Ultrahigh-temperature corrosion-resistant ceramic matrix composite turbine blade

Abstract

The utility model provides an ultra-high-temperature corrosion-resistant ceramic matrix composite turbine blade, which relates to the technical field of turbine engines and comprises a mounting seat, a damping plate is mounted on the inner side of the mounting seat, a ceramic blade main body is mounted above the mounting seat by matching with a bolt, and the ceramic blade main body comprises a heat dissipation groove, a reinforcing strip and a buffer groove. A threaded hole is formed in the middle of the bottom of the ceramic blade body. According to the ultra-high-temperature corrosion-resistant ceramic matrix composite turbine blade, the ultra-high-temperature corrosion-resistant ceramic matrix composite turbine blade is arranged, the mounting base and the damping plate which are combined in a matched mode through bolts are arranged on the basis of the turbine blade, the ceramic blade body is conveniently and independently disassembled and assembled through the arrangement of the mounting base, and the replacement and maintenance cost of the ceramic blade body is reduced; the damping plate achieves the buffering and shock-absorbing effects of the ceramic blade body.

Description

Technical Field

[0001] The utility model relates to the technical field of turbine engines, in particular to a turbine blade made of ultra-high temperature corrosion-resistant ceramic-based composite material. Background Art

[0002] In the aerospace and industrial fields, the performance of turbine engines is crucial. Turbine blades, as one of the core components of turbine engines, need to work in extreme high temperature, high pressure and high-speed airflow environments. Traditional metal turbine blades are prone to softening and deformation at high temperatures and have limited corrosion resistance. Therefore, ultra-high temperature corrosion-resistant ceramic-based composite turbine blades are needed to solve the problems of turbine engines. However, traditional ceramic-based composite turbine blades still have the following shortcomings when used:

[0003] Ceramic-based composite turbine blades will generate vibration and high temperature when rotating. Ceramic-based composite turbine blades are prone to cracking after long-term vibration and high temperature, which shortens the service life of the turbine blades. In addition, the ceramic-based composite turbine blades and the mounting seat are an integrated structure, which increases the replacement and maintenance cost of the ceramic-based composite turbine blades. Utility Model Content

[0004] The utility model discloses an ultra-high temperature corrosion-resistant ceramic-based composite material turbine blade. The mounting seat, the shock-absorbing plate, and the ceramic blade body are assembled with bolts. When the ceramic blade body rotates, the outside air can effectively enter the interior of the ventilation groove and the heat dissipation groove. The honeycomb structure can further accelerate the heat dissipation speed of the ceramic blade body, and the shock-absorbing plate realizes the buffering and shock-absorbing effect of the ceramic blade body.

[0005] In a first aspect of the present disclosure, an ultra-high temperature corrosion-resistant ceramic-based composite turbine blade is provided, specifically comprising: a mounting seat, a shock-absorbing plate is installed at the inner side of the mounting seat, a ceramic blade body is installed at the upper position of the mounting seat in conjunction with bolts, the ceramic blade body includes a heat dissipation groove, a reinforcement strip and a buffer groove, a threaded hole is opened in the middle position of the bottom of the ceramic blade body, a bolt mounting hole with a cylindrical stepped structure is opened in the middle position of the mounting seat, and a stabilizing bolt is installed between the bolt mounting hole and the threaded hole.

[0006] Furthermore, a stabilizing groove is provided on one side of the mounting seat. The stabilizing groove is a rectangular structure, and a strong magnet is installed inside the stabilizing groove.

[0007] Furthermore, two symmetrically distributed positioning blocks are provided above the mounting seat. The positioning blocks are cylindrical structures. Two mounting holes corresponding to the positioning blocks are provided at the bottom of the ceramic blade body. The positioning blocks pass through the interior of the mounting holes.

[0008] Furthermore, a reinforcement groove corresponding to the bottom of the ceramic blade body is opened above the mounting seat, and the bottom of the ceramic blade body extends to the inside of the reinforcement groove.

