting the centers of two adjacent air film holes;

[0018] The turbulence column is fixed to the impact orifice plate.

[0019] Optionally, the turbulence unit includes a turbulence space, which is formed by a plurality of turbulence columns, with equal spacing between adjacent turbulence columns; the turbulence columns are distributed at the edge of the turbulence space.

[0020] Both the V-shaped ribs and the air film holes are disposed within the turbulence space;

[0021] Several flow-disrupting elements are provided within the flow-disrupting space;

[0022] The tips of several V-shaped spoiler ribs on the same side are collinear, and the straight line where the tips of the V-shaped spoiler ribs are located is collinear with the connecting line between two adjacent spoiler columns.

[0023] Optionally, the V-shaped spoiler rib has an opening angle α of 45°-60°.

[0024] Optionally, the height H of the V-shaped spoiler rib is 0.1-0.2 mm.

[0025] Optionally, the cross-sectional width W of the V-shaped spoiler rib is 0.1-0.4 mm.

[0026] Optionally, the length L of the long side of the V-shaped spoiler rib is 2-5 mm.

[0027] Optionally, the turbulence units are arranged in a matrix or in a row between the impact orifice plate and the film gas orifice plate.

[0028] Optionally, when the turbulence units are arranged in a row, the spacing between two adjacent turbulence units is equal.

[0029] Optionally, when the turbulence units are arranged in rows, the turbulence space is a rectangular space formed by two rows of turbulence columns. Each row of turbulence columns consists of several turbulence columns, and several turbulence columns in the same turbulence column group are arranged collinearly.

[0030] The connecting lines at the centers of the turbulence-disrupting columns form the edge line of the rectangular space.

[0031] Several of the aforementioned baffles are arranged in a row and located between two rows of the aforementioned baffle column groups;

[0032] Each of the aforementioned turbulence-disrupting elements is located between two adjacent turbulence-disrupting columns.

[0033] Optionally, when the turbulence units are arranged in a matrix, each turbulence unit is formed by four turbulence pillars enclosing a square space, and the connecting lines of the four turbulence pillars enclosing the edge line of the square space.

[0034] One of the aforementioned baffles is provided within each of the square spaces.

[0035] Compared with the prior art, the present invention has the following advantages and technical effects:

[0036] In use, the cooling airflow enters the cold flow chamber through the impact holes, forming a jet that impacts the cold side of the film cooling perforated plate. After impact, the cooling airflow undergoes sufficient heat exchange with the turbulence unit composed of V-shaped ribs, turbulence columns, and film holes before flowing out of the film holes and into the combustion gas passage, forming a film covering on the hot side of the film cooling perforated plate. By arranging V-shaped ribs and turbulence columns on the cold side of the film cooling perforated plate, the high heat transfer and low flow resistance characteristics of the turbulence structure are utilized to increase the convective heat transfer area of ​​the cooling airflow in the inner cavity without affecting the film covering effect. This is beneficial to increasing the cooling efficiency of the layered plate structure. Furthermore, the structural design of this invention is simple in structure, easy to process, and has a good cooling effect, and can be applied to the design of cooling schemes for various turbine blades. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 This is an isometric view of the present invention;

[0039] Figure 2 This is a top view of the arrangement of V-shaped ribs, ribs, impact holes, and air film holes in Embodiment 2 of the present invention.

[0040] Figure 3 This is an isometric view of the arrangement of V-shaped ribs, ribs, and air film holes in Embodiment 2 of the present invention;

[0041] Figure 4 This is an isometric view of the V-shaped turbulence rib of the present invention;

[0042] Among them, 1. Impact orifice plate; 2. V-shaped baffle rib; 3. Baffle column; 4. Impact hole; 5. Film air hole; 6. Film air orifice plate. Detailed Implementation

[0043] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0044] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0045] Example 1:

[0046] Reference Figures 1 to 4 This invention discloses a laminated cooling structure with V-shaped baffles, comprising:

[0047] A cold flow cavity is formed between the impact orifice plate 1 and the film air orifice plate 6.

