Laminate cooling structure with wall turbulence ribs

Abstract

The invention belongs to the technical field of aero-engine turbine blade cooling, and particularly relates to a laminate cooling structure with wall turbulence ribs, which comprises an impact orifice plate and an air film orifice plate, and a cold flow cavity is formed between the impact orifice plate and the air film orifice 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 rectangular 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] The application belongs to the field of turbine blade cooling technology of an aero-engine, and particularly relates to a panel cooling structure with wall surface turbulence rib. BACKGROUND

[0002] An aero-engine is the power core of modern aviation industry. At present, the turbine inlet temperature of advanced aero-engines researched at home and abroad has exceeded 2100K, which is far higher than the maximum allowable temperature 1370K of the third generation single-crystal high-temperature alloy, the most advanced one at present. Even with the protection of thermal barrier coating, high-efficiency cooling technology is still needed to achieve heat dissipation. Therefore, turbine blade cooling technology is an important technology to ensure the safety and performance of an aero-engine.

[0003] As one of the most advanced turbine blade cooling technologies at present, the panel cooling technology has the functions of impingement cooling, internal heat transfer enhancement and film cooling, and has a high cooling efficiency. The panel cooling technology has been widely applied to the cooling scheme design of a new generation of aero-engines.

[0004] Generally, the greater the cold air flow is, the better the cooling effect of the hot end component is. However, the air flow of an aero-engine is limited, and excessive consumption of cold air will lead to the decrease of the thrust and overall efficiency of the engine. Therefore, how to obtain better cooling effect under the condition of consuming less cold air is still an important technical problem faced by the current aero-engine design.

[0005] Researches show that, among various internal cooling structures of turbine blades, the turbulence rib structure is one of the most widely used structures in terms of comprehensive cooling effect. In view of the high heat transfer and low loss performance of the turbulence rib structure, the application of the turbulence rib structure in the optimization design of the panel cooling structure can further enhance the flow heat transfer between the cooling air flow in the internal cavity of the panel cooling structure and the film hole plate, and further improve the cooling performance of the panel structure without increasing the amount of cold air.

[0006] Therefore, the application provides a panel cooling structure with wall surface turbulence rib. SUMMARY

[0007] The application aims to provide a panel cooling structure with wall surface turbulence rib to solve the above problems.

[0008] To achieve the above object, the application provides the following scheme.

[0009] A panel cooling structure with wall surface turbulence rib comprises:

[0010] An impingement hole plate and a film hole plate, a cold flow cavity is formed between the impingement hole plate and the film hole plate;

[0011] The cold flow cavity is communicated with a cold gas flow channel on one side and a fuel gas flow channel on the other side;

[0012] A plurality of turbulence units are arranged between the impact hole plate and the film hole plate.

[0013] The turbulence unit comprises a plurality of film holes formed on the film hole plate, and a plurality of rectangular turbulence ribs and a plurality of turbulence columns fixedly arranged on the film hole plate.

[0014] Every four rectangular turbulence ribs and one film hole constitute a turbulence part, and the four rectangular turbulence ribs are arranged around the film hole in the same turbulence part.

[0015] A plurality of impact holes are formed on the impact hole plate, and the impact holes are arranged alternately with the 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 film holes.

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

[0019] Optionally, a turbulence space is arranged in the turbulence unit, the turbulence space is formed by a plurality of turbulence columns, the distance between two adjacent turbulence columns is equal, and the turbulence columns are distributed on the edge of the turbulence space.

[0020] The rectangular turbulence rib and the film hole are arranged in the turbulence space.

[0021] A plurality of turbulence parts are arranged in the turbulence space.

[0022] The rectangular turbulence rib is arranged in line with two adjacent turbulence columns.

[0023] Optionally, the length L of the rectangular turbulence rib is 2-5 mm.

[0024] Optionally, the height H of the rectangular turbulence rib is 0.1-0.2 mm.

[0025] Optionally, the cross-sectional width W of the rectangular turbulence rib is 0.1-0.4 mm.

[0026] Optionally, the turbulence units are arranged in a matrix or in a row between the impact hole plate and the film hole plate.

