Gas turbine stationary blade structure and compressor

Abstract

The present invention discloses a gas turbine stator blade structure, comprising a plurality of stator blades, a hub, a plurality of mating structures disposed on the hub, and a compensation assembly. The stator blades include a first blade of a first blade type and a second blade of a second stator blade type. The mating structures are disposed correspondingly to the first blade or the second blade, positioning the bottom of the first blade or the bottom of the second blade at a preset stator blade position on the hub. The compensation assembly is disposed in the space defined by the second blade and the mating structure to compensate for airflow loss between the second blade and the mating structure. By providing the mating structures and the compensation assembly, the application makes the stator blade structure adaptable to different types of stator blades, thereby enabling the stator blade type to be changed without replacing the hub or the compressor cylinder.

Description

Technical Field

[0001] The present invention relates to a gas turbine, and in particular to a gas turbine stationary blade structure and a compressor. Background Art

[0002] Shrouded and cantilevered stator blades are two typical stator blade configurations in axial-flow compressors. Shrouded stator blades are characterized by their ends being mounted on the inner and outer rings, respectively. Both end surfaces are stationary, and there is no root gap. However, they are affected by leakage flow from the sealing cavity between the inner ring and the rotating shaft. Cantilevered stator blades lack an inner ring, with the inner endwall being a rotating hub. This presence of a root gap directly alters the stator's flow field structure. Structurally, shrouded stator blades offer excellent vibration characteristics, sufficient mechanical damping, and a reduced risk of vibration fatigue damage. Cantilevered stator blades offer advantages such as simple structure, low cost, low weight, and excellent mechanical properties. Aerodynamically, cantilevered stator blades can experience leakage due to the gap. Leakage flow at the blade tip mixes with the main flow, negatively impacting the blade passage and even the overall compressor performance. As discussed above, shrouded and cantilevered stator blades each have their own advantages and disadvantages. Different compressors select different stator blade configurations based on their specific characteristics, aerodynamic performance, rotor structural characteristics, and other factors. Some compressors have all shrouded stator blades, some have all cantilevered stator blades, and there are also compressors in which the front stages have shrouded stator blades and the rear stages have cantilevered stator blades.

[0003] Different stator blade structures correspond to different rotor structures. Therefore, in addition to aerodynamic performance requirements, the rotor structure is also one of the factors that need to be considered when selecting a stator blade structure.

[0004] Shrouded stator blades are typically connected by an inner ring at the shroud. The shroud and inner ring are located between the blade roots of the two stages of moving blades. Therefore, an annular groove is designed between the roots of the two stages of moving blades to provide space for the shroud and inner ring. Therefore, for compressors using shrouded stator blades, the rotor blades are typically axially mounted at the blade roots.

[0005] Compressors using cantilevered stator blades do not require annular grooves on the rotor to accommodate the blade shrouds and inner rings. Instead, the rotor hub surface must remain intact, serving as the internal flow path for the cantilevered stator blades. Therefore, for compressors using cantilevered stator blades, the rotor blades typically have circumferentially mounted blade roots.

[0006] Therefore, once the rotor structure is determined, the vane configuration is also determined. If aerodynamic performance requirements necessitate a change in the vane configuration, the rotor configuration must also be changed. If aerodynamic performance comparison tests are required for two vane configurations, two sets of compressor test pieces must be designed and manufactured for these comparative tests. The existing technology lacks a rotor and compressor that can accommodate both shrouded and cantilever vane configurations.

[0007] Patent CN114080508A discloses a compressor with shrouded stator blades. Specifically, Figure 1 As shown, the outlet guide vane 8 includes blade bodies 81 arranged at regular intervals in the circumferential direction on the axially downstream side of the axially most downstream impeller 4D, projecting from the compressor casing 1C, and an inner shroud 82 circumferentially connected to the blade bodies 81 on the radially inner side. The inner casing 9 is arranged on the axially downstream side of the axially most downstream impeller 4D, with a gap G between it and the impeller 4D, and extends in a cylindrical shape along the axis Ax direction. The compressor of this patent is not suitable for both shrouded and cantilevered stator blade structures.

