A high-conductivity vane structure with a perforated plate impingement cooling

Abstract

A high-conductivity blade structure with orifice-plate impingement cooling comprises a high-conductivity outer casing, a high-conductivity inner support and a high-conductivity blade, the high-conductivity blade comprising an outer shroud, a blade body and an inner shroud; the upper chamber is formed between the outer shroud and the high-conductivity outer casing, and an upper orifice plate is arranged in the upper chamber; the lower chamber is formed between the inner shroud and the high-conductivity inner support, and a lower orifice plate is arranged in the lower chamber; a plurality of air holes are formed in the upper orifice plate and the lower orifice plate; a first air inlet is arranged on the high-conductivity outer casing and connected to the upper chamber; a second air inlet is arranged on the high-conductivity inner support and connected to the lower chamber; a front chamber and a rear chamber are arranged in the blade body; the upper chamber is connected to the rear chamber through a rear chamber inlet on the outer shroud; the lower chamber is connected to the front chamber through a front chamber inlet on the inner shroud; a film hole is arranged on the leading edge of the blade body and connected to the front chamber; and a split slot is arranged on the trailing edge of the blade body and connected to the rear chamber. The structure can achieve good cooling effect on the blade shroud.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine, and particularly relates to a high-conductivity blade structure with hole-plate impingement cooling. BACKGROUND

[0002] With the continuous improvement of the thrust-to-weight ratio and thermal efficiency of advanced aero-engines, the turbine inlet temperature is also rising. Although the continuous improvement of the turbine inlet temperature can greatly improve the performance of the aero-engine, it further deteriorates the working environment of the turbine blade, causing the turbine blade to have a high thermal load and a reduced service life, and directly affecting the safety of the engine.

[0003] The high-conductivity blade is the frontmost component of the turbine component, and is always impacted by high-temperature, high-pressure and high-speed gas, and is very easy to have local overheating and even cracking, which seriously affects the service life of the blade. Moreover, the turbine inlet temperature is far higher than the melting point temperature of the blade material at present, so it is necessary to improve the structure of the high-conductivity blade to ensure the normal working of the high-conductivity blade during the entire flight process.

[0004] In the prior art, some patents have disclosed high-conductivity blades with cooling structures. For example, the patent with the announcement number CN209742976U discloses a high-pressure turbine guide vane of a marine gas turbine with a cooling structure, which comprises an upper edge plate of the blade, a blade body and a lower edge plate of the blade. The upper edge plate of the blade is arranged at the top end of the blade profile, and the lower edge plate of the blade is arranged at the bottom end of the blade profile. The blade body comprises a middle plate of the blade, a suction surface of the blade, a pressure surface of the blade, an impact sleeve, a cavity partition plate, a plurality of suction surface side turbulence ribs, a plurality of pressure surface side turbulence horizontal ribs, a plurality of pressure surface side turbulence vertical ribs and a plurality of trailing edge turbulence columns.

[0005] However, the high-conductivity blade in the above-mentioned prior art has the problem that a part of the cooling gas directly enters the inner cavity of the blade body to cool the blade body due to the fact that the airflow is not limited. In a severe case, the turbine inlet gas temperature is high, which leads to insufficient cooling of the edge plate of the blade, and the edge plate of the high-conductivity blade is easy to have local overheating and even cracking. SUMMARY

[0006] The main purpose of the present application is to provide a high-conductivity blade structure with hole-plate impingement cooling, which aims to solve the above-mentioned technical problems.

