Tadpole-shaped turbine baffle sealing ring

Abstract

The present application belongs to the field of sealing structures of aero-engines, and is a tadpole-shaped turbine baffle sealing ring, comprising an integrally arranged first ring body, a second ring body and an intermediate connecting ring; when the engine is working, the turbine baffle is affected by centrifugal loads and temperature loads, and changes from a fitted state to a separated state at the surface of the turbine disc and forms a gap N. The open tadpole-shaped sealing ring is radially opened to a predetermined position by the centrifugal load, and the gap N formed between the turbine baffle and the turbine disc is blocked, thereby ensuring a tight seal, avoiding non-designed leakage of compressor cooling air, ensuring that the air path between the turbine baffle and the turbine disc is sealed, and having vibration absorption capability. Due to the unique cross-sectional shape of the tadpole-shaped sealing ring, the tadpole-shaped sealing ring forms a deformed sealing state under the action of the centrifugal load during operation, which is more conducive to increasing the pressing force on the turbine baffle and the turbine disc, and improving the sealing effect. At the same time, the tadpole-shaped sealing ring uses less material than the circular sealing ring.

Description

Technical Field

[0001] The present application belongs to the field of aero-engine sealing structures, and in particular relates to a tadpole-shaped turbine baffle sealing ring. Background Art

[0002] The sealing structure in aircraft engines plays an extremely important role in improving engine efficiency and ensuring safe operation of the engine. As the engine continues to develop towards high power and high performance, the temperature before the turbine of the engine is getting higher and higher, which has exceeded the material tolerance limit of some components, and it is necessary to design a cooling flow path to reduce its temperature level. When designing the cooling flow path, metal sealing rings are widely used. This structure can seal the cooling air and avoid air loss, which can increase engine thrust, reduce engine fuel consumption, and improve engine and aircraft working efficiency and safety reliability.

[0003] As a high-temperature component in the engine, the turbine generally uses the method of drawing air from the compressor to form a cooling air flow path inside and on the surface of the blades in the flow channel to reduce its temperature level. In order to avoid undesigned leakage of cooling air in the cooling flow path, a "circular" cross-section open seal ring is generally used to seal between the turbine baffle (or comb sealing disk) and the turbine disk during operation. The cross-section of the seal ring is "circular" and it is assembled in the groove formed between the turbine baffle and the turbine disk. When the engine is working, the open seal ring pops open under the action of centrifugal load to ensure the seal between the turbine baffle and the turbine disk. The structure of the seal ring is as follows: Figure 1 shown.

[0004] The diameter size selection of "round" sealing rings is limited.

[0005] 1) If the diameter of the "round" sealing ring is large, the sealing ring is too rigid, which is not conducive to the rebound under the action of centrifugal force during operation, resulting in a decrease in sealing ability and vibration absorption ability;

[0006] 2) If the diameter of the "round" sealing ring is small, the sealing ring may easily fall out from the gap between the turbine baffle and the turbine disk during operation, damaging the blades and other flow path parts, endangering the safety of the test run.

[0007] Therefore, how to more effectively seal the turbine baffle and the turbine disk is a problem that needs to be solved. Summary of the invention

[0008] The purpose of the present application is to provide a tadpole-shaped turbine baffle sealing ring to solve the problems of poor sealing effect and poor assembly performance between the turbine baffle and the turbine disk in the prior art.

[0009] The technical solution of the present application is: a tadpole-shaped turbine baffle sealing ring, arranged in a sealing groove between the turbine baffle and the turbine disk, comprising an integrally arranged first ring body, a second ring body and an intermediate connecting ring; the first ring body, the second ring body and the intermediate connecting ring are all full-ring structures, the cross-sections of the first ring body and the second ring body are both arc surfaces, the diameter of the cross-section of the first ring body is larger than the diameter of the cross-section of the second ring body, the intermediate connecting ring is connected between the first ring body and the second ring body, and the width of the intermediate connecting ring gradually decreases from the first ring body to one side of the second ring body; the first ring body, the second ring body and the intermediate connecting ring are all elastic, and when the engine is not working, the center positions of the cross-sections of the first ring body and the second ring body are far apart, forming a non-deformed sealing state; when the engine is working, the intermediate connecting ring undergoes a concave deformation under the action of the centrifugal load, and the center positions of the cross-sections of the first ring body and the second ring body are close to each other, forming a deformed sealing state.

[0010] Preferably, the back side of the cross-section of the intermediate connecting ring is a straight line in the non-deformed sealed state, and is a convex arc line in the deformed sealed state; the front side of the cross-section of the intermediate connecting ring is a concave arc line in the non-deformed sealed state, and the concave curvature of the corresponding arc line increases in the deformed sealed state.

[0011] Preferably, the first ring body, the second ring body and the middle connecting ring are all made of high-temperature alloy wire.

[0012] Preferably, the first ring body, the second ring body and the middle connecting ring are manufactured by integral drawing using a tadpole-shaped model.

[0013] Preferably, the cross-sectional diameter of the first ring body is one time or more greater than the cross-sectional diameter of the second ring body.

