A sealing structure for the turbine baffle of an aeroengine

Abstract

A sealing structure for an aero-engine turbine baffle includes a turbine baffle, a turbine disk, a first sealing half-ring and a second sealing half-ring; during assembly, the deformed sliding end is positioned and clamped with the turbine baffle through cooperation with the sliding hole. When the turbine baffle is assembled onto the turbine disk, the sealing structure will not come out of the sealing ring cavity and get stuck between the turbine baffle and the turbine disk, eliminating the need for blind installation and providing good assembly performance. During operation, under the influence of centrifugal load and temperature load, etc., when the turbine baffle and the turbine disk change from the fitting state at the surface during assembly to a separated state, the deformed sliding end is radially freely extended in the sliding hole under the action of centrifugal load, sealing the gap formed between the turbine baffle and the turbine disk, ensuring sealing and avoiding non-designed leakage of the compressor cooling air.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and particularly relates to a sealing structure for a turbine baffle of an aero-engine. Background Art

[0002] The turbine is a hot-end component in an aero-engine and needs to introduce compressor air for cooling. The sealing structure plays an extremely important role in ensuring the full utilization of the compressor cooling air and avoiding non-design leakage. For an advanced aero-engine, when the engine speed and the inlet temperature of the turbine rotor remain unchanged, if the sealing of the high-pressure turbine reduces the leakage by 1%, the thrust increases by 8% and the fuel consumption rate decreases by 0.5%. Therefore, the sealing structure of the aero-engine turbine is of great significance for increasing the engine thrust, reducing the engine fuel consumption rate, improving the engine working efficiency and safety reliability.

[0003] With the continuous development of the engine towards the trends of high power, high performance and high reliability, the working temperature inside the engine is getting higher and higher. The non-metallic sealing rings used in traditional seals can no longer meet the usage requirements of the engine and are being replaced by more and more metal sealing rings.

[0004] Currently, high-temperature alloy open sealing rings are generally used in the turbines of aero-engines to seal between the baffle of the turbine during operation and the turbine disk. The cross-section of this sealing ring is "circular" and is assembled in the groove formed between the turbine baffle and the turbine disk. When the engine is operating, the open sealing ring springs open under the action of centrifugal load to ensure the sealing between the turbine baffle and the turbine disk. The structure of the sealing ring is as Figure 1 shown.

[0005] The existing sealing structure has the following disadvantages:

[0006] 1) During assembly, the sealing ring has no positioning and is blindly installed. During the assembly process, the sealing ring needs to be pre-placed in the groove of the turbine baffle. When the baffle is assembled onto the turbine disk, the sealing ring has no positioning in the groove and is blindly installed. It is impossible to determine whether the sealing ring is assembled in place, and there is a risk that the sealing ring will get stuck or even come out between the baffle and the disk, resulting in poor assembly performance;

[0007] 2) There are limitations in the selection of the diameter size of the circular cross-section of the sealing ring;

[0008] 3) When the diameter size of the "circular" open sealing ring is large, the sealing ring has strong rigidity, which is not conducive to the sealing ring springing open to the predetermined position under the action of centrifugal force during operation, and the ability to absorb the vibration of the turbine baffle decreases; when the diameter size of the "circular" open sealing ring is small, the sealing ring is likely to come out of the gap formed between the turbine baffle and the turbine disk during engine operation, hitting the rotor blades and other flow path components in the flow path and endangering the safety of the whole machine.

[0009] Therefore, how to more effectively seal between the turbine baffle and the turbine disk is a problem to be solved. Summary of the Invention

[0010] The purpose of the present application is to provide a sealing structure for an aeroengine turbine baffle to solve the problems of poor sealing effect and poor assembly between the turbine baffle and the turbine disk in the prior art.

[0011] The technical solution of the present application is: a sealing structure for an aeroengine turbine baffle, including a turbine baffle, a turbine disk, a first sealing half-ring and a second sealing half-ring; the turbine baffle and the turbine disk are coaxially and correspondingly connected, a sealing ring cavity is formed in the turbine baffle, the sealing ring cavity is coaxially arranged with the turbine disk, and the first sealing half-ring and the second sealing half-ring are symmetrically arranged on both sides inside the sealing ring cavity; both the first sealing half-ring and the second sealing half-ring are elastic members, four groups of sliding holes are formed in the turbine disk, and both ends of the first sealing half-ring and the second sealing half-ring are respectively inserted into different sliding holes to form a deformed sliding end, and the deformed sliding end passes through the sliding hole and extends out from the sliding hole; during operation, the deformed sliding end freely extends and deforms and slides into the sealing ring cavity along the sliding hole, and at the same time, as the sliding amount of the first sealing half-ring and the second sealing half-ring sliding into the sealing ring cavity increases, they deform themselves and always adhere to the side wall of the turbine disk.

