CN114370305B - Composite cooling structure for turbine stator blades of gas turbine - Google Patents
Composite cooling structure for turbine stator blades of gas turbine Download PDFInfo
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- CN114370305B CN114370305B CN202210086255.9A CN202210086255A CN114370305B CN 114370305 B CN114370305 B CN 114370305B CN 202210086255 A CN202210086255 A CN 202210086255A CN 114370305 B CN114370305 B CN 114370305B
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- inner cavity
- stator blade
- insert core
- core
- partition plate
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- 238000001816 cooling Methods 0.000 title claims abstract description 71
- 239000002131 composite material Substances 0.000 title claims abstract description 20
- 230000003068 static effect Effects 0.000 claims abstract description 11
- 238000005192 partition Methods 0.000 claims description 60
- 239000007789 gas Substances 0.000 claims description 39
- 239000000112 cooling gas Substances 0.000 claims description 7
- 239000013307 optical fiber Substances 0.000 claims 1
- 238000007789 sealing Methods 0.000 claims 1
- 230000008646 thermal stress Effects 0.000 abstract description 8
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 4
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 239000002737 fuel gas Substances 0.000 description 3
- 239000002184 metal Substances 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
Abstract
The invention relates to a cooling system of a gas turbine stator blade, in particular to a composite cooling structure of the gas turbine stator blade, which comprises a stator blade, wherein four hollow inner cavities are arranged in the stator blade; the hollow inner cavity close to the front edge of the stator blade is a first inner cavity, the hollow inner cavity close to the tail edge of the stator blade is a fourth inner cavity, a first insert core is arranged in the first inner cavity, and a fourth insert core is arranged in the fourth inner cavity; the first inserting core is of a thin-wall annular structure, two ends of the first inserting core are open, and the cross section of the first inserting core is of an open type structure; radial space is reserved between the first insert core and the inner wall of the static blade, and a plurality of air holes are formed in the surface of the insert core; the side wall of the stator blade is provided with a plurality of air film holes. The insert core is manufactured by adopting a mature stamping process, so that the manufacturing difficulty and the processing cost are reduced; meanwhile, the overall temperature uniformity of the blade is improved, the thermal stress is reduced, the failure probability of the tail edge of the stator blade is reduced, and the service life of the blade is prolonged.
Description
Technical Field
The invention relates to a cooling system of a gas turbine stator blade, in particular to a composite cooling structure of a gas turbine stator blade.
Background
It is known from the simple cycle mode of a gas turbine that by increasing the initial temperature of the gas at the inlet of the turbine, the specific power and performance of the gas turbine can be increased. The surrounding temperature of the turbine stator blade is high, the environment is bad, the initial temperature of the F-stage gas turbine is about 1400 ℃, and the bearing limit of the stator blade metal is far exceeded. Therefore, advanced turbine vane cooling structure designs are critical to safe operation of the gas turbine.
At present, the turbine stator blade of the gas turbine generally adopts a hollow structure, and cooling gas is introduced into the turbine stator blade to take away the heat of the stator blade. The common cooling structure is a 2-level or 3-level honeycomb duct structure nested in the hollow inner cavity of the stator blade, cooling air is firstly sprayed on the wall surface of the inner cavity of the stator blade through small holes on the side wall of the honeycomb duct to form impact cooling, and then flows out through small holes on the side wall of the stator blade to cover the outer wall surface of the stator blade to form air film cooling; the trailing edge of the stator blade adopts split joint jet cooling of turbulent flow columns and ribs, and cooling air is generally provided by a trailing edge cavity independently.
