Turbine rotor blade, turbine rotor and engine turbine

Abstract

The utility model discloses a turbine rotor blade, a turbine rotor and an engine turbine, which belong to the technical field of turbine engines and are used for solving the problem of insufficient connecting strength of an extension root and a tenon caused by overweight of the turbine blade. The turbine rotor blade provided by the utility model comprises a cavity, one end, positioned at the blade tip, of the cavity is provided with an opening, and the other end of the cavity is closed; the cavity sequentially comprises a first cavity section, a second cavity section, a third cavity section and a fourth cavity section in the radial direction of the blade. The first cavity section and the second cavity section are formed in the center of the interior of the tenon; the third cavity section and the fourth cavity section are respectively arranged in the extension root and the blade body and are respectively matched with the extension root and the blade body in appearance; the chordwise width of the first cavity section and the second cavity section along the blade is smaller than the chordwise width of the third cavity section along the blade. According to the turbine rotor blade, the strength and the rigidity of the blade are effectively considered, and the overall performance of an engine turbine is improved.

Description

Technical Field

[0001] This utility model belongs to the field of aero-engine technology and relates to a turbine rotor blade, a turbine rotor, and an engine turbine. Background Technology

[0002] High-pressure turbine blades are the main components of high-pressure turbines. They are directly subjected to the scouring of high-temperature and high-pressure gas and play the role of converting the potential energy of the gas into the mechanical energy of the high-speed rotating core rotor. Therefore, high-pressure turbine blades often bear very harsh combined aerodynamic, thermal and mechanical loads. These combined loads determine the lifespan of high-pressure turbine blades, which in turn directly determine the lifespan of aero engines.

[0003] The high-pressure turbines of small and medium-sized aero engines operate at high speeds, typically tens of thousands or even hundreds of thousands of revolutions per minute. Under these high speeds, an increase of one gram in the mass of the blades themselves usually results in an increase of several thousand Newtons in centrifugal load, posing a significant challenge to the blade root and tenon joint strength. Since the aerodynamic design of the blades is already completed and the number of blades is determined, the axial dimension of the tenon joint is often lengthened to gain strength reserves. However, excessively increasing the axial dimension of the tenon joint will increase the mass of the entire rotor system and introduce other risks. Utility Model Content

[0004] Based on the above analysis, the present invention aims to provide a turbine rotor blade, a turbine rotor, and an engine turbine to solve the technical problem of insufficient strength of the root and tenon connection caused by the excessive weight of the turbine blade.

[0005] The purpose of this utility model is mainly achieved through the following technical solutions.

[0006] This utility model provides a turbine rotor blade, including a cavity; the cavity is located inside the blade and extends radially through the blade, with an opening at one end of the cavity at the blade tip and a closed end at the other end; the cavity sequentially includes a first cavity segment, a second cavity segment, a third cavity segment, and a fourth cavity segment along the radial direction of the blade; the first and second cavity segments are located at the center inside the blade tenon; the third and fourth cavity segments are respectively located inside the blade root and blade body and are respectively matched with the shape of the blade root and blade body, and the inner diameter of the fourth cavity segment gradually decreases from the blade tip to the blade root; the cavity opening is smaller than the inner diameter of the fourth cavity segment; the chordal width of the first and second cavity segments along the blade is smaller than the chordal width of the third cavity segment along the blade.

[0007] Furthermore, the chordal width of the second cavity section along the blade is less than 1 / 3 of the chordal width of the third cavity section along the blade.

[0008] Furthermore, the chordal width of the first cavity segment along the blade is smaller than the chordal width of the second cavity segment along the blade.

[0009] Furthermore, it also includes a sealing element, which is fixed to the end of the blade tenon to seal one end of the first cavity segment.

[0010] Furthermore, it also includes a first rib plate disposed on the inner wall of the cavity (1), the first rib plate being located in the first cavity segment and the second cavity segment and perpendicular to the chord direction of the blade.

[0011] Furthermore, the first rib (3) extends into the third cavity (13).

[0012] Furthermore, it also includes a second rib plate disposed on the inner wall of the cavity (1), the second rib plate being located within the fourth cavity segment and perpendicular to the radial direction of the blade. Furthermore, at least two second rib plates are arranged at intervals along the radial direction of the blade.

[0013] A second aspect of this invention provides a turbine rotor, comprising a turbine disc, a turbine rotor neck, and any one of the turbine rotor blades provided in the first aspect of this invention.

[0014] A third aspect of this invention provides an engine turbine, including the turbine rotor provided in the second aspect of this invention.

[0015] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0016] 1. The turbine rotor blade of this utility model, by setting cavities inside the blade and matching the shape of the third and fourth cavities with the root and blade body respectively, significantly reduces the weight of the blade, effectively improves the strength of the blade, and increases the working efficiency of the turbine.