[0009] Furthermore, a group of ventilation slots are provided above the mounting seat, the ventilation slots are of rectangular structure, a heat dissipation slot is provided on the inner side of the ceramic blade body, and the ventilation slots and the heat dissipation slots are connected.

[0010] Furthermore, a group of reinforcement strips are provided on the outer side surface of the ceramic blade body, and a buffer groove is respectively provided on both sides of the reinforcement strips.

[0011] Furthermore, a group of heat dissipation structures are provided on the outer side surface of the ceramic blade body, and the heat dissipation structure is a honeycomb structure.

[0012] The utility model provides an ultra-high temperature corrosion-resistant ceramic-based composite material turbine blade, which has the following beneficial effects:

[0013] An ultra-high temperature corrosion-resistant ceramic-based composite material turbine blade is provided. A mounting seat and a shock-absorbing plate combined with bolts are provided on the basis of the turbine blade. The setting of the mounting seat facilitates the separate disassembly and assembly of the ceramic blade body, reducing the replacement and maintenance costs of the ceramic blade body. When the mounting seat is assembled at the bracket position of the worm gear, the shock-absorbing plate realizes the buffering and shock-absorbing effect of the ceramic blade body.

[0014] Heat dissipation grooves, reinforcement strips and honeycomb structures are set on the basis of the turbine blades. The outside air can effectively enter the ventilation grooves and the heat dissipation grooves, accelerating the natural heat dissipation speed of the ceramic blade body. The honeycomb structure can further accelerate the heat dissipation speed of the ceramic blade body, and the honeycomb structure can strengthen the ceramic blade body. The shock-absorbing plate realizes the buffering and shock-absorbing effect of the mounting seat, thereby extending the service life of the turbine blade. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings of the embodiments will be briefly introduced below.

[0016] The drawings described below only relate to some embodiments of the present invention, but are not intended to limit the present invention.

[0017] In the attached figure:

[0018] Figure 1 The figure shows the shaft side structure schematic diagram of the blade after assembly of the present application;

[0019] Figure 2 Shows the application Figure 1 A schematic diagram of the axle-side structure from an upward perspective;

[0020] Figure 3The figure shows the axial structural diagram of the ceramic blade body and the mounting seat after transverse section of the present application;

[0021] Figure 4 The figure shows the axial side schematic diagram of the mounting base and the blade splitting structure of the present application;

[0022] Figure 5 Shows the application Figure 4 A schematic diagram of the axle-side structure from an upward perspective;

[0023] Figure 6 A schematic diagram of the axial structure of the ceramic blade body and mounting seat after vertical sectioning of the present application is shown.

[0024] Reference Signs List

[0025] 1. Mounting seat; 101. Stable groove; 102. Positioning block;

[0026] 2. Shock-absorbing plate;

[0027] 3. Ceramic blade body; 301. Heat dissipation slot; 302. Reinforcement strip; 303. Buffer slot. DETAILED DESCRIPTION

[0028] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the described embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] Example 1: Please refer to Figures 1 to 6 :

[0030] The utility model proposes an ultra-high temperature corrosion-resistant ceramic-based composite material turbine blade, comprising: a mounting seat 1, a shock-absorbing plate 2 is installed at the inner side of the mounting seat 1, a stabilizing groove 101 is opened on one side of the mounting seat 1, the stabilizing groove 101 is a rectangular structure, a strong magnet is installed on the inner side of the stabilizing groove 101, and the stabilizing groove 101 can also be a cylindrical structure. The mounting seat 1 is made of a high-temperature resistant and corrosion-resistant metal material in the prior art, and the stabilizing groove 101 achieves a stabilizing effect of the strong magnet in the installation position. It is necessary to provide a stabilizing frame with a mounting groove on the basis of the mounting seat 1, and provide an iron sheet on the basis of the mounting groove of the stabilizing frame. The stabilizing frame is selected from a cylindrical stepped structure commonly used in turbines in the prior art. When the stabilizing block is installed in the inside of the stabilizing groove 101, the strong magnet automatically stabilizes the installation position of the mounting seat 1.