Patent CN1318734C discloses a cooling structure of a stator blade and a gas turbine, which has a impingement plate with a plurality of small holes arranged at a distance from the bottom surface of an inner ring to form a cavity, and guides cooling air from the small holes into the cavity. A leading edge flow passage is provided on the leading edge side in the width direction, and cooling air is introduced. Side runners are provided along both sides of the inner ring to guide cooling air to the trailing edge side. A header is formed widthwise near the trailing edge for conveying cooling air from the side flow passage. A plurality of trailing edge flow channels are provided at a predetermined interval in the width direction on the trailing edge side, and each of the trailing edge flow channels has one end connected to the header and the other end open to the trailing edge, and cooling air in the header is ejected from the trailing edge. Patent application CN202010553109.3 discloses an embodiment of a turbine stator blade, comprising: a blade profile having a leading edge and a trailing edge; an inner shroud disposed at one end of the airfoil and supporting the airfoil; an outer shroud disposed at the other end of the blade form and supporting the blade form, opposite to the inner shroud; the first cooling flow path and the second cooling flow path are formed inside and continue along the height direction; and a first flow path bending portion connecting the first cooling flow path and the second cooling flow path; the first flow path curvature is located inside the inner shroud or the outer shroud.
The main problems existing in the prior art are as follows:
firstly, honeycomb duct structural design is complicated, and the manufacturing degree of difficulty is high. Because the shape of the flow guide pipe is generally consistent with the shape of the inner cavity of the stator blade, the flow guide pipe is an irregular three-dimensional curved surface, and the die is difficult to design and manufacture by adopting stamping forming, so that the processing yield is low and the cost is high.
And secondly, the thermal stress of the tail edge of the stator blade is concentrated. The tail edge cooling gas of the stator blade comes from the outlet of the compressor, compared with the gas with very low temperature, the tail edge cooling gas enters the tail edge chamber and flows out from the split joint after the heat exchange of the tail edge column and the rib, the metal temperature of the inner wall surface of the tail edge is locally reduced by the cooling gas in the process, the uniformity of the temperature of the whole blade is poor, the thermal stress of the tail edge of the stator blade is concentrated, the tail edge of the stator blade becomes a failure concentrated point of the stator blade, and the service life of the stator blade is shortened.
In view of the foregoing, there is a need for a composite cooling structure for turbine stator blades of a gas turbine, which reduces manufacturing difficulty of a guide pipe, reduces thermal stress concentration at a trailing edge of the stator blade, and prolongs service life of the stator blade.
Disclosure of Invention
In order to solve the problems, the invention provides a composite cooling structure of a turbine stator blade of a gas turbine.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the composite cooling structure of the turbine stator blade of the gas turbine comprises stator blades, wherein the stator blades are hollow cooling blades, four hollow inner cavities are formed in the stator blades, and a core insert is arranged in each hollow inner cavity; the hollow inner cavity close to the front edge of the stator blade is a first inner cavity, the hollow inner cavity close to the tail edge of the stator blade is a fourth inner cavity, the insert core in the first inner cavity is a first insert core, and the insert core in the fourth inner cavity is a fourth insert core;
the first inserting core is of a thin-wall annular structure, two ends of the first inserting core are open, and the cross section of the first inserting core is of an open type structure; the upper end of the first insert core is welded with the stator blade, and the lower end of the first insert core is connected with the stator blade through a first blanking cover; radial intervals are reserved between the first insert core and the inner wall of the static blade to form a cavity clamping structure, and a plurality of air holes are formed in the surface of the first insert core; and a plurality of air film holes are formed in the side wall of the static blade.
Further, the fourth lock pin is of a thin-wall linear structure, the upper end of the fourth lock pin is welded with the stator blade, the lower end of the fourth lock pin is welded with the stator blade, and a plurality of air holes are formed in the fourth lock pin.
Further, a plurality of turbulent flow columns and a plurality of ribs are sequentially arranged at the tail edges of the static blades, and cooling air sequentially flows out through gaps among the turbulent flow columns and gaps among the ribs and split seams at the tail edges of the static blades.
Further, the diameter E of the spoiler column ranges from: e is more than or equal to 0.5mm and less than or equal to 4mm.
Further, the rib has a width M in the range of: m is more than or equal to 1mm and less than or equal to 5mm, and the range of the gap K of the rib is as follows: k is more than or equal to 1mm and less than or equal to 5mm.
