Gas turbine compressor stationary blade ring with crown stationary blades

Abstract

The gas turbine compressor stationary blade ring comprises a plurality of arc sections, each arc section comprises an outer ring section and a plurality of crown stationary blades, each crown stationary blade comprises a blade body, the root end of each blade body is integrally connected with a blade root, the top end of each blade body is integrally connected with a blade crown, and each blade root is detachably connected with the corresponding outer ring section. Each blade crown comprises a first cutting face and a second cutting face, the first cutting face of each crown stationary blade is tightly attached to the second cutting face of the adjacent crown stationary blade, the blade crowns of every two adjacent crown stationary blades are connected in a welded mode, and the blade crowns of the crown stationary blades in each arc section are combined to form an inner ring section of the arc section. The outer ring section in each arc section is used for being fixedly connected with a holding ring of the gas compressor, and the joints of the inner ring sections in every two adjacent arc sections are connected in a sealed mode. In a vibration environment, the top end of the blade body of the crown stationary blade in the stationary blade ring cannot be abraded, the safety and the reliability of operation of a gas turbine unit can be improved, and the service and maintenance cost can be greatly reduced.

Description

Technical Field

[0001] The utility model belongs to the technical field of gas turbine compressors, and in particular relates to a gas turbine compressor stator ring with shrouded stator blades. Background Art

[0002] In the design of the traditional F-class gas turbine unit, the compressor stator ring is an assembled structure, wherein the compressor stator ring includes a stator 1, an outer ring 2 and an inner ring 3, as shown in FIG. Figure 1 The stationary blade 1 includes a stationary blade body 101, the root end of the stationary blade body 101 is integrally connected to a stationary blade root 102 and the top end is integrally connected to a stationary blade top pin 103. Figure 2 The stator blade root 102 is detachably connected to the outer ring 2, and the stator blade top pin 103 is detachably connected to the inner ring 3. During the overhaul and even medium repair of the F-class gas turbine unit, it was found that the stator blade top pin 103 in the multi-stage compressor stator blade ring was severely worn, which caused certain hidden dangers to the safe operation of the unit. The main reason for the wear of the stator blade top pin 103 is that in the compressor stator blade ring structure design, the stator blade top pin 103 and the inner ring 3 are locked together by punching and riveting. Figure 3-Figure 5 ,in Figure 4 E represents the suction surface, F represents the pressure surface, where Figure 5 The G in the middle represents a punching and riveting connection. After punching and riveting, the contact between the inner ring 3 and the stator blade top pin 103 is sometimes only line contact or even point contact. Vibration is inevitable during the operation of the unit. For punching and riveting connections with inadequate processing quality, looseness may occur under repeated vibration impacts, resulting in continuous micro-motion wear between the inner ring 3 and the stator blade top pin 103 during the operation of the unit. After the unit has been running for a period of time, the stator blade top pin 103 will be severely worn. Therefore, the wear problem of the stator blade top pin 103 needs to be fundamentally solved. Utility Model Content

[0003] In view of the defects of the above-mentioned prior art, the utility model provides a gas turbine compressor stator ring with crowned stator blades. In a vibration environment, the top end of the blade body of the crowned stator blades in the gas turbine compressor stator ring will not have wear problems, which can improve the safety and reliability of the operation of the gas turbine unit and greatly reduce service and maintenance costs.

[0004] The technical solution adopted by the utility model to solve its technical problems is:

[0005] A gas turbine compressor stator ring with shrouded stator blades comprises a plurality of arc segments formed by segmented cutting, each of the arc segments comprising an outer ring segment and a plurality of shrouded stator blades, the shrouded stator blade comprising a blade body, a blade root being integrally connected to the root end of the blade body and a blade shroud being integrally connected to the top end, the blade root being detachably connected to the corresponding outer ring segment, the blade shroud comprising a first cutting surface and a second cutting surface being relatively arranged, the first cutting surface of the blade shroud in each of the shrouded stator blades being tightly fitted to the second cutting surface of the blade shroud in an adjacent shrouded stator blade, the blade shrouds of two adjacent shrouded stator blades being welded and connected, the blade shrouds of each shrouded stator blade in each of the arc segments are combined to form an inner ring segment of the corresponding arc segment, the outer ring segment in each of the arc segments being used for fixed connection to a holding ring of the compressor, and the inner ring segments in two adjacent arc segments being sealed and connected at the joints.

