Gas turbine

Abstract

The gas turbine comprises a volute, a connecting structure, a guider and a first elastic piece, and the volute comprises a gas channel and a gas outlet which communicate with each other. The connecting structure is located at the air outlet, the connecting structure and the volute are coaxially arranged, and a gap exists between the connecting structure and the volute. The guider and the connecting structure are coaxially arranged, and the guider is connected with the connecting structure and the volute. The guider comprises a guiding channel, and the guiding channel is communicated with the fuel gas channel through the gap. The first elastic piece is arranged on the outer side wall of the connecting structure in a sleeving mode and elastically abuts against the outer side wall of the connecting structure. The side, deviating from the connecting structure, of the first elastic piece is fixedly connected with the outer side wall of the volute. By adopting the gas turbine provided by the invention, the volute can freely expand in the elastic deformation direction of the first elastic piece, so that the risk that cracks occur to the volute or the guider or the connecting position of the volute and the guider due to thermal stress can be effectively reduced, and the reliability of the gas turbine is effectively improved; and the service life of the gas turbine is prolonged.

Description

Technical Field

[0001] The present application relates to the technical field of gas turbines, and in particular to a gas turbine. Background Art

[0002] The volute of a gas turbine is generally made of high-temperature alloy spin-welded to provide a flow channel for the high-temperature gas in the combustion chamber. During the operation of the gas turbine, the volute is in direct contact with the high-temperature gas, which will lead to a large temperature gradient between the volute surface and the connecting parts, resulting in large thermal stresses at the contact position between the volute and the connecting parts, as well as inside the connecting parts. Since the volute and the connecting parts are mostly rigidly connected at present, the above-mentioned thermal stress cannot be effectively absorbed, resulting in cracks in the volute or the connecting parts or the connection position of the two, which will affect the service life of the gas turbine and the reliability of the gas turbine.

[0003] Therefore, how to extend the service life of the gas turbine and improve the reliability of the gas turbine has become a difficult problem that needs to be solved urgently by technical personnel in this field. Summary of the invention

[0004] The present application provides a gas turbine for improving the reliability of the gas turbine and extending the service life of the gas turbine.

[0005] The present application provides a gas turbine, including a volute, a connecting structure, a guide and a first elastic member, wherein the volute includes a gas channel and an air outlet, and the air outlet is connected to the gas channel. The connecting structure is located at the air outlet and is coaxially arranged with the volute; there is a gap between the connecting structure and the side wall of the volute on the side close to the axis. The guide is coaxially arranged with the connecting structure, and the guide is connected to the connecting structure and to the volute. The guide includes a guide channel, and the guide channel is connected to the gas channel through the gap. The first elastic member is sleeved on the outer side wall of the connecting structure, and elastically abuts against the outer side wall of the connecting structure. The first elastic member is fixedly connected to the outer side wall of the volute.

[0006] With the gas turbine provided by the present application, since the guide and the volute are connected by a connecting structure and a first elastic member, after the high-temperature and high-pressure gas in the combustion chamber enters the volute, the heat-expanded volute squeezes the first elastic member to cause the first elastic member to undergo elastic deformation, thereby allowing the volute to expand freely in the direction of the elastic deformation of the first elastic member. This can effectively reduce the risk of cracks in the volute or the guide or at the connection between the two due to thermal stress, thereby effectively extending the service life of the gas turbine and improving the reliability of the gas turbine.

[0007] In a possible implementation of the present application, the connecting structure includes a slot, and along the axial direction of the volute, the notch of the slot faces the gas passage, and the first elastic member is inserted into the slot, which helps to improve the connection convenience between the first elastic member and the connecting structure.

[0008] In one possible implementation of the present application, since there is a gap between the end of the first elastic member located in the slot and the bottom of the slot along the axial direction of the volute, there is expansion space for at least part of the volute along the axial direction of the volute, which helps to further reduce the risk of cracks in the volute or the guide or the connection between the two due to thermal stress.

[0009] In a possible implementation of the present application, the gas turbine further includes a diffuser and a second elastic member, the diffuser is located on the side of the volute away from the guide, and the air outlet of the diffuser is connected to the air inlet of the volute. The second elastic member is located between the diffuser and the side wall of the volute, and the second elastic member is connected to the side wall of the diffuser and the volute, respectively. In this way, after the high-temperature and high-pressure gas in the combustion chamber enters the volute, the volute expands due to heat and squeezes the second elastic member, so that the second elastic member undergoes elastic deformation, so that the volute can expand freely in the direction of the elastic deformation of the second elastic member, which can effectively reduce the risk of cracks in the volute or diffuser or the connection between the two due to thermal stress, thereby effectively extending the service life of the gas turbine and improving the reliability of the gas turbine.