Further, the gas turbine stator blade composite cooling structure further comprises a second inner cavity and a third inner cavity, wherein the second inner cavity is arranged between the first inner cavity and the third inner cavity, the third inner cavity is arranged between the second inner cavity and the fourth inner cavity, and the third inner cavity is communicated with the fourth inner cavity; two second lock pins are oppositely arranged in the second inner cavity, and a radial space is reserved between the second lock pins and the inner wall of the stator blade to form a cavity clamping structure; a third insert core is arranged in the third inner cavity, and a radial interval is reserved between the third insert core and the inner wall of the stator blade to form a cavity clamping structure; the second lock pin is provided with a plurality of air holes, and the third lock pin is provided with a plurality of air holes.
Further, a first partition plate is arranged between the first inner cavity and the second inner cavity, a bulge is arranged in the middle of the first partition plate, two ends of an opening of the cross section of the first inserting core are welded with the bulge part of the first partition plate, and one end of the second inserting core is welded with the bulge part of the first partition plate; a second partition plate is arranged between the second inner cavity and the third inner cavity, a bulge is arranged in the middle of the second partition plate, and the other end of the second lock pin is welded with the bulge part of the second partition plate.
Furthermore, the second lock pin is of a thin-wall structure, the cross section of the second lock pin is U-shaped, the upper end of the second lock pin is welded with the stator blade, and the lower end of the second lock pin is connected with the stator blade through a second blocking cover.
Furthermore, the third lock pin is of a thin-wall annular structure, the upper end of the third lock pin is provided with a flange, the third lock pin is welded with the stator blade through the flange, the lower end of the third lock pin is closed, and the lower end of the third lock pin is a free end.
Further, a first partition plate is arranged between the first inner cavity and the second inner cavity, grooves are formed in two ends of the first partition plate, two ends of an opening of the cross section of the first inserting core are inserted into the grooves of the first partition plate, which are close to the first inner cavity, and one end of the second inserting core is inserted into the grooves of the first partition plate, which are close to the second inner cavity; a second partition plate is arranged between the second inner cavity and the third inner cavity, grooves are formed in two ends of the second partition plate, and the other end of the second lock pin is inserted into the grooves, close to the second inner cavity, of the second partition plate.
Further, the second lock pin is of a thin-wall structure, and the cross section of the second lock pin is of a linear structure.
Further, the third inserting cores are of thin-wall structures, the number of the third inserting cores is two, and the cross sections of the two third inserting cores are of linear structures; a third partition plate is arranged between the third inner cavity and the fourth inner cavity, grooves are formed in two ends of the third partition plate, one end of the third insert core is inserted into the groove, close to the third inner cavity, of the second partition plate, and the other end of the third insert core is inserted into the groove, close to the third inner cavity, of the third partition plate; the upper end of the third lock pin is welded with the stator blade, the lower end of the third lock pin is closed, and the lower end of the third lock pin is a free end.
Cooling air enters from the tops of the first inner cavity, the second inner cavity and the third inner cavity, and the cooling air entering the first inner cavity flows into main flow fuel gas from the air film holes on the static blades through the air holes on the first insert core; cooling air entering the second inner cavity flows into main flow fuel gas from the air film holes on the stator blades through the air holes on the second insert core; and cooling air entering the third inner cavity partially flows into the main flow gas from the air film holes on the static blades through the air holes on the third insert core, partially flows into the fourth inner cavity, partially flows into the main flow gas through the air film holes on the static blades, partially flows into the main flow gas through the air holes on the fourth insert core, sequentially passes through the vortex columns and the ribs, and flows into the main flow gas from the split joint of the tail edges of the static blades.
Compared with the prior art, the invention has the beneficial effects that:
(1) The first lock pin, the second lock pin and the fourth lock pin are all of non-closed structures and can be manufactured by adopting a mature stamping process, so that the shape of the curved surface of the inner wall of the blade is consistent to the shape of the curved surface of the inner wall of the blade for ensuring the same impact distance, and the difficulty in process manufacturing is reduced. The complex structure of the curved cylindrical honeycomb duct used in the traditional scheme is abandoned, and the curved cylindrical honeycomb duct becomes an effective way for reducing the manufacturing difficulty and cost of the stator blade.