[0006] Furthermore, the blade crown also includes an inner circumferential surface segment and an outer circumferential surface segment, and the inner circumferential surface segment and the outer circumferential surface segment are both between the first cutting surface and the second cutting surface. The top end of the blade body of each of the crowned stationary blades is connected to the outer circumferential surface segment of the corresponding blade crown. A welding groove is opened on the inner circumferential surface segment of the blade crown of each of the crowned stationary blades in each of the arc segments, and the welding grooves of the blade crowns of each of the crowned stationary blades in the arc segment are spliced ​​into an arc shape. The welding grooves of the blade crowns of each of the crowned stationary blades of the gas turbine compressor stationary blade ring are spliced ​​into a circular ring shape. Welding material is arranged in each welding groove of each of the arc segments, so that the blade crowns of two adjacent crowned stationary blades are welded and connected.

[0007] Furthermore, the seams between the inner ring segments of two adjacent arc segments are sealed and connected by a sealing key.

[0008] Furthermore, a sealing key groove is provided on the first cutting surface and the second cutting surface at the outer edge of the inner ring segment in each of the arc segments, one end of the sealing key is arranged in the corresponding sealing key groove on the inner ring segment in the corresponding arc segment, and the other end is arranged in the corresponding sealing key groove on the inner ring segment in the adjacent arc segment.

[0009] Furthermore, the material of the welding material is the same as that of the shrouded stationary blade.

[0010] Furthermore, some of the arc segments include a plurality of adjustment vanes, and the size of the blade crown at the top end of the blade body of the adjustment vane is different from that of the blade crown of the shrouded vane. The corresponding adjustment vane in the arc segment is arranged at a position between two adjacent shrouded vanes whose blade crown assembly gap needs to be adjusted. The blade root at the root end of the blade body of the adjustment vane is detachably connected to the outer ring segment, the first cutting surface of the blade crown in the adjustment vane is tightly fitted with the second cutting surface of the blade crown in the adjacent shrouded vane, the second cutting surface of the blade crown in the adjustment vane is tightly fitted with the first cutting surface of the blade crown in the adjacent shrouded vane, and the blade crown of the adjustment vane is welded to the blade crown of the adjacent shrouded vane.

[0011] Furthermore, the assembly gap between the blade crown of the adjustment stator blade and the blade crown of the adjacent shrouded stator blade in the corresponding arc segment is less than 0.05 mm, and the assembly gap between the blade crowns of two adjacent shrouded stator blades without adjustment stator blades in the corresponding arc segment is less than 0.05 mm.

[0012] Furthermore, the outer ring segment in each of the arc segments is fixedly connected to the holding ring of the compressor through a positioning pin, the joint between the outer ring segments in two adjacent arc segments forms a first thermal expansion gap, and the joint between the inner ring segments in two adjacent arc segments forms a second thermal expansion gap.

[0013] Furthermore, the first thermal expansion gap and the second thermal expansion gap are both controlled within a range of 4-4.5 mm.

[0014] Furthermore, a plurality of blade root grooves are provided on the inner circumferential surface of the outer ring segment in each of the arc segments, the number of which is equal to the number of blade roots of the shrouded stationary blades in the corresponding arc segment, and the blade roots are inserted in the corresponding blade root grooves.

[0015] Compared with the prior art, the beneficial effects of the utility model are:

[0016] The utility model provides a gas turbine compressor stator ring with crowned stator blades, comprising a plurality of arc segments formed by segmented cutting, each arc segment comprising an outer ring segment and a plurality of crowned stator blades, the crowned stator blade comprising a blade body, a root end portion of the blade body being integrally connected with a blade root and a top end portion being integrally connected with a blade crown, the blade root being detachably connected to the corresponding outer ring segment, the blade crown comprising a first cutting surface and a second cutting surface arranged oppositely, the first cutting surface of the blade crown in each crowned stator blade being tightly fitted with the second cutting surface of the blade crown in an adjacent crowned stator blade, the blade crowns of two adjacent crowned stator blades being welded and connected, the blade crowns of the crowned stator blades in each arc segment are combined to form an inner ring segment of the corresponding arc segment, the outer ring segment in each arc segment is used for fixed connection with a holding ring of the compressor, and the inner ring segments in two adjacent arc segments are sealed and connected at the joints. The top end of the blade body of the crowned stator blade in the gas turbine compressor stator blade ring is integrally connected with the blade crown, and the blade crowns of each crowned stator blade in each arc segment are combined to form an inner ring segment of the corresponding arc segment in the stator blade ring. Compared with the traditional stator blade ring with inner ring in the background technology, under the same vibration environment, the top end of the blade body of the crowned stator blade in the gas turbine compressor stator blade ring is firmly connected with the blade crown, and the top end of the blade body of the crowned stator blade in the gas turbine compressor stator blade ring will not have wear problems. Therefore, the utility model can fundamentally solve the problem of stator blade top pin wear in the gas turbine compressor stator blade ring in the background technology, can improve the safety and reliability of gas turbine unit operation, and can greatly reduce service and maintenance costs.

