CN105673089A - Crown-free air film cooling rotor blade for turbine of gas turbine - Google Patents
Crown-free air film cooling rotor blade for turbine of gas turbine Download PDFInfo
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- CN105673089A CN105673089A CN201610193629.1A CN201610193629A CN105673089A CN 105673089 A CN105673089 A CN 105673089A CN 201610193629 A CN201610193629 A CN 201610193629A CN 105673089 A CN105673089 A CN 105673089A
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- internal combustion
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
Abstract
The invention belongs to the technical field of gas turbine equipment, and particularly relates to a crown-free air film cooling rotor blade for a turbine of a gas turbine. The crown-free air film cooling rotor blade comprises a tenon root, an extending root, a margin plate and a blade profile; the tenon root is in transition connection with the blade profile through the extending root, air film holes are formed in the blade profile, and a blade top boss is arranged at the top of the blade profile; a first front cavity, a second front cavity, a first back cavity, a second back cavity and a tail edge chopping seam are formed inside the blade, rough ribs are arranged in the first front cavity, and the first front cavity and the second front cavity are separated through a metal separating plate integrated with a blade body; not less than one row of impact throttles are arranged on the metal separating plate, the first back cavity and the second back cavity form an inversed U-shaped cavity through the metal separating plate, rough ribs are arranged in the first back cavity, and turbulent flow columns are arranged in the second back cavity; pollution discharge holes are formed in the top end of the blade profile; and the blade top boss is in design of a semi-closed structure, and the molded line of the blade top boss is in smooth transition with the blade profile. The crown-free air film cooling rotor blade is simple in structure, reasonable in design, high in cold air using rate, efficient and low in manufacturing cost, and saves energy.
Description
Technical field:
The invention belongs to gas-turbine plant technical field, it is specifically related to a kind of internal combustion turbine turbine without hat gaseous film control spinner blade.
Background technology:
Improve the thermo-efficiency that internal combustion turbine turbine-entry temperature can effectively improve unit, current turbine-entry temperature is considerably beyond the heatproof limit of metallic substance, the main technique means of turbine blade thermal protection is comprised and uses cooling air to cool and at blade trypsin method thermal barrier coating, along with Materials science development, improving the metallic substance heatproof limit more and more difficult, potentiality are more and more less; Can expecting, efficient cooling structure can be increasing for the contribution improving turbine-entry temperature. Turbine rotor blade is all operated in the severe environment of high temperature, high pressure, high rotating speed in major part life cycle, inner high-efficient cooling structure can reduce metallic surface temperature, extend blade work-ing life, the turbine rotor blade of current band cooling structure is all processed by precision casting, therefore cooling structure also must be beneficial to casting, to improve yield rate. So, design a kind of can improve the high internal combustion turbine turbine of cold air utilization ratio without hat gaseous film control spinner blade be very necessary.
Summary of the invention:
The present invention makes up and improves above-mentioned the deficiencies in the prior art part, provide that a kind of structure is simple, reasonable in design, a kind of internal combustion turbine turbine of cold air utilization ratio height, energy-efficient, low cost of manufacture is without hat gaseous film control spinner blade, it is possible to promotes on a large scale and uses.
The technical solution used in the present invention is: a kind of internal combustion turbine turbine, without hat gaseous film control spinner blade, comprises tenon root, stretches root, listrium and blade profile, and by stretching, root transition is connected tenon root with blade profile, and blade profile is provided with air film hole, and blade profile top is provided with leaf top boss; This blade interior defines the first ante-chamber, the 2nd ante-chamber, the first rear chamber, the 2nd rear chamber and tail edge and splits seam, coarse rib it is provided with in first ante-chamber, metal isolation plate isolation by being integrated with blade between first ante-chamber and the 2nd ante-chamber, metal isolation plate is provided with the impact throttling being not less than 1 row, after first, behind chamber and the 2nd, chamber defines inverted U-shaped cavity by metal isolation plate, it is furnished with coarse rib in chamber after first, after the 2nd, in chamber, it is provided with turbulence columns;Described blade profile top is provided with blowdown hole.