[0010] In a possible implementation of the present application, the second elastic member includes a cantilever and a connecting portion, and since one end of the cantilever is connected to the side wall of the diffuser, and the free end of the cantilever is connected to the connecting portion, the side of the connecting portion away from the cantilever is fixedly connected to the side wall of the volute. In this way, the volute can have a degree of freedom of expansion along the movement direction of the free end of the cantilever, which is conducive to further reducing the risk of cracks in the volute or the diffuser or the connection between the two due to thermal stress, and improving the reliability of the gas turbine.

[0011] In a possible implementation of the present application, the gas turbine further includes a third elastic member, which is located between the side wall of the volute and the diffuser, and is closer to the guide relative to the second elastic member. Since the side wall of the diffuser is connected to the side wall of the volute through the third elastic member, and the side wall of the diffuser is connected to the guide. In this way, when the volute is heated and expanded, the volute squeezes the third elastic member to cause the third elastic member to undergo elastic deformation, thereby allowing the volute to expand freely along the elastic deformation direction of the third elastic member. This can effectively reduce the risk of cracks in the volute, diffuser, or guide due to thermal stress, and can also effectively reduce the stress at the root of the static blades in the guide, and improve the reliability of the gas turbine.

[0012] In a possible implementation of the present application, the gas turbine further includes a support structure, and since the support structure is located between the side wall of the diffuser and the guide, the support structure is connected to the side wall of the diffuser, and the support structure is connected to the guide. This can effectively improve the connection stability between the diffuser and the guide, and improve the overall stability of the gas turbine.

[0013] In a possible implementation of the present application, the gas turbine also includes a first fixing member and a locking structure, and the guide includes a first fixing portion extending in the axial direction of the volute, and along the axial direction of the volute, the first fixing portion is located between the first fixing member and the support structure, and the locking structure runs through the first fixing member, the first fixing portion and the support structure. The first fixing member is fixedly connected to the support structure through the locking structure. Since there is a gap between the first fixing portion and the first fixing member along the axial direction of the volute, when the volute expands due to heat, the volute can expand freely along the axial direction, or the guide can expand freely along the axial direction of the volute, thereby effectively reducing the thermal stress inside the volute and the guide, so as to extend the service life of the gas turbine and improve the reliability of the gas turbine.

[0014] In a possible implementation of the present application, along the axial direction of the volute, the gap between the first fixing portion and the first fixing member is a, and a satisfies: 0.01mm≤a≤0.03mm, so as to make the overall structure of the gas turbine more compact while satisfying the expansion space of the volute and the guide.

[0015] In a possible implementation of the present application, the gas turbine includes a plurality of first fixing members, which are arranged at intervals along the circumference of the volute. In this way, after the high-temperature and high-pressure gas enters the volute, when the guide or the first fixing member expands due to heat, it can expand freely toward the gap between two adjacent first fixing members, thereby effectively reducing the risk of cracks in the guide or the first fixing member caused by thermal stress and improving the reliability of the gas turbine.

[0016] In a possible implementation of the present application, the gas turbine includes a plurality of second elastic members, which are arranged at intervals along the circumference of the volute, so as to improve the connection reliability between the volute and the diffuser.

[0017] In a possible implementation of the present application, the gas turbine further includes a second fixing member, the guide includes a second fixing portion extending away from the axial direction of the volute, and along the axial direction of the volute, the second fixing portion is located between the second fixing member and the connection structure, and the second fixing member is fixedly connected to the first fixing portion. This is conducive to improving the connection stability between the guide and the connection structure.

[0018] In a possible implementation of the present application, the gas turbine includes a plurality of second fixing members, and the plurality of second fixing members are arranged at intervals along the circumference of the volute. In this way, after the high-temperature and high-pressure gas enters the volute, when the guide or the second fixing member expands due to heat, it can freely expand toward the gap between two adjacent second fixing members, thereby effectively reducing the risk of cracks in the guide or the second fixing member caused by thermal stress. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of the structure of a gas turbine provided for this application;

[0020] Figure 2 A schematic diagram of the local structure of the volute provided in this application;

[0021] Figure 3 A schematic diagram of the partial structure of the guide provided in this application;

[0022] Figure 4 for Figure 1 A partial enlarged view of the gas turbine at point A is provided;

[0023] Figure 5 Another structural schematic diagram of a gas turbine provided for this application;

[0024] Figure 6 for Figure 1 A partial enlarged view of the gas turbine at position B is provided;

[0025] Figure 7 A schematic diagram of the structure of the first fixing member provided in this application;

[0026] Figure 8 A schematic diagram of the partial structure of the guide provided in this application.