[0012] Preferably, an annular support ring is provided on the inner side wall of the turbine baffle close to the turbine disk, a sealing ring cavity is formed between the support ring, the turbine baffle and the turbine disk, there is a gap between the support ring and the turbine disk, and the sliding holes are formed in the support ring; the support ring includes a conical section and a straight section, the conical section is arranged between the turbine baffle and the straight section, the straight section is arranged along the radial direction of the engine, and the outer surface of the conical section close to the turbine disk is an inwardly concave arc surface.

[0013] Preferably, the sliding holes are arranged along the extension and deformation direction of the deformed sliding end, and the width of the sealing ring cavity is more than one time the diameter of the first sealing half-ring and the second sealing half-ring.

[0014] Preferably, the deformed sliding end has an open arc structure.

[0015] A sealing structure for a turbine baffle of an aeroengine according to the present application includes a turbine baffle, a turbine disk, a first sealing half-ring, and a second sealing half-ring. During assembly, the deformed sliding end is positioned and clamped with the turbine baffle through cooperation with the sliding hole. When the turbine baffle is assembled onto the turbine disk, the sealing structure will not come out of the sealing ring cavity and be stuck between the turbine baffle and the turbine disk, eliminating the need for blind assembly and providing good assemblability. During operation, under the influence of centrifugal load and temperature load, etc., when the turbine baffle and the turbine disk change from the fitting state at the surface during assembly to a separated state, the deformed sliding end is radially freely extended in the sliding hole under the action of the centrifugal load, sealing the gap formed between the turbine baffle and the turbine disk, ensuring sealing, and avoiding non-designed leakage of the compressor cooling air. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] To more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.

[0017] Figure 1 Schematic diagram of the background technology structure;

[0018] Figure 2 Schematic diagram of the overall structure of the present application;

[0019] Figure 3 is Figure 2 Enlarged view of part A in

[0020] Figure 4 Circumferential partial enlarged view of the turbine baffle of the present application;

[0021] Figure 5 Schematic diagram of the sealing of the turbine baffle sealing structure during operation of the present application.

[0022] 1. Turbine baffle; 2. Turbine disk; 3. First sealing half-ring; 4. Second sealing half-ring; 5. Sealing ring cavity; 6. Sliding hole; 7. Deformed sliding end; 8. Support ring. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] To make the purpose, technical solutions, and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

[0024] A sealing structure for a turbine baffle of an aeroengine, as Figure 2-4 shown, includes a turbine baffle 1, a turbine disk 2, a first sealing half-ring 3, and a second sealing half-ring 4.

[0025] The turbine baffle 1 and the turbine disk 2 are coaxially and correspondingly connected. A sealing ring cavity 5 is formed inside the turbine baffle 1, and the sealing ring cavity 5 is coaxially arranged with the turbine disk 2. The first sealing half-ring 3 and the second sealing half-ring 4 are symmetrically arranged on both sides inside the sealing ring cavity 5.

[0026] Both the first sealing half-ring 3 and the second sealing half-ring 4 are elastic members. Four groups of sliding holes 6 are formed on the turbine disk 2. The two ends of the first sealing half-ring 3 and the second sealing half-ring 4 are respectively inserted into different sliding holes 6 to form a deformed sliding end 7, and the deformed sliding end 7 passes through the sliding hole 6 and extends out from the sliding hole 6.

[0027] During operation, the deformed sliding end 7 freely extends and deforms and slides into the sealing ring cavity 5 along the sliding hole 6. At the same time, as the amount of the first sealing half-ring 3 and the second sealing half-ring 4 sliding into the sealing ring cavity 5 along with the deformed sliding end 7 increases, they deform themselves and always adhere to the side wall of the turbine disk 2.

[0028] During assembly, the deformed sliding end 7 is positioned and clamped with the turbine baffle 1 through cooperation with the sliding hole 6. When the turbine baffle 1 is assembled onto the turbine disk 2, the sealing structure will not fall out of the sealing ring cavity 5 and be stuck between the turbine baffle 1 and the turbine disk 2, and blind installation is not required, so the assembly property is good.

[0029] During the working process, the cooling air introduced from the compressor flows into the dovetail groove of the turbine disk 2 through the air holes on the turbine baffle 1, and flows out through the inner cavity channel and the surface small holes of the turbine rotor blades to form an air film, reducing the surface temperature of the turbine rotor blades.

[0030] Combined Figure 5 , affected by centrifugal loads and temperature loads, etc., when the turbine baffle 1 and the turbine disk 2 change from the fitting state at the surface during assembly to a separated state, the deformed sliding end 7 is stretched freely along the radial direction in the sliding hole 6 under the action of the centrifugal load, blocking the gap formed between the turbine baffle 1 and the turbine disk 2 to ensure sealing and avoid non-designed leakage of the compressor cooling air.