After described the first ante-chamber, the 2nd ante-chamber, first, behind chamber, the 2nd, chamber and tail edge split the cooling channel structure that seam defines spinner blade, wherein first via cold air enters the first ante-chamber along tenon root bottom part, enter the 2nd ante-chamber through impacting after throttle orifice distributes, then sprayed by the air film hole of leading edge locus; 2nd road cold air enters chamber after first along tenon root position, after U-shaped cavity is turned position enter the 2nd after chamber, the passage finally splitting seam according to Resistance Distribution along tail edge flows out.
After described the first ante-chamber, the 2nd ante-chamber, first, behind chamber, the 2nd, chamber and tail edge are split the cooling circulation part that seam defined spinner blade and are sprayed thermal barrier coating, spraying tack coat between thermal barrier coating and metal prevents thermal barrier coating from coming off, its blade cooling passage can metallic cementation preservative coat, prevent blade internal corrosion in high salinity Working environment.
Described leaf top boss designs for semi-closed structure, and its type line and blade profile smoothly transit, pressure face side, leaf top near tail edge without boss.
After the 2nd described ante-chamber and the 2nd, chamber is provided with stifled head, and it is convenient to remove inner runner core, and when precision casting, this position is a cavity, during cast blade off-type core, the lysate of cooling flow channel type core flows out from this cavity, and after having taken off type core, this position uses stifled head to close.
Coarse rib also can be arranged in the non-air film hole position of the 2nd described ante-chamber, and arranges 2～3 exhaust membrane holes at the leading edge locus of the 2nd ante-chamber.
Metal isolation plate between the rear chamber of described first and the 2nd rear chamber can arrange by-pass port, with the cold air distributed after the 2nd in chamber.
Described turbulence columns adopts the mode of wrong row to be arranged in the 2nd rear chamber.
The shape that described tail edge splits seam can be designed to be with the rectangle of fillet, circle, band to fall the zig-zag of fillet.
Described blowdown hole is arranged in each stream road blade tip position, and blowdown hole is blocked by leaf top boss, and washing away to avoid high-speed fuel gas affects filth-discharging effect, and blowdown hole utilizes centrifugal force to be discharged by dust.
The useful effect of the present invention: structure is simple, and reasonable in design, cold air utilization ratio height, energy-efficient, low cost of manufacture, is easy to promote on a large scale and use. Turbine rotor blade is all operated in the severe environment of high temperature, high pressure, high rotating speed in major part life cycle, and inner nothing hat gaseous film control structure can reduce metallic surface temperature, extends the work-ing life of blade. During operation, first via cold air enters in the middle part of blade, then flows to blade inlet edge air film hole, is conducive to improving the utilization ratio of cold air; First via orifice structure can regulate the total flux flowing to air film cold air and air film to distribute along the cold air flow of depth of blade, is conducive to reducing blade metallic portion thermograde; The U-shape structure on the 2nd tunnel had both improve the utilization ratio of cold air, turn avoid cold air resistance too big; The blowdown hole on leaf top can avoid cooling structure to be blocked by dust, and leaf top boss semi-closed structure can alleviate blade quality, reduces blade tip clearance, raises the efficiency under the prerequisite ensureing reliability. Cooling flowing path arranges stifled header structure, interior cold runner ceramic core and metal separation when being conducive to casting, it is to increase blade yield rate. Spray thermal barrier coating at blade flow-path, between thermal barrier coating and metal, spray tack coat prevent thermal barrier coating from coming off. Blade cooling passage can metallic cementation preservative coat, prevent blade internal corrosion in high salinity Working environment.The cooling structure of this blade can effectively reduce metallic surface temperature, and the advantage of this cooling structure is cold air utilization ratio height, and resistance is little, and the special construction at blade top when not having integral shroud, can effectively reduce blade tip clearance, it is to increase turbine efficiency.