[0027] Figure markings: 1-volute; 11-gas channel; 12-air inlet; 13-air outlet; 14-side wall; 2-connecting structure; 21-slot; 22-second protrusion; 3-guide; 31-inner ring; 32-outer ring; 33-static blade; 34-first fixing part; 341-first protrusion; 35-second fixing part; 36-second groove; 4-first elastic member; 5-diffuser; 6-second elastic member; 61-cantilever; 62-connecting part; 7-third elastic member; 8-supporting structure; 9-first fixing member; 91-first groove; 101-locking structure; 102-second fixing member. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical scheme and advantages of the present application clearer, the present application will be further described in detail below with reference to the accompanying drawings. However, the example embodiments can be implemented in various forms and should not be construed as being limited to the embodiments described herein. The same reference numerals in the figures represent the same or similar structures, and thus their repeated description will be omitted. The words expressing position and direction described in the embodiments of the present application are all illustrated by taking the accompanying drawings as examples, but changes may be made as needed, and the changes made are all included in the scope of protection of the present application. The drawings of the embodiments of the present application are only used to illustrate the relative position relationship, and they do not represent the true proportion.

[0029] It should be noted that specific details are described in the following description to facilitate understanding of the present application. However, the present application can be implemented in a variety of other ways different from those described herein, and those skilled in the art can make similar generalizations without violating the risk of the connotation of the present application. Therefore, the present application is not limited to the specific implementation methods disclosed below.

[0030] The volute of a gas turbine is generally made of high-temperature alloy spin-welded to provide a flow channel for the high-temperature gas in the combustion chamber. During the operation of the gas turbine, the volute is in direct contact with the high-temperature gas, which will lead to a large temperature gradient between the volute surface and the connecting parts, resulting in large thermal stresses at the contact position between the volute and the connecting parts, as well as inside the connecting parts. Since the volute and the connecting parts are mostly rigidly connected at present, the above-mentioned thermal stress cannot be effectively absorbed, resulting in cracks in the volute or the connecting parts or the connection position of the two, which will affect the service life of the gas turbine and the reliability of the gas turbine.

[0031] In view of this, in the gas turbine provided by the present application, by connecting the volute to other connecting parts through an elastic connector, the risk of cracks in the volute or the connecting parts or the connecting position of the two due to thermal stress can be reduced when the volute expands due to heat, thereby effectively extending the service life of the gas turbine and improving the reliability of the gas turbine. In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the drawings and specific embodiments.

[0032] refer to Figure 1 , Figure 1 A schematic diagram of the structure of a gas turbine provided in this application. The gas turbine includes a combustion chamber ( Figure 1The volute 1 includes a gas passage 11, an air inlet 12 and an air outlet 13, the air inlet 12 and the air outlet 13 are both connected to the gas passage 11, and the air inlet 12 of the volute 1 is connected to the combustion chamber, and the air outlet 13 is connected to the guide 3, so that the high-temperature and high-pressure gas in the combustion chamber enters the next working component, such as a turbine, through the volute 1 and the guide 3.

[0033] It can be understood that the shape of the volute 1 is annular, and as Figure 1 As shown, after the volute 1 is cut along the radial direction, the shape of the gas passage 11 shown can be exemplarily an arc shape, so as to change the flow direction of the airflow.

[0034] The connection structure 2 is used to realize the connection between the volute 1 and the guide 3. When the connection structure 2 is specifically set, the connection structure 2 is annular, and the connection structure 2 is located at the air outlet 13 of the volute 1 and is coaxially arranged with the volute 1. Figure 2 As shown, Figure 2 For display Figure 1 The projection view of the air outlet 13 of the volute 1 in the X direction is shown in FIG. 1 , and the side wall 14 is used to form the air outlet 13 and is close to the axis of the volute 1 relative to the connecting structure 2. The connecting structure 2 is sleeved on the outside of the side wall 14, and there is a gap between the connecting structure 2 and the side wall 14, and the gap can be used as a part of the air outlet 13.