[0031] Since the deformed sliding end 7 stretches freely along the radial direction in the sliding hole 6, but under the limitation of the sliding hole 6, its circumferential position is fixed and it can only slide out along the direction of the sliding hole 6. Under this limitation, the deformed sliding end 7 will not fall out of the sliding hole 6, and while the working track is stable, it will not damage other components in the flow passage.

[0032] Since the sealing between the turbine baffle 1 and the turbine disk 2 is controlled by the sliding amount of the deformed sliding end 7, the selection of the circular cross-section diameter size of the first sealing half-ring 3 and the second sealing half-ring 4 is not restricted.

[0033] Preferably, an annular support ring 8 is provided on the inner side wall of the turbine baffle 1 close to the turbine disk 2. A sealing ring cavity 5 is formed between the support ring 8, the turbine baffle 1 and the turbine disk 2. There is a gap between the support ring 8 and the turbine disk 2, and the sliding hole 6 is formed in the support ring 8.

[0034] The support ring 8 includes a conical section and a straight section. The conical section is arranged between the turbine baffle 1 and the straight section. The straight section is arranged along the radial direction of the engine. The outer surface of the conical section close to the turbine disk 2 is an inwardly concave arc surface.

[0035] By providing the support ring 8, stable support and limitation are provided for the first sealing half-ring 3 and the second sealing half-ring 4, ensuring the stable working performance of the sealing structure.

[0036] Preferably, the sliding hole 6 is arranged along the extension and deformation direction of the deformation sliding end 7. The width of the sealing ring cavity 5 is more than one time the diameter of the first sealing half-ring 3 and the second sealing half-ring 4. The inclined arrangement of the sliding hole 6 makes it easier for the first sealing half-ring 3 and the second sealing half-ring 4 to slide, and the friction force received is smaller.

[0037] The sliding hole 6 and the corners of the hole edge are polished smooth with a sand belt. After both ends of each section of the sealing ring pass through the small holes, a special tooling is used to bend the ends thereof to ensure the bending radian. By setting the width of the sealing ring cavity 5 to be larger, the first sealing half-ring 3 and the second sealing half-ring 4 have a larger deformation space to effectively seal between the turbine baffle 1 and the turbine disk 2.

[0038] Preferably, the deformation sliding end 7 has an open arc structure. During assembly, the sliding hole 6 and the corners of the hole edge are polished smooth with a sand belt. After the deformation sliding end 7 passes through the sliding hole 6, a special tooling is used to bend the ends thereof to ensure the bending radian. By setting the deformation sliding end 7 into an open arc structure, it is ensured that the first sealing half-ring 3 and the second sealing half-ring 4 can be stably limited and fixed by the deformation sliding end 7 when not working, and the deformation sliding end 7 can slide out stably during work.

[0039] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A sealing structure for an aeroengine turbine baffle, characterized in that: It includes a turbine baffle (1), a turbine disk (2), a first sealing half-ring (3) and a second sealing half-ring (4); the turbine baffle (1) and the turbine disk (2) are coaxially and correspondingly connected, a sealing ring cavity (5) is formed inside the turbine baffle (1), the sealing ring cavity (5) is coaxially arranged with the turbine disk (2), and the first sealing half-ring (3) and the second sealing half-ring (4) are symmetrically arranged on both sides inside the sealing ring cavity (5). Both the first sealing half-ring (3) and the second sealing half-ring (4) are elastic members. Four groups of sliding holes (6) are formed on the turbine disk (2). The two ends of the first sealing half-ring (3) and the second sealing half-ring (4) are respectively inserted into different sliding holes (6) to form a deformation sliding end (7), and the deformation sliding end (7) passes through the sliding hole (6) and extends out from the sliding hole (6). During operation, the deformation sliding end (7) freely extends and deforms and slides into the sealing ring cavity (5) along the sliding hole (6). At the same time, as the sliding amount of the first sealing half-ring (3) and the second sealing half-ring (4) sliding into the sealing ring cavity (5) increases along with the deformation sliding end (7), they deform themselves and always adhere to the side wall of the turbine disk (2). An annular support ring (8) is arranged on the inner side wall of the turbine baffle (1) close to the turbine disk (2). A sealing ring cavity (5) is formed between the support ring (8), the turbine baffle (1) and the turbine disk (2). There is a gap between the support ring (8) and the turbine disk (2), and the sliding holes (6) are formed on the support ring (8). The support ring (8) includes a conical section and a straight section. The conical section is arranged between the turbine baffle (1) and the straight section. The straight section is arranged along the radial direction of the engine. The outer surface of the conical section close to the turbine disk (2) is an inwardly concave arc surface. The sliding holes (6) are arranged along the extension and deformation direction of the deformation sliding end (7). The width of the sealing ring cavity (5) is more than one time the diameter of the first sealing half-ring (3) and the second sealing half-ring (4); the deformation sliding end (7) is in an open arc structure.

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