A structure for adjusting cold air flow distribution of an upper edge plate of a high-pressure turbine guide vane

Abstract

The application discloses a structure for adjusting cold gas flow distribution of an upper edge plate of a high-pressure turbine guide vane, comprising an outer casing and a high-pressure turbine guide vane; the high-pressure turbine guide vane is installed on the outer casing through the upper edge plate; a protection ring is arranged on the outer casing; a gas guide ring is arranged on the lower side of the protection ring; a gas guide groove is formed between the protection ring and the gas guide ring, and the opening direction of the gas guide groove is towards the blade body of the high-pressure turbine guide vane; a first area and a second area are formed on the protection ring and located on both sides of the blade front edge of the blade body; the first area is located on the blade basin side, and the second area is located on the blade back side; a plurality of first air inlets are arranged on the first area and are communicated with the gas guide groove; a plurality of second air inlets are arranged on the second area and are communicated with the gas guide groove; the total area of all the first air inlets in the first area is greater than the total area of all the second air inlets in the second area, so that the cold gas flow passing through the blade basin is increased, and the temperature of the upper edge plate of the blade is reduced.

Description

Technical Field

[0001] This invention relates to the field of aero-engine turbine blade cooling technology, and in particular to a structure for adjusting the distribution of cold air flow on the upper edge plate of a high-pressure turbine guide vane. Background Technology

[0002] The high-pressure turbine guide vane is located at the combustion chamber outlet and is directly exposed to the high-temperature combustion gas. The temperature level is relatively high, and the pressure at the blade head of the high-pressure turbine guide vane is higher than that at the blade back. This causes most of the cool air from the upstream outer casing to flow to the blade back side, making it difficult to form an effective cooling air film on the blade head side. As a result, the cooling effect is poor, and a significant high-temperature zone appears in the leading edge area of ​​the upper edge plate. Therefore, it is necessary to improve the cooling effect in this area and reduce the wall temperature.

[0003] In the prior art, for example, patent application CN115492643A discloses a cooling structure for the rim plate of an aero-engine turbine guide vane. Cooling gas is introduced into the cavity through various impact holes. The cooling gas entering the cavity impacts and cools the inner wall of the rim plate, creating turbulent flow. Finally, the cooling gas is discharged through various exhaust film holes, forming an air film on the inner surface of the rim plate, protecting it from high-temperature damage. Another example is patent application CN113202567A, which discloses a cooling structure design method for the rim plate of a high-pressure turbine guide vane. This method employs a combined cooling approach to cool the rim plate wall, reducing the hot spot temperature of the rim plate, improving the cooling effect, and extending the blade's lifespan.

[0004] However, none of the above-mentioned existing technologies can solve the problem that the pressure at the blade head of the high-pressure turbine guide vane is higher than the pressure at the blade back, causing most of the cool air from the upstream outer casing to flow to the blade back side, making it difficult to form an effective cooling air film on the blade head side and resulting in poor cooling effect. Summary of the Invention

[0005] The main objective of this invention is to propose a structure for adjusting the distribution of cold air flow on the upper edge plate of a high-pressure turbine guide vane, thereby solving the aforementioned technical problems.

[0006] To achieve the above objectives, this invention proposes a structure for adjusting the distribution of cold air flow on the upper edge plate of a high-pressure turbine guide vane, comprising an outer casing and a high-pressure turbine guide vane; the high-pressure turbine guide vane is mounted on the outer casing via an upper edge plate, a protective ring is provided on the outer casing, and an air guide ring is provided on the lower side of the protective ring, forming an air guide groove between the protective ring and the air guide ring, the opening of which faces the blade body of the high-pressure turbine guide vane; a first region and a second region are formed on both sides of the leading edge of the blade on the protective ring, the first region being located on the blade head side and the second region being located on the blade back side; a plurality of first air inlets are provided in the first region and connected to the air guide groove; a plurality of second air inlets are provided in the second region and connected to the air guide groove; the total area of ​​all first air inlets in the first region is greater than the total area of ​​all second air inlets in the second region.

[0007] Preferably, the diameter of the first air inlet is equal to the diameter of the second air inlet; the number of first air inlets in the first region is greater than the number of second air inlets in the second region.