[0017] In the utility model, the blade crown also includes an inner circumferential surface segment and an outer circumferential surface segment, both of which are between the first cutting surface and the second cutting surface, the top end of the blade body of each shrouded stationary blade is connected to the outer circumferential surface segment of the corresponding blade crown, a welding groove is provided on the inner circumferential surface segment of the blade crown of each shrouded stationary blade, the welding grooves of the blade crowns of each shrouded stationary blade in each arc segment are spliced ​​into an arc shape, the welding grooves of the blade crowns of each shrouded stationary blade in the stationary blade ring are spliced ​​into a circular ring shape, and welding materials are provided in each welding groove of each arc segment, so that the blade crowns of two adjacent shrouded stationary blades are welded and connected. In this way, by providing the welding groove on the inner circumferential surface segment of the blade crown of the shrouded stationary blade, the blade crowns of two adjacent shrouded stationary blades are welded and connected when the first cutting surface of the blade crown of each shrouded stationary blade in each arc segment is closely fitted with the second cutting surface of the blade crown of the adjacent shrouded stationary blade.

[0018] In the utility model, the inner ring segment seams of two adjacent arc segments are sealed and connected by a sealing key, so that air leakage between the two adjacent arc segments can be prevented by the arrangement of the sealing key.

[0019] In the utility model, some arc segments include a plurality of adjustment vanes, the size of the blade crown at the top end of the blade body of the adjustment vane is different from the blade crown size of the shrouded vane, the adjustment vane in the corresponding arc segment is arranged at a position between two adjacent shrouded vanes whose assembly gap of the blade crown needs to be adjusted, the blade root at the root end of the blade body of the adjustment vane is detachably connected to the outer ring segment, the first cutting surface of the blade crown in the adjustment vane is closely fitted with the second cutting surface of the blade crown in the adjacent shrouded vane, the second cutting surface of the blade crown in the adjustment vane is closely fitted with the first cutting surface of the blade crown in the adjacent shrouded vane, and the blade crown of the adjustment vane is welded to the blade crown of the adjacent shrouded vane. In this way, by setting the adjustment vane, the processing error of the shrouded vane in the vane ring of the gas turbine compressor can be compensated, and the assembly gap between the blade crown of the adjustment vane and the blade crown of the adjacent shrouded vane before welding can be ensured to meet the requirements, and the assembly gap between the blade crowns of two adjacent shrouded vanes without the adjustment vane before welding can be ensured to meet the requirements.

[0020] In the utility model, the outer ring segment in each arc segment is used for fixed connection with the holding ring of the compressor through the positioning pin, the joint between the outer ring segments in two adjacent arc segments forms a first thermal expansion gap, and the joint between the inner ring segments in two adjacent arc segments forms a second thermal expansion gap. In this way, the positioning pin in each arc segment serves as the absolute dead point of thermal expansion of the outer ring segment in the corresponding arc segment, the first thermal expansion gap facilitates the outer ring segment in the corresponding arc segment to fully expand thermally, and the second thermal expansion gap facilitates the inner ring segment in the corresponding arc segment to fully expand thermally. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the assembly of a conventional gas turbine compressor stator ring in the background technology;

[0022] Figure 2 for Figure 1 A schematic diagram of the structure of one of the stationary blades;

[0023] Figure 3 for Figure 1 AA direction cross-sectional structure schematic diagram;

[0024] Figure 4 for Figure 3 BB direction cross-sectional structure schematic diagram;

[0025] Figure 5 for Figure 4 Schematic diagram of the cross-sectional structure in the CC direction;

[0026] Figure 6 It is a schematic diagram of the assembly of a gas turbine compressor stator ring with shrouded stator blades in the utility model;