[0035] It should be noted that the present application does not limit the material and cross-sectional shape of the connection structure 2. For example, it can be a high-temperature alloy with a temperature resistance greater than 900° C., which is beneficial to prolonging the service life of the connection structure 2. Figure 1 As shown, the shape of the radial cross-section of the connection structure 2 can be exemplarily C-shaped or G-shaped, which is beneficial to improving the structural reliability of the connection structure 2.

[0036] When the guide 3 is specifically set, Figure 1 As shown, the guide 3 is connected to the connection structure 2 and to the volute 1. Specifically, as Figure 3 As shown, Figure 3 For display Figure 1 The projection view of the guide 3 in the X direction shown in the figure, the guide 3 may include an inner ring 31 and an outer ring 32 arranged coaxially, and the outer ring 32 is sleeved on the outer side of the inner ring 31. The inner ring 31 and the outer ring 32 are connected radially by a plurality of static blades 33, and the plurality of static blades 33 are evenly distributed along the circumference of the inner ring 31 to form a guide channel for the airflow, and the guide channel can be used to change the flow direction and speed of the airflow. In the present application, the guide channel is connected to the gas channel 11 through the gap between the connecting structure 2 and the volute 1, so that the airflow in the gas channel 11 can be evenly introduced to the next working component, such as a turbine.

[0037] In an optional embodiment, the inner ring 31 of the guide 3 is connected to the side wall 14 of the volute, and the outer ring 32 of the guide is connected to the connection structure 2, and can be connected to the side of the connection structure 2 away from the first elastic member 4. In this way, the guide channel can be directly opposite to and connected to the air outlet, which is conducive to improving the flow efficiency of the airflow and improving the structural compactness of the gas turbine.

[0038] The first elastic member 4 is used to realize the connection between the connection structure 2 and the volute 1. When the first elastic member 4 is specifically set, the first elastic member 4 is in the shape of a ring and is sleeved on the outer wall of the connection structure 2 and elastically abuts against the outer wall of the connection structure 2. At the same time, the first elastic member 4 is fixedly connected to the outer wall of the volute 1. Exemplarily, the side of the first elastic member 4 facing away from the connection structure 2 is fixedly connected to the outer wall of the volute 1, which can make the structure of the gas turbine more compact. In addition, if Figure 1 The shape of the radial cross-section of the first elastic member 4 can be exemplarily a C-shape, which can effectively improve the structural simplicity and reliability of the first elastic member 4 while meeting the expansion and contraction requirements of the first elastic member 4 .

[0039] With the gas turbine provided by the present application, since the guide 3 and the volute 1 are connected via the connecting structure 2 and the first elastic member 4, after the high-temperature and high-pressure gas in the combustion chamber enters the volute 1, the heat-expanded volute 1 can squeeze the first elastic member 4 to cause the first elastic member 4 to undergo elastic deformation, thereby allowing the volute 1 to expand freely in the direction of the elastic deformation of the first elastic member 4. This can effectively reduce the risk of cracks in the volute 1 or the guide 3 or the connection between the two due to thermal stress, thereby effectively extending the service life of the gas turbine and improving the reliability of the gas turbine.

[0040] In a specific embodiment, reference is made to Figure 1 and Figure 4 , Figure 4 for Figure 1 The connecting structure 2 may include a slot 21, and along the radial direction of the volute 1, the slot 21 is arranged on the outer side wall of the connecting structure 2 on the side away from the axis of the volute 1, and the slot 21 surrounds the outer side wall of the connecting structure 2. Figure 4The slot 21 is oriented toward the gas passage 11, and the first elastic member 4 is inserted into the slot 21. For example, along the radial direction of the volute 1, the inner wall of the first elastic member 4 close to the axis of the volute 1 is inserted into the slot 21, which is conducive to improving the connection convenience and structural compactness between the first elastic member 4 and the connecting structure 2. Moreover, such a design can also make the connection positions between the volute 1 and the first elastic member 4, and between the first elastic member 4 and the connecting structure 2 sealed to prevent gas leakage.

[0041] It is worth mentioning that continue to refer to Figure 4 Since there is a gap between the end of the first elastic member 4 in the slot 21 and the bottom of the slot 21 along the axial direction of the volute 1, at least part of the volute 1 has expansion space along the axial direction of the volute 1, which is beneficial to further reduce the risk of cracks in the volute 1 or the guide 3 due to thermal stress.