(2) The cooling structure fully considers the characteristics of temperature distribution of the stator blade during working, and the front edge and the whole suction surface of the stator blade are subjected to efficient impact cooling by inserting the insert core; in order to reduce the thermal stress of the tail edge, the traditional scheme is abandoned, low-temperature cooling gas with small flow is directly supplied into the tail edge column-rib cavity, and the cooling gas with large flow reaches the tail edge column-rib and the split joint part for cooling after being fully subjected to heat exchange and temperature rise in the third cavity and the fourth cavity. The stepped utilization of cooling air cooling capacity is realized, cooling efficiency is improved, meanwhile, the overall temperature uniformity of the blade is improved, thermal stress is reduced, the failure probability of the tail edge of the stator blade is reduced, and the service life of the blade is prolonged.
(3) The invention controls the flow speed and turbulence of the cooling air flow by limiting the sizes of the turbulence columns and the ribs, thereby controlling the heat exchange quantity of the cooling air and the blades, leading the temperature at the tail edge to be more uniform and having smaller thermal stress.
Drawings
Fig. 1 is a schematic external structure of a first embodiment of the present invention.
Fig. 2 is a cross-sectional view A-A of fig. 1.
Fig. 3 is a sectional view of B-B of fig. 2.
Fig. 4 is a D-D cross-sectional view of fig. 3.
Fig. 5 is a sectional E-E view of fig. 3.
Fig. 6 is a partial enlarged view of fig. 3 at C.
Fig. 7 is a partial enlarged view of F in fig. 3.
Fig. 8 is a cross-sectional view of a second embodiment of the present invention.
Reference numerals illustrate:
1-stationary blades; 2-a first ferrule; 3-a second ferrule; 4-a third ferrule; 5-fourth ferrule; 6-upper blanking cover; 7-a first blanking cover; 8-a second blanking cover; 9-a third blanking cover;
101-air film holes; 102-a turbulent flow column; 103-ribs; 104-splitting; 105-upper edge plate; 106, a lower edge plate; 107-a first separator; 108-a second separator; 109-a third separator;
200-pore; 201-a first lumen; 202-a second lumen; 203-a third lumen; 204-fourth lumen.
Detailed Description
The technical solutions of the present invention will be clearly described below with reference to the accompanying drawings, and it is obvious that the described embodiments are not all embodiments of the present invention, and all other embodiments obtained by a person skilled in the art without making any inventive effort are within the scope of protection of the present invention. It should be noted that, the positional or positional relationship indicated by the terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", etc. are based on the positional or positional relationship shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Example 1
1-6, the invention provides a composite cooling structure of a turbine stator blade of a gas turbine, which comprises a stator blade 1, wherein the stator blade 1 is a hollow cooling blade, the upper end of the stator blade 1 is provided with an upper edge plate 105, the lower end is provided with a lower edge plate 106, and a plurality of air-vent film holes 101 are arranged on the side wall of the stator blade 1; the inside of the stator blade 1 is provided with a first baffle 107, a second baffle 108 and a third baffle 109, a first inner cavity 201 is formed between the front edge of the stator blade 1 and the first baffle 107, a second inner cavity 202 is formed between the first baffle 107 and the second baffle 108, a third inner cavity 203 is formed between the second baffle 108 and the third baffle 109, and a fourth inner cavity 204 is formed between the third baffle 109 and the tail edge; a first blanking cover 7 is arranged below the first inner cavity 201, a boss is arranged on the first blanking cover 7, and the boss of the first blanking cover 7 is embedded into the lower end of the first inner cavity 201 and is welded with the stator blade 1; a gap is reserved between the side face of the boss of the first blanking cover 7 and the inner wall of the stator blade 1, a first insert core 2 is arranged in the first inner cavity 201, the first insert core 2 is of a thin-wall annular structure, two ends of the first insert core are open, and the cross section of the first insert core 2 is of an open structure; the outer wall of the upper end of the first lock pin 2 is welded with the upper edge plate 105 in an annular mode, the lower end of the first lock pin 2 is inserted into a gap between the first blanking cover 7 and the lower edge plate 106, and the first lock pin 2 is in clearance fit with the first blanking cover 7; a certain gap is reserved between the first insert core 2 and the inner wall of the stator blade 1, a plurality of air holes 200 are formed in the first insert core 2, cooling air flows in from an upper end opening of the first insert core 2, the cooling air impacts the inner wall of the stator blade 1 through the air holes 200 in the first insert core 2, then the cooling air flows in main flow gas from the gas film holes 101 in the stator blade 1, and a gas mold with lower temperature is formed on the outer surface of the stator blade 1 under the action of pressure and friction force of the main flow gas, so that the stator blade 1 is thermally insulated and cooled.