[0031] In the embodiments of the present disclosure, reference Figures 1 to 6 As shown, a ceramic blade body 3 is installed at the upper position of the mounting base 1 in conjunction with bolts. The ceramic blade body 3 includes a heat dissipation groove 301, a reinforcement strip 302 and a buffer groove 303. When the mounting base 1 is assembled at the bracket position of the worm gear, the shock-absorbing plate 2 realizes the buffering and shock-absorbing effect of the ceramic blade body 3. Two symmetrically distributed positioning blocks 102 are provided at the upper position of the mounting base 1. The positioning blocks 102 are cylindrical structures. Two mounting holes corresponding to the positioning blocks 102 are opened at the bottom position of the ceramic blade body 3. The positioning blocks 102 pass through the interior of the mounting holes. The positioning blocks 102 achieve the effect of circumferential and lateral stability of the splicing position of the mounting base 1 and the ceramic blade body 3.

[0032] In the embodiments of the present disclosure, reference Figures 1 to 6 As shown, a threaded hole is opened in the middle position of the bottom of the ceramic blade body 3, and a bolt mounting hole with a cylindrical stepped structure is opened in the middle position of the mounting base 1. A fixing bolt is installed between the bolt mounting hole and the threaded hole. The fixing bolt firmly connects the mounting base 1 and the ceramic blade body 3. A reinforcement groove corresponding to the bottom of the ceramic blade body 3 is opened at the upper position of the mounting base 1. The bottom of the ceramic blade body 3 extends to the inside of the reinforcement groove. The setting of the reinforcement groove strengthens the force strength of the bottom of the ceramic blade body 3. A group of ventilation grooves are opened at the upper position of the mounting base 1. The ventilation grooves are rectangular structures. A heat dissipation groove 301 is opened on the inner side of the ceramic blade body 3. The ventilation grooves and the heat dissipation grooves 301 are connected. The outside air can effectively enter the interior of the ventilation grooves and the heat dissipation grooves 301, thereby accelerating the natural heat dissipation speed of the ceramic blade body 3.

[0033] In the embodiments of the present disclosure, reference Figures 1 to 6 As shown, a group of reinforcement strips 302 are provided on the outer side of the ceramic blade body 3. It is necessary to open a group of installation grooves corresponding to the reinforcement strips 302 on the basis of the stable frame of the ceramic blade body 3, so that the reinforcement strips 302 can effectively reinforce the upper part of the ceramic blade body 3. A buffer groove 303 is opened on both sides of the reinforcement strip 302. The buffer groove 303 is an arc structure. The buffer groove 303 can make the flowing air flow in a streamlined manner. The outer side of the ceramic blade body 3 is provided with a group of heat dissipation structures. The heat dissipation structure is a honeycomb structure. The honeycomb structure can further accelerate the heat dissipation speed of the ceramic blade body 3, and the honeycomb structure can strengthen the ceramic blade body 3.

[0034] Example 2, based on Example 1, refer to Figures 1 to 6 As shown, the material of the shock-absorbing plate 2 is selected as a material that is capable of being used in the existing technology and is corrosion-resistant as needed. The shock-absorbing plate 2 is selected between metal and rubber materials as needed. The shock-absorbing plate 2 is selected as a material with good buffering effect as needed to ensure the normal operation of the turbine.

[0035] Example 3, based on Example 1, refer to Figures 1 to 6 As shown, a group of honeycomb heat dissipation structures can also be provided on the inner side of the heat dissipation groove 301 .

