Gas turbine compressor stationary blade ring with upper and lower crown stationary blades

Abstract

The utility model discloses a gas turbine compressor stationary blade ring with upper and lower crown stationary blades, which comprises a plurality of arc sections, each arc section comprises a plurality of upper and lower crown stationary blades, each upper and lower crown stationary blade comprises a blade body, a blade root crown is arranged at the root end of the blade body, a blade top crown is arranged at the top end of the blade body, and the blade root crown comprises a first outer ring cutting surface and a second outer ring cutting surface. The blade top crown comprises a first inner ring cutting face and a second inner ring cutting face, the first outer ring cutting face of each upper and lower crown stationary blade is tightly attached to the second outer ring cutting face of the adjacent upper and lower crown stationary blade, and the first inner ring cutting face is tightly attached to the second inner ring cutting face of the adjacent upper and lower crown stationary blade. The blade root crowns and the blade top crowns of every two adjacent upper and lower crown stationary blades are welded, the blade root crowns of all the upper and lower crown stationary blades in each arc section form an outer ring section, the blade top crowns of all the upper and lower crown stationary blades in each arc section form an inner ring section, and joints of the inner ring sections in every two adjacent arc sections are connected in a sealed mode. The top ends of the blade bodies of the upper and lower crown stationary blades in the stationary blade ring are not abraded, and an outer ring does not need to be additionally machined.

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 upper and lower crown 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 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 stationary blade root 102 is detachably connected to the outer ring 2, and the stationary blade top pin 103 is detachably connected to the inner ring 3.

[0003] During the overhaul and even medium overhaul 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 worn out, 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 design of the compressor stator blade ring structure, 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 the punching and riveting connection. After the 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. The unit will inevitably vibrate during operation, and the punching and riveting connection will loosen under the repeated vibration impact, resulting in continuous micro-wear of 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, it is necessary to fundamentally solve the wear problem of the stator blade top pin 103.

[0004] In addition, since the compressor stator ring in the F-class gas turbine unit includes an outer ring 2, the outer ring 2 needs to be additionally processed, and each stator blade root 102 needs to be assembled into the corresponding blade root groove of the outer ring 2. The assembly requires high precision and the assembly process is relatively complicated. Utility Model Content

[0005] In view of the defects of the above-mentioned prior art, the utility model provides a gas turbine compressor stator ring having upper and lower crown stator blades. Under a vibration environment, the top ends of the upper and lower crown stator blades in the gas turbine compressor stator ring will not have wear problems, and the gas turbine compressor stator ring does not require additional processing of the outer ring.

[0006] The technical solution adopted by the utility model to solve its technical problems is:

[0007] A gas turbine compressor stator blade ring with upper and lower crown stator blades, comprising a plurality of arc segments formed by segmented cutting, each of the arc segments comprising a plurality of upper and lower crown stator blades, the upper and lower crown stator blades comprising a blade body, the root end of the blade body being integrally connected with a blade root crown and the top end being integrally connected with a blade top crown, the blade root crown comprising a first outer ring cutting surface and a second outer ring cutting surface arranged oppositely, the blade top crown comprising a first inner ring cutting surface and a second inner ring cutting surface arranged oppositely, the first outer ring cutting surface of the blade root crown in each of the upper and lower crown stator blades being closely fitted with the second outer ring cutting surface of the blade root crown in the adjacent upper and lower crown stator blades The blade root crowns of two adjacent upper and lower crown static blades are welded and connected, the first inner ring cutting surface of the blade top crown in each of the upper and lower crown static blades is tightly fitted with the second inner ring cutting surface of the blade top crown in the adjacent upper and lower crown static blades, and the blade top crowns of two adjacent upper and lower crown static blades are welded and connected, the blade root crowns of each upper and lower crown static blade in each arc segment are combined to form the outer ring segment of the corresponding arc segment, and the blade top crowns are combined to form the inner ring segment of the corresponding arc segment, the outer ring segment in each arc segment is used to be fixedly connected to the holding ring of the compressor, and the joints of the inner ring segments in two adjacent arc segments are sealed by a sealing key.