Accompanying drawing illustrates:
Fig. 1 is the three-dimensional structure schematic diagram of the present invention.
Fig. 2 is the cross-sectional view of the present invention.
Fig. 3 is the cooling structure schematic diagram of the present invention.
Fig. 4 is the position view in blowdown hole in the present invention.
Embodiment:
With reference to each figure, a kind of internal combustion turbine turbine, without hat gaseous film control spinner blade, comprises tenon root 1, stretches root 2, listrium 3 and blade profile 4, and by stretching, root 2 transition is connected tenon root 1 with blade profile 4, and blade profile 4 is provided with air film hole 6, and blade profile 4 top is provided with leaf top boss 5; This blade interior defines the first ante-chamber 14, the rear chamber 15 of the 2nd ante-chamber 13, first, the 2nd rear chamber 16 and tail edge and splits seam 10, coarse rib 8 it is provided with in first ante-chamber 14, metal isolation plate isolation by being integrated with blade between first ante-chamber 14 and the 2nd ante-chamber 13, metal isolation plate is provided with the impact throttling 11 being not less than 1 row, after first, behind chamber 15 and the 2nd, chamber 16 defines inverted U-shaped cavity by metal isolation plate, it is provided with turbulence columns 9 in chamber 16 after being furnished with coarse rib the 8, two in chamber 15 after first; Described blade profile 4 top is provided with blowdown hole 12; After first ante-chamber 14, the 2nd ante-chamber 13, first, behind chamber 15, the 2nd, chamber 16 and tail edge split the cooling channel structure that seam 10 defines spinner blade, wherein first via cold air enters the first ante-chamber 14 bottom tenon root 1, enter the 2nd ante-chamber 13 through impacting after throttle orifice 11 distributes, then sprayed by the air film hole 6 of leading edge locus; 2nd road cold air enters chamber 15 after first along tenon root 1 position, after U-shaped cavity is turned position enter the 2nd after chamber 16, the passage finally splitting seam 10 according to Resistance Distribution along tail edge flows out; Behind chamber 15, the 2nd, chamber 16 and tail edge are split the cooling circulation parts that seam 10 defined spinner blade and are sprayed thermal barrier coating after first ante-chamber 14, the 2nd ante-chamber 13, first, spraying tack coat between thermal barrier coating and metal prevents thermal barrier coating from coming off, its blade cooling passage can metallic cementation preservative coat, prevent blade internal corrosion in high salinity Working environment; Described leaf top boss 5 designs for semi-closed structure, and its type line and blade profile 4 smoothly transit, and pressure face side, leaf top is without boss near tail edge, and this boss adopts built-up welding boss structure, and pressure face is not closed near position, tail edge; After the 2nd described ante-chamber 13 and the 2nd, chamber 16 is provided with stifled 7, and it is convenient to remove inner runner core, and when precision casting, this position is a cavity, during cast blade off-type core, the lysate of cooling flow channel type core flows out from this cavity, and after having taken off type core, this position uses stifled 7 to close; Coarse rib 8 also can be arranged in the non-air film hole position of the 2nd ante-chamber 13, and arranges 2～3 exhaust membrane holes 6 at the leading edge locus of the 2nd ante-chamber 13; Metal isolation plate between first rear chamber 15 and the 2nd rear chamber 16 can arrange by-pass port, with the cold air distributed after the 2nd in chamber 16; Described turbulence columns 9 adopt the mode of wrong row to be arranged in the 2nd after in chamber 16, turbulence columns 9 and coarse rib 8, be used for enhanced heat exchange; The shape that described tail edge splits seam 10 can be designed to be with the rectangle of fillet, circle, band to fall the zig-zag of fillet; Described blowdown hole 12 is arranged in each stream road blade tip position, and blowdown hole 12 is blocked by leaf top boss 5, and washing away to avoid high-speed fuel gas affects filth-discharging effect, and blowdown hole 12 utilizes centrifugal force to be discharged by dust.