[0048] One side of the cold flow chamber is connected to the cold flow channel, and the other side of the cold flow chamber is connected to the gas flow channel;

[0049] Several turbulence units are arranged between the impact orifice plate 1 and the film gas orifice plate 6;

[0050] The turbulence unit includes several air film holes 5 opened on the air film perforated plate 6, as well as several V-shaped turbulence ribs 2 and several turbulence columns 3 fixedly arranged with the air film perforated plate 6;

[0051] Two V-shaped ribs 2 and one air film hole 5 constitute a turbulence section. Within the same turbulence section, two V-shaped ribs 2 are symmetrically arranged on both sides of the air film hole 5 and the tips of the two V-shaped ribs 2 face opposite directions.

[0052] The impact plate 1 has several impact holes 4, which are staggered with the air film holes 5.

[0053] Impact hole 4 is located between two adjacent turbulence units;

[0054] The center of impact hole 4 is coplanar with the line connecting the centers of the two adjacent air film holes 5;

[0055] The turbulence column 3 is fixed to the impact orifice plate 1.

[0056] In use, the cooling airflow enters the cold flow cavity through the impact hole 4, forming a jet that impacts the cold side of the film perforated plate 6. After impact, the cooling airflow fully exchanges heat with the turbulence unit composed of the V-shaped turbulence ribs 2, turbulence columns 3, and film perforations 5, and then flows out from the film perforations 5 and enters the combustion passage, forming a film covering on the hot side of the film perforated plate 6. By arranging the V-shaped turbulence ribs 2 and turbulence columns 3 on the cold side of the film perforated plate 6, the high heat transfer and low flow resistance characteristics of the turbulence structure are utilized to increase the convective heat transfer area of ​​the cooling airflow in the inner cavity without affecting the film covering effect. This is beneficial to increasing the cooling efficiency of the layered plate structure. Moreover, the structural design of this invention has the characteristics of simple structure, convenient processing, and good cooling effect, and can be applied to the design of cooling schemes for various turbine blades.

[0057] Furthermore, the diameter of the air film hole 5 is between 0.3-1.0 mm, the pitch / row spacing of the air film hole 5 is between 0.5-1 mm, the diameter of the air film hole 5 / the diameter of the impact hole 4 is between 0.6-1.2 mm, and the row spacing of the air film hole 5 / the diameter of the air film hole 5 is between 5-10 mm.

[0058] Furthermore, the turbulence column 3 is cylindrical, the diameter of the air film hole 5 / the diameter of the turbulence column 3 is between 0.6 and 1.2, the pitch of the turbulence column 3 / the row spacing is equal to 1, the diameter of the air film hole 5 / the row spacing of the turbulence column 3 is between 0.2 and 0.4, and the diameter of the air film hole 5 / the height of the turbulence column 3 is between 0.6 and 1.2.

[0059] As an optional implementation, the turbulence unit is provided with a turbulence space, which is formed by a number of turbulence columns 3, with the spacing between two adjacent turbulence columns 3 being equal; the turbulence columns 3 are distributed at the edge of the turbulence space.

[0060] Both the V-shaped ribs 2 and the air film holes 5 are set in the turbulence space;

[0061] Several flow-disrupting elements are installed within the flow-disrupting space;

[0062] The tips of several V-shaped spoiler ribs 2 on the same side are collinear, and the straight line where the tip of the V-shaped spoiler rib 2 is located is collinear with the connecting line between two adjacent spoiler columns 3.

[0063] As an optional implementation, the V-shaped spoiler rib 2 has an opening angle α of 45°-60°.

[0064] As an optional implementation, the height H of the V-shaped spoiler rib 2 is 0.1-0.2 mm.

[0065] As an optional implementation, the cross-sectional width W of the V-shaped spoiler rib 2 is 0.1-0.4 mm.

[0066] As an optional implementation, the long side length L of the V-shaped spoiler rib 2 is 2-5mm.

[0067] As an optional implementation, the turbulence units are arranged in a matrix or in a row between the impact orifice plate 1 and the film gas orifice plate 6.

[0068] As an optional implementation, when the turbulence units are arranged in a row, the spacing between two adjacent turbulence units is equal.

[0069] As an optional implementation, when the turbulence units are arranged in rows, the turbulence space is a rectangular space formed by two rows of turbulence columns. Each row of turbulence columns consists of several turbulence columns 3, and several turbulence columns 3 in the same turbulence column group are arranged collinearly.