[0008] Furthermore, the blade root crown also includes an outer ring inner circumferential surface segment and an outer ring outer circumferential surface segment, and the outer ring inner circumferential surface segment and the outer ring outer circumferential surface segment are both between the first outer ring cutting surface and the second outer ring cutting surface. The blade body root end of each of the upper and lower crown stator blades is connected to the outer ring inner circumferential surface segment of the corresponding blade root crown. An outer ring welding groove is opened on the outer ring outer circumferential surface segment of the blade root crown in each of the upper and lower crown stator blades. The outer ring welding grooves of the blade root crowns in each of the upper and lower crown stator blades of each of the arc segments are spliced ​​into an arc shape. The outer ring welding grooves of the blade root crowns in each of the upper and lower crown stator blades of the gas turbine compressor stator blade ring are spliced ​​into a circular ring shape. An outer ring welding material is arranged in each of the outer ring welding grooves of each of the arc segments, so that the blade root crowns of two adjacent upper and lower crown stator blades are welded and connected.

[0009] Furthermore, the material of the outer ring welding material is the same as the material of the upper and lower crown stationary blades.

[0010] Furthermore, the blade top crown also includes an inner ring inner circumferential surface segment and an inner ring outer circumferential surface segment, and the inner ring inner circumferential surface segment and the inner ring outer circumferential surface segment are both between the first inner ring cutting surface and the second inner ring cutting surface. The top end of the blade body of each of the upper and lower crown static blades is connected to the inner ring outer circumferential surface segment of the corresponding blade top crown. An inner ring welding groove is opened on the inner ring inner circumferential surface segment of the blade top crown in each of the upper and lower crown static blades. The inner ring welding grooves of the blade top crowns in each of the upper and lower crown static blades in each of the arc segments are spliced ​​into an arc shape. The inner ring welding grooves of the blade top crowns in each of the upper and lower crown static blades of the gas turbine compressor static blade ring are spliced ​​into a circular ring shape. Inner ring welding material is provided in each inner ring welding groove of each of the arc segments, so that the blade top crowns of two adjacent upper and lower crown static blades are welded and connected.

[0011] Furthermore, the material of the inner ring welding material is the same as the material of the upper and lower crown static blades.

[0012] Furthermore, a sealing key groove is provided on the first inner ring cutting surface and the second inner ring 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.

[0013] Furthermore, part of the circular arc segment includes a plurality of adjustable stationary blades, the adjustable stationary blade includes an adjustable blade body, the root end of the adjustable blade body is integrally connected with an adjustable blade root crown and the top end is integrally connected with an adjustable blade top crown, the adjustable blade root crown includes a first adjusting outer ring cutting surface and a second adjusting outer ring cutting surface that are relatively arranged, the adjustable blade top crown includes a first adjusting inner ring cutting surface and a second adjusting inner ring cutting surface that are relatively arranged, the adjustable blade root crown size of the adjustable stationary blade is different from the blade root crown size of the upper and lower crown stationary blades, the adjustable blade top crown size of the adjustable stationary blade is different from the blade top crown size of the upper and lower crown stationary blades, and the corresponding adjustable stationary blade in the circular arc segment is arranged at a position between two adjacent upper and lower crown stationary blades where the assembly gap between the blade root crown and the blade top crown needs to be adjusted, and the adjustable The first adjustment outer ring cutting surface of the adjustable blade root crown in the node stator blade is tightly fitted with the second outer ring cutting surface of the blade root crown in the adjacent upper and lower crown stator blades, the second adjustment outer ring cutting surface of the adjustable blade root crown in the adjustable stator blade is tightly fitted with the first outer ring cutting surface of the blade root crown in the adjacent upper and lower crown stator blades, the first adjustment inner ring cutting surface of the adjustable blade top crown in the adjustable stator blade is tightly fitted with the second inner ring cutting surface of the blade top crown in the adjacent upper and lower crown stator blades, the second adjustment inner ring cutting surface of the adjustable blade top crown in the adjustable stator blade is tightly fitted with the first inner ring cutting surface of the blade top crown in the adjacent upper and lower crown stator blades, the adjustable blade root crown of the adjustable stator blade is welded to the blade root crown of the adjacent upper and lower crown stator blades, and the adjustable blade top crown of the adjustable stator blade is welded to the blade top crown of the adjacent upper and lower crown stator blades.