This turbine rotor blade main body is processed by precision casting, and wherein air film hole 6, tail edge split seam 10 and blowdown hole 12 all adopts electromachining, and leaf roof construction built-up welding is processed. tenon root 1 is the connecting portion of blade and the turbine disk, needs to meet intensity criterion when designing, stretching root 2 is the transition structure between tenon root 1 and blade profile, and the outside stretching root 2 cools the heat that can reduce high-temperature fuel gas and transmit to tenon root 1 position by cold air, listrium 3 ensures the flow passage of combustion gas according to design, blade profile position needs to meet pneumatic requirement and requirement of strength. blade top is semiclosed boss structure, type line and the blade profile of leaf top boss 5 should smoothly transit, and ensure good aerodynamic characteristic, and the scantlings of the structure of boss should be determined according to pneumatic, intensity net effect, boss adopts the mode of built-up welding to process, and material and airfoil portion divide identical. the angle of the coarse rib 8 of the first ante-chamber 14 access arrangement can be level, it can also be band angle, coarse rib 8 with angle is in pressure face side and surface side staggered arrangement, the cross section size of coarse rib 8, length, angle, spacing distance, quantity are determined according to the net effect of heat transfer and flow friction characteristics, and its geometric parameter also will in conjunction with the precision of precision casting. plate isolation is isolated by metal between first ante-chamber 14 and the 2nd ante-chamber 13, metal isolation plate and blade are one, metal isolation plate arranges a row or multi-row impact orifice structure, regulate the cold air in the 2nd ante-chamber 13 along the distribution of blade radial by impacting the size in throttling 11 holes, also regulating the first ante-chamber 14 and the cold air flow of the 2nd ante-chamber 13, the result that the size impacting throttle orifice 11 is calculated by pipe network flow resistance is determined. coarse rib 8 can also be arranged in 2nd ante-chamber 13 non-air film hole position, the geometric parameter of coarse rib 8 is determined by the net effect of heat transfer and flow friction characteristics, 2nd ante-chamber 13 arranges 2～3 exhaust membrane holes 6 at leading edge locus, cold air covers blade pressure face and surface position after spraying along air film hole 6 respectively, isolation high-temperature fuel gas, air film, the quantity of 6, angle, aperture are obtained by Flow-induced vibration calculation optimization, and film hole structure is obtained by the mode of electromachining. after first, the heat exchange of the coarse rib Final 8 is arranged in chamber 15, the geometric parameter defining method of coarse rib 8 is identical with the first ante-chamber 14, after first, behind chamber 15 and the 2nd, chamber 16 forms inverted u-shaped structure, isolate plate by metal and separate room, two chambeies, metal isolation plate and blade are one, metal isolation plate can arrange by-pass port, distribute the cold air in chamber 16 after the 2nd, turbulence columns 9 is arranged in chamber 16 after 2nd, increase the indoor cold air turbulivity in chamber, strengthen heat exchange effect, arrange flow-disturbing more, 9 adopt the structure formation of wrong row, the distribution of turbulence columns 9, diameter, quantity is determined by the net effect of heat transfer and flow friction characteristics. the shape that tail edge splits seam 10 has band to fall the rectangle of fillet, circle, band to fall the zig-zag of fillet, tail edge splits shape and the geometric parameter of seam 10 by the net effect decision of heat exchange and flow resistance, the intensity of type core when must consider to cast in addition, circular tail edge is split crack structure and is obtained by the mode of electromachining, and the structure of all the other shapes is processed by precision casting. blowdown hole 12 is arranged in each stream road blade tip position, blowdown hole 12 should be blocked by boss, avoid high-speed fuel gas to wash away and affect filth-discharging effect, the geometric parameter in blowdown hole 12 is determined: the air conditioning quantity flowed out through blowdown hole 12 can not be too many, and the size in blowdown hole 12 must ensure that dust can be discharged smoothly according to two principles.Stifled 7 is a cavity when precision casting, and during cast blade off-type core, the lysate of cooling flow channel type core flows out from this cavity, and after having taken off type core, this position uses stifled header structure to close. In order to reduce the metal temperature of spinner blade further, spray thermal barrier coating at blade flow-path. Spraying tack coat between thermal barrier coating and metal prevents thermal barrier coating from coming off. Blade cooling passage can ooze non-corrosive metal (NCM) layer, prevents blade internal corrosion in high salinity Working environment.