[0070] The connecting lines at the center of the spoiler column 3 enclose the edge of the rectangular space;

[0071] Several flow-dispersing elements are arranged in a row and located between two rows of flow-dispersing column groups;

[0072] Any of the turbulence-causing components is located between two adjacent turbulence-causing columns 3.

[0073] As an optional implementation, when the turbulence units are arranged in a matrix, the turbulence units are formed by four turbulence pillars 3 enclosing a square space, and the connecting lines of the four turbulence pillars 3 enclosing the edge line of the square space.

[0074] A spoiler is installed in each square space.

[0075] Example 2:

[0076] Taking the arrangement of the turbulence units in a row as an example, the present invention includes an impact perforated plate 1, a V-shaped turbulence rib 2, a cylindrical turbulence column 3, an impact hole 4, an air film hole 5, and an air film perforated plate 6.

[0077] Impact holes 4 and air film holes 5 are respectively provided on the impact orifice plate 1 and the air film orifice plate 6. The two ends of the cylindrical turbulence column 3 are respectively fixed to the air film orifice plate 6 and the impact orifice plate 1. There are several cylindrical turbulence columns 3, and they are distributed in a matrix.

[0078] A cold flow cavity is formed between the impact orifice plate 1 and the film gas orifice plate 6.

[0079] The cooling airflow enters the cold flow chamber through the impact hole 4, forming a jet that impacts the cold side of the film gas orifice plate 6. After the impact, the cooling airflow exchanges heat fully with the V-shaped turbulence ribs 2 and turbulence columns 3, and then flows out from the film gas hole 5 and enters the gas combustion passage, forming a film gas covering on the hot side of the film gas orifice plate 6.

[0080] The film air holes 5 and the impact holes 4 are arranged in a straight line, and turbulence columns 3 are set on both sides of the line connecting the staggered film air holes 5 and the impact holes 4.

[0081] On the cold side of the air film perforated plate 6, a V-shaped friction rib 2 is arranged at the midpoint of the line connecting the adjacent air film perforations 5 and the impact holes 4.

[0082] The ratio of the number of air film holes 5, impact holes 4, turbulence columns 3, and V-shaped turbulence ribs 2 is 1:1:2:2.

[0083] The V-shaped spoiler rib 2 is a V-shaped prism structure with a rectangular cross-section. The tip of the V-shaped spoiler rib 2 coincides with the center of the line connecting the axes of the adjacent spoiler columns 3. The V-shaped opening of the V-shaped spoiler rib 2 points towards the film air hole 5. Its opening angle α is between 45° and 60°, its length L is between 2 and 5 mm, its height H is between 0.1 and 0.2 mm, and its width W is between 0.1 and 0.4 mm.

[0084] Numerical calculation methods were used to verify the improvement in cooling efficiency.

[0085] The computational domain is divided into the main (gas) channel, the cooling gas channel, and the shelf cooling structure, with the two sides of the span defined as periodic boundary conditions.

[0086] Example 3:

[0087] This example illustrates a laminated cooling structure with wall-mounted baffles for turbine blades. The film cooling hole 5 has a diameter of 0.6 mm, the impingement hole 4 has a diameter of 0.6 mm, and the pitch of the impingement hole 4 is 6 mm. The combustion gas temperature is 2000 K, the mainstream pressure is 2.8 MPa, and the cooling gas temperature is 850 K. The baffle column 3 has a height and diameter of 0.6 mm and a diameter of 1 mm. The long side length of the V-shaped baffle 2 is 3 mm, the height of the V-shaped baffle 2 is 0.2 mm, and the width of the V-shaped baffle 2 is 0.4 mm.

[0088] The blowing ratio is defined as:

[0089]

[0090] Where, ρ c u c ρ represents the density and velocity of the cold air, respectively. ∞ u ∞ The prevailing density and velocity are as follows. In this example, the blowing ratio is taken as 0.8.

[0091] The flow and temperature fields were calculated using the commercial CFD software Ansys Fluent. The overall cooling efficiency was defined as:

[0092]

[0093] Among them, T g As the mainstream temperature, T w Here, T represents the temperature of the hot sidewall of the film cooling plate, and T represents the temperature of the cooling gas. Under the same computational boundary conditions, the average overall cooling efficiency using a conventional circular baffle plate is 0.758, while the average overall cooling efficiency of the plate with added baffles is 0.852, an improvement of 12.4%.