[0027] Optionally, when the turbulence units are arranged in a row, the distance between two adjacent turbulence units is equal.

[0028] Optionally, when the turbulence unit is arranged in rows, the turbulence space is a rectangular space formed by two rows of turbulence column groups, each of which is composed of a plurality of turbulence columns, and the plurality of turbulence columns in the same turbulence column group are arranged in a line;

[0029] The connecting lines of the centers of the turbulence columns form the edge lines of the rectangular space;

[0030] The plurality of turbulence portions are arranged in rows and located between the two rows of turbulence column groups;

[0031] Any of the turbulence portions is located between two adjacent turbulence columns.

[0032] Optionally, when the turbulence unit is arranged in rows, the number ratio of the gas film hole, the impact hole, the turbulence column and the rectangular turbulence rib is 1:1:2:3.

[0033] Optionally, when the turbulence unit is arranged in a matrix, the turbulence unit is surrounded by four turbulence columns to form a square space, and the connecting lines of the four turbulence columns form the edge lines of the square space.

[0034] Each of the square spaces is provided with one turbulence portion.

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

[0036] In use, the cooling air flows through the impact hole into the cold flow cavity to form a jet flow impacting the cold side of the gas film hole plate, and the cooling air after impact exchanges heat with the turbulence unit composed of the rectangular turbulence rib, the turbulence column and the gas film hole, and then flows out from the gas film hole and enters the gas passage to form a gas film cover on the hot side of the gas film hole plate. By arranging the rectangular turbulence rib and the turbulence column on the cold side of the gas film hole plate, the high heat exchange and low flow resistance characteristics of the turbulence structure are utilized to increase the convective heat exchange area of the cooling air in the inner cavity without affecting the gas film cover effect, which is beneficial to increasing the cooling efficiency of the layer plate structure, and the structural design of the present application has the characteristics of simple structure, convenient processing and good cooling effect, and can be applied to the cooling scheme design of various turbine blades. BRIEF DESCRIPTION OF DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor under the premise of the drawings:

[0038] Fig. 1 The isometric view of the present application;

[0039] Fig. 2 It is the plan view of the rectangular spoiler rib, the spoiler column, the impact hole, the air film hole arrangement of embodiment 2 of the application;

[0040] Fig. 3 It is the axonometric view of the rectangular spoiler rib of the application;

[0041] Wherein, 1, impact hole plate; 2, rectangular spoiler rib; 3, spoiler column; 4, impact hole; 5, air film hole; 6, air film hole plate. DETAILED DESCRIPTION

[0042] The technical solutions in the embodiments of the application will be apparently and completely described below with the drawings in the embodiments of the application, and obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by the person skilled in the art without creative labor belong to the protection scope of the application.

[0043] In order to make the above-mentioned purposes, features and advantages of the application more apparent and easy to understand, the application will be further described in detail below with the drawings and specific embodiments.

[0044] Embodiment 1:

[0045] Reference Figs. 1 to 3 The application discloses a kind of wall surface spoiler rib's laminate cooling structure, comprising:

[0046] Impact hole plate 1 and air film hole plate 6, cold flow cavity is formed between impact hole plate 1 and air film hole plate 6;

[0047] Cold flow cavity side is communicated with cold gas flow channel, and cold flow cavity other side is communicated with gas flow channel;

[0048] Impact hole plate 1 and air film hole plate 6 are provided with several spoiler units;

[0049] Spoiler unit includes several air film holes 5 opened on air film hole plate 6, and several rectangular spoiler ribs 2 and several spoiler columns 3 fixedly arranged with air film hole plate 6;

[0050] Every four rectangular spoiler ribs 2 and an air film hole 5 constitute a spoiler part, and four rectangular spoiler ribs 2 are arranged around the periphery of air film hole 5 in the same spoiler part;

[0051] Several impact holes 4 are opened on impact hole plate 1, and impact hole 4 is staggered with air film hole 5;

[0052] Impact hole 4 is located between adjacent two spoiler units;

[0053] The center of impact hole 4 is coplanar with the connecting line of the center of adjacent two air film holes 5;

[0054] The turbulence column 3 is fixed with the impingement orifice plate 1.