[0027] Figure 7 It is a schematic diagram of the three-dimensional structure of one of the stationary blades with a crown in the utility model;

[0028] Figure 8 for Figure 6 DD direction cross-sectional structure schematic diagram;

[0029] Fig. 9 It is a schematic diagram of a three-dimensional structure of a welding connection between blade crowns of two adjacent stator blades with crowns in one arc segment of the utility model;

[0030] Fig.10 It is a schematic diagram of multiple arc segments formed by segmented cutting of a gas turbine compressor stator ring with shrouded stator blades in the utility model;

[0031] Fig.11 It is a schematic diagram of a partial three-dimensional structure in which the joint of the inner ring segments of two adjacent arc segments in the utility model is sealed and connected by a sealing key;

[0032] Fig.12 It is a three-dimensional structural schematic diagram of a sealing keyway on an inner ring segment in one of the arc segments of the utility model;

[0033] Fig.13 Schematic diagram of the three-dimensional structure of the sealing key.

[0034] Explanation of the reference numerals in the figure: 1. stationary blade, 101. stationary blade body, 102. stationary blade root, 103. stationary blade top pin, 2. outer ring, 3. inner ring, 4. stationary blade with crown, 401. blade body, 402. blade root, 403. blade crown, 40301. first cutting surface, 40302. second cutting surface, 404. welding groove, 5. welding material, 6. sealing key, 7. sealing keyway, 8. locating pin, 9. second thermal expansion gap, 10. arc segment, E. suction surface, F. pressure surface, G. punching and riveting connection. DETAILED DESCRIPTION

[0035] The following is a further detailed description of the specific implementations of the present invention in conjunction with the accompanying drawings. These implementations are only used to illustrate the present invention, but not to limit the present invention.

[0036] In the description of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0037] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0038] In addition, in the description of the present invention, unless otherwise specified, “plurality” means two or more.

[0039] like Figure 6-Figure 10As shown, a gas turbine compressor stator ring with shrouded stator blades includes a plurality of arc segments 10 formed by segmented cutting, each arc segment 10 includes an outer ring segment and a plurality of shrouded stator blades 4, the shrouded stator blade 4 includes a blade body 401, a root end of the blade body 401 is integrally connected to a blade root 402 and a top end is integrally connected to a blade shroud 403, the blade root 402 is detachably connected to the corresponding outer ring segment, and the blade shroud 403 includes a first cutting surface 40301 and a second cutting surface 40302 arranged opposite to each other, The first cutting surface 40301 of the blade crown 403 in each crowned stationary blade 4 is tightly fitted with the second cutting surface 40302 of the blade crown 403 in the adjacent crowned stationary blade 4, the blade crowns 403 of two adjacent crowned stationary blades 4 are welded and connected, the blade crowns 403 of each crowned stationary blade 4 in each circular arc segment 10 are combined to form an inner ring segment of the corresponding circular arc segment 10, the outer ring segment in each circular arc segment 10 is used for fixed connection with the holding ring of the compressor, and the inner ring segments of two adjacent circular arc segments 10 are sealed at the joints.

[0040] The top end of the blade body 401 of the crowned stator blade 4 in the gas turbine compressor stator blade ring is integrally connected with the blade crown 403, and the blade crowns 403 of each crowned stator blade 4 in each arc segment 10 are combined to form an inner ring segment of the corresponding arc segment 10 in the stator blade ring. Compared with the traditional stator blade ring with inner ring in the background technology, under the same vibration environment, the top end of the blade body 401 of the crowned stator blade 4 in the gas turbine compressor stator blade ring is firmly connected with the blade crown 403, and the top end of the blade body 401 of the crowned stator blade 4 in the gas turbine compressor stator blade ring will not have wear problems. Therefore, the utility model can fundamentally solve the problem of wear of the stator blade top pin 103 in the gas turbine compressor stator blade ring in the background technology, can improve the safety and reliability of the operation of the gas turbine unit, and can greatly reduce the service and maintenance costs.

