Light high-strength turbine

Abstract

The utility model discloses a light high-strength turbine, and belongs to the technical field of turbines, the light high-strength turbine is characterized by comprising a turbine disc and a blade body, and the blade body comprises a mortise part matched with the turbine disc; the blade part comprises a front edge area, a rear edge area, a blade back area and a blade belly area; the cavity chamber is arranged in the middle of the blade part; the cooling mechanism comprises a first cooling flow channel and a second cooling flow channel; the first main runner is arranged in the front edge area, and the first main runner extends to the mortise part; the outlet hole is formed in the rear edge area and located on one side of the blade belly area; wherein the first cooling flow channel is arranged in a blade back area, the second cooling flow channel is arranged in a blade belly area, and the first cooling flow channel and the second cooling flow channel are connected with the first main flow channel and the outlet hole. The turbine is light in weight, high in structural strength and capable of cooling the blade body.

Description

Technical Field

[0001] The present application belongs to the field of turbine technology, and in particular relates to a lightweight and high-strength turbine. Background Art

[0002] A turbine is a fan in a car or airplane engine that uses exhaust gases to blow fuel vapor into the engine, improving performance. A turbine is a rotary power machine that converts the energy of a flowing fluid into mechanical work. It is a key component of aircraft engines, gas turbines, and steam turbines.

[0003] The existing Chinese patent with publication number CN113153445B, a mortise and tenon structure of a turbine engine turbine working blade and a turbine engine, including a turbine disk and a blade, the turbine disk includes a turbine disk body and a tenon structure, the tenon structure includes a first tenon and a second tenon located at the middle end of the first tenon, convex teeth are symmetrically distributed on both sides of the first tenon, and a groove structure is formed between the two adjacent tenon structures; the blade includes a blade body, a tenon and groove structure for mortise and tenon with the tenon structure, the tenon and groove structure includes a first tenon mortise with the first tenon, a second tenon mortise with the second tenon and located inside the first tenon; the first tenon includes a third tenon and a fourth tenon; a limiting member for axially limiting the blade is provided between one end of the first tenon close to the groove structure and the groove structure.

[0004] Although the above turbine avoids excessive stress, the gas temperature at the turbine is much higher than the temperature resistance limit of the material used for the turbine blades, so effective cooling measures are needed to protect the turbine blades. Summary of the Invention

[0005] The purpose of this application is to provide a lightweight and high-strength turbine to address the above-mentioned technical problems. The turbine has light weight, high structural strength, and can cool the blade body.

[0006] The present application provides a lightweight and high-strength turbine, comprising a turbine disk and a blade body, wherein the blade body comprises:

[0007] The tongue and groove portion cooperates with the turbine disc;

[0008] The blade part includes the leading edge area, the trailing edge area, the dorsal area, and the ventral area;

[0009] A hollow chamber is placed in the middle of the blade;

[0010] A cooling mechanism comprising a first cooling channel and a second cooling channel;

[0011] a first main flow channel disposed in the leading edge region, the first main flow channel extending to the tongue and groove portion;

[0012] An outlet hole is placed in the trailing edge area and on one side of the ventral area of ​​the blade;

[0013] The first cooling channel is placed in the back area of ​​the blade, and the second cooling channel is placed in the belly area of ​​the blade. Both the first cooling channel and the second cooling channel are connected to the first main channel and the outlet hole.

[0014] The blade body is installed and connected to the turbine disc through the tongue and groove part. The blade part has a larger weight reduction effect by setting a hollow cavity. The cooling medium is introduced into the blade part through the cooling mechanism to cool the blade part. The cooling medium is introduced through the first main channel and flows into the first cooling channel and the second cooling channel respectively. The back area of ​​the blade is cooled through the first cooling channel, and the belly area of ​​the blade is cooled through the second cooling channel. The cooling medium passing through the first cooling channel and the second cooling channel is discharged at the outlet hole. The back area of ​​the blade and the belly area of ​​the blade are separated by the hollow cavity, and the cooling effect is ensured by the first cooling channel and the second cooling channel.

[0015] Furthermore, the blade body further comprises:

[0016] A second main flow channel is disposed on the back of the blade and connected to the first cooling flow channel;

[0017] a third main flow channel, disposed in the blade belly area and connected to the second cooling flow channel;

[0018] Wherein, the second main flow channel and the third main flow channel both extend to the mortise and tenon portion.

[0019] The second main channel is connected to the first cooling channel, and the flow rate of the cooling medium in the first cooling channel is independently supplemented and adjusted. The third main channel is connected to the second cooling channel, and the flow rate of the cooling medium in the second cooling channel is independently supplemented and adjusted. The second main channel and the third main channel both extend to the mortise and tenon portion, making it easy to introduce cooling medium into the second main channel and the third main channel.

[0020] Furthermore, the first cooling channel and the second cooling channel are in a herringbone shape.

[0021] By arranging the first cooling channel and the second cooling channel in a herringbone shape, the structural strength of the blade portion is further ensured, while the residence time of the cooling medium is increased, thereby improving the cooling efficiency.