[0055] In use, the cooling airflow enters the cold flow cavity through the impingement orifice 4, forms a jet flow to impinge on the cold side of the film hole plate 6, and after fully exchanging heat with the turbulence unit composed of the rectangular turbulence rib 2, the turbulence column 3 and the film hole 5, flows out from the film hole 5 and enters the gas passage, and forms a gas film cover on the hot side of the film hole plate 6. By arranging the rectangular turbulence rib 2 and the turbulence column 3 on the cold side of the film hole plate 6, the high heat exchange and low flow resistance characteristics of the turbulence structure are utilized, the convective heat exchange area of the cooling airflow in the cavity is increased without affecting the gas film cover effect, which is beneficial to increase the cooling efficiency of the panel structure, and the structure design of the application has the characteristics of simple structure, convenient processing and good cooling effect, and can be applied to the cooling scheme design of various turbine blades.

[0056] As an optional embodiment, a turbulence space is arranged in the turbulence unit, the turbulence space is formed by a plurality of turbulence columns 3, and the distance between adjacent two turbulence columns 3 is equal; and the turbulence columns 3 are distributed on the edges of the turbulence space.

[0057] The rectangular turbulence rib 2 and the film hole 5 are arranged in the turbulence space.

[0058] A plurality of turbulence parts are arranged in the turbulence space.

[0059] The rectangular turbulence rib 2 is arranged in line with the adjacent two turbulence columns 3.

[0060] As an optional embodiment, the length L of the rectangular turbulence rib 2 is 2-5 mm.

[0061] As an optional embodiment, the height H of the rectangular turbulence rib 2 is 0.1-0.2 mm.

[0062] As an optional embodiment, the cross-sectional width W of the rectangular turbulence rib 2 is 0.1-0.4 mm.

[0063] As an optional embodiment, the turbulence units are arranged in a matrix or in a row between the impingement orifice plate 1 and the film hole plate 6.

[0064] As an optional embodiment, when the turbulence units are arranged in a row, the distance between adjacent two turbulence units is equal.

[0065] As an optional embodiment, 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 column groups is composed of a plurality of turbulence columns 3, and the plurality of turbulence columns 3 in the same turbulence column group are arranged in line.

[0066] The connecting line of the centers of the turbulence columns 3 forms the edge line of the rectangular space.

[0067] The several turbulence parts are arranged in rows and located between two rows of turbulence column groups.

[0068] Any turbulence part is located between two adjacent turbulence columns 3.

[0069] As an optional embodiment, when the turbulence units are arranged in rows, the number ratio of the film holes 5, the impact holes 4, the turbulence columns 3 and the rectangular turbulence ribs 2 is 1:1:2:3.

[0070] As an optional embodiment, when the turbulence units are arranged in a matrix, the turbulence units are surrounded by four turbulence columns 3 to form a square space, and the connecting lines of the four turbulence columns 3 form the edge lines of the square space.

[0071] One turbulence part is arranged in each square space.

[0072] Embodiment 2:

[0073] Taking the case that the turbulence units are arranged in rows, the application comprises an impact hole plate 1, a rectangular turbulence rib 2, a cylindrical turbulence column 3, an impact hole 4, a film hole 5 and a film hole plate 6.

[0074] The impact hole plate 1 and the film hole plate 6 are respectively provided with impact holes 4 and film holes 5 arranged in a staggered manner, and the two ends of the cylindrical turbulence column 3 are respectively fixedly connected to the film hole plate 6 and the impact hole plate 1; the cylindrical turbulence column 3 has several and is distributed in a matrix.

[0075] A cold flow cavity is formed between the impact hole plate 1 and the film hole plate 6.

[0076] The cooling air flows into the cold flow cavity through the impact hole 4 to form a cold side of the jet impact film hole plate 6, and the cooling air after impact flows out from the film hole 5 after fully exchanging heat with the rectangular turbulence rib 2 and the turbulence column 3 and enters the gas passage to form a gas film cover on the hot side of the film hole plate 6.

[0077] The film holes 5 and the impact holes 4 adopt a forward arrangement, and the turbulence columns 3 are arranged on both sides of the connecting lines of the staggered film holes 5 and the impact holes 4.