[0008] Optionally, the number of first air inlets in the first region is equal to the number of second air inlets in the second region; the diameter of the first air inlet is greater than the diameter of the second air inlet.

[0009] Preferably, the first air inlet and the second air inlet are arranged in a circumferential ring.

[0010] Preferably, the protective ring is inclined, and the angle between the axial direction of the first or second air inlet and the blade axis is α, where α is an acute angle; the angle between the air outlet direction of the air guide groove and the axial direction of the first or second air inlet is β, where β = 90°.

[0011] Preferably, an annular baffle is provided at the front end of the inner wall of the outer casing, and a casing retaining ring is provided at the rear end of the inner wall; a blade retaining ring is provided on the outer side of the upper edge plate of the high-pressure turbine guide vane; the front end of the upper edge plate abuts against the annular baffle, and the blade retaining ring is engaged with the casing retaining ring.

[0012] Preferably, a sealing rope is provided between the front end of the upper edge plate and the annular baffle.

[0013] Preferably, a receiving groove is provided at the front end of the upper edge plate, and the sealing rope is installed in the receiving groove; the thickness of the sealing rope is greater than the depth of the receiving groove.

[0014] Preferably, an integrally formed mounting ring is provided on the outer side of the protective ring, and the connection between the mounting ring and the protective ring forms an air return groove.

[0015] Preferably, a mounting slot is provided on the mounting ring; the air return groove and the mounting slot make the cross-section of the mounting ring "S" shaped.

[0016] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0017] (1) In this invention, since the total area of ​​all first air inlets in the first region on the blade basin side is greater than the total area of ​​all second air inlets in the second region on the blade back side, the distribution of cold air flow through the blade basin side and blade back side is adjusted by using the leading edge of the blade as the dividing point and the different air inlet areas on both sides, thereby increasing the cold air flow through the blade basin and reducing the temperature of the upper edge plate of the blade. This invention solves the problem that the holes on the current outer casing are circumferentially uniformly arranged, which easily leads to a large induced air volume, a low amount of cold air flowing through the upper edge plate on the blade basin side, and a large amount of cold air flowing through the blade back side, resulting in a high temperature of the upper edge plate on the blade basin side.

[0018] (2) In this invention, by setting the angle between the axial direction of the first air inlet or the second air inlet and the blade axis to an acute angle, and setting the angle between the axial direction of the first air inlet or the second air inlet and the air outlet direction of the air guide groove to a right angle, the cold air flow entering from the first air inlet or the second air inlet can be blown along the air guide groove to the blade, thereby providing a better cooling effect on the blade.

[0019] (3) In this invention, the high-pressure turbine guide blades are installed on the outer casing by means of a structure in which the casing retainer and the blade retainer are interlocked. The structure is simple and easy to install. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced 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 the structures shown in these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the structure for adjusting the cold air flow distribution on the upper edge plate of the high-pressure turbine guide vane provided by the present invention;

[0022] Figure 2 The intake principle diagram is provided by the present invention for the structure of adjusting the cold air flow distribution on the upper edge plate of the high-pressure turbine guide vane;

[0023] Figure 3 This is a diagram showing the state of the cold air flowing out of the air inlet of the outer casing passing over the upper edge plate of the blade in this invention.

[0024] Explanation of reference numerals: 1. Outer casing; 1a. Protective ring; 1b. Air guide ring; 1c. Air guide groove; 1d. Annular baffle; 1e. Casing retaining ring; 2. High-pressure turbine guide vane; 2a. Upper edge plate; 2b. Blade body; 2c. Lower edge plate; 2d. Blade leading edge; 2e. Blade retaining ring; 3. First area; 3a. First air inlet; 4. Second area; 4a. Second air inlet; 5. Sealing rope; 6. Mounting ring; 6a. Air return groove; 6b. Mounting slot. Detailed Implementation