The middle position of the first partition plate 107 is provided with bulges towards the first inner cavity 201 and the second inner cavity 202, two ends of the opening on the cross section of the first insert core 2 are provided with folded edges, and the outer wall of the folded edge of the first insert core 2 is contacted with the first partition plate 107 and is abutted against the bulges of the first partition plate 107.
A second blanking cover 8 is arranged below the second inner cavity 202, a boss is arranged on the second blanking cover 8, the boss of the second blanking cover 8 is embedded into the second inner cavity 202, and a gap is reserved between the boss of the second blanking cover 8 and the inner wall of the stator blade 1; the second inner cavity 202 is internally provided with second lock pins 3, the number of the second lock pins 3 is two, the second lock pins 3 are of a thin-wall structure, two ends of the second lock pins are open, the cross section of the second lock pins 3 is U-shaped, the outer wall of the upper end of each second lock pin 3 is welded with the upper edge plate 105 in an annular mode, the lower end of each second lock pin 3 is inserted into a gap between the second plug cover 8 and the stationary blade 1, and the second lock pins 3 are in clearance fit with the second plug cover 8; a gap is reserved between the side surface of the second insert core 3 and the stator blade 1, a plurality of air holes 200 are formed in the second insert core 3, cooling air flows in from an upper end opening of the second insert core 3, the cooling air impacts the inner wall of the stator blade 1 through the air holes 200 in the second insert core 3, and then the cooling air flows in main flow gas from the air film holes 101 in the stator blade 1.
The middle part position of the second partition plate 108 is provided with a bulge towards the second inner cavity 202, the outer wall of the folded edge at one side of the second lock pin 3 is contacted with the first partition plate 107 and is abutted against the bulge of the first partition plate 107, and the outer wall of the folded edge at the other side of the second lock pin 3 is contacted with the second partition plate 108 and is abutted against the bulge of the second partition plate 108.
The lower parts of the third inner cavity 203 and the fourth inner cavity 204 are communicated, a third blanking cover 9 is arranged below the third inner cavity 203 and the fourth inner cavity 204, a boss is arranged on the third blanking cover 9, and the boss of the third blanking cover 9 is embedded into an annular space formed by the second partition plate 108 and the lower edge plate 106; the third inner cavity 203 is internally provided with a third inserting core 4, the third inserting core 4 is of a thin-wall annular structure, the upper end of the third inserting core 4 is provided with an opening, the upper end of the third inserting core 4 is provided with a flange, the third inserting core 4 is welded with the stator blade 1 through the flange, the lower end of the third inserting core 4 is closed, and the lower end of the third inserting core 4 is a free end. The cross section of the third lock pin 4 is quadrilateral, each side is a straight line segment, and a certain gap is reserved between each side and the inner wall of the stator blade.
The lower opening of the third partition plate 109 enables the third inner cavity 203 to be communicated with the fourth inner cavity 204 in the lower direction, an upper blanking cover 6 is arranged above the fourth inner cavity 204, a boss is arranged on the upper blanking cover 6, the boss of the upper blanking cover 6 is embedded into an annular space formed by the third partition plate 109 and the upper edge plate 105, and the upper end of the fourth inner cavity 204 is closed; a fourth insert core 5 is arranged in the fourth inner cavity 204, the fourth insert core 5 is of a thin-wall linear structure, the upper end of the fourth insert core 5 is inserted into a gap between the upper blanking cover 6 and the upper edge plate 105, the lower end of the fourth insert core 5 is welded with the lower edge plate 106, and a plurality of air holes 200 are formed in the fourth insert core 5; one side edge of the fourth lock pin 5 is provided with a folded edge, the folded edge is connected with the third partition plate 109 in a welding way, and the other side edge of the fourth lock pin 5 is connected with the tail edge of the stator blade 1 in a welding way.