[0017] 2. The turbine rotor blade of this utility model, by setting the width of the first cavity section and the second cavity section along the chord direction to be smaller than the width of the third cavity section, can reduce the weight of the blade while retaining the rigidity of the tenon part, thus taking into account both the strength and rigidity of the blade and improving the overall performance of the turbine blade.

[0018] 3. The turbine rotor blade of this utility model has an opening at one end of the blade tip and a closing at the tenon end through the cavity. On the one hand, when the gas flows through the blade tip, the opening at the blade tip can increase the loss of gas flow, thereby reducing the original gas leakage and forming a function equivalent to a comb, thereby improving the aerodynamic performance of the turbine. On the other hand, it can also make the cavity a dead cavity, preventing high-temperature gas from flowing into the cavity from the tenon end, thus ensuring the operating performance of the turbine.

[0019] 4. The turbine rotor blade of this utility model can increase the overall rigidity of the blade with the cavity by setting ribs in the cavity.

[0020] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained through the embodiments described and the accompanying drawings, which are particularly pointed out. Attached Figure Description

[0021] Figure 1 This is one of the schematic diagrams of the cross-sectional structure of a turbine rotor blade according to an embodiment of the present utility model;

[0022] Figure 2 This is the second schematic diagram of the cross-sectional structure of the turbine rotor blade in this embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of the turbine rotor of Embodiment 3 of this utility model.

[0024] Figure label:

[0025] 10- Turbine rotor blades;

[0026] 1-Cavity; 101-Cavity opening; 11-First cavity segment; 12-Second cavity segment; 13-Third cavity segment; 14-Fourth cavity segment; 2-Sealing component; 3-First rib; 4-Second rib;

[0027] 20 - Turbine turntable; 30 - Turbine neck. Detailed Implementation

[0028] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0029] Example 1

[0030] This embodiment provides a turbine rotor blade, such as Figure 1As shown, the blade includes a cavity 1. The cavity 1 is located inside the blade and extends radially through the blade. One end of the cavity 1 at the blade tip has a cavity opening 101, and the other end of the cavity 1 is closed. The cavity 1, along the radial direction of the blade, sequentially includes a first cavity segment 11, a second cavity segment 12, a third cavity segment 13, and a fourth cavity segment 14. The first cavity segment 11 and the second cavity segment 12 are located at the center inside the blade tenon. The third cavity segment 13 and the fourth cavity segment 14 are respectively located inside the blade root and the blade body, and are respectively matched to the shape of the blade root and the blade body. The inner diameter of the fourth cavity segment 14 gradually decreases from the blade tip to the blade root. The cavity opening 101 is smaller than the inner diameter of the fourth cavity segment 14. The chordal width of the first cavity segment 11 and the second cavity segment 12 along the blade is smaller than the chordal width of the third cavity segment 13 along the blade.

[0031] In this embodiment, the turbine rotor blade, by providing a cavity 1 within the blade and matching the shapes of the third cavity section 13 and the fourth cavity section 14 with the blade root and blade body respectively, significantly reduces the blade mass, effectively improves the blade strength, and increases the turbine's working efficiency. Simultaneously, by setting the chordal widths of the first cavity section 11 and the second cavity section 12 along the blade to be smaller than the chordal width of the third cavity section 13 along the blade, the blade mass is reduced while maintaining the rigidity of the blade tenon, thus balancing the blade's strength and rigidity and improving the overall performance of the turbine blade. The inner diameter of the fourth cavity section 14 extends from the blade tip... As the blade thickness gradually decreases from the tip to the root and the opening 101 is smaller than the inner diameter of the fourth cavity, the blade wall thickness gradually increases from the tip to the root, thereby increasing the strength and rigidity of the blade body and ensuring the rigidity of the tip. In addition, the cavity 1 is open at the tip and closed at the tenon end. On the one hand, when the gas flows through the tip, the cavity opening 101 at the tip increases the loss of gas flow, thereby reducing the original gas leakage, forming a function similar to a comb, thus improving the aerodynamic performance of the turbine. On the other hand, it also makes the cavity 1 a dead cavity, preventing high-temperature gas from flowing into the cavity 1 from the tenon end, thus ensuring the operating performance of the turbine.

[0032] Preferably, the chordal width of the second cavity segment 12 along the blade is less than 1 / 3 of the chordal width of the third cavity segment 13 along the blade. This can reduce the overall weight of the blade by up to about 17%, effectively solving the problem of insufficient strength of the tenon and tenon joint caused by excessive blade weight, while also ensuring the rigidity of the tenon part.

[0033] Preferably, the chordal width of the first cavity segment 11 along the blade is smaller than the chordal width of the second cavity segment 12 along the blade, so as to further improve the rigidity of the tenon at the tenon connection end, while reducing the width of the first cavity segment 11, which is beneficial to sealing the cavity 1 at the tenon end.

[0034] like Figure 1 and Figure 2As shown, in order to prevent high-temperature gas from flowing into cavity 1 from the blade root, and also to take into account the manufacturability of cavity 1, this embodiment also includes a sealing component 2. The sealing component 2 is welded to the end of the blade tenon, thereby sealing one end of the first cavity section 11.

