Multi-hole injection nozzle of gas turbine

Abstract

The utility model provides a gas turbine multi-hole jet nozzle, which relates to the gas turbine nozzle field, and comprises a nozzle and a plurality of groups of flow channels arranged in the nozzle, the flow channels are bent in the nozzle, the inlets of all the flow channels are connected and communicated through a connecting cover, and the connecting cover is connected with the nozzle. The end, away from the spray head, of the connecting cover is connected with and penetrates through a spray pipe, heat dissipation holes penetrating through the spray head are formed in the middle of the spray head and located between the adjacent flow channels, and the connecting cover is provided with notches exposing the heat dissipation holes. According to the porous injection nozzle of the gas turbine, by manufacturing the spray head with the bent flow channels, the length of fuel passing through the flow channels can be increased, so that the heat exchange area of the fuel and the spray head can be increased, the spray head can be cooled through the fuel, meanwhile, the heat dissipation holes are formed between the adjacent flow channels, and the heat dissipation efficiency is improved. And when air flows through the heat dissipation holes, the spray head can be cooled.

Description

Technical Field

[0001] This utility model relates to the field of gas turbine nozzle technology, specifically to a multi-hole injection nozzle for gas turbines. Background Technology

[0002] CN113483359B discloses a nozzle head for a gas turbine and a nozzle for a gas turbine. The nozzle head for a gas turbine includes a body, which comprises an input section, a premixing section, and an output section connected axially. The input section has an air delivery channel and a fuel delivery channel. The premixing section has a first fuel delivery chamber communicating with the fuel delivery channel and a premixing channel communicating with the air delivery channel. The first fuel delivery chamber is adjacent to the side wall of the premixing section and is connected to the premixing channel. The output section has an outlet hole communicating with the premixing channel. The nozzle head for a gas turbine provided by this technical solution has the advantages of strong flame stabilization capability and the ability to cool the body. However, the different diameters, positions, and nozzle angles of the various sections in this technical solution make production difficult. Therefore, a nozzle that is easy to manufacture and can be cooled is needed. Utility Model Content

[0003] To address the shortcomings of existing technologies, this utility model provides a multi-hole injection nozzle for gas turbines, which solves the problem of high production difficulty of cooling nozzles mentioned in the background technology.

[0004] Technical solution

[0005] To achieve the above objectives, this utility model is implemented through the following technical solution: a gas turbine multi-hole injection nozzle, including a nozzle head and multiple sets of flow channels disposed inside the nozzle head. The flow channels are bent inside the nozzle head, and the inlets of all flow channels are connected and connected through a connecting cover. The end of the connecting cover away from the nozzle head is connected and connected through a nozzle pipe.

[0006] Furthermore, the nozzle has a heat dissipation hole in the middle between adjacent flow channels, and the connecting cover has a notch to expose the heat dissipation hole.

[0007] Furthermore, the nozzle is divided into a front section, a middle section, and a rear section. The middle section has a set of through holes with parallel flow channels. The front section and the middle section have connecting holes on their respective sides that are close to each other, which are used to connect the set of flow channels. The front, middle, and rear sections of the nozzle are sealed and connected to each other.

[0008] Furthermore, a sealing ring is provided along the connection hole on the side of the front and rear sections that are close to each other, and sealing insertion grooves adapted to the sealing rings are provided on both sides of the middle section.

[0009] Furthermore, the front, middle, and rear sections are fixed by welding, and welding rings are provided at the connection points between the front and middle sections and between the middle and rear sections.

[0010] Furthermore, the cross-sectional shape of the welding ring is a right trapezoid, and the faces corresponding to the short sides of adjacent welding rings are in contact with each other.

[0011] Furthermore, the flow channels are divided into inner and outer groups. The gap between the flow channels in the inner ring is different from the gap between the flow channels in the outer ring. The heat dissipation holes are located between the flow channels in the inner ring and the flow channels in the outer ring.

[0012] The beneficial effects of this utility model are as follows:

[0013] 1. The gas turbine multi-hole injection nozzle, by manufacturing a nozzle with a bent flow channel, can increase the length of fuel passing through the flow channel, thereby increasing the heat exchange area between the fuel and the nozzle, and thus cooling the nozzle through the fuel. At the same time, heat dissipation holes are set between adjacent flow channels, and the nozzle can be cooled when air flows through the heat dissipation holes.

[0014] 2. The gas turbine multi-hole injection nozzle is divided into a front section, a middle section, and a rear section. The middle section has a set of parallel flow channels through holes. The front and middle sections have connecting holes on their respective sides to connect the flow channels. The front, middle, and rear sections of the nozzle are sealed to each other. This design allows the nozzle to be produced separately. By dividing it into three sections, drilling holes in each section, and then connecting them, the production difficulty of the nozzle can be reduced. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of this utility model;

[0016] Figure 2 This is a schematic diagram of the front-end connection of this utility model;

[0017] Figure 3 This is a schematic diagram of the middle section connection of this utility model;

[0018] Figure 4 This is a partial sectional view of the present invention.