[0014] The tadpole-shaped turbine baffle sealing ring of the present application comprises a first ring body, a second ring body and an intermediate connecting ring which are integrally arranged; when the engine is working, the turbine baffle is affected by centrifugal loads and temperature loads, and the turbine disc changes from a fitted state to a separated state at the surface and forms a gap N; the open tadpole-shaped sealing ring is radially opened to a predetermined position by the centrifugal load, and the gap N formed between the turbine baffle and the turbine disc is blocked, thereby ensuring a tight seal, avoiding non-designed leakage of compressor cooling air, ensuring a tight seal of the air path between the turbine baffle and the turbine disc, and having vibration absorption capability. Due to the unique cross-sectional shape of the tadpole-shaped sealing ring, the tadpole-shaped sealing ring forms a deformed sealed state under the action of the centrifugal load during operation, which is more conducive to increasing the clamping force on the turbine baffle and the turbine disc, and improving the sealing effect. At the same time, the tadpole-shaped sealing ring uses less material than the circular sealing ring. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0016] Figure 1 It is a schematic diagram of the background technology structure;

[0017] Figure 2 This is a schematic diagram of the overall structure of the tadpole-shaped sealing ring of this application;

[0018] Figure 3 This is a schematic diagram of the cross-sectional structure of the tadpole-shaped sealing ring of the present application;

[0019] Figure 4 This is a schematic diagram of the overall structure of this application;

[0020] Figure 5 for Figure 4 Enlarged view of part A in the middle;

[0021] Figure 6 This is a schematic diagram of the connection structure of the tadpole-shaped sealing ring when the engine of this application is working;

[0022] Figure 7 This is a schematic diagram of the elastic deformation of the tadpole-shaped sealing ring of the present application.

[0023] 1. Turbine baffle; 2. Turbine disc; 3. Sealing groove; 4. First ring body; 5. Second ring body; 6. Middle connecting ring; 7. Contact surface; 8. Tenon and groove; 9. Air vent. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0025] A tadpole-shaped turbine baffle seal ring, such as Figure 2-4 , arranged in the sealing groove 3 between the turbine baffle 1 and the turbine disk 2, the width of the sealing groove 3 gradually increases from the inside to the outside, and this design is a conventional design in this field and will not be described in detail.

[0026] It includes an integrally arranged first ring body 4, a second ring body 5 and an intermediate connecting ring 6; the first ring body 4, the second ring body 5 and the intermediate connecting ring 6 are all integral ring structures, the cross sections of the first ring body 4 and the second ring body 5 are both arc surfaces, the diameter of the cross section of the first ring body 4 is larger than the diameter of the cross section of the second ring body 5, the intermediate connecting ring 6 is connected between the first ring body 4 and the second ring body 5, and the width of the intermediate connecting ring 6 gradually decreases from the first ring body 4 to the second ring body 5 side;

[0027] Combination Figure 7, the first ring body 4, the second ring body 5 and the middle connecting ring 6 are all elastic. When the engine is not working, the center positions of the cross sections of the first ring body 4 and the second ring body 5 are far apart, forming a non-deformed sealing state; when the engine is working, the middle connecting ring 6 is concavely deformed under the centrifugal load, and the center positions of the cross sections of the first ring body 4 and the second ring body 5 are close to each other, forming a deformed sealing state. The solid line represents the non-deformed sealing state, and the dotted line represents the deformed sealing state.

[0028] The diameter of the tadpole-shaped sealing ring is ΦB, and it is an open structure. The cross-sectional shape of the front view of the tadpole-shaped sealing ring is the same as the cross-sectional shape of the circular sealing ring in the background art. The first ring body 4 can be considered as the head of the tadpole-shaped sealing ring, with a radius of R(1); the second ring body 5 can be considered as the tail of the tadpole-shaped sealing ring, with a radius of R(3); the centers of the first ring body 4 and the second ring body 5 are spaced L apart and smoothly transitioned by the arc R(2) on the intermediate connecting ring 6.

[0029] The radial length M of the tadpole-shaped sealing ring plays a practical role when it is working, which is the same as the role played by a circular sealing ring with the same diameter size M. The radial length of the tadpole-shaped sealing ring under the same sealing groove 3 is greater than the diameter of the circular sealing ring, but the mass and rigidity of the tadpole-shaped sealing ring are smaller than those of the circular sealing ring; this can better ensure that the tadpole-shaped sealing ring will not escape from the gap N formed between the turbine baffle 1 and the turbine disk 2, avoid damage to the flow channel parts, and ensure the safety of the test run.

[0030] The following is a detailed description of the assembly and working principle of the tadpole-shaped sealing ring;

[0031] Combination Figure 5 During the assembly process, that is, when the engine is not working, the tadpole-shaped sealing ring is first placed in the groove of the turbine baffle 1, and then the tadpole-shaped sealing ring and the turbine baffle 1 are assembled together with the turbine disk 2 through the tooling, and the turbine baffle 1 and the turbine disk 2 are fitted at the contact surface 7. Then, the tadpole-shaped sealing ring is placed in the closed groove formed by the turbine baffle 1 and the turbine disk 2. At this time, the tadpole-shaped sealing ring forms a non-deformed sealing state and can be sealed between the turbine baffle 1 and the turbine disk 2.