[0022] Furthermore, a reinforcement portion is provided inside the cavity.

[0023] The reinforcement part is placed in the cavity, and the reinforcement part is integrally connected with the blade part, so that the structural strength of the blade part is further improved by the reinforcement part.

[0024] Furthermore, the outlet hole is provided with a protrusion.

[0025] A raised portion is provided at the outlet hole, and the raised portion is integrally connected to the blade portion. The raised portion increases the turbulence of the air in the trailing edge area, thereby ensuring the cooling effect of the trailing edge area.

[0026] Furthermore, the turbine disc is provided with a tenon portion that cooperates with the tenon groove portion.

[0027] The tenon portion cooperates with the tenon groove portion to improve the connection stability between the blade portion and the turbine disk, and ensure the strength of the installation structure.

[0028] The first main flow channel, the second main flow channel and the third main flow channel convey the cooling medium through the communication channels between the tenon groove portion and the tenon head portion.

[0029] The beneficial effects of this application are:

[0030] 1. The blade part is provided with a larger cavity to improve the weight reduction effect.

[0031] 2. The back area of ​​the blade is cooled through the first cooling channel, the belly area of ​​the blade is cooled through the second cooling channel, and the cooling medium is introduced through the cooling mechanism to cool the blade part.

[0032] 3. Further improve the structural strength of the blade part through the reinforcement part. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A schematic structural diagram of the turbine of this application;

[0034] Figure 2 This is a schematic structural diagram of the blade body of this application;

[0035] Figure 3 This is a schematic structural diagram of the first cooling channel of the present application;

[0036] Figure 4 For this application Figure 3 Structural diagram at AA of FIG.

[0037] The reference numerals in the figure are: 100, turbine disc; 110, tenon portion; 200, blade body; 201, cavity; 210, tenon groove portion; 220, blade portion; 221, leading edge area; 222, trailing edge area; 223, blade back area; 224, blade belly area; 230, cooling mechanism; 231, first cooling channel; 232, second cooling channel; 240, first main channel; 250, outlet hole; 251, protrusion; 260, second main channel; 270, third main channel; 280, reinforcement portion. DETAILED DESCRIPTION

[0038] The following will be combined with the accompanying drawings in the embodiments of the present application to clearly describe the technical solutions in the embodiments of the present application. Obviously, the embodiments described are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field are within the scope of protection of this application.

[0039] The terms "first," "second," and the like in the specification and claims of this application are used to distinguish similar objects, and are not used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, so that the embodiments of this application can be implemented in an order other than that illustrated or described herein, and that the objects distinguished by "first," "second," and the like are generally of the same type, and do not limit the number of objects; for example, the first object can be one or more. In addition, the term "and / or" in the specification and claims refers to at least one of the connected objects, and the character " / " generally indicates that the objects connected are in an "or" relationship.

[0040] The following provides a detailed description of the embodiments of the present application through specific embodiments and their application scenarios in conjunction with the accompanying drawings.

[0041] Example 1:

[0042] like Figure 1-Figure 4 As shown, the embodiment of the present application provides a lightweight and high-strength turbine, including a turbine disk 100 and a blade body 200. The blade body 200 includes:

[0043] The tongue and groove portion 210 cooperates with the turbine disk 100;

[0044] The blade portion 220 includes a leading edge region 221, a trailing edge region 222, a blade back region 223, and a blade belly region 224;

[0045] The hollow chamber 201 is located in the middle of the blade portion 220;

[0046] The cooling mechanism 230 includes a first cooling channel 231 and a second cooling channel 232;

[0047] A first main flow channel 240 is disposed in the leading edge area 221 , and the first main flow channel 240 extends to the tongue and groove portion 210 ;

[0048] The outlet hole 250 is disposed in the trailing edge region 222 and is located on one side of the blade belly region 224;

[0049] The first cooling channel 231 is located in the blade back area 223 , and the second cooling channel 232 is located in the blade belly area 224 . Both the first cooling channel 231 and the second cooling channel 232 are connected to the first main channel 240 and the outlet hole 250 .

[0050] The blade body 200 is installed and connected to the turbine disk 100 through the tongue and groove portion 210. The blade portion 220 greatly improves the weight reduction effect by setting the hollow cavity 201. The cooling medium is introduced through the cooling mechanism 230 to cool the blade portion 220. The cooling medium is introduced through the first main channel 240 and flows into the first cooling channel 231 and the second cooling channel 232 respectively. The blade back area 223 is cooled through the first cooling channel 231, and the blade belly area 224 is cooled through the second cooling channel 232. The cooling medium passing through the first cooling channel 231 and the second cooling channel 232 is discharged at the outlet hole 250. The blade back area 223 and the blade belly area 224 are separated by the hollow cavity 201, and the cooling effect is ensured by the first cooling channel 231 and the second cooling channel 232.