[0008] In view of the above technical problems, the present invention is specially introduced. Summary of the Invention

[0009] The main purpose of the present invention is to provide a gas turbine stator blade structure and a compressor, which are used to solve the technical problem of changing the stator blade form without replacing the rotor and the compressor cylinder.

[0010] In order to achieve the above-mentioned purpose, according to one aspect of the present invention, a gas turbine stator blade structure is provided, comprising a plurality of stator blades, a hub, a plurality of matching structures arranged on the hub, and a compensation assembly, wherein the stator blade comprises a first blade of a first blade type and a second blade of a second stator blade type, the matching structure is arranged corresponding to the first blade or the second blade, the bottom of the first blade or the bottom of the second blade is positioned at a preset stator blade position of the hub, and the compensation assembly is arranged in a space defined by the second blade and the matching structure to compensate for the airflow loss between the second blade and the matching structure.

[0011] Furthermore, the matching structure includes a first mounting groove and a second mounting groove opened on the hub, the first mounting groove is used to install the bottom of the first blade, or is set corresponding to the second blade to position the bottom of the first blade or the second blade to the preset position of the stationary blade, and the second mounting groove is used to install the compensation component to compensate for the airflow loss between the first mounting groove and the second blade.

[0012] Furthermore, the first mounting groove is connected to the second mounting groove, and the second mounting groove is located below the first mounting groove and on a side away from the bottom of the stationary blade.

[0013] Furthermore, the compensation assembly includes a plurality of first flow channel compensation blocks, which are connected in series along the circumference of the second installation groove to form a first flow channel compensation block group.

[0014] Furthermore, the compensation assembly includes a second flow channel compensation block, which is connected in series with the first flow channel compensation block group and fixedly connected to the wheel hub to limit the circumferential movement of the first flow channel compensation block group along the second mounting groove.

[0015] Furthermore, the second mounting groove is a dovetail groove or an inverted T-shaped groove.

[0016] Furthermore, it also includes a third installation groove, which is connected to the second installation groove and is distributed in the same circumference, and the first flow channel compensation block enters the second installation groove through the third installation groove.

[0017] Furthermore, the first flow channel compensation block includes a root portion, which enters the second installation groove through the third installation groove. The root portion is matched with the second installation groove to limit the axial movement of the first flow channel compensation block along the wheel hub.

[0018] Furthermore, the circumferential width of the third mounting groove is greater than the circumferential width of the root.

[0019] Furthermore, the first flow channel compensation block includes a blocking portion, which is at least partially disposed in the first mounting groove, and reduces airflow loss between the tip of the second blade and the hub by filling the space of the first mounting groove.

[0020] Furthermore, the blocking portion has a first flow channel surface, and the first flow channel surface is coplanar with the circumferential outer edge of the hub.

[0021] Furthermore, the thickness of the blocking portion is adjustable, and the airflow distribution between the tip of the second blade and the hub can be changed by changing the thickness of the blocking portion.

[0022] Furthermore, a connecting portion is provided between the root portion and the blocking portion, and the connecting portion is at least partially located in the first mounting groove. The root portion, the blocking portion and the connecting portion are an integrated structure.

[0023] Furthermore, the second flow channel compensation block is at least partially located in the first installation groove, and the second flow channel compensation block includes a second flow channel surface located on the top thereof, and the second flow channel surface is coplanar with the first flow channel surface, forming a complete flow channel surface surrounding the matching structure.

[0024] Furthermore, the second flow channel compensation block includes a bottom plate, the bottom plate is provided with a first mounting hole, and the second flow channel compensation block is fixedly connected to the bottom of the first mounting groove through the first mounting hole.

[0025] Furthermore, a second mounting hole is provided at the bottom of the first mounting groove. The second mounting hole and the first mounting hole are coaxial and have the same diameter. The second flow channel compensation block and the first mounting groove are fixedly connected through the first mounting hole and the second mounting hole.