[0032] Combination Figure 6 , cooling flow path when the engine is working: the cooling air introduced from the compressor flows into the groove 8 of the turbine disk 2 through the air introduction holes 9 opened on the turbine baffle 1, and flows out through the internal channels and surface openings of the turbine rotor blades, forming a cooling air flow path, reducing the temperature level of the turbine rotor blades to below the allowable temperature of the blade material.

[0033] The working principle of the tadpole-shaped sealing ring when the engine is working: the turbine baffle 1 is affected by centrifugal loads and temperature loads, and changes from a fitted state to a separated state with the turbine disk 2 at the contact surface 7 and forms a gap N. The open tadpole-shaped sealing ring is radially rebounded to a predetermined position under the action of the centrifugal load, and the gap N formed between the turbine baffle 1 and the turbine disk 2 is blocked to ensure a tight seal, avoid non-designed leakage of the compressor cooling gas, ensure that the air path between the turbine baffle 1 and the turbine disk 2 is sealed, and has vibration absorption capability. Due to the unique cross-sectional shape of the tadpole-shaped sealing ring, the tadpole-shaped sealing ring forms a deformed sealing state under the action of the centrifugal load when working, which is more conducive to increasing the clamping force on the turbine baffle 1 and the turbine disk 2 and improving the sealing effect. At the same time, the tadpole-shaped sealing ring uses less material than the circular sealing ring.

[0034] Preferably, the back side of the cross section of the intermediate connecting ring 6 is a straight line in the non-deformed sealing state and a convex arc line in the deformed sealing state; the front side of the cross section of the intermediate connecting ring 6 is a concave arc line in the non-deformed sealing state, and the concave curvature of the corresponding arc line increases in the deformed sealing state. By setting the front side of the cross section of the intermediate connecting ring 6 to a concave arc line and the back side to a straight line, the tadpole-shaped sealing ring is easier to deform.

[0035] Preferably, the first ring body 4, the second ring body 5 and the middle connecting ring 6 are all made of high-temperature alloy wires, which have strong high-temperature resistance and high elasticity.

[0036] Preferably, the first ring body 4, the second ring body 5 and the middle connecting ring 6 are manufactured by integral drawing using a tadpole-shaped model, which is convenient to manufacture and has high precision.

[0037] Preferably, the cross-sectional diameter of the first ring body 4 is one or more times greater than the cross-sectional diameter of the second ring body 5, so that the weight of the first ring body 4 is significantly greater than the weight of the second ring body 5. When subjected to centrifugal force, the first ring body 4 is farther away from the turbine disk 2 and is subjected to a greater centrifugal force than the second ring body 5, so that it is easier to radially bounce or deform.

[0038] The above is only a specific implementation 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 a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A tadpole-shaped turbine baffle sealing ring, arranged in a sealing groove (3) between a turbine baffle (1) and a turbine disk (2), Features: The invention comprises a first ring body (4), a second ring body (5) and an intermediate connecting ring (6) which are integrally arranged; the first ring body (4), the second ring body (5) and the intermediate connecting ring (6) are all integral ring structures; the cross sections of the first ring body (4) and the second ring body (5) are both arc surfaces; the diameter of the cross section of the first ring body (4) is greater than the diameter of the cross section of the second ring body (5); the intermediate connecting ring (6) is connected between the first ring body (4) and the second ring body (5); the width of the intermediate connecting ring (6) gradually decreases from the first ring body (4) to the second ring body (5); The first ring body (4), the second ring body (5) and the middle connecting ring (6) are all elastic. When the engine is not working, the center positions of the cross sections of the first ring body (4) and the second ring body (5) are far apart, forming a non-deformed sealed state. When the engine is working, the middle connecting ring (6) undergoes a concave deformation under the action of the centrifugal load, and the center positions of the cross sections of the first ring body (4) and the second ring body (5) are close together, forming a deformed sealed state.

2. The tadpole-shaped turbine baffle sealing ring according to claim 1, Features: The back side of the cross section of the intermediate connecting ring (6) is a straight line in the non-deformed sealed state, and is an outward convex arc line in the deformed sealed state; the front side of the cross section of the intermediate connecting ring (6) is a concave arc line in the non-deformed sealed state, and the concave curvature of the corresponding arc line increases in the deformed sealed state.

3. The tadpole-shaped turbine baffle sealing ring according to claim 1, Features: The first ring body (4), the second ring body (5) and the intermediate connecting ring (6) are all made of high-temperature alloy wire.

4. The tadpole-shaped turbine baffle sealing ring according to claim 1, Features: The first ring body (4), the second ring body (5) and the intermediate connecting ring (6) are manufactured by integral drawing using a tadpole-shaped model.

5. The tadpole-shaped turbine baffle seal ring according to claim 1, Features: The cross-sectional diameter of the first ring body (4) is one time or more greater than the cross-sectional diameter of the second ring body (5).

Images