[0094] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0095] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A layered cooling structure with V-shaped baffles, characterized in that, include: An impact orifice plate (1) and a film gas orifice plate (6) are provided, and a cold flow cavity is formed between the impact orifice plate (1) and the film gas orifice plate (6); One side of the cold flow chamber is connected to the cold flow channel, and the other side of the cold flow chamber is connected to the gas flow channel; Several turbulence units are provided between the impact orifice plate (1) and the air film orifice plate (6); The turbulence unit includes a plurality of air film holes (5) opened on the air film perforated plate (6), and a plurality of V-shaped turbulence ribs (2) and a plurality of turbulence columns (3) fixedly disposed with the air film perforated plate (6); Each pair of V-shaped ribs (2) and one air film hole (5) constitute a turbulence section. Within the same turbulence section, two V-shaped ribs (2) are symmetrically arranged on both sides of the air film hole (5) and the tips of the two V-shaped ribs (2) face opposite directions. The impact plate (1) has a plurality of impact holes (4), and the impact holes (4) and the air film holes (5) are arranged alternately. The impact hole (4) is located between two adjacent turbulence units; The center of the impact hole (4) is coplanar with the line connecting the centers of the two adjacent air film holes (5); The turbulence column (3) is fixed to the impact plate (1).

2. The layered cooling structure with V-shaped baffles according to claim 1, characterized in that: The turbulence unit is provided with a turbulence space, which is formed by a plurality of turbulence columns (3), and the distance between two adjacent turbulence columns (3) is equal; the turbulence columns (3) are distributed at the edge of the turbulence space; The V-shaped turbulence rib (2) and the air film hole (5) are both disposed within the turbulence space; A plurality of the aforementioned turbulence-inducing components are provided within the turbulence-inducing space; The tips of several V-shaped ribs (2) on the same side are collinear, and the straight line where the tip of the V-shaped rib (2) is located is collinear with the connecting line between two adjacent ribs (3).

3. A layered cooling structure with V-shaped baffles according to claim 2, characterized in that: The V-shaped spoiler rib (2) has an opening angle α of 45°-60°.

4. A layered cooling structure with V-shaped baffles according to claim 2, characterized in that: The height H of the V-shaped spoiler rib (2) is 0.1-0.2 mm.

5. A layered cooling structure with V-shaped baffles according to claim 2, characterized in that: The cross-sectional width W of the V-shaped spoiler rib (2) is 0.1-0.4 mm.

6. A layered cooling structure with V-shaped baffles according to claim 2, characterized in that: The length L of the long side of the V-shaped spoiler rib (2) is 2-5mm.

7. A layered cooling structure with V-shaped baffles according to claim 2, characterized in that: The turbulence units are arranged in a matrix or in a row between the impact perforated plate (1) and the air film perforated plate (6).

8. A layered cooling structure with V-shaped baffles according to claim 7, characterized in that: When the turbulence-disrupting units are arranged in a row, the spacing between two adjacent turbulence-disrupting units is equal.

9. A layered cooling structure with V-shaped baffles according to claim 8, characterized in that: When the turbulence units are arranged in a row, the turbulence space is a rectangular space formed by two rows of turbulence columns. Each row of turbulence columns is composed of several turbulence columns (3). Several turbulence columns (3) in the same turbulence column group are arranged collinearly. The connecting lines of the centers of the turbulence-disrupting columns (3) enclose the edge line of the rectangular space; Several of the aforementioned baffles are arranged in a row and located between two rows of the aforementioned baffle column groups; Each of the aforementioned turbulence-disrupting elements is located between two adjacent turbulence-disrupting columns (3).

10. A layered cooling structure with V-shaped baffles according to claim 7, characterized in that: When the turbulence units are arranged in a matrix, the turbulence units are enclosed by four turbulence pillars (3) to form a square space, and the connecting lines of the four turbulence pillars (3) enclose the edge line of the square space; One of the aforementioned baffles is provided within each of the square spaces.

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