[0026] Furthermore, the second flow channel compensation block includes a third mounting hole located at the top thereof, and the diameter of the third mounting hole is larger than the diameters of the second mounting hole and the first mounting hole.

[0027] Furthermore, the first blade includes a blade crown, which is close to the blade tip of the first blade. The blade crown is sleeved in the first mounting groove to fix one end of the first blade.

[0028] Furthermore, a stationary blade inner ring is provided between the blade crown and the first mounting groove, and the stationary blade inner ring reduces the flow channel gap between the blade crown and the first mounting groove, thereby reducing the vibration of the first blade.

[0029] Furthermore, the hub is provided with multiple stages of moving blades, and the matching structure surrounds the hub and is arranged between the moving blades of adjacent stages.

[0030] Furthermore, the moving blades are installed along the axial direction of the hub, and the first flow channel compensation block is locked and connected to the moving blades of the adjacent stage to limit the axial movement of the moving blades along the hub.

[0031] Furthermore, a groove is provided on at least one side of the blocking portion of the first flow channel compensation block close to the moving blade, and a protrusion is provided at the root of the moving blade, and the protrusion is cooperatively connected with the groove.

[0032] The stator blade structure proposed by the technical solution of the present invention achieves at least the following beneficial effects:

[0033] 1. The gas turbine stator blade structure is adapted to both cantilevered and shrouded stator blades by providing a matching structure and a compensating assembly. This allows the stator blade type to be changed without replacing the hub or compressor cylinder.

[0034] 2. The gas turbine stator blade structure securely connects the second flow channel compensation block to the hub, thereby limiting the circumferential movement of the first flow channel compensation block group along the second mounting groove and forming a complete flow channel surface surrounding the mating structure, thereby maximally compensating for the airflow loss between the second blade and the mating structure.

[0035] 3. The first flow channel compensation block used in the gas turbine stator blade structure is an integrated structure, which is convenient for batch processing and manufacturing. It can be widely used in gas turbines to compensate for the airflow loss between the second blade and the matching structure;

[0036] 4. The thickness of the blocking portion of the first flow channel compensation block of the gas turbine stator blade structure is adjustable, so that the airflow distribution between the second blade tip and the hub can be changed by changing the thickness of the blocking portion;

[0037] 5. The first flow channel compensation block is locked to the moving blade to limit the axial movement of the moving blade along the hub

[0038] To achieve the above object, according to another aspect of the present invention, a compressor is provided, comprising a stationary blade structure and a cylinder, wherein the cylinder is connected to one end of a first blade or a second blade.

[0039] The compressor proposed by the technical solution of the present invention achieves at least the following beneficial effects:

[0040] 1. Through optimized design, the compressor can be adapted to both cantilevered and shrouded stator blades. Different stator blade types can be selected without changing the hub and compressor cylinder, meeting different aerodynamic performance and structural integrity requirements.

[0041] 2. In order to meet the requirements for comparative test and verification of the aerodynamic performance of cantilever stator blades and shrouded stator blades, the stator blade type can be changed without replacing the hub and compressor cylinder. The comparative test can be carried out using the same set of test pieces, which can greatly save test costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The accompanying drawings, which constitute part of the present invention, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0043] Figure 1 A schematic diagram of patent CN114080508A of the prior art is shown;

[0044] Figure 2 A front view of a gas turbine stator blade structure according to an embodiment of the present invention is shown;

[0045] Figure 3 A schematic diagram of the coordination structure of an embodiment of the present invention is shown;

[0046] Figure 4 An exploded view of the installation of a compensation assembly according to an embodiment of the present invention is shown;

[0047] Figure 5 A schematic diagram of a first flow channel compensation block according to an embodiment of the present invention is shown;

[0048] Figure 6 A schematic diagram of installing the second flow channel compensation block according to an embodiment of the present invention is shown;

[0049] Figure 7 A schematic diagram of a buckle structure according to an embodiment of the present invention is shown;

[0050] Figure 8 A schematic diagram of a compressor in which all stator blades are shrouded stator blades is shown according to an embodiment of the present invention;

[0051] Figure 9 A schematic diagram of a compressor in which all stator blades are cantilevered stator blades is shown according to an embodiment of the present invention.