[0007] To achieve the above object, the application provides a high-conductivity blade structure with a perforated plate impingement cooling, which comprises a high-conductivity blade installed between a high-conductivity outer casing and a high-conductivity inner support, wherein the high-conductivity blade comprises an outer rim plate, a blade body and an inner rim plate; the outer rim plate is arranged at the upper end of the blade body, and the inner rim plate is arranged at the lower end of the blade body; an upper chamber is formed between the outer rim plate and the high-conductivity outer casing, and an upper perforated plate is arranged in the upper chamber; a lower chamber is formed between the inner rim plate and the high-conductivity inner support, and a lower perforated plate is arranged in the lower chamber; a plurality of air holes are formed in the upper perforated plate and the lower perforated plate; a first air inlet is arranged on the high-conductivity outer casing and connected to the upper chamber; a second air inlet is arranged on the high-conductivity inner support and connected to the lower chamber; a front chamber and a rear chamber are arranged in the blade body; the upper chamber is connected to the rear chamber through a rear chamber inlet on the outer rim plate; the lower chamber is connected to the front chamber through a front chamber inlet on the inner rim plate; a film hole is arranged on the leading edge of the blade body and connected to the front chamber; and a split joint is arranged on the trailing edge of the blade body and connected to the rear chamber.

[0008] Preferably, a first area is arranged on the upper perforated plate, and no air hole is arranged in the first area; and the first area is located directly above the rear chamber inlet.

[0009] Preferably, a second area is arranged on the lower perforated plate, and no air hole is arranged in the second area; and the second area is located directly below the front chamber inlet.

[0010] Preferably, the thickness of the upper perforated plate and the lower perforated plate is 0.8 mm.

[0011] Preferably, the diameter of the air holes on the upper perforated plate and the lower perforated plate is φ1.5 mm.

[0012] Preferably, the air holes on the upper perforated plate are perpendicular to the outer rim plate; and the air holes on the lower perforated plate are perpendicular to the inner rim plate.

[0013] Preferably, an annular clamping groove is arranged on the right end of the high-conductivity outer casing, and an arc-shaped clamping table is integrally formed on the outer surface of the outer rim plate; the opening direction of the annular clamping groove is horizontally to the right, and the arc-shaped clamping table is clamped in the annular clamping groove.

[0014] Preferably, a slot is arranged on the high-conductivity inner support, and a plug is integrally formed on the lower surface of the inner rim plate; the opening direction of the slot is outward along the radial direction of the high-conductivity inner support, and the plug is inserted into the slot.

[0015] Preferably, a gap t1 with uniform spacing is formed between the lower surface of the upper perforated plate and the outer surface of the outer rim plate, and t1≥2 mm is satisfied.

[0016] Preferably, the upper surface of the lower orifice plate and the lower surface of the inner rim plate form a gap t2 with uniform spacing, satisfying: t2≥2mm.

[0017] Due to the adoption of the above technical solutions, the application has the following beneficial effects:

[0018] (1) In the application, the cold air of the two gas streams of the combustion chamber can be efficiently utilized to cool the high guide vane. Specifically, one gas stream enters the upper chamber from the first air inlet of the high guide outer casing, is dispersed and introduced by the upper orifice plate, and then enters the rear chamber of the blade body and finally flows out from the tail edge split of the blade body; the other gas stream enters the lower chamber from the second air inlet of the high guide inner support, is dispersed and introduced by the lower orifice plate, and then enters the front chamber of the blade body and finally flows out from the film hole of the leading edge of the blade body. By arranging the upper orifice plate and the lower orifice plate, the gas stream is dispersed and introduced, the dispersed gas stream can impact on the outer rim plate and the inner rim plate to perform convection heat exchange on the rim plates of the blade, and then enters the inner cavity of the blade body to cool the blade body.

[0019] (2) In the application, the flow direction of the gas stream is changed by the upper orifice plate and the lower orifice plate, the gas stream is prevented from directly entering the chamber inside the blade body, the outer rim plate and the inner rim plate can be well cooled, the local overheating or even cracking of the rim plates of the high guide vane during the use of the engine is avoided, the temperature gradient of the blade body is reduced, the strength and service life of the blade are improved, and the safety hidden danger is reduced.

[0020] (3) The high guide vane structure with orifice plate impact cooling provided by the application has low implementation cost, and the working environment of other turbine blades is not affected during the improvement of the high guide vane. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only some embodiments of the application, and other drawings can be obtained by those skilled in the art without creative labor based on the drawings shown.