[0041] In one embodiment,

[0042] The blade crown 403 also includes an inner circumference segment and an outer circumference segment, both of which are located between the first cutting surface 40301 and the second cutting surface 40302. The top end of the blade body 401 of each shrouded stationary blade 4 is connected to the outer circumference segment of the corresponding blade crown 403. A welding groove 404 is provided on the inner circumference segment of the blade crown 403 of each shrouded stationary blade 4. Figure 7 The welding grooves 404 of the blade crowns 403 of each of the shrouded stationary blades 4 of each arc segment 10 are spliced ​​into an arc shape, and the welding grooves 404 of the blade crowns 403 of each of the shrouded stationary blades 4 of the stationary blade ring are spliced ​​into a circular ring shape. The welding grooves 404 of each arc segment 10 are provided with welding materials 5, so that the blade crowns 403 of two adjacent stationary blades 4 with shrouds are welded and connected. Fig. 9 .

[0043] In this way, the welding groove 404 is opened on the inner circumferential surface segment of the blade crown 403 of the crowned stationary blade 4, so that the blade crowns 403 of two adjacent crowned stationary blades 4 can be welded and connected when the first cutting surface 40301 of the blade crown 403 of each crowned stationary blade 4 in each arc segment 10 is tightly fitted with the second cutting surface 40302 of the blade crown 403 of the adjacent crowned stationary blade 4.

[0044] Among them, the welding groove is specifically processed in the following way: the blade root 401 of each crowned stationary blade 4 after machining is installed on the inner circumference of the outer ring, and the blade crown 403 of each crowned stationary blade 4 is spliced ​​into a circular ring, and then a circle of welding groove is machined on the inner circumference of the circular ring spliced ​​by each blade crown 403, and welding material 5 is arranged in a circle of welding groove, so that the blade crowns 403 of two adjacent crowned stationary blades 4 are welded and connected.

[0045] Preferably, the material of the welding material 5 is the same as that of the shrouded stationary blade 4. This can avoid thermal expansion caused by welding of dissimilar materials.

[0046] Preferably, the cross-sectional length of the welding material 5 arranged in two adjacent welding grooves 404 is 1 / 3-1 / 2 of the length of the corresponding first cutting surface 40301 or the second cutting surface 40302 and the cross-sectional width of the welding material 5 is 3 / 10-7 / 10 of the width of the corresponding first cutting surface 40301 or the second cutting surface 40302.

[0047] In one embodiment,

[0048] The inner ring segment joints of two adjacent arc segments 10 are sealed and connected by a sealing key 6. Fig.11 In this way, the provision of the sealing key 6 can prevent air leakage between two adjacent arc segments 10 .

[0049] Preferably, a sealing key groove 7 is provided on the first cutting surface 40301 and the second cutting surface 40302 at the outer edge of the inner ring segment in each arc segment 10. Fig.12 One end of the sealing key 6 is arranged in the corresponding sealing key groove 7 on the inner ring segment of the corresponding arc segment 10, and the other end is arranged in the corresponding sealing key groove 7 on the inner ring segment of the adjacent arc segment 10. The three-dimensional structure diagram of the sealing key 6 is shown in Fig.13 .

[0050] In one embodiment,

[0051] The partial arc segment 10 includes a plurality of adjustment vanes, and the size of the blade crown at the top end of the blade body of the adjustment vane is different from the size of the blade crown 403 of the crowned vane 4. The adjustment vane in the corresponding arc segment 10 is arranged at a position between two adjacent crowned vanes 4 whose assembly gap needs to be adjusted. The blade root at the root end of the blade body of the adjustment vane is detachably connected to the outer ring segment. The first cutting surface of the blade crown in the adjustment vane is tightly fitted with the second cutting surface 40302 of the blade crown 403 in the adjacent crowned vane 4, and the second cutting surface of the blade crown in the adjustment vane is tightly fitted with the first cutting surface 40301 of the blade crown 403 in the adjacent crowned vane 4. The blade crown of the adjustment vane is welded to the blade crown 403 of the adjacent crowned vane 4.

[0052] In this way, by adjusting the setting of the stator blades, the processing error of the crowned stator blades 4 in the stator blade ring of the gas turbine compressor can be compensated, ensuring that the assembly gap between the blade crown of the adjusted stator blade and the blade crown 403 of the adjacent crowned stator blade 4 before welding meets the requirements, and ensuring that the assembly gap between the blade crowns 403 of two adjacent crowned stator blades 4 that are not set with adjustment blades before welding meets the requirements.

[0053] Preferably, the assembly gap between the blade crown of the adjustment stator blade in the corresponding arc segment 10 and the blade crown 403 of the adjacent shrouded stator blade 4 is less than 0.05 mm, and the assembly gap between the blade crowns 403 of two adjacent shrouded stator blades 4 without adjustment stator blades in the corresponding arc segment 10 is less than 0.05 mm.