[0052] The above drawings include the following reference numerals:

[0053] 20. Cylinder; 100. Hub; 110. Matching structure; 112. First mounting groove; 114. Second mounting groove; 116. Third mounting groove; 140. Moving blade; 142. Bump; 200. Compensation assembly; 220. First flow channel compensation block; 222. Blocking portion; 223. Connecting portion; 224. Root; 226. Groove; 240. Second flow channel compensation block; 242. Top; 244. Bottom plate; 300. Stationary blade; 310. First blade; 320. Second blade; 330. Blade crown; 340. Stationary blade inner ring; 1122. Second mounting hole; 2221. First flow channel surface; 2421. Second flow channel surface; 2422. Third mounting hole; 2441. First mounting hole DETAILED DESCRIPTION

[0054] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0055] The present invention is described in further detail below with reference to specific embodiments. These embodiments are not to be construed as limiting the scope of protection claimed by the present invention. The term "including" when used indicates the existence of a feature, but does not exclude the existence or addition of one or more other features; the terms "lateral", "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be construed as limiting the present invention; in addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be construed as indicating or implying relative importance.

[0056] In this description, it should be noted that, unless otherwise specified or limited, the terms "installed," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to direct connections, indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art will understand the specific meanings of these terms in the present invention. Furthermore, in the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0057] Example:

[0058] The prior art lacks a rotor and compressor that can accommodate both shrouded and cantilevered stator blades. The present invention provides a mating structure and compensating components on the gas turbine hub, making it compatible with both cantilevered and shrouded stator blades. This allows the stator blade type to be changed without replacing the rotor or compressor casing.

[0059] According to one aspect of the present invention, a gas turbine stator blade structure is proposed, such as Figure 2 As shown, it includes a plurality of stationary blades 300 , a hub 100 , a plurality of matching structures 110 provided on the hub 100 , and a compensation assembly 200 .

[0060] Specifically, the stator blades include a first blade 310 of a first blade type and a second blade 320 of a second stator blade type. The matching structure 110 is arranged corresponding to the first blade 310 or the second blade 320. The bottom of the first blade 310 or the bottom of the second blade 320 is positioned at the preset stator blade position of the hub 100. The compensation component 200 is arranged in the space defined by the second blade 320 and the matching structure 110 to compensate for the airflow loss between the second blade 320 and the matching structure 110.

[0061] like Figure 2 、 Figure 3 As shown, the mating structure 110 includes a first mounting slot 112 and a second mounting slot 114 defined on the hub 100. The first mounting slot 112 is used to mount the bottom of the first blade 310, or is provided correspondingly to the second blade 320, positioning the bottom of the first blade 310 or the second blade 320 at a predetermined position on the stator blade. The first mounting slot 112 and the second mounting slot 114 are connected, with the second mounting slot 114 located below the first mounting slot 112 and away from the stator blade bottom. The second mounting slot 114 is used to mount the compensation assembly 200 to compensate for airflow loss between the first mounting slot 112 and the second blade 320.

[0062] Furthermore, the mating structure 110 includes a third mounting groove 116, which communicates with the second mounting groove 114 and is distributed along the same circumference. Preferably, the second mounting groove 114 can be shaped as a dovetail groove or an inverted T-shaped groove. The second mounting groove is provided to secure the compensating assembly and prevent it from detaching radially from the hub, while the third mounting groove is provided to facilitate installation of the compensating assembly.

[0063] like Figure 4As shown, the compensation assembly 200 includes a plurality of first flow channel compensation blocks 220 and second flow channel compensation blocks 240. The first flow channel compensation blocks 220 are connected in series along the circumference of the second mounting slot 114 to form a first flow channel compensation block group, and each first flow channel compensation block 220 enters the second mounting slot 114 through the third mounting slot 116. The second flow channel compensation blocks 240 are connected in series with the first flow channel compensation block group and are fixedly connected to the hub 100 to limit the circumferential movement of the first flow channel compensation block group along the second mounting slot 114. In this way, the first flow channel compensation block group is fixed to the hub to compensate for airflow losses between the second blade 320 and the mating structure 110.