[0014] Furthermore, the assembly clearance between the regulating blade root crown of the regulating stator blade in the corresponding arc segment and the blade root crown of the adjacent upper and lower crown stator blades is less than 0.05mm, the assembly clearance between the regulating blade top crown of the regulating stator blade in the corresponding arc segment and the blade top crown of the adjacent upper and lower crown stator blades is less than 0.05mm, and the assembly clearance between the blade root crowns and the blade top crowns of two adjacent upper and lower crown stator blades in the corresponding arc segment where no regulating stator blades are provided are both less than 0.05mm.

[0015] 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 an outer ring thermal expansion gap, and the joint between the inner ring segments in two adjacent arc segments forms an inner ring thermal expansion gap.

[0016] Furthermore, the outer ring thermal expansion gap and the inner ring thermal expansion gap are both controlled within a range of 4-4.5 mm.

[0017] Compared with the prior art, the beneficial effects of the utility model are:

[0018] In the utility model, the blade tops of the upper and lower crown stator blades in the stator blade ring of the gas turbine compressor are integrally connected with the blade top crown, and the blade top crowns of the upper and lower crown stator blades in each arc segment are combined to form an inner ring segment of the corresponding arc segment. Compared with the traditional stator blade ring with an outer ring and an inner ring in the background technology, under the same vibration environment, the blade tops of the upper and lower crown stator blades in the stator blade ring of the gas turbine compressor are firmly connected with the blade top crown, and the blade tops of the upper and lower crown stator blades in the stator blade ring of the gas turbine compressor will not have wear problems. Therefore, the utility model can fundamentally solve the problem of wear of the stator blade top pins in the stator blade ring of the gas turbine compressor in the background technology, and can improve the operation of the gas turbine unit. Safety and reliability, and can greatly reduce service and maintenance costs; and the blade root crowns of the upper and lower crown stator blades in each arc segment are combined to form the outer ring segment of the corresponding arc segment, so the gas turbine compressor stator blade ring does not need additional processing of the outer ring, and compared with the traditional stator blade ring in the background technology, each stator blade root needs to be assembled into the corresponding blade root groove of the outer ring, and each arc segment in the utility model can form the outer ring segment of the corresponding arc segment by welding the blade root crowns of two adjacent upper and lower crown stator blades, thereby eliminating the assembly process of the stator blade root and the blade root groove in the background technology, and the assembly process is relatively simple; in addition, the setting of the sealing key can prevent leakage between two adjacent arc segments. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the assembly of a conventional gas turbine compressor stator ring in the background technology;

[0020] Figure 2 for Figure 1 A schematic diagram of the structure of one of the stationary blades;

[0021] Figure 3 for Figure 1 AA direction cross-sectional structure schematic diagram;

[0022] Figure 4 for Figure 3 BB direction cross-sectional structure schematic diagram;

[0023] Figure 5 for Figure 4 Schematic diagram of the cross-sectional structure in the CC direction;

[0024] Figure 6 It is a schematic diagram of the assembly of a gas turbine compressor stator ring with upper and lower crown stator blades in the utility model;

[0025] Figure 7 for Figure 6 A schematic diagram of a local enlarged structure;

[0026] Figure 8 It is a schematic diagram of the three-dimensional structure of one of the upper and lower crown static blades in the utility model;

[0027] Fig. 9 for Figure 8 A schematic diagram of the three-dimensional structure in another direction;

[0028] Fig.10 for Figure 6 DD direction cross-sectional structure schematic diagram;

[0029] Fig.11 It is a schematic diagram of multiple arc segments formed by segmented cutting of a gas turbine compressor stator ring with upper and lower crown stator blades in the utility model;

[0030] 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;

[0031] Fig.13 Schematic diagram of the three-dimensional structure of the sealing key.

[0032] Explanation of 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. upper and lower crown stationary blades, 401. blade body, 402. blade root crown, 40201. first outer ring cutting surface, 40202. second outer ring cutting surface, 40203. outer ring inner circumference segment, 40204. outer ring outer circumference segment, 403. blade top crown , 40301, first inner ring cutting surface, 40302, second inner ring cutting surface, 40303, inner ring inner circumferential surface segment, 40304, inner ring outer circumferential surface segment, 404, outer ring welding groove, 405, inner ring welding groove, 5, outer ring welding material, 6, inner ring welding material, 7, sealing key, 8, sealing keyway, 9, locating pin, 10, arc segment, E, suction surface, F, pressure surface, G, punching and riveting connection. DETAILED DESCRIPTION

[0033] 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.

