A jet gas turbine guide vane device

Abstract

This invention provides a jet-type gas turbine guide device, including a guide, a heat dissipation assembly, and a flow divider. The guide consists of an outer ring, inside which is an inner ring. The invention features a hollow cavity inside the blade, with heat dissipation holes arranged along the inner side of the blade, communicating with the hollow cavity. Through holes are formed around the surface of the outer ring, and fuel injectors are installed on the surface of these through holes. During operation, the fuel injectors inject fuel into the hollow cavity inside the blade through the through holes. The fuel entering the hollow cavity carries away the heat generated by the blade, thus cooling it and preventing thermal stress at the leading edge that could cause cracks. The fuel flows out through the heat dissipation holes and into the combustion chamber. This guide has a cooling and heat dissipation structure, thereby improving its service life.

Description

Technical Field

[0001] This utility model relates to the field of guide device technology, specifically to a jet-type gas turbine guide device. Background Technology

[0002] A gas turbine is a mechanical device that uses the energy of natural gas to generate power. In a gas turbine, natural gas is compressed by a compressor, mixed with air, and burned at high temperatures in the combustion chamber. The high-temperature gas produced by combustion flows through the turbine, causing it to rotate. This rotation, in turn, drives the entire rotor through the main shaft. The gas turbine consists of two parts: the rotor and the stator. The stator includes the turbine guide vane. Although the turbine guide vane is a stationary component, its operating conditions are extremely harsh. Under high temperatures, the mechanical properties of the material degrade rapidly. Furthermore, the temperature at the combustion chamber outlet is not spatially uniform; the temperature is higher in the middle and lower at the edges, creating a significant temperature gradient in the radial direction. This temperature gradient causes significant thermal stress on the leading edge of the guide vane blades. In practical applications, since the guide vane blades lack a cooling structure, this thermal stress can cause cracks in the middle of the leading edge, leading to guide vane failure. Utility Model Content

[0003] The purpose of this invention is to provide a jet-type gas turbine guide device to solve the problem mentioned in the background art, where thermal stress causes cracks in the middle of the leading edge of the guide due to the lack of a cooling structure on the guide blades, leading to guide failure.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a jet-type gas turbine guide device, comprising a guide, a heat dissipation assembly, and a flow divider;

[0005] Wherein: the guide is composed of an outer ring, the inner ring is provided inside the outer ring, and a blade is provided between the outer ring and the inner ring;

[0006] The heat dissipation assembly includes a hollow cavity formed inside the blade, heat dissipation holes arranged on the inner surface of the blade and communicating with the hollow cavity, and a plurality of through holes formed around the surface of the outer ring and communicating with the hollow cavity, and an oil injection nozzle installed on the surface of the through holes;

[0007] The inner ring surface is provided with a flow divider, which has a conical structure.

[0008] As a preferred embodiment of this utility model: plug-in blocks are installed around the bottom of the diverter, and fixing bolts are inserted and connected to the surface of the plug-in blocks. Multiple mounting grooves are opened on the edge of the inner ring, and the plug-in blocks are inserted into the mounting grooves.

[0009] As a preferred embodiment of this utility model: a fixing ring is installed on one end edge of the outer ring, and the surface of the fixing ring is provided with a plurality of mounting holes.

[0010] As a preferred embodiment of this utility model, the mounting hole is located between two adjacent oil nozzles.

[0011] As a preferred embodiment of this utility model, the inner ring is a hollow structure.

[0012] As a preferred embodiment of this utility model, the surface of the flow divider is coated with a high-temperature resistant ceramic coating.

[0013] Compared with the prior art, the beneficial effects of this utility model are:

[0014] (1) A hollow cavity is provided inside the blade, and heat dissipation holes are arranged on the inner side of the blade. The heat dissipation holes are connected to the hollow cavity. Through holes are provided around the outer surface. Fuel injectors are installed on the surface of the through holes. During operation, the fuel injectors inject fuel into the hollow cavity inside the blade through the through holes. The fuel enters the hollow cavity and carries away the temperature generated by the blade, thereby cooling the blade and preventing thermal stress at the leading edge from causing cracks. The fuel flows out through the heat dissipation holes and enters the combustion chamber. The guide has a cooling and heat dissipation structure, thereby improving the service life of the guide.

[0015] (2) A flow divider is provided on the surface of the inner ring. The flow divider with a conical structure is installed corresponding to the air inlet end of the guide, so that the airflow can be dispersed to the blades and the air inlet resistance can be reduced. Insert blocks are installed around the bottom of the flow divider. The edge of the inner ring is provided with an installation groove. The flow divider is inserted into the installation groove through the insert blocks and fixed by fixing bolts to ensure the stability of the flow divider installation. The surface of the flow divider is coated with a ceramic coating, which has good heat resistance and can reduce the surface temperature when the airflow rubs against the flow divider at high speed. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0017] Figure 2 This is a schematic diagram of the heat dissipation component structure of this utility model;

[0018] Figure 3 This is a schematic diagram of the installation structure of the flow divider of this utility model;

[0019] Figure 4 This is a schematic diagram of the fixing ring structure of this utility model.

[0020] In the diagram: 1. Guide; 101. Outer ring; 102. Inner ring; 103. Blade; 2. Heat dissipation assembly; 201. Hollow cavity; 202. Heat dissipation hole; 203. Through hole; 204. Oil injection nozzle; 3. Diverter; 4. Connector block; 5. Fixing bolt; 6. Mounting groove; 7. Fixing ring; 8. Mounting hole. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0022] Please see Figures 1-4 A jet-type gas turbine guide device includes: a guide 1, a heat dissipation assembly 2 and a flow divider 3; the guide 1 is composed of an outer ring 101, an inner ring 102 is provided inside the outer ring 101, and a blade 103 is provided between the outer ring 101 and the inner ring 102.