First via cold air enters in the middle part of blade, then flows to blade inlet edge air film hole 6, is conducive to improving the utilization ratio of cold air; First via orifice structure can regulate the total flux flowing to air film cold air and air film to distribute along the cold air flow of depth of blade, is conducive to reducing blade metallic portion thermograde; The U-shape structure on the 2nd tunnel had both improve the utilization ratio of cold air, turn avoid cold air resistance too big; The blowdown hole 12 on leaf top can avoid cooling structure to be blocked by dust, and leaf top boss 5 semi-closed structure can alleviate blade quality, reduces blade tip clearance, raises the efficiency under the prerequisite ensureing reliability. Interior cold runner ceramic core and metal separation when being conducive to casting for stifled 7, it is to increase blade yield rate. The advantage of spinner blade cooling structure is cold air utilization ratio height, and resistance is little, and the special construction at blade top when not having integral shroud, can effectively reduce blade tip clearance, it is to increase turbine efficiency. The structure of the present invention is simple, and reasonable in design, cold air utilization ratio height, energy-efficient, low cost of manufacture, is easy to promote on a large scale and use.
Claims (10)
1. an internal combustion turbine turbine is without hat gaseous film control spinner blade, it is characterized in that: this blade comprises tenon root (1), stretch root (2), listrium (3) and blade profile (4), by stretching, root (2) transition is connected tenon root (1) with blade profile (4), blade profile (4) is provided with air film hole (6), and blade profile (4) top is provided with leaf top boss (5), this blade interior defines the first ante-chamber (14), 2nd ante-chamber (13), chamber (15) after first, after 2nd, chamber (16) and tail edge split seam (10), coarse rib (8) it is provided with in first ante-chamber (14), metal isolation plate isolation by being integrated with blade between first ante-chamber (14) and the 2nd ante-chamber (13), metal isolation plate is provided with impact throttling (11) being not less than 1 row, after first, behind chamber (15) and the 2nd, chamber (16) defines inverted U-shaped cavity by metal isolation plate, it is furnished with coarse rib (8) in chamber (15) after first, it is provided with turbulence columns (9) in chamber (16) after 2nd, described blade profile (4) top is provided with blowdown hole (12).
2. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: after described the first ante-chamber (14), the 2nd ante-chamber (13), first, behind chamber (15), the 2nd, chamber (16) and tail edge split the cooling channel structure that seam (10) defines spinner blade, wherein first via cold air enters the first ante-chamber (14) along tenon root (1) bottom, enter the 2nd ante-chamber (13) through impacting after throttle orifice (11) distributes, then sprayed by the air film hole (6) of leading edge locus; 2nd road cold air enters chamber (15) after first along tenon root (1) position, after U-shaped cavity is turned position enter the 2nd after chamber (16), finally split the passage outflow of seam (10) along tail edge according to Resistance Distribution.
3. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: after described the first ante-chamber (14), the 2nd ante-chamber (13), first, behind chamber (15), the 2nd, chamber (16) and tail edge are split the cooling circulation part that seam (10) defined spinner blade and sprayed thermal barrier coating, spraying tack coat between thermal barrier coating and metal prevents thermal barrier coating from coming off, its blade cooling passage can metallic cementation preservative coat, prevent blade internal corrosion in high salinity Working environment.
4. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: described leaf top boss (5) is designed for semi-closed structure, its type line and blade profile (4) smoothly transit, pressure face side, leaf top near tail edge without boss.
5. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: after the 2nd described ante-chamber (13) and the 2nd, chamber (16) is provided with stifled head (7), it is convenient to remove inner runner core, when precision casting, this position is a cavity, during cast blade off-type core, the lysate of cooling flow channel type core flows out from this cavity, and after having taken off type core, this position uses stifled head (7) to close.
6. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: coarse rib (8) also can be arranged in the non-air film hole position of the 2nd described ante-chamber (13), and arrange 2～3 exhaust membrane holes (6) at the leading edge locus of the 2nd ante-chamber (13).
7. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: the metal isolation plate between the rear chamber (15) of described first and the 2nd rear chamber (16) can arrange by-pass port, with the cold air distributed after the 2nd in chamber (16).
8. one internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterised in that: described turbulence columns (9) adopts the mode of wrong row to be arranged in the 2nd rear chamber (16).
9. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterised in that: the shape that described tail edge splits seam (10) can be designed to be with the zig-zag of the rectangle of fillet, circle, band fillet.
10. a kind of internal combustion turbine turbine according to claim 1 is without hat gaseous film control spinner blade, it is characterized in that: described blowdown hole (12) is arranged in each stream road blade tip position, blowdown hole (12) is blocked by leaf top boss (5), washing away to avoid high-speed fuel gas and affect filth-discharging effect, blowdown hole (12) utilize centrifugal force to be discharged by dust.
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| CN201610193629.1A CN105673089B (en) | 2016-03-31 | 2016-03-31 | A kind of Gas Turbine is without hat gaseous film control rotor blade |
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| CN201610193629.1A CN105673089B (en) | 2016-03-31 | 2016-03-31 | A kind of Gas Turbine is without hat gaseous film control rotor blade |
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| CN105673089A true CN105673089A (en) | 2016-06-15 |
| CN105673089B CN105673089B (en) | 2018-06-29 |
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| CN106435355A (en) * | 2016-08-31 | 2017-02-22 | 南京赛达机械制造有限公司 | Water-cooled type steam turbine vane |
| CN107013255A (en) * | 2017-06-01 | 2017-08-04 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with continuous straight rib partly splits seam cooling structure |
| CN109736898A (en) * | 2019-01-11 | 2019-05-10 | 哈尔滨工程大学 | A kind of blade inlet edge gaseous film control pore structure of staggeredly compound angle |
| WO2021104002A1 (en) * | 2019-11-29 | 2021-06-03 | 大连理工大学 | Curvilinear exhaust slit structure for trailing edge of turbine blade |
| CN110863864A (en) * | 2019-12-11 | 2020-03-06 | 沈阳航空航天大学 | Turbine blade with transversely-meandering alternately-shrinking and-expanding short channels inside |
| CN110863864B (en) * | 2019-12-11 | 2022-05-10 | 沈阳航空航天大学 | Turbine blade with internal transversely-winding alternately-shrinking and-expanding short channels |
| CN112459849A (en) * | 2020-10-27 | 2021-03-09 | 哈尔滨广瀚燃气轮机有限公司 | Cooling structure for turbine blade of gas turbine |
| CN114109514A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Turbine blade pressure surface cooling structure |
| CN114109514B (en) * | 2021-11-12 | 2023-11-28 | 中国航发沈阳发动机研究所 | Turbine blade pressure surface cooling structure |
| CN115126547A (en) * | 2022-05-29 | 2022-09-30 | 中国船舶重工集团公司第七0三研究所 | Suction side exhaust air-cooled turbine movable vane tail edge structure |
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Effective date of registration: 20190805 Address after: 150078 No. 31 Honghu Road, Yingbin Road, Harbin hi tech Industrial Development Zone, Heilongjiang, Harbin, China Patentee after: Longjiang broad sail gas turbine Co., Ltd. Address before: 150000 transmission department, No. 35, Honghu Road, Daoli District, Heilongjiang, Harbin Patentee before: No.703 Inst. China Ship Heavy Industry Group Co. |