[0025] 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 a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0026] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0027] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0028] Combination Figure 1 , Figure 2As shown, a structure for adjusting the distribution of cold air flow on the upper edge plate of a high-pressure turbine guide vane includes an outer casing 1 and a high-pressure turbine guide vane 2. The high-pressure turbine guide vane 2 is mounted on the outer casing 1 via an upper edge plate 2a. A protective ring 1a is provided on the outer casing 1, and an air guide ring 1b is provided on the lower side of the protective ring 1a. An air guide groove 1c is formed between the protective ring 1a and the air guide ring 1b, and the opening direction of the air guide groove 1c faces the blade body 2b of the high-pressure turbine guide vane 2. A first region 3 and a second region 4 are formed on both sides of the leading edge 2d of the blade body 2b on the protective ring 1a. The first region 3 is located on the blade head side, and the second region 4 is located on the blade back side. A plurality of first air inlets 3a are provided in the first region 3 and connected to the air guide groove 1c. A plurality of second air inlets 4a are provided in the second region 4 and connected to the air guide groove 1c. The total area of ​​all the first air inlets 3a in the first region 3 is greater than the total area of ​​all the second air inlets 4a in the second region 4.

[0029] By adopting the above structure, with the leading edge 2d of the blade as the dividing point, the total air intake area of ​​the air intake holes set on both sides of the blade basin side and the blade back side is different, which achieves the effect of adjusting the distribution of cold air flow through the blade basin side and the blade back side. Since the total air intake area on the blade basin side is greater than the total air intake area on the blade back side, the cold air flow through the blade basin is increased, and the temperature of the upper edge plate of the blade is reduced.

[0030] To control the air intake area of ​​the air inlets in the first region 3 on the leaf blade side and the second region 4 on the leaf back side, the following method can be used:

[0031] ① The diameter of the first air inlet 3a is equal to the diameter of the second air inlet 4a, and the number of first air inlets 3a in the first region 3 is greater than the number of second air inlets 4a in the second region 4.

[0032] ② The number of first air inlets 3a in the first region 3 is equal to the number of second air inlets 4a in the second region 4; the diameter of the first air inlet 3a is greater than the diameter of the second air inlet 4a.

[0033] Both of the above methods can make the total area of ​​all first air inlets 3a in the first region 3 greater than the total area of ​​all second air inlets 4a in the second region 4, thereby increasing the flow rate of cold air passing through the blade basin.

[0034] Combination Figure 1 As shown, in order to facilitate the marking and accurate positioning of the first air inlet 3a and the second air inlet 4a during processing, the first air inlet 3a and the second air inlet 4a are arranged in a circumferential ring.

[0035] Combination Figure 2As shown, the protective ring 1a is inclined, and the angle between the axis of the first air inlet 3a or the second air inlet 4a and the axis of the blade 2b is α, where α is an acute angle; the angle between the air outlet direction of the air guide groove 1c and the axis of the first air inlet 3a or the second air inlet 4a is β, where β = 90°.

[0036] Cold airflow path Figure 2 As shown by the arrows, by controlling the angles as described above, the cool air can enter the air guide groove 1c along the axial direction of the first air inlet 3a and the second air inlet 4a, and then be blown towards the blade 2b along the air guide groove 1c, thus providing better cooling for the blade 2b.

[0037] Combination Figure 2 As shown, an annular stop 1d is provided at the front end of the inner wall of the outer casing 1, and a casing retaining ring 1e is provided at the rear end of the inner wall; a blade retaining ring 2e is provided on the outer side of the upper edge plate 2a of the high-pressure turbine guide vane 2; the front end of the upper edge plate 2a abuts against the annular stop 1d, and the blade retaining ring 2e is engaged with the casing retaining ring 1e. The annular stop 1d provides axial restraint, and the interlocking structure of the casing retaining ring 1e and the blade retaining ring 2e allows the high-pressure turbine guide vane 2 to be installed on the outer casing 1. The structure is simple and easy to install.

[0038] To ensure the airtightness between the high-pressure turbine guide vane 2 and the outer casing 1, a sealing rope 5 is provided between the front end of the upper edge plate 2a and the annular baffle 1d.

[0039] In this embodiment, a receiving groove is provided at the front end of the upper edge plate 2a, and the sealing rope 5 is installed in the receiving groove; the thickness of the sealing rope 5 is greater than the depth of the receiving groove. The receiving groove serves to install the sealing rope 5, and by designing the thickness of the sealing rope 5, the sealing effect is further guaranteed.