[0034] like Figure 6-Figure 11As shown, a gas turbine compressor stator ring with upper and lower crown stator blades includes a plurality of arc segments 10 formed by segmented cutting, each arc segment 10 includes a plurality of upper and lower crown stator blades 4, the upper and lower crown stator blades 4 include a blade body 401, the root end of the blade body 401 is integrally connected with a blade root crown 402 and the top end is integrally connected with a blade top crown 403, the blade root crown 402 includes a first outer ring cutting surface 40201 and a second outer ring cutting surface 40202 arranged oppositely, the blade top crown 403 includes a first inner ring cutting surface 40301 and a second inner ring cutting surface 40302 arranged oppositely, the first outer ring cutting surface 40201 of the blade root crown 402 in each upper and lower crown stator blade 4 is tightly connected to the second outer ring cutting surface 40202 of the blade root crown 402 in the adjacent upper and lower crown stator blade 4 The blade root crowns 402 of two adjacent upper and lower crown stationary blades 4 are closely fitted, and the blade root crowns 402 of the blade root crowns 402 of each upper and lower crown stationary blade 4 are welded and connected. The first inner ring cutting surface 40301 of the blade top crown 403 in each upper and lower crown stationary blade 4 is closely fitted with the second inner ring cutting surface 40302 of the blade top crown 403 in the adjacent upper and lower crown stationary blade 4. The blade top crowns 403 of two adjacent upper and lower crown stationary blades 4 are welded and connected. The blade root crowns 402 of each upper and lower crown stationary blade 4 in each arc segment 10 are combined to form the outer ring segment of the corresponding arc segment 10, and the blade top crowns 403 are combined to form the inner ring segment of the corresponding arc segment 10. The outer ring segment in each arc segment 10 is used to be fixedly connected with the holding ring of the compressor. The inner ring segment joints of two adjacent arc segments 10 are sealed and connected by a sealing key 7, wherein the three-dimensional structural schematic diagram of the sealing key 7 is shown in Fig.13 .

[0035] The top ends of the blade bodies 401 of the upper and lower crown stator blades 4 in the gas turbine compressor stator blade ring are integrally connected with the blade top crown 403, and the blade top crowns 403 of the upper and lower crown stator blades 4 in each arc segment 10 are combined to form the inner ring segment of the corresponding arc segment 10. Compared with the traditional stator blade ring with an outer ring and an inner ring in the background technology, under the same vibration environment, the top ends of the blade bodies 401 of the upper and lower crown stator blades 4 in the gas turbine compressor stator blade ring are firmly connected with the blade top crown 403, and the top ends of the blade bodies 401 of the upper and lower crown stator blades 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 pins in the gas turbine compressor stator blade ring in the background technology, and can improve the operation of the gas turbine unit. The safety and reliability can be improved, and the service and maintenance costs can be greatly reduced; and the blade root crowns 402 of the upper and lower crown stator blades 4 in each arc segment 10 are combined to form the outer ring segment of the corresponding arc segment 10, so the gas turbine compressor stator blade ring does not need to additionally process the outer ring, and compared with the traditional stator blade ring in the background technology, which requires each stator blade root to be assembled into the corresponding blade root groove of the outer ring, each arc segment 10 in the utility model can form the outer ring segment of the corresponding arc segment 10 by welding the blade root crowns 402 of two adjacent upper and lower crown stator blades 4, thereby eliminating the assembly process of the stator blade root and the blade root groove in the background technology, and the assembly process is relatively simple; in addition, the setting of the sealing key 7 can prevent air leakage between two adjacent arc segments 10.

[0036] In one embodiment,

[0037] like Figure 8 and Fig. 9 As shown, the blade root crown 402 also includes an outer ring inner circumference segment 40203 and an outer ring outer circumference segment 40204, and the outer ring inner circumference segment 40203 and the outer ring outer circumference segment 40204 are both located between the first outer ring cutting surface 40201 and the second outer ring cutting surface 40202. The root end of the blade body 401 of each upper and lower crown stationary blade 4 is connected to the outer ring inner circumference segment 40203 of the corresponding blade root crown 402. The outer ring outer circumference segment 40203 of the blade root crown 402 of each upper and lower crown stationary blade 4 An outer ring welding groove 404 is opened on the circumferential surface segment 40204, and the outer ring welding grooves 404 of the blade root crowns 402 of each upper and lower crown stator blades 4 of each arc segment 10 are spliced ​​into an arc shape, and the outer ring welding grooves 404 of the blade root crowns 402 of each upper and lower crown stator blades 4 of the gas turbine compressor stator blade ring are spliced ​​into a circular ring shape, and an outer ring welding material 5 is arranged in each outer ring welding groove 404 of each arc segment 10, so that the blade root crowns 402 of two adjacent upper and lower crown stator blades 4 are welded and connected.