[0054] This can ensure that the first cutting surface of the blade crown in the adjustment stator blade before welding is fully and tightly fitted with the second cutting surface 40302 of the blade crown 403 in the adjacent crowned stator blade 4, and can ensure that the second cutting surface of the blade crown in the adjustment stator blade before welding is fully and tightly fitted with the first cutting surface 40301 of the blade crown 403 in the adjacent crowned stator blade 4, and can ensure that the first cutting surface 40301 and the second cutting surface 40302 of two adjacent crowned stator blades 4 that are not provided with adjustment stator blades before welding are fully and tightly fitted.

[0055] In one embodiment,

[0056] The outer ring section in each arc segment 10 is used to be fixedly connected to the compressor holding ring through the positioning pin 8, see Fig.10 The joint between the outer ring segments in two adjacent arc segments 10 forms a first thermal expansion gap, and the joint between the inner ring segments in two adjacent arc segments 10 forms a second thermal expansion gap 9, see Fig.11 .

[0057] In this way, the positioning pin 8 in each arc segment 10 serves as the absolute dead point of thermal expansion of the outer ring segment in the corresponding arc segment 10. The first thermal expansion gap facilitates sufficient thermal expansion of the outer ring segment in the corresponding arc segment 10, and the second thermal expansion gap 9 facilitates sufficient thermal expansion of the inner ring segment in the corresponding arc segment 10.

[0058] Preferably, the first thermal expansion gap and the second thermal expansion gap 9 are both controlled at 4-4.5 mm.

[0059] In one embodiment, a plurality of blade root grooves are provided on the inner circumference of the outer ring segment in each arc segment 10, the number of which is equal to the number of blade roots 402 of the shrouded stationary blades 4 in the corresponding arc segment 10, and the blade roots 402 are inserted into the corresponding blade root grooves.

[0060] After the gas turbine compressor stator ring in the utility model is assembled and welded, the subsequent outer ring part fine processing, sealing tooth processing, segmented cutting of the stator ring to form each arc segment 10 and installation of the sealing key 6 are carried out in sequence, which is consistent with the processing sequence required after the traditional compressor stator ring in the background technology is completed, ensuring that the compressor stator ring of the present utility model is consistent with the traditional compressor stator ring in the background technology in terms of both the use effect and the assembly method of the sliding holding ring.

[0061] In the utility model, the distribution angles of the crowned stator blades 4 in the stator blade ring of the gas turbine compressor are different. On the one hand, this is to make the downstream moving blades avoid the airflow excitation force and prevent resonance. On the other hand, the moving blades of the gas turbine compressor are relatively thin. Reducing the airflow excitation force can reduce the blade body stress of the moving blades during operation to a certain extent, thereby improving the safety margin of use.

[0062] In summary, the utility model can fundamentally solve the problem of wear of the stator blade top pin 103 in the stator blade ring of the gas turbine compressor in the background technology, can improve the safety and reliability of the operation of the gas turbine unit, and can significantly reduce service and maintenance costs.

[0063] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and substitutions can be made without departing from the technical principle of the present invention. These improvements and substitutions should also be regarded as the protection scope of the present invention.

Claims

1. A gas turbine compressor stator ring with shrouded stator blades, characterized in that: The invention comprises a plurality of circular arc segments (10) formed by segmented cutting, each of the circular arc segments (10) comprises an outer ring segment and a plurality of shrouded stationary blades (4), the shrouded stationary blades (4) comprising a blade body (401), the root end of the blade body (401) being integrally connected with a blade root (402) and the top end being integrally connected with a blade shroud (403), the blade root (402) being detachably connected to the corresponding outer ring segment, the blade shroud (403) comprising a first cutting surface (40301) and a second cutting surface (40302) arranged opposite to each other, and the blade shroud in each of the shrouded stationary blades (4) The first cutting surface (40301) of (403) is tightly fitted with the second cutting surface (40302) of the blade crown (403) in the adjacent crowned stationary blade (4), and the blade crowns (403) of two adjacent crowned stationary blades (4) are welded and connected. The blade crowns (403) of each crowned stationary blade (4) in each arc segment (10) are combined to form the inner ring segment of the corresponding arc segment (10), and the outer ring segment in each arc segment (10) is used for fixed connection with the holding ring of the compressor, and the inner ring segments in two adjacent arc segments (10) are sealed and connected at the joints.