[0051] Furthermore, the blade body 200 further includes:

[0052] The second main flow channel 260 is located in the blade back area 223 and connected to the first cooling flow channel 231;

[0053] The third main flow channel 270 is disposed in the blade belly region 224 and connected to the second cooling flow channel 232;

[0054] The second main flow channel 260 and the third main flow channel 270 both extend to the tongue and groove portion 210 .

[0055] The second main channel 260 is connected to the first cooling channel 231, and the flow rate of the cooling medium in the first cooling channel 231 is independently supplemented and adjusted. The third main channel 270 is connected to the second cooling channel 232, and the flow rate of the cooling medium in the second cooling channel 232 is independently supplemented and adjusted. The second main channel 260 and the third main channel 270 both extend to the mortise and tenon portion 210, so as to facilitate the introduction of cooling medium into the second main channel 260 and the third main channel 270.

[0056] Furthermore, the first cooling channel 231 and the second cooling channel 232 are in a herringbone shape.

[0057] By arranging the first cooling channel 231 and the second cooling channel 232 in a herringbone shape, the structural strength of the blade portion 220 is further ensured, while the residence time of the cooling medium is increased, thereby improving the cooling efficiency.

[0058] Example 2:

[0059] like Figure 4 As shown, the embodiment of the present application provides a lightweight and high-strength turbine. In addition to the above-mentioned technical features, a reinforcement portion 280 is further provided inside the cavity 201 .

[0060] The reinforcement portion 280 is disposed in the cavity 201 , and the reinforcement portion 280 is integrally connected to the blade portion 220 , so that the structural strength of the blade portion 220 is further improved by the reinforcement portion 280 .

[0061] Furthermore, the outlet hole 250 is provided with a protrusion 251 .

[0062] A protrusion 251 is provided at the outlet hole 250 , and the protrusion 251 is integrally connected to the blade portion 220 . The protrusion 251 increases the turbulence of the air in the trailing edge region 222 , thereby ensuring a cooling effect in the trailing edge region 222 .

[0063] Example 3:

[0064] like Figure 1 As shown, the embodiment of the present application provides a lightweight and high-strength turbine. In addition to the above-mentioned technical features, the turbine disc 100 is further provided with a tenon portion 110 that cooperates with the tenon groove portion 210.

[0065] The tenon portion 110 cooperates with the tenon groove portion 210 to improve the connection stability between the blade portion 220 and the turbine disk 100 and ensure the strength of the installation structure.

[0066] The first main flow channel 240 , the second main flow channel 260 , and the third main flow channel 270 transport the cooling medium through the communication channels between the tenon portion 110 and the tenon groove portion 210 .

[0067] It should be noted that, in this article, the terms "comprise", "include" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the statement "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device comprising the element. In addition, it should be noted that the scope of the methods and devices in the embodiments of the present application is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in the opposite order according to the functions involved. For example, the described method may be performed in an order different from that described, and various steps may also be added, omitted, or combined. In addition, the features described with reference to certain examples may be combined in other examples.

[0068] The embodiments of the present application are described above in conjunction with the accompanying drawings, but the present application is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the guidance of this application, ordinary technicians in this field can also make many forms without departing from the purpose of this application and the scope of protection of the claims, all of which are within the protection of this application.

Claims

1. A lightweight and high-strength turbine, comprising a turbine disk (100) and a blade body (200), characterized in that: The blade body (200) comprises: The tongue and groove portion (210) cooperates with the turbine disc (100); The blade portion (220) includes a leading edge region (221), a trailing edge region (222), a blade back region (223), and a blade belly region (224); A hollow chamber (201) is disposed in the middle of the blade portion (220); A cooling mechanism (230) includes a first cooling channel (231) and a second cooling channel (232); A first main flow channel (240) is disposed in the leading edge region (221), wherein the first main flow channel (240) extends to the tongue and groove portion (210); An outlet hole (250) is disposed in the trailing edge region (222) and is located on one side of the blade belly region (224); The first cooling channel (231) is placed on the blade back region (223), and the second cooling channel (232) is placed on the blade belly region (224). The first cooling channel (231) and the second cooling channel (232) are both connected to the first main channel (240) and the outlet hole (250).

2. The lightweight and high-strength turbine according to claim 1, characterized in that: The blade body (200) further includes: A second main flow channel (260) is disposed on the blade back region (223) and is connected to the first cooling flow channel (231); A third main flow channel (270) is disposed in the blade belly region (224) and connected to the second cooling flow channel (232); Wherein, the second main flow channel (260) and the third main flow channel (270) both extend to the tongue and groove portion (210).

3. The lightweight and high-strength turbine according to claim 1, characterized in that: The first cooling channel (231) and the second cooling channel (232) are in a herringbone shape.

4. The lightweight and high-strength turbine according to claim 1, characterized in that: A reinforcement portion (280) is provided inside the cavity chamber (201).

5. The lightweight and high-strength turbine according to claim 1, characterized in that: The outlet hole (250) is provided with a protrusion (251).

6. The lightweight and high-strength turbine according to claim 1, characterized in that: The turbine disc (100) is provided with a tenon portion (110) that cooperates with the tenon groove portion (210).

Images