[0064] like Figure 5 As shown, the first flow channel compensation block 220 includes a root portion 224 and a blocking portion 222, and a connecting portion 223 is provided between the root portion 224 and the blocking portion 222. Figure 3 As shown, the circumferential width of the third mounting groove 116 is greater than the circumferential width of the root 224, so that the root 224 enters the second mounting groove 114 through the third mounting groove 116, and is connected with the second mounting groove 114 through the root 224 to limit the axial movement of the first flow channel compensation block 220 along the wheel hub 100.

[0065] Specifically, the blocking portion 222 is at least partially disposed within the first mounting groove 112, filling the space within the first mounting groove 112 to reduce airflow loss between the tip of the second blade 320 and the hub 100. The blocking portion 222 has a first flow path surface 2221 that is coplanar with the circumferential outer edge of the hub 100. The thickness of the blocking portion 222 is adjustable, and the airflow distribution between the tip of the second blade 320 and the hub 100 can be varied by changing the thickness of the blocking portion 222.

[0066] Furthermore, the connecting portion 223 is at least partially located within the first mounting groove 112. The root portion 224, the sealing portion 222, and the connecting portion 223 form an integral structure, meaning that the first flow channel compensation block 220 is a one-piece structure. Preferably, the first flow channel compensation block 220 is symmetrical with respect to the second mounting groove 114. This one-piece structure facilitates mass production and can be widely used in gas turbines to compensate for airflow losses between the second blade 320 and the mating structure 110.

[0067] like Figure 6 As shown, the second flow channel compensation block 240 is at least partially located within the first mounting groove 112. The second flow channel compensation block 240 includes a second flow channel surface 2421 located at its top 242. The second flow channel surface 2421 is coplanar with the first flow channel surface 2221, forming a complete flow channel surface surrounding the mating structure 110. The complete flow channel surface can maximize compensation for airflow losses between the second blade 320 and the mating structure 110.

[0068] In addition, reference Figure 4 As shown, the second flow channel compensation block 240 includes a bottom plate 244 , and a first mounting hole 2441 is defined on the bottom plate 244 . The second flow channel compensation block 240 is fixedly connected to the bottom of the first mounting groove 112 through the first mounting hole 2441 .

[0069] Specifically, a second mounting hole 1122 is provided at the bottom of the first mounting slot 112. The second mounting hole 1122 and the first mounting hole 2441 are coaxial and have the same diameter. The first mounting hole 2441 and the second mounting hole 1122 securely connect the second flow channel compensation block 240 to the first mounting slot 112. The second flow channel compensation block 240 also includes a third mounting hole 2422 located at its top 242. The diameter of the third mounting hole 2422 is larger than the diameters of the second mounting hole 1122 and the first mounting hole 2441 to facilitate the insertion of the nut of the bolt. Preferably, the second flow channel compensation block 240 is a symmetrical structure relative to the second mounting slot 114, and the first mounting hole 2441, the second mounting hole 1122, and the third mounting hole 2422 are each two symmetrical holes relative to the second mounting slot 114, with the second mounting hole 1122 being a bolt hole.

[0070] When installing the compensation assembly 200 , first, multiple first flow channel compensation blocks are sequentially inserted into the second installation groove 114 , and then the second flow channel compensation block 240 is inserted into the fixing area of ​​the second installation groove 114 and fixed.

[0071] Preferably, refer to Figure 4 As shown, when the second flow channel compensation block 240 is actually installed, it can be fixed with bolts. The bolt is passed through the third mounting hole 2422 as a whole, and the stud of the bolt is passed through the first mounting hole 2441 and inserted into the second mounting hole 1122 at the bottom of the first mounting slot 112. Further preferably, two bolts are used, which are respectively inserted into three pairs of mounting holes symmetrical with respect to the second mounting slot 114. Tightening both bolts can achieve a fixed connection between the second flow channel compensation block 240 and the bottom of the first mounting slot 112. The effect after the installation is completed can be seen. Figure 6 The second flow channel compensation block is fixedly connected to the wheel hub, thereby limiting the circumferential movement of the first flow channel compensation block group along the second installation groove 114.