2. A gas turbine compressor stator ring with shrouded stator blades according to claim 1, characterized in that: The blade crown (403) further comprises an inner circumferential surface segment and an outer circumferential surface segment, wherein the inner circumferential surface segment and the outer circumferential surface segment are both located between the first cutting surface (40301) and the second cutting surface (40302), the top end of the blade body (401) of each of the shrouded stationary blades (4) is connected to the outer circumferential surface segment of the corresponding blade crown (403), and a welding groove (404) is provided on the inner circumferential surface segment of the blade crown (403) of each of the shrouded stationary blades (4). The welding grooves (404) of the blade crowns (403) of each of the shrouded stationary blades (4) of the arc segments (10) are spliced ​​into an arc shape, and the welding grooves (404) of the blade crowns (403) of each of the shrouded stationary blades (4) of the gas turbine compressor stationary blade ring are spliced ​​into a circular ring shape. Welding material (5) is provided in each of the welding grooves (404) of each of the arc segments (10), so that the blade crowns (403) of two adjacent shrouded stationary blades (4) are welded and connected.

3. The gas turbine compressor stator ring with shrouded stator blades according to claim 1, characterized in that: The inner ring segment joints of two adjacent arc segments (10) are sealed and connected via a sealing key (6).

4. A gas turbine compressor stator ring with shrouded stator blades according to claim 3, characterized in that: A sealing key groove (7) is provided on the first cutting surface (40301) and the second cutting surface (40302) at the outer edge of the inner ring segment in each of the arc segments (10); one end of the sealing key (6) is arranged in the corresponding sealing key groove (7) on the inner ring segment in the corresponding arc segment (10), and the other end is arranged in the corresponding sealing key groove (7) on the inner ring segment in the adjacent arc segment (10).

5. The gas turbine compressor stator ring with shrouded stator blades according to claim 2, characterized in that: The material of the welding material (5) is the same as that of the shrouded stationary blade (4).

6. The gas turbine compressor stator ring with shrouded stator blades according to claim 1, characterized in that: Part of the circular arc segment (10) includes a plurality of adjustment vanes, the size of the blade crown at the top end of the blade body of the adjustment vane is different from the size of the blade crown (403) of the vane with a crown (4), the adjustment vane in the corresponding circular arc segment (10) is arranged at a position between two adjacent vanes with a crown (4) whose assembly gap needs to be adjusted, the blade root at the root end of the blade body of the adjustment vane is detachably connected to the outer ring segment, the first cutting surface of the blade crown in the adjustment vane is tightly fitted with the second cutting surface (40302) of the blade crown (403) of the adjacent vane with a crown (4), the second cutting surface of the blade crown in the adjustment vane is tightly fitted with the first cutting surface (40301) of the blade crown (403) of the adjacent vane with a crown (4), and the blade crown of the adjustment vane is welded to the blade crown (403) of the adjacent vane with a crown (4).

7. A gas turbine compressor stator ring with shrouded stator blades according to claim 6, characterized in that: The assembly clearance between the blade crown (403) of the adjusting stationary blade in the corresponding arc segment (10) and the blade crown (403) of the adjacent stationary blade with a crown (4) is less than 0.05 mm, and the assembly clearance between the blade crowns (403) of two adjacent stationary blades with a crown (4) that are not provided with an adjusting stationary blade in the corresponding arc segment (10) is less than 0.05 mm.

8. The gas turbine compressor stator ring with shrouded stator blades according to claim 1, characterized in that: The outer ring segment in each of the arc segments (10) is fixedly connected to the holding ring of the compressor via a positioning pin (8); the joint between the outer ring segments in two adjacent arc segments (10) forms a first thermal expansion gap; and the joint between the inner ring segments in two adjacent arc segments (10) forms a second thermal expansion gap (9).

9. A gas turbine compressor stator ring with shrouded stator blades according to claim 8, characterized in that: The first thermal expansion gap and the second thermal expansion gap (9) are both controlled within a range of 4-4.5 mm.

10. The gas turbine compressor stator ring with shrouded stator blades according to claim 1, characterized in that: A plurality of blade root grooves are provided on the inner circumferential surface of the outer ring segment in each of the arc segments (10), the number of which is equal to the number of blade roots (402) of the shrouded stationary blades (4) in the corresponding arc segment (10), and the blade roots (402) are inserted into the corresponding blade root grooves.

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