Turbine blade and aircraft engine

Abstract

The present invention relates to the technical field of aircraft engines, and in particular to a turbine blade and an aircraft engine. A turbine blade comprises: a blade body, which is arranged in a casing, and a groove is provided on the upper end surface of the blade body; a spring piece, which is arranged in the groove, and the spring piece comprises two elastic thin metal sheets, the upper parts of the two elastic thin metal sheets are fixedly connected to form a telescopic part, and the telescopic part is suitable for relative movement along the guide direction of the groove and in contact with the casing, and the lower parts of the two elastic thin metal sheets are mutually deviated to form a limiting part, and the groove has a limiting structure that cooperates with the limiting part. With this structure of the turbine blade, when the blade body rotates, the telescopic part of the spring piece extends from the groove under the action of the rotating centrifugal force, and the upper end of the telescopic part contacts the casing, thereby achieving a tight sealing of the blade tip, making full use of the fuel gas energy, and further avoiding damage to the inner wall of the casing caused by excessive blade tip load.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a turbine blade and an aero-engine. Background Art

[0002] There is a certain gap between the turbine blades and the casing to ensure that the turbine blades meet the engine performance requirements. When the engine is running at low speed, the rotor temperature and speed are low, and the turbine blades are also less elongated. This will result in a larger gap between the turbine blades and the casing. Under the pressure difference between the pressure surface and the suction surface of the vortex blade, the excessive gap will often cause gas leakage, thereby reducing the engine's working efficiency and increasing fuel consumption. In the existing technology, the problem of gas leakage is usually solved by increasing the length of the turbine blades to reduce the gap between the turbine blades and the casing. However, due to the different expansion responses of the turbine blades and the casing, the gap between the turbine blades and the casing also changes under different operating conditions of the engine. When the engine is running at high speed, the turbine blades are extended, which reduces the gap between the turbine blades and the casing, causing the blade tips of the turbine blades to directly rub against the casing, thereby damaging the turbine blades. Therefore, there is an urgent need for a vortex blade that can avoid friction between the blade tips and the casing. Summary of the Invention

[0003] Therefore, the technical problem to be solved by the present invention is that the blade tip of the turbine blade directly rubs against the casing in the prior art, causing damage to the turbine blade, thereby providing a turbine blade and an aircraft engine.

[0004] In order to solve the above problems, the present invention provides a turbine blade, comprising:

[0005] The blade body is arranged in the casing, and the upper end surface of the blade body is provided with a groove;

[0006] The spring piece is arranged in the groove, and the spring piece includes two elastic thin metal sheets. The upper parts of the two elastic thin metal sheets are fixedly connected to form a telescopic part. The telescopic part is suitable for relative movement along the guide direction of the groove and in contact with the receiver. The lower parts of the two elastic thin metal sheets deviate from each other to form a limiting part. The groove has a limiting structure that cooperates with the limiting part.

[0007] Furthermore, the limiting structure is a cavity, which is arranged at the lower end of the groove. The cavity is connected to the groove, and the limiting part is arranged in the cavity. The lower ends of the two elastic thin metal sheets respectively contact the inner wall of the cavity.

[0008] Furthermore, as the lower ends of the two elastic thin metal sheets extend toward the bottom of the cavity, the distance between the lower ends of the two elastic thin metal sheets gradually increases.

[0009] Furthermore, the groove is arranged along the blade profile centerline of the blade body.

[0010] Furthermore, the depth of the groove is L, the height A+B+C of the spring piece is greater than the depth L of the groove, and the height of the spring piece A+B is less than the depth L of the groove.

[0011] Furthermore, the distance W between the lower ends of the two elastic thin metal sheets is greater than the width S of the cavity.

[0012] Furthermore, the blade body is fixedly arranged on the wheel disc.

[0013] Furthermore, a base is provided at the bottom of the blade body, and the blade body is arranged on the wheel disc through the base.

[0014] Furthermore, the base is mortise-jointed with the wheel disc.

[0015] The present invention also provides an aircraft engine, comprising: the turbine blades described in any one of the above solutions.