[0022] Figure 1 FIG. 1 is a schematic view of the high guide vane structure with orifice plate impact cooling provided by the application;

[0023] Figure 2 FIG. 2 is a structural schematic view of the upper orifice plate in the application;

[0024] Figure 3 FIG. 3 is a structural schematic view of the lower orifice plate in the application;

[0025] Figure 4The high-conductivity blade rim temperature field distribution contrast chart of the high-conductivity blade without the orifice plate and the high-conductivity blade with the orifice plate is provided.

[0026] BRIEF DESCRIPTION OF DRAWINGS 1, high-conductivity blade; 2, high-conductivity outer casing; 2a, first air inlet; 2b, annular clamping groove; 3, high-conductivity inner support; 3a, second air inlet; 3b, insertion slot; 4, upper orifice plate; 4a, first area; 5, lower orifice plate; 5a, second area; 6, outer rim plate; 6a, rear cavity inlet; 6b, annular clamping table; 7, inner rim plate; 7a, front cavity inlet; 7b, insertion block; 8, blade body; 8a, front cavity; 8b, rear cavity; 8c, film hole; 9, upper cavity; 10, lower cavity; 11, air hole. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative labor fall within the protection scope of the present application.

[0028] It should be noted that all directionality indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative positional relationship, movement condition, etc. between components in a certain posture (as shown in the drawings), and if the certain posture changes, the directionality indications also change accordingly.

[0029] In addition, the description of “first”, “second” and the like in the present application is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features defined as “first”, “second” can explicitly or implicitly include at least one of the features. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of a person of ordinary skill in the art, and when the combination of technical solutions contradicts each other or cannot be realized, it should be considered that the combination of technical solutions does not exist and is not within the protection scope required by the present application.

[0030] Combination Figures 1 to 3As shown, it is a specific embodiment of a high-conductivity blade structure with hole-plate impingement cooling provided by the application, which comprises a high-conductivity blade 1 installed between a high-conductivity outer casing 2 and a high-conductivity inner support 3, wherein the high-conductivity blade 1 comprises an outer edge plate 6, a blade body 8 and an inner edge plate 7; the outer edge plate 6 is arranged at the upper end of the blade body 8, and the inner edge plate 7 is arranged at the lower end of the blade body 8; an upper chamber 9 is formed between the outer edge plate 6 and the high-conductivity outer casing 2, and an upper hole plate 4 is arranged in the upper chamber 9; a lower chamber 10 is formed between the inner edge plate 7 and the high-conductivity inner support 3, and a lower hole plate 5 is arranged in the lower chamber 10; a plurality of air holes 11 are formed in the upper hole plate 4 and the lower hole plate 5; a first air inlet 2a is arranged on the high-conductivity outer casing 2 to communicate with the upper chamber 9; a second air inlet 3a is arranged on the high-conductivity inner support 3 to communicate with the lower chamber 10; a front chamber 8a and a rear chamber 8b are arranged inside the blade body 8; the upper chamber 9 and the rear chamber 8b are communicated through a rear chamber inlet 6a on the outer edge plate 6; the lower chamber 10 and the front chamber 8a are communicated through a front chamber inlet 7a on the inner edge plate 7; a film hole 8c is arranged on the leading edge of the blade body 8, and the film hole 8c is communicated with the front chamber 8a; a split gap is arranged on the trailing edge of the blade body 8, and the split gap is communicated with the rear chamber 8b.

[0031] By adopting the above structure, the cooling principle is as shown in Figure 1 Figure 1 The arrows in the figure represent the direction of the airflow. Specifically: the cold air of the two airflows from the combustion chamber is used to cool the high-conductivity blade, one airflow enters the upper chamber 9 from the first air inlet 2a of the high-conductivity outer casing 2, and after the airflow is dispersed and guided through the upper hole plate 4, it enters the rear chamber 8b of the blade body 8, and finally flows out from the split gap of the trailing edge of the blade body 8; the other airflow enters the lower chamber 10 from the second air inlet 3a of the high-conductivity inner support 3, and after the airflow is dispersed and guided through the lower hole plate 5, it enters the front chamber 8a of the blade body 8, and finally flows out from the film hole 8c of the leading edge of the blade body 8. Therefore, by arranging the upper hole plate 4 and the lower hole plate 4, the effect of dispersing and guiding the airflow is achieved, and the dispersed airflow can impact on the outer edge plate 6 and the inner edge plate 7 to perform convective heat exchange on the inner and outer edge plates of the blade, and then enter the inner cavity of the blade body to cool the blade body.