[0042] It should be noted that, along the axial direction of the volute 1, the length of the portion of the first elastic member 4 located in the slot 21 can be adjusted according to actual needs, and can be 50 mm or 80 mm for example, and the corresponding depth of the slot 21 can be 70 mm or 100 mm for example, so as to make the structure of the gas turbine more compact while satisfying the axial expansion space of the volute 1.

[0043] In a specific embodiment, Figure 1 As shown, the gas turbine may further include a diffuser 5 and a second elastic member 6. The diffuser 5 is located on the side of the volute 1 away from the guide vane 3, and the air outlet of the diffuser 5 is connected to the combustion chamber. In the present application, the diffuser 5 can be used to compress the absorbed air to increase the flow rate and pressure of the inhaled air and then deliver it to the combustion chamber, thereby providing the combustion chamber with a sufficient air-fuel mixture.

[0044] Continue to refer Figure 1 , the second elastic member 6 is located between the diffuser 5 and the side wall of the volute 1, and the second elastic member 6 is connected to the side wall of the diffuser 5 and the volute 1 respectively. In this way, after the high-temperature and high-pressure gas in the combustion chamber enters the volute 1, the volute 1 is heated and expands to squeeze the second elastic member 6, so that the second elastic member 6 undergoes elastic deformation, so that the volute 1 can expand freely along the direction of the elastic deformation of the second elastic member 6, which can effectively reduce the risk of cracks in the volute 1 or the diffuser 5 or the connection between the two due to thermal stress, thereby effectively extending the service life of the gas turbine and improving the reliability of the gas turbine.

[0045] For details, please refer to Figure 1The second elastic member 6 includes a cantilever 61 and a connecting portion 62. One end of the cantilever 61 is connected to the side wall of the diffuser 5, and the free end of the cantilever 61 is connected to the connecting portion 62, and the side of the connecting portion 62 facing away from the cantilever 61 is fixedly connected to the side wall of the volute 1. In this way, the volute 1 has a degree of freedom of expansion along the moving direction of the free end of the cantilever 61, which is conducive to further reducing the risk of cracks in the volute 1 or the diffuser 5 or the connection position of the two due to thermal stress, and improving the reliability of the gas turbine.

[0046] It should be noted that the material of the cantilever 61 can be a high-temperature alloy with a temperature resistance of not less than 900°C, which is conducive to extending the service life of the cantilever 61. In addition, the length of the cantilever 61 can be adjusted according to actual needs. The exemplary length of the cantilever 61 can be 110 mm or 140 mm, so as to meet the elastic requirements of the cantilever 61 and the expansion requirements of the volute 1, and at the same time, it can make the structure of the gas turbine more compact.

[0047] It is worth mentioning that the cantilever 61 can be exemplarily welded to the flange, and the flange is fixed to the end of the air outlet of the diffuser 5 by bolts. In this way, the connection requirements between the second elastic member 6 and the diffuser 5 can be met while improving the compactness and reliability of the connection between the volute 1 and the diffuser 5.

[0048] When the connecting portion 62 is specifically set, the shape of the radial cross-sectional surface of the connecting portion 62 along the volute 1 can be exemplarily an arc, and along the axial direction of the volute 1, the arc-shaped protrusion faces the volute 1, and there is a gap between the connecting portion 62 and the side wall of the diffuser 5, so that the volute 1 has axial freedom, thereby further reducing the risk of cracks in the volute 1 or the diffuser 5 due to thermal stress, and improving the reliability of the gas turbine.

[0049] In one possible implementation, reference Figure 5 , Figure 5 Another structural schematic diagram of the gas turbine provided in the present application can be used to show another arrangement of the second elastic member 6. Specifically, the gas turbine can be provided with a plurality of second elastic members 6, and the plurality of second elastic members 6 are arranged at intervals along the circumference of the volute 1, so as to improve the connection reliability between the volute 1 and the diffuser 5.

[0050] It is worth mentioning that in another possible implementation, the shape of the cantilever 61 can be exemplarily annular, and the second elastic member 6 can be provided with a plurality of connecting portions 62, and the connecting portions 62 are arranged at intervals along the circumference of the cantilever 61. By providing the second elastic member 6 as an integral structure, it can meet the space requirement for thermal expansion of the volute 1 while facilitating the installation convenience between the diffuser 5 and the second elastic member 6.