[0016] The present invention has the following advantages:

[0017] 1. The present invention discloses a turbine blade, comprising: a blade body and a spring clip, wherein the blade body is arranged in a casing, and a groove is formed on the upper end surface of the blade body; the spring clip is arranged in the groove, and the spring clip comprises two elastic thin metal sheets, the upper parts of the two elastic thin metal sheets are fixedly connected to form a telescopic part, the telescopic part is suitable for relative movement along the guide direction of the groove and abutting against the casing, the lower parts of the two elastic thin metal sheets are separated from each other to form a limiting part, and the lower ends of the two elastic thin metal sheets respectively abut against the inner wall of the groove.

[0018] With this structure of turbine blade, when the blade body rotates, the telescopic part of the shrapnel extends from the groove under the action of the rotating centrifugal force, and the upper end of the telescopic part comes into contact with the casing, thereby achieving a tight seal on the blade tip and making full use of the fuel gas energy. Further, it avoids damage to the inner wall of the casing caused by excessive load on the blade tip.

[0019] 2. For the turbine blade of this structure, the limiting part is set in the cavity, and the lower ends of the two elastic thin metal sheets respectively contact the inner wall of the cavity, so that the cavity can limit the spring piece and prevent the spring piece from being thrown out of the groove due to the centrifugal force of rotation. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0021] Figure 1 A schematic structural diagram of a turbine blade according to an embodiment of the present invention;

[0022] Figure 2 This is a schematic structural diagram of a blade body according to an embodiment of the present invention;

[0023] Figure 3 Schematic diagram of the structure of the spring in the embodiment of the present invention;

[0024] Figure 4 A schematic structural diagram of a turbine blade according to an embodiment of the present invention;

[0025] Figure 5 This is a schematic structural diagram of a roulette wheel according to an embodiment of the present invention;

[0026] Figure 6 Schematic diagram of a spring in an embodiment of the present invention;

[0027] Description of reference numerals:

[0028] 1. Blade body; 2. Groove; 3. Shrapnel; 4. Elastic thin metal sheet; 5. Cavity; 6. Casing; 7. Base; 8. Disc. DETAILED DESCRIPTION

[0029] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0030] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0031] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0032] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0033] Example 1

[0034] like Figures 1 to 6 As shown, this embodiment provides a turbine blade, comprising: a blade body 1 and a spring clip 3. The blade body 1 is disposed within a casing 6, and a groove 2 is defined on the upper end surface of the blade body 1. The spring clip 3 is disposed within the groove 2 and comprises two elastic thin metal sheets 4. The upper portions of the two elastic thin metal sheets 4 are fixedly connected to form a telescopic portion, which is adapted to move relative to each other along the guide direction of the groove 2 and to contact the casing 6. The lower portions of the two elastic thin metal sheets 4 are oriented away from each other to form a limiting portion. The groove 2 includes a limiting structure that cooperates with the limiting portion.

[0035] Specifically, the upper end surface of the blade body 1 defines a groove 2, the length of which is shorter than that of the blade body 1. The upper portions of two elastic thin metal sheets 4 are fixedly connected by welding to form a telescopic portion that can move within the groove 2. The lower portions of the two elastic thin metal sheets 4 are separated from each other to form a stop. The lower portions of the two elastic thin metal sheets 4 are first manually pinched together to fit together and then placed within the groove 2. The lower portions of the elastic thin metal sheets 4 within the groove 2, lacking pressure, expand due to their own elastic force and contact the inner wall of the groove 2. When the blade body 1 begins to rotate, the telescopic portion of the spring sheet 3 extends from the groove 2 under the action of the centrifugal force of rotation. The top of the spring sheet 3 contacts the casing 6, achieving a tight seal on the blade tip. When the stop slides to the stop structure, the stop structure provides resistance to the stop, preventing the spring sheet 3 from flying out of the groove 2 under the action of the centrifugal force of rotation.

[0036] Furthermore, the limiting structure is a cavity 5, which is arranged at the lower end of the groove 2. The cavity 5 is connected to the groove 2, and the limiting part is arranged in the cavity 5. The lower ends of the two elastic thin metal sheets 4 respectively contact the inner wall of the cavity 5.

[0037] Specifically, such as Figure 1As shown, a cavity 5 is provided at the lower end of the groove 2, and a stopper is disposed within the cavity 5. The lower ends of the metal sheets respectively contact the inner walls of the cavity 5, allowing the stopper to slide within the cavity 5. When the telescopic portion extends under the action of the centrifugal force of rotation, the stopper moves along with the telescopic portion. When the stopper moves to the connection between the cavity 5 and the groove 2, the cavity 5 limits the stopper, preventing it from entering the groove 2. When the blade body 1 stops rotating, the stopper falls to the bottom of the cavity 5 under the action of the weight of the spring 3, allowing the telescopic portion to retract into the groove 2.