[0036] The working principle of this embodiment is as follows:

[0037] During installation, it is necessary to first set up a casting mold, use the casting mold to cast the ceramic blade body 3, assemble the mounting base 1, the damping plate 2, and the ceramic blade body 3 with bolts, and select an ultra-high temperature corrosion-resistant ceramic-based composite material for the ceramic blade body 3. It is necessary to set a stable frame with a mounting groove on the basis of the mounting base 1, and set an iron sheet on the basis of the mounting groove of the stable frame, and firmly install the ceramic blade body 3 with the mounting base 1 on the stable frame of the turbine;

[0038] When in use, the ceramic blade body 3 is installed firmly on the outside of the turbine drive shaft in conjunction with a stabilizing frame. When the ceramic blade body 3 rotates, the outside air can effectively enter the interior of the ventilation groove and the heat dissipation groove 301, thereby accelerating the natural heat dissipation speed of the ceramic blade body 3. The honeycomb structure can further accelerate the heat dissipation speed of the ceramic blade body 3, and the honeycomb structure can strengthen the ceramic blade body 3, and the shock-absorbing plate 2 realizes the buffering and shock-absorbing effect of the ceramic blade body 3.

[0039] In this article, there are several points to note:

[0040] 1. The drawings of the embodiments of the present disclosure only relate to the structures related to the embodiments of the present disclosure. Other structures may refer to conventional designs.

[0041] 2. In the absence of conflict, the embodiments of the present disclosure and the features therein may be combined with each other to form new embodiments.

[0042] The above are only specific embodiments of the present disclosure, but the scope of protection of the present disclosure is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this disclosure should be included in the scope of protection of the present disclosure. Therefore, the scope of protection of the present disclosure should be based on the scope of protection of the claims.

Claims

1. Ultra-high temperature corrosion-resistant ceramic matrix composite turbine blades, including: A mounting base (1), a damping plate (2) and a ceramic blade body (3), characterized in that a damping plate (2) is installed at the inner side of the mounting base (1), a ceramic blade body (3) is installed at the upper position of the mounting base (1) in conjunction with bolts, the ceramic blade body (3) includes a heat dissipation groove (301), a reinforcement strip (302) and a buffer groove (303), a threaded hole is opened at the middle position of the bottom of the ceramic blade body (3), a bolt mounting hole with a cylindrical stepped structure is opened at the middle position of the mounting base (1), and a fixing bolt is installed between the bolt mounting hole and the threaded hole.

2. The ultra-high temperature corrosion-resistant ceramic matrix composite material turbine blade according to claim 1, characterized in that: A stabilizing groove (101) is provided on one side of the mounting seat (1). The stabilizing groove (101) is a rectangular structure, and a strong magnet is installed on the inner side of the stabilizing groove (101).

3. The ultra-high temperature corrosion-resistant ceramic matrix composite material turbine blade according to claim 1, characterized in that: Two symmetrically distributed positioning blocks (102) are provided above the mounting seat (1), the positioning blocks (102) being cylindrical in structure, and two mounting holes corresponding to the positioning blocks (102) are provided at the bottom of the ceramic blade body (3), with the positioning blocks (102) passing through the interior of the mounting holes.

4. The ultra-high temperature corrosion-resistant ceramic matrix composite material turbine blade according to claim 1, characterized in that: A reinforcement groove corresponding to the bottom of the ceramic blade body (3) is provided above the mounting seat (1), and the bottom of the ceramic blade body (3) extends to the interior of the reinforcement groove.

5. The ultra-high temperature corrosion-resistant ceramic matrix composite material turbine blade according to claim 1, characterized in that: A group of ventilation slots are provided above the mounting seat (1), and a heat dissipation slot (301) is provided inside the ceramic blade body (3), and the ventilation slots and the heat dissipation slot (301) are connected.

6. The ultra-high temperature corrosion-resistant ceramic matrix composite material turbine blade according to claim 1, characterized in that: A group of reinforcement strips (302) are provided on the outer side surface of the ceramic blade body (3), and a buffer groove (303) is respectively provided on both sides of the reinforcement strips (302).

7. The ultra-high temperature corrosion-resistant ceramic matrix composite material turbine blade according to claim 1, characterized in that: The outer side surface of the ceramic blade body (3) is provided with a group of heat dissipation structures.

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