[0032] In combination with Figure 2 Figure 3 ​​As shown, in order to further avoid the airflow directly entering into the front chamber 8a and the rear chamber 8b of the blade body 8, and make the airflow better impact cooling on the outer edge plate 6 and the inner edge plate 7, a first area 4a is arranged on the upper hole plate 4, and the air holes 11 are not arranged in the first area 4a; the first area 4a is located directly above the rear chamber inlet 6a, and a plurality of air holes 11 are arranged at intervals on the positions outside the first area 4a. A second area 5a is arranged on the lower hole plate 5, and the air holes 11 are not arranged in the second area 5a; the second area 5a is located directly below the front chamber inlet 7a, and a plurality of air holes 11 are arranged at intervals on the positions outside the second area 5a. Since the air holes 11 are not arranged on the first area 4a and the second area 5a, and the two areas block and limit the rear chamber inlet 6a and the front chamber inlet 7a respectively. Therefore, the airflow can first impact the inner edge plate 7 and the outer edge plate 6 of the blade for convective heat exchange, and then enter the inner cavity of the blade body 8 to cool the blade body.

[0033] In the embodiment, the thicknesses of the upper hole plate 4 and the lower hole plate 5 are both 0.8 mm. The diameters of the air holes 11 on the upper hole plate 4 and the lower hole plate 5 are both φ1.5 mm.

[0034] Further, the air holes 11 on the upper hole plate 4 are perpendicular to the outer edge plate 6; and the air holes 11 on the lower hole plate 5 are perpendicular to the inner edge plate 7. The purpose of the structure is to make the airflow vertically impact on the outer edge plate 6 and the inner edge plate 7 for convective heat exchange.

[0035] In combination Figure 1 As shown, an annular clamping groove 2b is arranged at the right end of the high-conductivity outer casing 2, and an arc-shaped clamping table 6b is integrally formed on the outer surface of the outer edge plate 6; the opening direction of the annular clamping groove 2b is horizontally to the right, and the arc-shaped clamping table 6b is clamped in the annular clamping groove 2b. A plug groove 3b is arranged on the high-conductivity inner support 3, and a plug block 7b is integrally formed on the lower surface of the inner edge plate 7; the opening direction of the plug groove 3b is outward along the radial direction of the high-conductivity inner support 3, and the plug block 7b is inserted into the plug groove 3b. By using the structure that the annular clamping groove 2b and the arc-shaped clamping table 6b are clamped with each other, and by using the structure that the plug block 7b and the plug groove 3b are inserted with each other, the high-conductivity blade 1 is conveniently and quickly assembled with the high-conductivity outer casing 2 and the high-conductivity inner support 3.

[0036] In combination Figure 1 As shown, in order to make the airflow after passing through the upper hole plate 4 uniformly impact cooling on the outer edge plate 6, it is required that a uniform gap t1 is formed between the lower surface of the upper hole plate 4 and the outer surface of the outer edge plate 6, and t1≥2 mm. Similarly, in order to make the airflow after passing through the lower hole plate 5 uniformly impact cooling on the inner edge plate 7, it is required that a uniform gap t2 is formed between the upper surface of the lower hole plate 5 and the lower surface of the inner edge plate 7, and t2≥2 mm.

[0037] In the present embodiment, the number of ventilation holes 11 on the upper hole plate 4 is not less than 88; the number of ventilation holes 11 on the lower hole plate 5 is not less than 88. Of course, the number of ventilation holes 11 can also be determined according to the area size of the inner edge plate 7 and the outer edge plate 6.