[0038] In this way, an outer ring welding groove 404 is opened on the outer ring outer peripheral surface segment 40204 of the blade root crown 402 of the upper and lower crown stator blades 4, so that the blade root crowns 402 of two adjacent upper and lower crown stator blades 4 can be welded and connected when the first outer ring cutting surface 40201 of the blade root crown 402 of each upper and lower crown stator blade 4 in each arc segment 10 is tightly fitted with the second outer ring cutting surface 40202 of the blade root crown 402 of the adjacent upper and lower crown stator blades 4.

[0039] Preferably, the material of the outer ring welding material 5 is the same as that of the upper and lower crown vanes 4. This can avoid thermal expansion caused by welding of dissimilar materials.

[0040] In one embodiment,

[0041] like Figure 8 and Fig. 9 As shown, the blade crown 403 also includes an inner ring inner circumference segment 40303 and an inner ring outer circumference segment 40304, and the inner ring inner circumference segment 40303 and the inner ring outer circumference segment 40304 are both located between the first inner ring cutting surface 40301 and the second inner ring cutting surface 40302. The top end of the blade body 401 of each upper and lower crown stationary blade 4 is connected to the inner ring outer circumference segment 40304 of the corresponding blade crown 403, and the inner ring inner circumference segment 40303 of the blade crown 403 of each upper and lower crown stationary blade 4 is opened. There is an inner ring welding groove 405, and the inner ring welding grooves 405 of the blade top crowns 403 of each upper and lower crown stator blades 4 of each arc segment 10 are spliced ​​into an arc shape, and the inner ring welding grooves 405 of the blade top crowns 403 of each upper and lower crown stator blades 4 of the gas turbine compressor stator blade ring are spliced ​​into a circular ring shape. Inner ring welding materials 6 are arranged in each inner ring welding groove 405 of each arc segment 10, and inner ring welding materials 6 are arranged in each inner ring welding groove 405 of the arc segment 10, so that the blade top crowns 403 of two adjacent upper and lower crown stator blades 4 are welded and connected.

[0042] In this way, an inner ring welding groove 405 is opened on the inner ring inner circumferential surface segment 40303 of the blade top crown 403 of the upper and lower crown vanes 4, so that the blade top crowns 403 of two adjacent upper and lower crown vanes 4 can be welded and connected when the first inner ring cutting surface 40301 of the blade top crown 403 of each upper and lower crown vane 4 in each arc segment 10 is tightly fitted with the second inner ring cutting surface 40302 of the blade top crown 403 of the adjacent upper and lower crown vanes 4.

[0043] Preferably, the material of the inner ring welding material 6 is the same as that of the upper and lower crown stationary blades 4. This can avoid thermal expansion caused by welding of dissimilar materials.

[0044] In one embodiment, a sealing key groove 8 is provided on the first inner ring cutting surface 40301 and the second inner ring cutting surface 40302 at the outer edge of the inner ring segment in each arc segment 10. Fig.12One end of the sealing key 7 is arranged in the corresponding sealing key groove 8 on the inner ring segment in the corresponding arc segment 10, and the other end is arranged in the corresponding sealing key groove 8 on the inner ring segment in the adjacent arc segment 10.