[0072] like Figure 2As shown, the first blade 310 includes a shroud 330, which is located near the tip of the first blade 310 and is sleeved within the first mounting slot 112 to secure one end of the first blade 310. A stationary blade inner ring 340 is disposed between the shroud 330 and the first mounting slot 112. The stationary blade inner ring 340 is used to reduce the flow path gap between the shroud 330 and the first mounting slot 112, thereby reducing vibration of the first blade 310.

[0073] Furthermore, the hub 100 is provided with multiple stages of rotor blades 140. The mating structure 110 surrounds the hub 100 and is positioned between adjacent stages of rotor blades 140. The rotor blades 140 are mounted axially of the hub 100, and the first flow channel compensation block 220 is locked to the adjacent stages of rotor blades 140 to restrict axial movement of the rotor blades 140 along the hub 100.

[0074] Preferably, if Figure 7 As shown, the sealing portion 222 of the first flow channel compensation block 220 is provided with a groove 226 on at least one side close to the moving blade 140, and the root of the moving blade 140 is provided with a protrusion 142, which is matched with the groove 226 to form a snap-fit ​​structure to limit the axial movement of the moving blade 140 along the hub 100.

[0075] Specifically, the buckle structure includes but is not limited to the following three methods. The first method is that at one end of the first flow channel compensation block 220, a groove 226 is provided on the side of the blocking portion 222 away from the first flow channel surface 2221, which cooperates with the outward protrusion 142 of the blade root of the corresponding adjacent moving blade 140. Figure 7 the second way is to provide a groove 226 in the first flow channel compensation block 220 at one end of the first flow channel surface 2221, and the corresponding adjacent blade 140 blade root inward projection 142 cooperates, see Figure 7 The above two structural forms can realize the axial displacement of the adjacent blades of the first level by the first compensation component. The third method is to provide grooves 226 at both ends of the first flow channel compensation block 220, which cooperate with the protrusions 142 of the blade roots of the front and rear adjacent blades 140, see Figure 7 The middle matching form, this structural form can realize the one-stage compensation component to simultaneously limit the axial displacement of the front and rear stages of the moving blades.

[0076] It should be noted that the stator blade type of the first blade 310 is a shrouded stator blade, and the stator blade type of the second blade 320 is a cantilever stator blade.

[0077] The stator blade structure proposed in this application can be applied to different stator blade types. When installing a cantilever stator blade, a flow channel compensation component can be inserted into the second mounting groove to compensate for the airflow loss between the cantilever stator blade and the hub; when installing a shrouded stator blade, the blade shroud and the stator blade inner ring can be installed into the first mounting groove.

[0078] In summary, from the above description, it can be seen that the stator blade structure proposed in the above embodiments of the present invention achieves the following technical effects:

[0079] 1. The gas turbine stator blade structure is adapted to both cantilevered and shrouded stator blades by providing a matching structure and a compensating assembly. This allows the stator blade type to be changed without replacing the hub or compressor cylinder.

[0080] 2. The gas turbine stator blade structure securely connects the second flow channel compensation block to the hub, thereby limiting the circumferential movement of the first flow channel compensation block group along the second mounting groove and forming a complete flow channel surface surrounding the mating structure, thereby maximally compensating for the airflow loss between the second blade and the mating structure.

[0081] 3. The first flow channel compensation block used in the gas turbine stator blade structure is an integrated structure, which is convenient for batch processing and manufacturing. It can be widely used in gas turbines to compensate for the airflow loss between the second blade and the matching structure;

[0082] 4. The thickness of the blocking portion of the first flow channel compensation block of the gas turbine stationary blade structure is adjustable, so that the airflow distribution between the second blade tip and the hub can be changed by changing the thickness of the blocking portion.