[0051] In a specific embodiment, Figure 1 As shown, the gas turbine may further include a third elastic member 7. Specifically, the third elastic member 7 is located between the side wall of the volute 1 and the diffuser 5, and is closer to the guide 3 relative to the second elastic member 6. Since the side wall of the diffuser 5 is connected to the side wall of the volute 1 through the third elastic member 7, and the side wall of the diffuser 5 is connected to the guide 3, when the volute 1 is heated and expanded, the volute 1 that is heated and expanded squeezes the third elastic member 7, so that the third elastic member 7 is elastically deformed, so that the volute 1 is freely expanded in the direction of the elastic deformation of the third elastic member 7, which can effectively reduce the risk of cracks in the volute 1, the diffuser 5, or the guide 3 due to thermal stress, and can also effectively reduce the stress at the root of the static blade 33 in the guide 3, and improve the reliability of the gas turbine.

[0052] When the third elastic member 7 is specifically provided, the shape of the third elastic member 7 can be exemplarily a circular ring, and the side wall 14 of the volute 1 is sleeved on the outer side of the third elastic member 7. Figure 1 As shown, the shape of the radial cross-section of the third elastic member 7 along the volute 1 is exemplarily an arc, and one bent portion of the arc is connected to the side wall of the volute 1, and the other bent portion is connected to the side wall of the diffuser 5, and the third elastic member 7 is exemplarily connected to the side walls of the volute 1 and the diffuser 5 by welding. At the same time, along the axial direction of the volute 1, the arc-shaped protrusion faces the diffuser 5 relative to the guide 3. The third elastic member 7 provided by the present application can meet the requirements of the elastic connection between the volute 1 and the diffuser 5 to reduce thermal stress while making the structure of the gas turbine more concise.

[0053] It is worth mentioning that a plurality of through holes are also provided on the surface of the third elastic member 7, and the plurality of through holes are evenly arranged along the circumference of the third elastic member 7, so that cold air can enter to cool the surface of the volute 1, thereby reducing the thermal expansion of the volute 1 and reducing the thermal stress of the volute 1 and other components connected thereto.

[0054] It should be noted that, in other possible embodiments of the present application, the structure of the third elastic member 7 may also be set with reference to the structure of the second elastic member 6. Specifically, the third elastic member includes a cantilever and a connecting portion, wherein the cantilever is connected to the side wall of the volute 1, and the connecting portion is connected to the side wall of the diffuser 5. In addition, the connection method between the cantilever and the side wall of the volute 1, and the connection method between the connecting portion and the diffuser 5 can be exemplarily welding.

[0055] In addition, if Figure 1As shown, the gas turbine may further include a support structure 8, which is located between the side wall of the diffuser 5 and the guide vane 3. At the same time, the support structure 8 is connected to the side wall of the diffuser 5, and the support structure 8 is connected to the guide vane 3, so that the guide vane 3 is connected to the side wall of the diffuser 5 through the support structure 8, which can effectively improve the overall stability of the gas turbine.

[0056] It should be noted that the material hardness of the support structure 8 is higher than the material hardness of the third elastic member 7, which can further improve the overall stability of the gas turbine. In a possible embodiment of the present application, the material of the support structure 8 is exemplarily a high-temperature alloy, so as to improve the temperature resistance of the support structure 8 while meeting the strength requirements and extend the service life of the support structure 8.

[0057] In a specific embodiment, Figure 6 As shown, Figure 6 for Figure 1 A partial enlarged view of the gas turbine at B is provided. The gas turbine further includes a first fixing member 9 and a locking structure 101, and the guide 3 includes a first fixing portion 34 extending in the axial direction of the volute 1. Along the axial direction of the volute 1, the first fixing portion 34 is located between the first fixing member 9 and the support structure 8, and the locking structure 101 penetrates the first fixing member 9, the first fixing portion 34 and the support structure 8, and the first fixing member 9 is fixedly connected to the support structure 8 through the locking structure 101, and along the axial direction of the volute 1, there is a gap a between the first fixing portion 34 and the first fixing member 9, and an exemplary a satisfies: 0.01mm≤a≤0.03mm. Then, when the volute 1 is heated and expanded, the volute 1 can expand freely in the axial direction, or the guide 3 can expand freely in the axial direction of the volute 1, thereby effectively reducing the thermal stress inside the volute 1 and the guide 3, so as to extend the service life of the gas turbine and improve the reliability of the gas turbine.

[0058] It should be noted that the present application does not limit the structure of the first fixing portion 34 . Exemplarily, it may be a bending structure toward the axial direction of the volute 1 , or it may be a protrusion protruding from the side wall of the volute 1 .