[0038] Furthermore, as the lower ends of the two elastic thin metal sheets 4 extend toward the bottom of the cavity 5 , the distance between the lower ends of the two elastic thin metal sheets 4 gradually increases.

[0039] Furthermore, the groove 2 is arranged along the blade profile centerline of the blade body 1. Specifically, the spring piece 3 arranged in the groove 2 can better interfere with the casing 6 to achieve a tight seal on the blade tip.

[0040] Further, such as Figure 6 As shown, the depth of the groove 2 is L, the height A+B+C of the spring piece 3 is greater than the depth L of the groove 2, and the height of the spring piece 3A+B is less than the depth L of the groove 2.

[0041] It should be noted that the extension of the spring 3 is Δ L, the assembly clearance is A. When the spring 3 extends Δ When L is greater than or equal to the assembly gap A, the spring piece 3 comes into contact with the casing 6 , and the spring piece 3 achieves a tight seal on the blade tip under the restriction of the rotating centrifugal force and the casing 6 .

[0042] Furthermore, the distance W between the lower ends of the two elastic thin metal sheets 4 is greater than the width S of the cavity.

[0043] Furthermore, the blade body 1 is fixedly arranged on the wheel disc 8 .

[0044] Furthermore, a base 7 is provided at the bottom of the blade body 1, and the blade body 1 is provided on the wheel disc 8 through the base 7.

[0045] Preferably, in this embodiment, the base 7 and the wheel disc 8 are mortise-jointed.

[0046] Example 2

[0047] This embodiment discloses an aircraft engine, including turbine blades, which are the turbine blades described in the first embodiment.

[0048] Obviously, the above embodiments are merely examples for clarity of explanation and are not intended to limit the implementation methods. Those skilled in the art will readily appreciate that other variations or modifications based on the above descriptions are possible. It is not necessary and impossible to enumerate all implementation methods here. Obvious variations or modifications arising therefrom remain within the scope of protection of the present invention.

Claims

1. A turbine blade, characterized in that: include: A blade body (1) is arranged in a casing (6), and a groove (2) is formed on the upper end surface of the blade body (1); A spring piece (3) is arranged in the groove (2), and the spring piece (3) includes two elastic thin metal sheets (4). The upper parts of the two elastic thin metal sheets (4) are fixedly connected to form a telescopic portion. The telescopic portion is suitable for relatively moving along the guide direction of the groove (2) and contacting the casing (6). The lower parts of the two elastic thin metal sheets (4) are separated from each other to form a limiting portion. The groove (2) has a limiting structure that cooperates with the limiting portion. The limiting structure is a cavity (5), the cavity (5) is arranged at the lower end of the groove (2), the cavity (5) is communicated with the groove (2), the limiting portion is arranged in the cavity (5), and the lower ends of the two elastic thin metal sheets (4) respectively contact the inner wall of the cavity (5); In the direction in which the lower ends of the two elastic thin metal sheets (4) extend toward the bottom of the cavity (5), the distance between the lower ends of the two elastic thin metal sheets (4) gradually increases.

2. The turbine blade according to claim 1, characterized in that: The groove (2) is arranged along the blade profile center line of the blade body (1).

3. The turbine blade according to claim 1 or 2, characterized in that: The depth of the groove (2) is L, the height A+B+C of the spring piece (3) is greater than the depth L of the groove (2), and the height A+B of the spring piece (3) is less than the depth L of the groove (2).

4. The turbine blade according to claim 3, characterized in that: The distance W between the lower ends of the two elastic thin metal sheets (4) is greater than the width S of the cavity.

5. The turbine blade according to claim 1, wherein: The blade body (1) is fixedly arranged on the wheel disc (8).

6. The turbine blade according to claim 5, characterized in that: A base (7) is provided at the bottom of the blade body (1), and the blade body (1) is arranged on the wheel disc (8) through the base (7).

7. The turbine blade according to claim 6, characterized in that: The base (7) and the wheel disc (8) are mortise-jointed.

8. An aircraft engine, characterized in that: include: A turbine blade as claimed in any one of claims 1 to 7.

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