[0019] Among them, 1. Nozzle; 2. Flow channel; 3. Connecting cover; 4. Spray pipe; 5. Heat dissipation hole; 11. Front section; 12. Middle section; 13. Rear section; 101. Through hole; 102. Connecting hole; 103. Sealing ring; 104. Sealing insertion groove; 105. Welding ring. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0021] See Figure 1-4 The gas turbine multi-hole injection nozzle includes a nozzle 1 and multiple sets of flow channels 2 disposed inside the nozzle 1. The flow channels 2 are bent inside the nozzle 1. The inlets of all flow channels 2 are connected and connected through a connecting cover 3. The end of the connecting cover 3 away from the nozzle 1 is connected and connected to a nozzle pipe 4. By setting the flow channels 2 in a bent form, the residence time of fuel in the nozzle 1 can be increased, thereby enabling the fuel to cool the nozzle.

[0022] The nozzle 1 has a heat dissipation hole 5 in the middle between the adjacent flow channels 2, and the connecting cover 3 has a notch that exposes the heat dissipation hole 5. By setting the heat dissipation hole 5, the compressed air can pass through the heat dissipation hole 5, thereby achieving the effect of heat dissipation and cooling.

[0023] The nozzle 1 is divided into a front section 11, a middle section 12, and a rear section 13. The middle section 12 has a set of through holes 101 parallel to the flow channels 2. The front section 11 and the middle section 12 have connecting holes 102 on their respective sides to connect the set of flow channels 2. The front, middle and rear sections of the nozzle 1 are sealed to each other. This arrangement allows the nozzle 1 to be produced separately. By dividing it into three sections, opening holes in each section, and then connecting them, the production difficulty of the nozzle 1 can be reduced.

[0024] A sealing ring 103 is provided along the connecting hole 102 on one side of the front section 11 and the rear section 13 that are close to each other. A sealing insertion groove 104 adapted to the sealing ring 103 is provided on both sides of the middle section 12. The sealing insertion groove 104 can be milled out by a milling machine. The sealing ring 103 is inserted into the inside of the sealing insertion groove 104, thereby dividing the flow channel 2 and making the connection end of the flow channel 2 sealed.

[0025] The front section 11, the middle section 12, and the rear section 13 are fixed by welding. Welding rings 105 are provided at the connection points between the front section 11 and the middle section 12, and between the middle section 12 and the rear section 13. The production cost is lower by using welding.

[0026] The cross-sectional shape of the welding ring 105 is a right trapezoid. The faces of the short sides of adjacent welding rings 105 are in contact with each other. This arrangement allows the welding rings 105 to form a molten pool when they come into contact with each other. Welding can be performed by simple polishing. Welding can be performed by single-sided welding and double-sided forming.

[0027] The flow channel 2 is divided into inner and outer groups. The gap between the inner flow channel 2 is different from the gap between the outer flow channel 2. The heat dissipation hole 5 is located between the inner flow channel 2 and the outer flow channel 2. This arrangement can increase the number of flow channels 2 in the effective space and dissipate heat between the gaps of the flow channels 2.

[0028] In use, by manufacturing a nozzle 1 with a bent flow channel 2, the length of fuel passing through the flow channel 2 can be increased, thereby increasing the heat exchange area between the fuel and the nozzle 1, and thus cooling the nozzle 1 through the fuel. At the same time, heat dissipation holes 5 are provided between adjacent flow channels 2, and the nozzle 1 can be cooled when air flows through the heat dissipation holes 5.

[0029] It should be noted that in this paper, relational terms such as first and second are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0030] 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 equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A gas turbine porous injection nozzle comprising a head (1) and a plurality of groups of flow channels (2) arranged inside the head (1), characterized in that: The flow channel (2) is bent inside the nozzle (1), the inlets of all flow channels (2) are connected and penetrated by the connecting cover (3), and the connecting cover (3) is connected and penetrated by the nozzle (4) away from the nozzle (1).

2. The gas turbine porous injection nozzle of claim 1, wherein: The middle part of the nozzle (1) is located between adjacent flow channels (2) and is provided with a heat dissipation hole (5) penetrating the nozzle (1), and the connecting cover (3) is provided with a notch exposing the heat dissipation hole (5).

3. The gas turbine porous injection nozzle of claim 1, wherein: The nozzle (1) is divided into a front section (11), a middle section (12) and a rear section (13), the middle section (12) is provided with a group of through holes (101) parallel to the flow channels (2), the front section (11) and the middle section (12) are respectively provided with a connecting hole (102) for connecting a group of flow channels (2) on one side close to each other, and the front section, the middle section and the rear section of the nozzle (1) are sealingly connected.

4. The gas turbine porous injection nozzle of claim 3, wherein: The front section (11) and the rear section (13) are provided with a sealing plug ring (103) on one side close to each other along the connecting hole (102), and the middle section (12) is provided with a sealing plug groove (104) adapted to the sealing plug ring (103) on both sides.

5. A gas turbine porous injection nozzle according to claim 3 or 4, characterised in that: The front section (11), the middle section (12) and the rear section (13) are fixed by welding. The front section (11), the middle section (12) and the rear section (13) are provided with a welding ring (105) at the connection between them.

6. The gas turbine porous injection nozzle of claim 5, wherein: The cross-sectional shape of the welding ring (105) is a right trapezoid, and the short sides of adjacent welding rings (105) correspond to the surfaces in contact with each other.

7. The gas turbine porous injection nozzle of claim 2, wherein: The flow channel (2) is divided into two groups, the gap between the flow channels (2) in the inner ring is different from the gap between the flow channels (2) in the outer ring, and the heat dissipation hole (5) is located between the flow channels (2) in the inner ring and the flow channels (2) in the outer ring.

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