[0059] When the first fixing member 9 is specifically set, its shape can be an annular shape, for example, a flange, so that the flange can be coaxial with the guide 3 and the first fixing portion 34, which is conducive to improving the installation convenience of the first fixing member 9. It can be understood that the shape of the first fixing member 9 can be adjusted according to the actual shape. For example, its shape can also be an arc shape, and multiple first fixing members 9 can be set, and multiple first fixing members 9 are arranged at intervals and coaxially along the circumference of the volute 1. In this way, after the high-temperature and high-pressure gas enters the volute 1, when the guide 3 or the first fixing member 9 expands due to heat, it can expand freely toward the gap between the two adjacent first fixing members 9, thereby effectively reducing the risk of cracks in the guide 3 or the first fixing member 9 caused by thermal stress, and improving the reliability of the gas turbine.

[0060] In addition, in one possible implementation, reference Figure 7 , Figure 7 This is a schematic diagram of the structure of the first fixing member 9 provided in the present application, which is used to show the structure of the first fixing member 9 along the axial direction of the volute 1. The first fixing member 9 also includes a plurality of first grooves 91, which are evenly distributed along the circumference of the first fixing member 9, and the openings of the plurality of first grooves 91 are all facing the axis of the first fixing member 9. Figure 8 , Figure 8 The schematic diagram of the partial structure of the guide 3 provided in the present application is used to show the structure of the first fixing portion 34 of the guide 3 along the axial direction of the volute 1. Specifically, the first fixing portion 34 includes a plurality of first protrusions 341 extending away from the axis of the volute, and the plurality of first protrusions 341 are evenly distributed along the axial direction of the first fixing portion 34, and are arranged one-to-one with the plurality of first grooves 91, and the first protrusions 341 are inserted into the first grooves 91, so that the first fixing portion 34 and the first fixing member 9 can be mutually limited in the circumferential direction, thereby further improving the connection reliability of the guide 3 and the first fixing member 9 during the installation or operation of the gas turbine.

[0061] It should be noted that the present application does not limit the specific form of the locking structure 101, which can be exemplarily a bolt, so as to make the locking structure 101 more concise while meeting the connection requirements of the first fixing member 9, the first fixing portion 34 and the supporting structure 8.

[0062] In a specific embodiment, reference is made to Figure 1 and Figure 4 The gas turbine may further include a second fixing member 102, and the guide 3 may further include a second fixing portion 35 extending away from the axial direction of the volute 1. Along the axial direction of the volute 1, since the second fixing portion 35 is located between the second fixing member 102 and the connecting structure 2, and the second fixing member 102 is fixedly connected to the first fixing portion 34, it is beneficial to improve the connection stability between the guide 3 and the connecting structure 2.

[0063] When the second fixing member 102 is specifically set, the second fixing member 102 is in the shape of a circular ring, and can be exemplarily a flange, and the second fixing member 102 is coaxial with the guide 3 so that the guide 3 is coaxially fixed with the connecting structure 2 and the volute 1.

[0064] In addition, the structural form of the second fixing portion 35 can refer to the first fixing portion 34 and will not be described in detail here.

[0065] It is understandable that the second fixing member 102 may also be in an arc shape, and the gas turbine includes a plurality of second fixing members 102, and the plurality of second fixing members 102 are arranged at intervals along the circumference of the volute 1. In this way, after the high-temperature and high-pressure gas enters the volute 1, since the plurality of second fixing members 102 are arranged at intervals, when the guide 3 or the second fixing member 102 is heated and expanded, it can freely expand toward the gap between two adjacent second fixing members 102, thereby effectively reducing the risk of cracks in the guide 3 or the second fixing member 102 caused by thermal stress.

[0066] In one possible implementation, continue to refer to Figure 4 , along the axial direction of the volute 1, the connection structure 2 includes a second protrusion 22, and the second protrusion 22 is close to the axis of the volute 1 relative to the first elastic member 4. The guide 3 includes a second groove 36, the second groove 36 is arranged on the outer ring 32, and the notch of the second groove 36 faces the connection structure 2, and the first protrusion 341 is inserted into the first groove 91. In this way, during the installation process of the gas turbine, the first groove 91 and the first protrusion 341 can be inserted to achieve the pre-positioning of the guide 3 and the connection structure 2, which is conducive to improving the installation convenience of the guide 3 and the connection structure 2.