[0038] The above only describes the preferred embodiments of the present application, and does not limit the patent scope of the present application. Any equivalent structural transformation, direct / indirect application in other related technical fields, or the like within the inventive concept of the present application and using the content of the present application specification and drawings are included in the patent protection scope of the present application.

Claims

1. A high-guide blade structure with perforated plate impact cooling, comprising a high-guide blade (1) installed between a high-guide outer casing (2) and a high-guide inner support (3), wherein the high-guide blade (1) comprises an outer edge plate (6), a blade body (8), and an inner edge plate (7); the outer edge plate (6) is disposed at the upper end of the blade body (8), and the inner edge plate (7) is disposed at the lower end of the blade body (8); characterized in that: An upper chamber (9) is formed between the outer edge plate (6) and the high-conductivity outer casing (2), and an upper perforated plate (4) is provided in the upper chamber (9); a lower chamber (10) is formed between the inner edge plate (7) and the high-conductivity inner support (3), and a lower perforated plate (5) is provided in the lower chamber (10); multiple vent holes (11) are provided on both the upper perforated plate (4) and the lower perforated plate (5); a first air inlet (2a) is provided on the high-conductivity outer casing (2) and connects to the upper chamber (9); a second air inlet (3a) is provided on the high-conductivity inner support (3) and connects to the lower chamber (10); A front chamber (8a) and a rear chamber (8b) are provided inside the blade (8); the upper chamber (9) and the rear chamber (8b) are connected through a rear chamber inlet (6a) on the outer edge plate (6); the lower chamber (10) and the front chamber (8a) are connected through a front chamber inlet (7a) on the inner edge plate (7); An air film hole (8c) is provided at the leading edge of the blade (8), and the air film hole (8c) is connected to the front chamber (8a); a slit is provided at the trailing edge of the blade (8), and the slit is connected to the rear chamber (8b); A first region (4a) is provided on the upper perforated plate (4), and no vent (11) is provided in the first region (4a); the first region (4a) is located directly above the rear cavity inlet (6a); A second region (5a) is provided on the lower perforated plate (5), and the vent (11) is not provided in the second region (5a); the second region (5a) is located directly below the front cavity inlet (7a).

2. The high-conductivity blade structure with perforated plate impact cooling as described in claim 1, characterized in that: The thickness of both the upper perforated plate (4) and the lower perforated plate (5) is 0.8 mm.

3. The high-guide-force blade structure with perforated plate impact cooling as described in claim 1, characterized in that: The diameter of the vent holes (11) on the upper perforated plate (4) and the lower perforated plate (5) is φ1.5mm.

4. The high-conductivity blade structure with perforated plate impact cooling as described in claim 1, characterized in that: The vent hole (11) on the upper perforated plate (4) is perpendicular to the outer edge plate (6); the vent hole (11) on the lower perforated plate (5) is perpendicular to the inner edge plate (7).

5. The high-conductivity blade structure with perforated plate impact cooling as described in claim 1, characterized in that: An annular groove (2b) is provided at the right end of the high-conductivity outer casing (2), and an arc-shaped locking platform (6b) is integrally formed on the outer surface of the outer edge plate (6); the opening direction of the annular groove (2b) is horizontal to the right, and the arc-shaped locking platform (6b) is engaged in the annular groove (2b).

6. The high-conductivity blade structure with perforated plate impact cooling as described in claim 1, characterized in that: A slot (3b) is provided on the high-conducting inner support (3), and an insert (7b) is integrally formed on the lower surface of the inner edge plate (7); the opening direction of the slot (3b) is radially outward along the high-conducting inner support (3), and the insert (7b) is inserted into the slot (3b).

7. The high-conductivity blade structure with perforated plate impact cooling as described in claim 1, characterized in that: A uniformly spaced gap t1 is formed between the lower surface of the upper perforated plate (4) and the outer surface of the outer edge plate (6), satisfying: t1≥2mm.

8. The high-conductivity blade structure with perforated plate impact cooling as described in claim 1, characterized in that: A uniformly spaced gap t2 is formed between the upper surface of the lower perforated plate (5) and the lower surface of the inner edge plate (7), satisfying: t2≥2mm.

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