[0045] In one embodiment,

[0046] The partial arc segment 10 includes a plurality of adjustable stationary blades, the adjustable stationary blade includes an adjustable blade body, the root end of the adjustable blade body is integrally connected with an adjustable blade root crown and the top end is integrally connected with an adjustable blade top crown, the adjustable blade root crown includes a first adjusting outer ring cutting surface and a second adjusting outer ring cutting surface that are relatively arranged, the adjusting blade top crown includes a first adjusting inner ring cutting surface and a second adjusting inner ring cutting surface that are relatively arranged, the size of the adjustable blade root crown of the adjustable stationary blade is different from the size of the blade root crown 402 of the upper and lower crown stationary blades 4, the size of the adjustable blade top crown of the adjustable stationary blade is different from the size of the blade top crown 403 of the upper and lower crown stationary blades 4, the corresponding adjustable stationary blade in the arc segment 10 is arranged at a position between two adjacent upper and lower crown stationary blades 4 where the assembly gap between the blade root crown 402 and the blade top crown 403 needs to be adjusted, and the first adjusting outer ring cutting surface of the adjusting blade root crown in the adjusting stationary blade The second outer ring cutting surface 40202 of the blade root crown 402 of the adjacent upper and lower crown stator blade 4 is tightly fitted, the second adjusting outer ring cutting surface of the adjusting blade root crown in the adjusting stator blade is tightly fitted with the first outer ring cutting surface 40201 of the blade root crown 402 of the adjacent upper and lower crown stator blade 4, the first adjusting inner ring cutting surface of the adjusting blade top crown in the adjusting stator blade is tightly fitted with the second inner ring cutting surface 40302 of the blade top crown 403 of the adjacent upper and lower crown stator blade 4, the second adjusting inner ring cutting surface of the adjusting blade top crown in the adjusting stator blade is tightly fitted with the first inner ring cutting surface 40301 of the blade top crown 403 of the adjacent upper and lower crown stator blade 4, the adjusting blade root crown of the adjusting stator blade is welded to the blade root crown 402 of the adjacent upper and lower crown stator blade 4, and the adjusting blade top crown of the adjusting stator blade is welded to the blade top crown 403 of the adjacent upper and lower crown stator blade 4.

[0047] In this way, by adjusting the setting of the stator blades, the processing errors of the upper and lower crown stator blades 4 in the stator blade ring of the gas turbine compressor can be compensated, ensuring that the assembly gap between the adjustable blade root crown of the adjustable stator blade and the blade root crown 402 of the adjacent upper and lower crown stator blade 4 before welding meets the requirements, and ensuring that the assembly gap between the adjustable blade top crown of the adjustable stator blade and the blade top crown 403 of the adjacent upper and lower crown stator blades 4 before welding meets the requirements, and ensuring that the assembly gap between the blade root crowns 402 and the blade top crowns 403 in two adjacent upper and lower crown stator blades 4 without adjustable stator blades before welding both meet the requirements.

[0048] Preferably, the assembly clearance between the regulating blade root crown of the regulating stator blade in the corresponding arc segment 10 and the blade root crown 402 of the adjacent upper and lower crown stator blades 4 is less than 0.05 mm, the assembly clearance between the regulating blade top crown of the regulating stator blade in the corresponding arc segment 10 and the blade top crown 403 of the adjacent upper and lower crown stator blades 4 is less than 0.05 mm, and the assembly clearance between the blade root crowns 402 and the blade top crowns 403 of two adjacent upper and lower crown stator blades 4 in the corresponding arc segment 10 where no regulating stator blades are provided are both less than 0.05 mm.

[0049] In one embodiment,

[0050] The outer ring segment in each arc segment 10 is fixedly connected to the holding ring of the compressor through a positioning pin 9, and the joint between the outer ring segments in two adjacent arc segments 10 forms an outer ring thermal expansion gap, and the joint between the inner ring segments in two adjacent arc segments 10 forms an inner ring thermal expansion gap.

[0051] In this way, the positioning pin 9 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 outer ring thermal expansion gap facilitates sufficient thermal expansion of the outer ring segment in the corresponding arc segment 10, and the inner ring thermal expansion gap facilitates sufficient thermal expansion of the inner ring segment in the corresponding arc segment 10.

[0052] Preferably, the thermal expansion gap of the outer ring and the thermal expansion gap of the inner ring are both controlled at 4-4.5 mm.

[0053] In the utility model, the outer ring welding groove and the inner ring welding groove are specifically processed in the following manner: the blade root crowns 402 of the upper and lower crown stationary blades 4 after machining are spliced ​​into a circular ring, and the blade top crowns 403 of the upper and lower crown stationary blades 4 are spliced ​​into a circular ring, and then a circle of outer ring welding groove is machined on the outer circumferential surface of the circular ring spliced ​​by the blade root crowns 402, and an outer ring welding material 5 is arranged in the circle of outer ring welding groove, so that the blade root crowns 402 of two adjacent upper and lower crown stationary blades 4 are welded and connected, and a circle of inner ring welding groove is machined on the inner circumferential surface of the circular ring spliced ​​by the blade top crowns 403, and an inner ring welding material 6 is arranged in the circle of inner ring welding groove, so that the blade top crowns 403 of two adjacent upper and lower crown stationary blades 4 are welded and connected. 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 7 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.