[0023] Please see Figure 1 , Figure 2 The heat dissipation assembly 2 includes a hollow cavity 201 inside the blade 103. Heat dissipation holes 202 are arranged on the inner surface of the blade 103 and communicate with the hollow cavity 201. A plurality of through holes 203 are arranged around the surface of the outer ring 101 and communicate with the hollow cavity 201. An oil injection nozzle 204 is installed on the surface of the through holes 203.

[0024] In practical use: A hollow cavity 201 is formed inside the blade 103, and heat dissipation holes 202 are arranged on the inner side of the blade 103, which are connected to the hollow cavity 201. Through holes 203 are formed around the surface of the outer ring 101, and fuel injectors 204 are installed on the surface of the through holes 203. During operation, the fuel injectors 204 inject fuel into the hollow cavity 201 inside the blade 103 through the through holes 203. The fuel entering the hollow cavity 201 carries away the temperature generated by the blade 103, thereby cooling the blade 103 and preventing thermal stress at the leading edge from causing cracks. The fuel flows out through the heat dissipation holes 202 and enters the combustion chamber. This guide 1 has a cooling and heat dissipation structure for the blade 103, thereby improving the service life of the guide 1.

[0025] Please see Figure 1 , Figure 3The inner ring 102 has a flow divider 3 on its surface. The flow divider 3 has a conical structure. The bottom of the flow divider 3 is equipped with plug-in blocks 4. The surface of the plug-in blocks 4 is connected with fixing bolts 5. The edge of the inner ring 102 has multiple mounting grooves 6. The plug-in blocks 4 are inserted into the mounting grooves 6. The surface of the flow divider 3 is coated with a high-temperature resistant ceramic coating.

[0026] In practical use: A flow divider 3 is provided on the surface of the inner ring 102. The flow divider 3, which has a conical structure, is installed corresponding to the air inlet end of the guide 1, so as to facilitate the dispersion of airflow to the blades 103 and reduce air intake resistance. Insertion blocks 4 are installed around the bottom of the flow divider 3. The edge of the inner ring 102 is provided with an installation groove 6. The flow divider 3 is inserted into the installation groove 6 through the insertion blocks 4 and fixed by fixing bolts 5 to ensure the stable installation of the flow divider 3. The surface of the flow divider 3 is coated with a ceramic coating, which gives it good heat resistance and can reduce the surface temperature when the airflow rubs against the flow divider 3 at high speed.

[0027] Please see Figure 1 , Figure 4 A fixing ring 7 is installed on one end edge of the outer ring 101. The surface of the fixing ring 7 is provided with several mounting holes 8, which are located between two adjacent oil nozzles 204.

[0028] In practical use: One end edge of the outer ring 101 is connected to a fixing ring 7. The guide 1 is fixedly installed through the mounting hole 8 on the surface of the fixing ring 7. The mounting hole 8 is opened between two adjacent oil nozzles 204 so that there will be no interference between the structural components during installation.

[0029] Please see Figure 3 The inner ring 102 is a hollow structure.

[0030] In practical use: the inner ring 102 adopts a hollow structure design, which can reduce the structural weight.

[0031] A hollow cavity 201 is formed inside the blade 103. Heat dissipation holes 202 are arranged on the inner side of the blade 103 and communicate with the hollow cavity 201. Through holes 203 are formed around the surface of the outer ring 101. A fuel injector 204 is installed on the surface of the through holes 203. During operation, the fuel injector 204 injects fuel into the hollow cavity 201 inside the blade 103 through the through holes 203. The fuel entering the hollow cavity 201 carries away the temperature generated by the blade 103, thereby cooling the blade 103 and preventing thermal stress at the leading edge from causing cracks. The fuel flows out through the heat dissipation holes 202 and enters the combustion chamber. This guide 1 has a cooling and heat dissipation structure for the blade 103, thereby improving the service life of the guide 1.

[0032] The contents not described in detail in this description are existing technologies known to those skilled in the art. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A jet-type gas turbine guide vane device, characterized in that, include: The guide (1) is composed of an outer ring (101), and an inner ring (102) is provided inside the outer ring (101). A blade (103) is provided between the outer ring (101) and the inner ring (102). The heat dissipation assembly (2) includes a hollow cavity (201) opened inside the blade (103), heat dissipation holes (202) are arranged on the inner surface of the blade (103), the heat dissipation holes (202) are connected to the hollow cavity (201), a plurality of through holes (203) are opened around the surface of the outer ring (101), the through holes (203) are connected to the hollow cavity (201), and an oil injection nozzle (204) is installed on the surface of the through holes (203). The flow divider (3) is provided on the surface of the inner ring (102), and the flow divider (3) has a conical structure.

2. The jet-type gas turbine guide device according to claim 1, characterized in that: The bottom of the shroud (3) is equipped with plug-in blocks (4), and the surface of the plug-in blocks (4) is connected with fixing bolts (5). The inner ring (102) has multiple mounting grooves (6) on its edge, and the plug-in blocks (4) are inserted into the mounting grooves (6).

3. The jet-type gas turbine guide device according to claim 1, characterized in that: A fixing ring (7) is installed on one end edge of the outer ring (101), and a plurality of mounting holes (8) are provided on the surface of the fixing ring (7).

4. The jet-type gas turbine guide vane device according to claim 3, characterized in that: The mounting hole (8) is located between two adjacent oil nozzles (204).

5. The jet-type gas turbine guide device according to claim 1, characterized in that: The inner ring (102) has a hollow structure.

6. The jet-type gas turbine guide device according to claim 1, characterized in that: The surface of the flow divider (3) is coated with a high-temperature resistant ceramic coating.

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