[0083] 5. The first flow channel compensation block is locked to the moving blade to limit the axial movement of the moving blade along the hub.

[0084] According to another aspect of the present invention, a compressor is provided. Figure 2 As shown, it includes the above-mentioned stator blade structure and the cylinder 20, and the cylinder 20 is connected to one end of the first blade 310 or the second blade 320. This compressor can be used with both cantilever stator blades and shrouded stator blades, so that the stator blade type can be changed without replacing the hub and the compressor cylinder. Figure 8 As shown, all the compressor stators are shrouded stators, or as shown in Figure 9 As shown, all the compressor stator blades are cantilevered stator blades. Alternatively, the compressor may have shrouded stator blades in the front stage and cantilevered stator blades in the rear stage.

[0085] In summary, from the above description, it can be seen that the compressor proposed in the above embodiments of the present invention achieves the following technical effects:

[0086] 1. Through optimized design, the compressor can be adapted to both cantilevered and shrouded stator blades. Different stator blade types can be selected without changing the hub and compressor cylinder, meeting different aerodynamic performance and structural integrity requirements.

[0087] 2. In order to meet the requirements for comparative test and verification of the aerodynamic performance of cantilever stator blades and shrouded stator blades, the stator blade type can be changed without replacing the hub and compressor cylinder. The comparative test can be carried out using the same set of test pieces, which can greatly save the test cost.

[0088] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A gas turbine stator blade structure, characterized in that: The invention comprises a plurality of stationary blades (300), a hub (100), a plurality of matching structures (110) arranged on the hub (100), and a compensation assembly (200). The stationary blade (300) includes a first blade (310) of a first blade type and a second blade (320) of a second stationary blade type, The matching structure (110) is arranged corresponding to the first blade (310) or the second blade (320), and the bottom of the first blade (310) or the bottom of the second blade (320) is positioned at a preset position of a stationary blade of the hub (100). The compensation component (200) is arranged in a space defined by the second blade (320) and the matching structure (110) to compensate for airflow loss between the second blade (320) and the matching structure (110); The matching structure (110) includes a first mounting groove (112) and a second mounting groove (114) provided on the hub (100), wherein the first mounting groove (112) is used to mount the bottom of the first blade (310), or is provided corresponding to the second blade (320), so as to position the bottom of the first blade (310) or the second blade (320) at a preset position of the stationary blade, and the second mounting groove (114) is used to mount the compensation assembly (200) so as to compensate for airflow loss between the first mounting groove (112) and the second blade (320); The compensation assembly (200) comprises a plurality of first flow channel compensation blocks (220), wherein the first flow channel compensation blocks (220) are connected in series along the circumference of the second installation groove (114) to form a first flow channel compensation block group; The compensation assembly (200) includes a second flow channel compensation block (240), the second flow channel compensation block (240) is connected in series with the first flow channel compensation block group, and the second flow channel compensation block (240) is fixedly connected to the wheel hub (100) to limit the circumferential movement of the first flow channel compensation block group along the second mounting groove (114).

2. The stationary blade structure according to claim 1, characterized in that: The first mounting groove (112) and the second mounting groove (114) are in communication, and the second mounting groove (114) is located below the first mounting groove (112) and on a side away from the bottom of the stationary blade.

3. The stationary blade structure according to claim 1, characterized in that: The second mounting groove (114) is a dovetail groove or an inverted T-shaped groove.

4. The stationary blade structure according to claim 3, characterized in that: The invention also includes a third mounting groove (116), wherein the third mounting groove (116) is communicated with the second mounting groove (114) and is distributed in the same circumference, and the first flow channel compensation block (220) enters the second mounting groove (114) through the third mounting groove (116).

5. The stationary blade structure according to claim 4, characterized in that: The first flow channel compensation block (220) includes a root portion (224), and the root portion (224) enters the second mounting groove (114) through the third mounting groove (116). The root portion (224) is connected to the second mounting groove (114) through the matching connection, thereby limiting the axial movement of the first flow channel compensation block (220) along the wheel hub (100).