Cooling air flows in from the upper opening of the third inner cavity 203, one part of the cooling air impacts the inner wall of the stator blade 1 through the air holes 200 on the third insert core 4, then flows into main flow fuel gas from the air film holes 101 on the stator blade 1, and the other part of the cooling air enters the fourth inner cavity 204 from the opening below the third inner cavity 203 through the air holes 200 on the third insert core 4; one part of the cooling air entering the fourth inner cavity 204 flows into the main flow gas through the gas film holes 101 on the stator blade 1, and the other part flows out of the split joint 104 of the stator blade 1 through the gas holes 200 on the fourth insert core 5.
The tail edge of the stator blade 1 is sequentially provided with a plurality of turbulence columns 102 and a plurality of ribs 103, and part of cooling air in the fourth inner cavity 204 sequentially passes through the fourth insert core 5, gaps among the turbulence columns 102 and gaps among the ribs 103 and flows out through split seams 104 of the tail edge of the stator blade. Referring to fig. 7, the diameter E of the spoiler column 102 ranges from: e is more than or equal to 0.5mm and less than or equal to 4mm. The width M of the ribs 103 ranges from: m is more than or equal to 1mm and less than or equal to 5mm, and the range of the clearance K of the rib 103 is as follows: k is more than or equal to 1mm and less than or equal to 5mm.
Because the cooling air in the fourth inner cavity 204 comes from the third inner cavity 203, the temperature of the cooling air entering the fourth inner cavity 204 is higher than that of the inlet of the third inner cavity 203, the temperature difference between the tail edge and the cooling air is relatively reduced, the thermal stress is reduced, the failure probability of the tail edge of the stator blade is further reduced, and the service life of the stator blade 1 is prolonged.
Referring to fig. 6, the ratio of the distance L between the first ferrule 2 and the inner wall of the stator blade 1 to the aperture D of the air hole 200 on the first ferrule 2 is: the ratio of the distance L between the second lock pin 3, the third lock pin 4 and the fourth lock pin 5 and the inner wall of the stator blade 1 to the pore diameter D of the corresponding lock pin is also equal to or less than 1 and equal to or less than 6, and accordingly, the air mold formed by the outer wall of the stator blade can be ensured, and the cooling effect is better.
Example two
Referring to fig. 8, the difference between the present embodiment and the first embodiment is that: the middle part of the first partition plate 107 is not provided with a bulge, two ends of the first partition plate 107 are provided with four grooves, each groove comprises two grooves in the first inner cavity 201 and two grooves in the second inner cavity 202, the cross section of the first insert core 2 is U-shaped, and two side edges of the first insert core 2 are inserted into the grooves on the first partition plate 107 for positioning; the middle part of the second partition board 108 is not provided with a bulge, two ends of the second partition board 108 are provided with four grooves, the four grooves comprise two grooves in the second inner cavity 202 and two grooves in the third inner cavity 203, the second lock pin 3 is a straight sheet or an arc sheet with a certain radian, one end side edge of the two second lock pins 3 is inserted into the groove of the first partition board 107, and the other end side edge of the second lock pin 3 is inserted into the groove of the second partition board 108 for positioning.
The third partition 109 is not provided with a bulge, the two ends of the third partition 109 are provided with three grooves, the three grooves comprise two grooves in the third inner cavity 203 and one groove in the fourth inner cavity 204, the number of the third inserting cores 4 is two, the third inserting cores 4 are straight sheets or arc sheets with a certain radian, one end side edges of the two third inserting cores 4 are inserted into the grooves of the second partition 108, and the other end side edges of the third inserting cores 4 are inserted into the grooves of the third partition 109 for positioning.