[0035] Example 2

[0036] The turbine rotor blade of this embodiment differs from that of Embodiment 1 in that it also includes a first rib 3 and a second rib 4 disposed on the inner wall of the cavity 1. Both the first rib 3 and the second rib 4 are disposed in the cavity 1 and are integrally cast and machined with the blade to increase the overall rigidity of the hollow blade.

[0037] Preferred, such as Figure 1 and Figure 2 The first rib 3 shown is located within the first cavity 11 and the second cavity 12 and is arranged perpendicular to the chord direction. For example, a first rib 3 is provided at the center of the first cavity 11 and the second cavity 12. Both sides of the first rib 3 are connected to the inner walls of the tenon and the extension root. Preferably, the first rib 3 extends to the third cavity 13, so that the overall rigidity of the tenon and the extension root is enhanced.

[0038] Preferred, such as Figure 1 and Figure 2 As shown, the second rib 4 is located within the fourth cavity section 14 and is perpendicular to the radial direction of the blade. The overall outline of the second rib 4 is the same as the outline of the inner diameter of the blade at its location, so that the stiffness of the blade at that location can be uniformly strengthened by the second rib 4. The second rib 4 has multiple machined core holes to maintain the connectivity of the cavity 1 and the manufacturability during manufacturing.

[0039] Preferably, at least two second ribs 4 are arranged at radial intervals along the blade so that the blade stiffness can be enhanced in the radial direction.

[0040] Example 3

[0041] This embodiment discloses a turbine rotor, including the turbine rotor blade 10 of Embodiment 1.

[0042] like Figure 3 As shown, the turbine rotor in this embodiment also includes a turbine disk 20 and a turbine neck 30, and a plurality of turbine rotor blades 10 are arranged radially on the turbine disk 20.

[0043] The turbine rotor of this embodiment adopts the turbine rotor blade 10 of Embodiment 1, which greatly reduces the mass of the blade, effectively improves the strength of the blade, increases the working efficiency of the turbine, and also takes into account the strength and stiffness of the blade, thus improving the overall performance of the turbine rotor.

[0044] Example 4

[0045] This embodiment provides an engine turbine, including the turbine rotor of Embodiment 2. By configuring the turbine rotor of Embodiment 2, the safety performance of the engine turbine can be improved by reducing the weight of the turbine rotor blades.

[0046] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A turbine rotor blade, characterized in that, Includes cavity (1); The cavity (1) is located inside the blade and extends radially through the blade. The cavity (1) has an opening (101) at one end of the blade tip and is closed at the other end. The cavity (1) includes, in sequence along the radial direction of the blade, a first cavity segment (11), a second cavity segment (12), a third cavity segment (13), and a fourth cavity segment (14); The first cavity (11) and the second cavity (12) are located at the center inside the blade tenon; The third cavity (13) and the fourth cavity (14) are respectively opened inside the root and the leaf body and are respectively matched with the shape of the root and the leaf body. The inner diameter of the fourth cavity (14) gradually decreases from the leaf tip to the leaf root. The opening (101) is smaller than the inner diameter of the fourth cavity (14). The width of the first cavity segment (11) and the second cavity segment (12) along the chord direction of the blade is smaller than the width of the third cavity segment (13) along the chord direction of the blade.

2. The turbine rotor blade according to claim 1, characterized in that, The width of the second cavity segment (12) along the blade in the chord direction is less than 1 / 3 of the width of the third cavity segment (13) along the blade in the chord direction.

3. The turbine rotor blade according to claim 2, characterized in that, The width of the first cavity segment (11) along the blade is smaller than the width of the second cavity segment (12) along the blade.

4. The turbine rotor blade according to claim 1, characterized in that, It also includes a sealing element (2), which is fixed to the end of the blade tenon to seal one end of the first cavity segment (11).

5. The turbine rotor blade according to any one of claims 1 to 4, characterized in that, It also includes a first rib (3) disposed on the inner wall of the cavity (1), the first rib (3) being located in the first cavity segment (11) and the second cavity segment (12) and perpendicular to the chord direction of the blade.

6. The turbine rotor blade according to claim 5, characterized in that, The first rib (3) extends to the third cavity (13).

7. The turbine rotor blade according to claim 1, characterized in that, It also includes a second rib (4) disposed on the inner wall of the cavity (1), the second rib (4) being located in the fourth cavity section (14) and perpendicular to the radial direction of the blade.

8. The turbine rotor blade according to claim 7, characterized in that, At least two second ribs (4) are arranged at intervals along the radial direction of the blade.

9. A turbine rotor, characterized in that, It includes a turbine rotor disk (20), a turbine rotor neck (30), and a turbine rotor blade (10) as described in any one of claims 1 to 8.

10. An engine turbine, characterized in that, Includes the turbine rotor as described in claim 9.

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