6. The stationary blade structure according to claim 5, characterized in that: The circumferential width of the third mounting groove (116) is greater than the circumferential width of the root portion (224).

7. The stationary blade structure according to claim 5, characterized in that: The first flow channel compensation block (220) includes a blocking portion (222), wherein the blocking portion (222) is at least partially disposed in the first mounting groove (112), and reduces airflow loss between the tip of the second blade (320) and the hub (100) by filling the space of the first mounting groove (112).

8. The stationary blade structure according to claim 7, characterized in that: The blocking portion (222) has a first flow channel surface (2221), and the first flow channel surface (2221) is coplanar with the circumferential outer edge of the hub (100).

9. The stationary blade structure according to claim 7 or 8, characterized in that: The thickness of the blocking portion (222) is adjustable, and the airflow distribution between the tip of the second blade (320) and the hub (100) is changed by changing the thickness of the blocking portion (222).

10. The stationary blade structure according to claim 7 or 8, characterized in that: A connecting portion (223) is provided between the root portion (224) and the blocking portion (222); the connecting portion (223) is at least partially located in the first mounting groove (112); and the root portion (224), the blocking portion (222) and the connecting portion (223) form an integral structure.

11. The stationary blade structure according to claim 8, characterized in that: The second flow channel compensation block (240) is at least partially located in the first mounting groove (112), and the second flow channel compensation block (240) includes a second flow channel surface (2421) located at the top (242) thereof, and the second flow channel surface (2421) is coplanar with the first flow channel surface (2221), forming a complete flow channel surface surrounding the matching structure (110).

12. The stationary blade structure according to claim 11, characterized in that: The second flow channel compensation block (240) comprises a base plate (244), the base plate (244) being provided with a first mounting hole (2441), and the second flow channel compensation block (240) is fixedly connected to the bottom of the first mounting groove (112) via the first mounting hole (2441).

13. The stationary blade structure according to claim 12, characterized in that: A second mounting hole (1122) is provided at the bottom of the first mounting groove (112), the second mounting hole (1122) and the first mounting hole (2441) being coaxial and having the same diameter, and the second flow channel compensation block (240) and the first mounting groove (112) are fixedly connected via the first mounting hole (2441) and the second mounting hole (1122).

14. The stationary blade structure according to claim 13, characterized in that: The second flow channel compensation block (240) comprises a third mounting hole (2422) located at a top portion (242) thereof, wherein the diameter of the third mounting hole (2422) is larger than the diameters of the second mounting hole (1122) and the first mounting hole (2441).

15. The stationary blade structure according to claim 1, characterized in that: The first blade (310) includes a blade crown (330), the blade crown (330) is close to the blade tip of the first blade (310), and the blade crown (330) is sleeved in the first mounting groove (112) to achieve fixation of one end of the first blade (310).

16. The stationary blade structure according to claim 15, characterized in that: A stationary blade inner ring (340) is provided between the blade crown (330) and the first mounting groove (112), and the stationary blade inner ring (340) reduces the flow channel gap between the blade crown (330) and the first mounting groove (112), thereby reducing vibration of the first blade (310).

17. The stationary blade structure according to claim 7, characterized in that: The hub (100) is provided with multiple stages of moving blades (140), and the matching structure (110) surrounds the hub (100) and is arranged between the moving blades (140) of adjacent stages.

18. The stationary blade structure according to claim 17, characterized in that: The moving blades (140) are installed along the axial direction of the hub (100), and the first flow channel compensation block (220) is locked and connected to the moving blades (140) of the adjacent stage to limit the axial movement of the moving blades (140) along the hub (100).

19. The stationary blade structure according to claim 18, characterized in that: A groove (226) is provided on at least one side of the sealing portion (222) of the first flow channel compensation block (220) close to the moving blade (140), and a protrusion (142) is provided at the root of the moving blade (140), and the protrusion (142) is cooperatively connected with the groove (226).

20. A compressor, comprising the stationary blade structure according to any one of claims 1 to 19 and a cylinder (20), wherein the cylinder (20) is connected to one end of the first blade (310) or the second blade (320).

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