The fourth lock pin 5 is a straight sheet, one end side edge of the fourth lock pin 5 is inserted into a groove of the third partition plate 109 to be positioned, and the other end side edge of the fourth lock pin 5 is welded and fixed with the inner wall at the tail edge of the stator blade 1.
The above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to examples, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the scope of the technical solution of the present invention, which is intended to be covered by the claims of the present invention.
Claims (10)
1. The composite cooling structure of the turbine stator blade of the gas turbine comprises stator blades, wherein the stator blades are hollow cooling blades, four hollow inner cavities are formed in the stator blades, and a core insert is arranged in each hollow inner cavity; the hollow inner cavity close to the front edge of the stator blade is a first inner cavity, the hollow inner cavity close to the tail edge of the stator blade is a fourth inner cavity, the insert core in the first inner cavity is a first insert core, and the insert core in the fourth inner cavity is a fourth insert core;
the novel optical fiber connector is characterized in that the first inserting core is of a thin-wall annular structure, two ends of the first inserting core are open, and the cross section of the first inserting core is of an open type structure; the upper end of the first insert core is welded with the stator blade, and the lower end of the first insert core is connected with the stator blade through a first blanking cover; radial intervals are reserved between the first insert core and the inner wall of the static blade to form a cavity clamping structure, and a plurality of air holes are formed in the surface of the first insert core; a plurality of air film holes are formed in the side wall of each static blade;
the gas turbine stator blade composite cooling structure further comprises a second inner cavity and a third inner cavity, wherein the second inner cavity is arranged between the first inner cavity and the third inner cavity, the third inner cavity is arranged between the second inner cavity and the fourth inner cavity, and the third inner cavity is communicated with the fourth inner cavity; two second lock pins are oppositely arranged in the second inner cavity, and a radial space is reserved between the second lock pins and the inner wall of the stator blade to form a cavity clamping structure; a third insert core is arranged in the third inner cavity, and a radial interval is reserved between the third insert core and the inner wall of the stator blade to form a cavity clamping structure; the second inserting core is provided with a plurality of air holes, and the third inserting core is provided with a plurality of air holes; and sealing covers are welded on the upper part and the lower part of the fourth inner cavity, and cooling gas is from the third inner cavity.
2. The gas turbine stator blade composite cooling structure of claim 1, wherein the fourth insert core is of a thin-wall linear structure, the upper end of the fourth insert core is welded with the stator blade, the lower end of the fourth insert core is welded with the stator blade, and a plurality of air holes are formed in the fourth insert core.
3. The composite cooling structure of the turbine stator blade of the gas turbine according to claim 1, wherein a plurality of turbulence columns and a plurality of ribs are sequentially arranged at the tail edge of the stator blade, and cooling air sequentially flows out through gaps between the turbulence columns and gaps between the ribs and through split seams of the tail edge of the stator blade.
4. The gas turbine stator vane composite cooling structure of claim 3 wherein the diameter E of the turbulator post ranges from: e is more than or equal to 0.5mm and less than or equal to 4mm; the width M of the ribs is in the range of: m is more than or equal to 1mm and less than or equal to 5mm, and the range of the gap K of the rib is as follows: k is more than or equal to 1mm and less than or equal to 5mm.
5. The gas turbine stator vane composite cooling structure of claim 1, wherein a first partition plate is arranged between the first inner cavity and the second inner cavity, a bulge is arranged in the middle of the first partition plate, two ends of an opening of a cross section of the first insert core are welded with bulge parts of the first partition plate, and one end of the second insert core is welded with the bulge parts of the first partition plate; a second partition plate is arranged between the second inner cavity and the third inner cavity, a bulge is arranged in the middle of the second partition plate, and the other end of the second lock pin is welded with the bulge part of the second partition plate.
6. The gas turbine stator blade composite cooling structure of claim 1, wherein the second insert core is of a thin-wall structure, the cross section of the second insert core is U-shaped, the upper end of the second insert core is welded with the stator blade, and the lower end of the second insert core is connected with the stator blade through a second plug cover.