[0054] In the utility model, the distribution angles of the upper and lower crown 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.

[0055] In summary, the utility model can fundamentally solve the problem of wear of the stator blade top pin 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 greatly reduce the service and maintenance costs; and the stator blade ring of the gas turbine compressor does not require additional processing of the outer ring, and the utility model can save the assembly process of the stator blade root and the blade root groove in the background technology, and the assembly process is relatively simple; in addition, the setting of the sealing key 7 can prevent leakage between two adjacent arc segments 10.

[0056] 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 having upper and lower crown stator blades, characterized in that: The invention comprises a plurality of arc segments (10) formed by segmented cutting, each of the arc segments (10) comprises a plurality of upper and lower crown stationary blades (4), the upper and lower crown stationary blades (4) comprise a blade body (401), the root end of the blade body (401) is integrally connected with a blade root crown (402), and the top end is integrally connected with a blade top crown (403), the blade root crown (402) comprises a first outer ring cutting surface (40201) and a second outer ring cutting surface (40202), the blade top crown (403) comprises a first inner ring cutting surface (40301) and a second inner ring cutting surface (40302), and the first outer ring cutting surface (40201) of each of the upper and lower crown stationary blades (4) is tightly connected to the second outer ring cutting surface (40202) of the adjacent upper and lower crown stationary blades (4). The blade root crowns (402) and the blade top crowns (403) of the two adjacent upper and lower crown blades (4) are welded together. The blade root crowns (402) of the upper and lower crown blades (4) in each arc segment (10) are combined to form the outer ring segment of the corresponding arc segment (10), and the blade top crowns (403) are combined to form the inner ring segment of the corresponding arc segment (10). The outer ring segment in each arc segment (10) is used for fixed connection with the holding ring of the compressor. The inner ring segment joints of the two adjacent arc segments (10) are sealed by a sealing key (7).

2. A gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 1, characterized in that: The blade root crown (402) further comprises an outer ring inner circumferential surface segment (40203) and an outer ring outer circumferential surface segment (40204), wherein the outer ring inner circumferential surface segment (40203) and the outer ring outer circumferential surface segment (40204) are both located between the first outer ring cutting surface (40201) and the second outer ring cutting surface (40202), and the root end of the blade body (401) of each of the upper and lower crown stationary blades (4) is connected to the outer ring inner circumferential surface segment (40203) of the corresponding blade root crown (402), and the outer ring outer circumferential surface of the blade root crown (402) of each of the upper and lower crown stationary blades (4) is An outer ring welding groove (404) is provided on the segment (40204), and the outer ring welding grooves (404) of the blade root crowns (402) of each upper and lower crown stator blades (4) of each arc segment (10) are spliced ​​into an arc shape. The outer ring welding grooves (404) of the blade root crowns (402) of each upper and lower crown stator blades (4) of the gas turbine compressor stator blade ring are spliced ​​into a circular ring shape. An outer ring welding material (5) is provided in each outer ring welding groove (404) of each arc segment (10), so that the blade root crowns (402) of two adjacent upper and lower crown stator blades (4) are welded and connected.

3. The gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 2, characterized in that: The material of the outer ring welding material (5) is the same as the material of the upper and lower crown stationary blades (4).

4. The gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 1, characterized in that: The blade crown (403) further comprises an inner ring inner circumference segment (40303) and an inner ring outer circumference segment (40304), wherein the inner ring inner circumference segment (40303) and the inner ring outer circumference segment (40304) are both located between the first inner ring cutting surface (40301) and the second inner ring cutting surface (40302), and the top end of the blade body (401) of each of the upper and lower crown stationary blades (4) is connected to the inner ring outer circumference segment (40304) of the corresponding blade crown (403), and the inner ring inner circumference of the blade crown (403) of each of the upper and lower crown stationary blades (4) is An inner ring welding groove (405) is provided on the segment (40303), and the inner ring welding grooves (405) of the blade top crowns (403) of each upper and lower crown stator blades (4) of each arc segment (10) are spliced ​​into an arc shape. The inner ring welding grooves (405) of the blade top crowns (403) of each upper and lower crown stator blades (4) of the gas turbine compressor stator blade ring are spliced ​​into a circular ring shape. Inner ring welding materials (6) are provided in each inner ring welding groove (405) of each arc segment (10), so that the blade top crowns (403) of two adjacent upper and lower crown stator blades (4) are welded and connected.