[0078] The cold side of the film hole plate 6, the middle positions of the connecting lines between adjacent film holes 5 and the middle positions of the connecting lines of adjacent film holes 5 and impact holes 4 are evenly arranged with the rectangular turbulence ribs 2.

[0079] The number ratio of the film holes 5, the impact holes 4, the turbulence columns 3 and the rectangular turbulence ribs 2 is 1:1:2:3.

[0080] The rectangular turbulence rib 2 is a quadrangular prism with a rectangular cross section, the length L is 2-5 mm, the height H of the rectangular turbulence rib 2 is 0.1-0.2 mm, and the width W of the rectangular turbulence rib 2 is 0.1-0.4 mm.

[0081] The numerical calculation method is used to verify the improvement effect of the cooling efficiency.

[0082] The calculation region is divided into a main flow (gas) channel, a cooling gas channel and a panel cooling structure, and the two span sides are defined as periodic boundary conditions.

[0083] Example 3:

[0084] This example is a panel cooling structure with wall disturbance ribs for a turbine blade. The diameter of the film hole 5 is 0.6mm, the diameter of the impact hole 4 is 0.6mm, and the pitch of the impact hole 4 is 6mm. The gas temperature is 2000K, the main flow pressure is 2.8MPa, and the cooling gas temperature is 850K. The height of the disturbance column 3 is 0.6mm, the diameter of the disturbance column 3 is 1mm, the length of the rectangular disturbance rib 2 is 3mm, the height of the rectangular disturbance rib 2 is 0.2mm, and the width of the rectangular disturbance rib 2 is 0.4mm.

[0085] The blowing ratio is defined as:

[0086]

[0087] Wherein, ρ c , u c are the density and velocity of the cooling gas, and ρ ∞ , u ∞ are the density and velocity of the main flow. In this example, the blowing ratio is 0.8.

[0088] The commercial CFD software Ansys Fluent is used to calculate and solve the flow field and temperature field. The comprehensive cooling efficiency is defined as:

[0089]

[0090] Wherein, T g is the main flow temperature, T w is the hot side wall temperature of the film hole plate, and T is the cooling gas temperature. Under the same calculation boundary conditions, the average comprehensive cooling efficiency of the traditional circular disturbance column panel is 0.758, and the average comprehensive cooling efficiency of the panel after adding the disturbance rib is 0.844, which is increased by 11.3%.

[0091] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0092] The above described embodiments are only to illustrate the preferred modes of the present application, and are not intended to limit the scope of the present application. Any modification and improvement made by those skilled in the art to the technical solutions of the present application without departing from the design spirit of the present application shall fall within the protection scope of the present application.

Claims

1. A layered cooling structure with wall-mounted 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 rectangular turbulence ribs (2) and a plurality of turbulence columns (3) fixedly disposed with the air film perforated plate (6); Each set of four rectangular ribs (2) and one air film hole (5) constitutes a turbulence section. Within the same turbulence section, four rectangular ribs (2) are arranged around the air film hole (5). 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 plate cooling structure with wall-mounted 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 rectangular rib (2) and the air film hole (5) are both disposed within the turbulence space; Several flow-disrupting elements are provided within the flow-disrupting space; The rectangular baffle rib (2) is arranged collinearly with the two adjacent baffle columns (3).

3. A layered cooling structure with wall-mounted baffles according to claim 2, characterized in that: The length L of the rectangular spoiler rib (2) is 2-5mm.

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

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

6. A layered cooling structure with wall-mounted 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).

7. A layered cooling structure with wall-mounted baffles according to claim 6, characterized in that: When the turbulence-disrupting units are arranged in a row, the spacing between two adjacent turbulence-disrupting units is equal.

8. A layered cooling structure with wall-mounted baffles according to claim 7, 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).

9. A layered cooling structure with wall-mounted baffles according to claim 7, characterized in that: When the turbulence units are arranged in a row, the ratio of the number of the air film holes (5), the impact holes (4), the turbulence columns (3) and the rectangular turbulence ribs (2) is 1:1:2:

3.

10. A layered cooling structure with wall-mounted baffles according to claim 6, 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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