7. The gas turbine vane composite cooling structure of claim 1, wherein the second insert is of a thin-walled structure and the cross-section of the second insert is of a linear structure.
8. The gas turbine stator vane composite cooling structure according to claim 1 or 6, wherein the third insert core is of a thin-wall annular structure, a flange is arranged at the upper end of the third insert core, the third insert core is welded with the stator vane through the flange, the lower end of the third insert core is closed, and the lower end of the third insert core is a free end.
9. The gas turbine stator vane composite cooling structure of claim 5, wherein the third insert cores are of a thin-wall structure, the number of the third insert cores is two, and the cross sections of the two third insert cores are of a linear structure; a third partition plate is arranged between the third inner cavity and the fourth inner cavity, grooves are formed in two ends of the third partition plate, one end of the third insert core is inserted into the groove, close to the third inner cavity, of the second partition plate, and the other end of the third insert core is inserted into the groove, close to the third inner cavity, of the third partition plate; the upper end of the third lock pin is welded with the stator blade, the lower end of the third lock pin is closed, and the lower end of the third lock pin is a free end.
10. The gas turbine stator vane composite cooling structure of claim 1, wherein a first partition plate is arranged between the first inner cavity and the second inner cavity, grooves are formed at two ends of the first partition plate, two ends of an opening of a cross section of the first insert core are inserted into the grooves of the first partition plate, which are close to the first inner cavity, and one end of the second insert core is inserted into the grooves of the first partition plate, which are close to the second inner cavity; a second partition plate is arranged between the second inner cavity and the third inner cavity, grooves are formed in two ends of the second partition plate, and the other end of the second lock pin is inserted into the grooves, close to the second inner cavity, of the second partition plate.
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| CN202210086255.9A CN114370305B (en) | 2022-01-25 | 2022-01-25 | Composite cooling structure for turbine stator blades of gas turbine |
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| CN202210086255.9A CN114370305B (en) | 2022-01-25 | 2022-01-25 | Composite cooling structure for turbine stator blades of gas turbine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0785339A1 (en) * | 1996-01-04 | 1997-07-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Cooled turbine vane |
| CN202023597U (en) * | 2011-04-21 | 2011-11-02 | 西北工业大学 | Shrouded cooling blade of gas turbine |
| EP2711502A1 (en) * | 2011-05-13 | 2014-03-26 | Mitsubishi Heavy Industries, Ltd. | Turbine stator vane |
| CN108757047A (en) * | 2018-05-25 | 2018-11-06 | 哈尔滨工程大学 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
| CN109139128A (en) * | 2018-10-22 | 2019-01-04 | 中国船舶重工集团公司第七0三研究所 | A kind of marine gas turbine high-pressure turbine guide vane cooling structure |
-
2022
- 2022-01-25 CN CN202210086255.9A patent/CN114370305B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0785339A1 (en) * | 1996-01-04 | 1997-07-23 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Cooled turbine vane |
| CN202023597U (en) * | 2011-04-21 | 2011-11-02 | 西北工业大学 | Shrouded cooling blade of gas turbine |
| EP2711502A1 (en) * | 2011-05-13 | 2014-03-26 | Mitsubishi Heavy Industries, Ltd. | Turbine stator vane |
| CN108757047A (en) * | 2018-05-25 | 2018-11-06 | 哈尔滨工程大学 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
| CN109139128A (en) * | 2018-10-22 | 2019-01-04 | 中国船舶重工集团公司第七0三研究所 | A kind of marine gas turbine high-pressure turbine guide vane cooling structure |
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| CN114370305A (en) | 2022-04-19 |
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Address after: No. 1188, Dongxin Road, Hangzhou, Zhejiang, 310022 Applicant after: Hangzhou Steam Turbine Holding Co.,Ltd. Address before: No. 1188, Dongxin Road, Hangzhou, Zhejiang, 310022 Applicant before: HANGZHOU TURBINE POWER GROUP CO.,LTD. |
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