5. The gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 4, characterized in that: The material of the inner ring welding material (6) is the same as the material of the upper and lower crown stationary blades (4).

6. The gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 1, characterized in that: A sealing key groove (8) is provided on the first inner ring cutting surface (40301) and the second inner ring 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 (7) is arranged in the corresponding sealing key groove (8) on the inner ring segment in the corresponding arc segment (10), and the other end is arranged in the corresponding sealing key groove (8) on the inner ring segment in the adjacent arc segment (10).

7. The gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 1, characterized in that: Part of the circular arc segment (10) includes a plurality of adjustable stationary blades, wherein the adjustable stationary blade includes an adjustable blade body, the root end of the adjustable blade body is integrally connected with an adjustable blade root crown and the top end is integrally connected with an adjustable blade top crown, the adjustable blade root crown includes a first adjustable outer ring cutting surface and a second adjustable outer ring cutting surface that are relatively arranged, and the adjustable blade top crown includes a first adjustable inner ring cutting surface and a second adjustable inner ring cutting surface that are relatively arranged, the size of the adjustable blade root crown of the adjustable stationary blade is different from the size of the blade root crown (402) of the upper and lower crown stationary blades (4), and the size of the adjustable blade top crown of the adjustable stationary blade is different from the size of the blade top crown (403) of the upper and lower crown stationary blades (4), and the corresponding adjustable stationary blade in the circular arc segment (10) is arranged at a position between two adjacent upper and lower crown stationary blades (4) whose assembly gap between the blade root crown (402) and the blade top crown (403) needs to be adjusted, and the first adjustable outer ring cutting surface of the adjustable blade root crown in the adjustable stationary blade is aligned with the adjacent The second outer ring cutting surface (40202) of the blade root crown (402) of the upper and lower crown stator blades (4) is tightly fitted, the second outer ring cutting surface of the adjusting blade root crown in the adjusting stator blade is tightly fitted with the first outer ring cutting surface (40201) of the blade root crown (402) of the adjacent upper and lower crown stator blades (4), the first inner ring cutting surface of the adjusting blade top crown in the adjusting stator blade is tightly fitted with the second inner ring cutting surface (40302) of the blade top crown (403) of the adjacent upper and lower crown stator blades (4), the second inner ring cutting surface of the adjusting blade top crown in the adjusting stator blade is tightly fitted with the first inner ring cutting surface (40301) of the blade top crown (403) of the adjacent upper and lower crown stator blades (4), the adjusting blade root crown of the adjusting stator blade is welded to the blade root crown (402) of the adjacent upper and lower crown stator blades (4), and the adjusting blade top crown of the adjusting stator blade is welded to the blade top crown (403) of the adjacent upper and lower crown stator blades (4).

8. The gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 7, characterized in that: The assembly clearance between the adjustable blade root crown of the adjustable static blade in the corresponding arc segment (10) and the blade root crown (402) of the adjacent upper and lower crown static blades (4) is less than 0.05 mm, the assembly clearance between the adjustable blade top crown of the adjustable static blade in the corresponding arc segment (10) and the blade top crown (403) of the adjacent upper and lower crown static blades (4) is less than 0.05 mm, and the assembly clearance between the blade root crowns (402) and the assembly clearance between the blade top crowns (403) in two adjacent upper and lower crown static blades (4) without adjustable static blades in the corresponding arc segment (10) are both less than 0.05 mm.

9. The gas turbine compressor stator ring with upper and lower shroud 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 (9); the joint between the outer ring segments in two adjacent arc segments (10) forms an outer ring thermal expansion gap; and the joint between the inner ring segments in two adjacent arc segments (10) forms an inner ring thermal expansion gap.

10. A gas turbine compressor stator ring with upper and lower shroud stator blades according to claim 9, characterized in that: The outer ring thermal expansion gap and the inner ring thermal expansion gap are both controlled at 4-4.5 mm.

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