[0067] In summary, the gas turbine provided by the present application, since the volute 1 is connected to some connecting parts by elastic parts, for example, the volute 1 and the guide 3 are connected by the first elastic part 4, after the high-temperature and high-pressure gas in the combustion chamber enters the volute 1, the heat-expanded volute 1 can squeeze the first elastic part 4, so that the first elastic part 4 undergoes elastic deformation, thereby allowing the volute 1 to expand freely in the direction of the elastic deformation of the first elastic part 4, thereby effectively reducing the risk of cracks in the volute 1 or the guide 3 or the connection between the two due to thermal stress, thereby effectively extending the service life of the gas turbine and improving the reliability of the gas turbine.

[0068] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A gas turbine, characterized in that: It includes a volute, a connecting structure, a guide and a first elastic member, wherein: The volute comprises a gas passage and a gas outlet, and the gas outlet is communicated with the gas passage; The connecting structure is located at the air outlet and is coaxially arranged with the volute; there is a gap between the connecting structure and the side wall of the volute on the side close to the axis; The guide is coaxially arranged with the connection structure, connected with the connection structure and connected with the volute; the guide comprises a guide channel, and the guide channel is connected with the gas channel through the gap; The first elastic member is sleeved on the outer side wall of the connection structure and elastically abuts against the outer side wall of the connection structure; the first elastic member is fixedly connected to the outer side wall of the volute.

2. The gas turbine according to claim 1, characterized in that The connection structure comprises a slot, and along the axial direction of the volute, the notch of the slot faces the gas passage, and the first elastic member is inserted into the slot.

3. The gas turbine according to claim 2, characterized in that Along the axial direction of the volute, there is a gap between the end of the first elastic member located at the slot and the bottom of the slot.

4. The gas turbine according to claim 1, characterized in that The gas turbine further comprises a diffuser and a second elastic member, wherein the diffuser is located on a side of the volute away from the guide, and an air outlet of the diffuser is communicated with an air inlet of the volute; The second elastic member is located between the diffuser and the side wall of the volute, and the second elastic member is connected to the diffuser and the side wall of the volute respectively.

5. The gas turbine according to claim 4, characterized in that The second elastic member includes a cantilever and a connecting portion, one end of the cantilever is connected to the side wall of the diffuser, and the free end of the cantilever is connected to the connecting portion; and a side of the connecting portion facing away from the cantilever is fixedly connected to the side wall of the volute.

6. The gas turbine according to claim 4, characterized in that The gas turbine also includes a third elastic member, which is located between the side wall of the volute and the diffuser and is close to the guide relative to the second elastic member; the side wall of the diffuser is connected to the side wall of the volute through the third elastic member, and the side wall of the diffuser is connected to the guide.

7. The gas turbine according to claim 6, characterized in that The gas turbine further comprises a support structure, wherein the support structure is located between the side wall of the diffuser and the guide; the support structure is connected to the side wall of the diffuser, and the support structure is connected to the guide.

8. The gas turbine according to claim 7, characterized in that The gas turbine further comprises a first fixing member and a locking structure, the guide comprises a first fixing portion extending in the axial direction of the volute, the first fixing portion is located between the first fixing member and the supporting structure along the axial direction of the volute, and the locking structure penetrates the first fixing member, the first fixing portion and the supporting structure; the first fixing member is fixedly connected to the supporting structure through the locking structure; Along the axial direction of the volute, a gap exists between the first fixing portion and the first fixing member.

9. The gas turbine according to claim 8, characterized in that Along the axial direction of the volute, a gap a is provided between the first fixing portion and the first fixing member, and a satisfies: 0.01 mm ≤ a ≤ 0.03 mm.

10. The gas turbine according to claim 8, characterized in that The gas turbine includes a plurality of the first fixing members, and the plurality of the first fixing members are arranged at intervals along the circumference of the volute.

11. The gas turbine according to any one of claims 4 to 10, characterized in that: The gas turbine includes a plurality of the second elastic members, and the plurality of the second elastic members are arranged at intervals along the circumference of the volute.

12. The gas turbine according to claim 3, characterized in that The gas turbine also includes a second fixing member, and the guide includes a second fixing portion extending along the axial direction away from the volute, and along the axial direction of the volute, the second fixing portion is located between the second fixing member and the connecting structure, and the second fixing member is fixedly connected to the first fixing portion.

13. The gas turbine according to claim 12, characterized in that: The gas turbine includes a plurality of the second fixing members, and the plurality of the second fixing members are arranged at intervals along the circumference of the volute.

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