[0040] Combination Figure 1 As shown, an integrally formed mounting ring 6 is provided on the outer side of the protective ring 1a. An air return groove 6a is formed at the connection point between the mounting ring 6 and the protective ring 1a. The purpose of the mounting ring 6 is to facilitate the connection between the outer casing 1 and other components on the engine. Because of the air return groove 6a, the cold air blown onto the protective ring 1a forms a return flow at the location of the air return groove 6a (e.g., ...). Figure 1 As shown by the middle arrow A), the recirculated cold air can enter the first air intake 3a and the second air intake 4a, ensuring the effective intake of cold air.

[0041] Combination Figure 1As shown, a mounting groove 6b is provided on the mounting ring 6; the air return groove 6a and the mounting groove 6b make the cross-section of the mounting ring 6 form an "S" shape. The purpose of providing the mounting groove 6b is to facilitate the engagement of the outer casing 1 with other components on the engine. At the same time, the "S"-shaped structure of the cross-section strengthens the mounting ring 6, increasing its strength.

[0042] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A structure for adjusting the distribution of cold air flow on the upper edge plate of a high-pressure turbine guide vane, comprising an outer casing (1) and a high-pressure turbine guide vane (2); wherein the high-pressure turbine guide vane (2) is mounted on the outer casing (1) via an upper edge plate (2a), characterized in that: A protective ring (1a) is provided on the outer casing (1), and an air guide ring (1b) is provided on the lower side of the protective ring (1a). An air guide groove (1c) is formed between the protective ring (1a) and the air guide ring (1b). The opening direction of the air guide groove (1c) is towards the blade body (2b) of the high-pressure turbine guide blade (2). A first region (3) and a second region (4) are formed on both sides of the leading edge (2d) of the leaf blade (2b) on the protective ring (1a). The first region (3) is located on the leaf basin side, and the second region (4) is located on the leaf back side. Multiple first air inlets (3a) are provided in the first region (3) and connected to the air guide groove (1c); Multiple second air inlets (4a) are provided in the second region (4) and connected to the air guide groove (1c); The total area of ​​all first air inlets (3a) in the first region (3) is greater than the total area of ​​all second air inlets (4a) in the second region (4); The protective ring (1a) is inclined, and the angle between the axis of the first air inlet (3a) or the second air inlet (4a) and the axis of the blade (2b) is α, where α is an acute angle; the angle between the air outlet direction of the air guide groove (1c) and the axis of the first air inlet (3a) or the second air inlet (4a) is β, where β = 90°. An integrally formed mounting ring (6) is provided on the outer side of the protective ring (1a), and an air return groove (6a) is formed at the connection between the mounting ring (6) and the protective ring (1a).

2. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 1, characterized in that: The diameter of the first air inlet (3a) is equal to the diameter of the second air inlet (4a); The number of first air inlets (3a) in the first region (3) is greater than the number of second air inlets (4a) in the second region (4).

3. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 1, characterized in that: The number of first air inlets (3a) in the first region (3) is equal to the number of second air inlets (4a) in the second region (4); The diameter of the first air inlet (3a) is larger than the diameter of the second air inlet (4a).

4. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 1, characterized in that: The first air inlet (3a) and the second air inlet (4a) are arranged in a circumferential ring.

5. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 1, characterized in that: An annular baffle (1d) is provided at the front end of the inner wall of the outer casing (1), and a casing retaining ring (1e) is provided at the rear end of the inner wall. A blade retaining ring (2e) is provided on the outer side of the upper edge plate (2a) of the high-pressure turbine guide vane (2); The front end of the upper edge plate (2a) abuts against the annular baffle (1d), and the blade retaining ring (2e) is engaged with the casing retaining ring (1e).

6. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 5, characterized in that: A sealing rope (5) is provided between the front end of the upper edge plate (2a) and the annular baffle (1d).

7. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 6, characterized in that: A receiving groove is provided at the front end of the upper edge plate (2a), and the sealing rope (5) is installed in the receiving groove; the thickness of the sealing rope (5) is greater than the depth of the receiving groove.

8. The structure for adjusting the cold air flow distribution on the upper edge plate of a high-pressure turbine guide vane as described in claim 1, characterized in that: A mounting slot (6b) is provided on the mounting ring (6); the air return groove (6a) and the mounting slot (6b) make the cross section of the mounting ring (6) have an "S" shape.

Images