CN105673089B - A kind of Gas Turbine is without hat gaseous film control rotor blade - Google Patents
A kind of Gas Turbine is without hat gaseous film control rotor blade Download PDFInfo
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- CN105673089B CN105673089B CN201610193629.1A CN201610193629A CN105673089B CN 105673089 B CN105673089 B CN 105673089B CN 201610193629 A CN201610193629 A CN 201610193629A CN 105673089 B CN105673089 B CN 105673089B
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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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
Abstract
The invention belongs to gas-turbine plant technical fields, more particularly to a kind of Gas Turbine without hat gaseous film control rotor blade, including tenon root, root, listrium and blade profile are stretched, tenon root is connect with blade profile by stretching root transition, blade profile is equipped with air film hole, and leaf top boss is equipped at the top of blade profile；The blade interior forms the first ante-chamber, the second ante-chamber, the first back cavity, the second back cavity and trailing edge and splits seam, coarse rib is equipped in first ante-chamber, it is isolated between first ante-chamber and the second ante-chamber by the metal isolation board being integrated with blade, the impact that metal isolation board is equipped with not less than 1 row throttles, first back cavity and the second back cavity form inverted U-shaped cavity by metal isolation board, coarse rib is disposed in first back cavity, turbulence columns are equipped in the second back cavity；Blade profile top is equipped with mudhole；Leaf top boss is designed for semi-closed structure, and molded line smoothly transits with blade profile.The structure of the present invention is simple, reasonable design, and cold air utilization rate is high, energy-efficient, and manufacture is at low cost.
Description
Technical field：
The invention belongs to gas-turbine plant technical fields, turn more particularly to a kind of Gas Turbine without hat gaseous film control
Blades.
Background technology：
The thermal efficiency of unit can effectively be improved by improving Gas Turbine inlet temperature, and turbine-entry temperature has been at present
Through the resistance to extreme temperature considerably beyond metal material, cooling air is included the use of to the technical way of turbo blade thermal protection
It is cooled down and in blade trypsin method thermal barrier coating, as material science develops, improves metal material resistance to extreme temperature increasingly
Difficulty, potentiality are less and less；It is contemplated that efficient cooling structure can increasingly for improving the contribution of turbine-entry temperature
Greatly.Turbine rotor blade is all operated in most of life cycle in high temperature, high pressure, high-revolving adverse circumstances, internal high
Effect cooling structure can reduce metallic surface temperature, extend blade service life, at present the turbine rotor blade with cooling structure
All it is to be processed by hot investment casting, therefore cooling structure must also be conducive to casting, to improve yield rate.So design is a kind of
It is very necessary that the high Gas Turbine of cold air utilization rate, which can be improved, without hat gaseous film control rotor blade.
Invention content：
In place of the present invention makes up and improves above-mentioned the deficiencies in the prior art, provide a kind of simple in structure, reasonable design,
A kind of Gas Turbine that cold air utilization rate is high, energy-efficient, manufacture is at low cost is without hat gaseous film control rotor blade, Ke Yi great
Promote and use to scale.
The technical solution adopted by the present invention is：A kind of Gas Turbine without hat gaseous film control rotor blade, including tenon root,
Root, listrium and blade profile are stretched, tenon root is connect with blade profile by stretching root transition, and blade profile is equipped with air film hole, and leaf top is equipped at the top of blade profile
Boss；The blade interior forms the first ante-chamber, the second ante-chamber, the first back cavity, the second back cavity and trailing edge and splits seam, in the first ante-chamber
Equipped with coarse rib, it is isolated between the first ante-chamber and the second ante-chamber by the metal isolation board being integrated with blade, metal isolation board
It is equipped with the impact not less than 1 row to throttle, the first back cavity and the second back cavity form inverted U-shaped sky by metal isolation board
Chamber is disposed with coarse rib in the first back cavity, turbulence columns is equipped in the second back cavity；The blade profile top is equipped with mudhole.
First ante-chamber, the second ante-chamber, the first back cavity, the second back cavity and the trailing edge splits seam and forms the cold of rotor blade
But channel design, wherein first via cold air enter the first ante-chamber along tenon root bottom part, before entering second after impact throttle orifice distribution
Chamber, then sprayed by the air film hole of leading edge locus；Second road cold air enters the first back cavity along tenon root position, turns through U-shaped cavity
Position enters the second back cavity afterwards, and the channel outflow that seam is split along trailing edge is finally distributed according to resistance.
First ante-chamber, the second ante-chamber, the first back cavity, the second back cavity and the trailing edge splits seam and forms rotor blade
Cooling circulation part spraying thermal barrier coating, spraying adhesive layer prevents thermal barrier coating from coming off between thermal barrier coating and metal, leaf
Piece cooling duct can prevent the blade interior in high salt point of working environment from corroding with metallic cementation erosion resistant coating.
The leaf top boss is designed for semi-closed structure, and molded line smoothly transits with blade profile, and leaf pressure on top surface surface side is close
Trailing edge is nearby without boss.
Second ante-chamber and the second back cavity are equipped with plug, convenient for removing inner runner core, in hot investment casting
The position is a cavity, and during cast blade off-type core, the lysate of coolant flow channel core is flowed out from the cavity, has taken off core
Afterwards, which is closed using plug.
The non-air film hole site of second ante-chamber can also arrange coarse rib, and in the leading edge locus cloth of the second ante-chamber
Put 2~3 exhaust fenestras.
By-pass prot can be arranged on metal isolation board between first back cavity and the second back cavity, to distribute the second back cavity
Interior cold air.
The turbulence columns are arranged in a manner that mistake is arranged in the second back cavity.
The shape that the trailing edge splits seam may be designed as the rectangle with rounded corner, circle, the zigzag with rounded corner.
The mudhole is arranged in each flow path vane tip position, and mudhole is blocked by leaf top boss, to avoid height
Quick burning gas washes away influence filth-discharging effect, and mudhole is discharged dust using centrifugal force.
Beneficial effects of the present invention：Simple in structure, reasonable design, cold air utilization rate is high, energy-efficient, and manufacture is at low cost,
It is easy to promote and use on a large scale.Turbine rotor blade is all operated in high temperature, high pressure, high rotating speed in most of life cycle
Adverse circumstances in, it is internal to reduce metallic surface temperature without hat gaseous film control structure, extend the service life of blade.Operation
When first via cold air enter in the middle part of the blade, then flow to blade inlet edge air film hole, be conducive to improve the utilization rate of cold air；First
Road orifice structure can adjust the total flow for flowing to air film cold air and air film and is distributed along the cold air flow of blade height, favorably
In reduction blade metallic portion temperature gradient；The U-shaped structure on the second tunnel had both improved the utilization rate of cold air, in turn avoided cold air resistance
Power is too big；The mudhole on leaf top can be blocked to avoid cooling structure by dust, and leaf top boss semi-closed structure can mitigate blade
Quality reduces blade tip clearance, efficiency is improved under the premise of reliability is ensured.Cooling flowing path sets stopper structure, is conducive to cast
Interior cold runner ceramic core is detached with metal when making, and improves blade yield rate.Thermal barrier coating is sprayed in blade flow passage component, in heat
Adhesive layer is sprayed between barrier coating and metal prevents thermal barrier coating from coming off.Blade cooling channel can be prevented with metallic cementation erosion resistant coating
Blade interior is corroded in high salt point of working environment.The cooling structure of the blade can effectively reduce metallic surface temperature, this is cold
But it is cold air utilization rate height the advantages of structure, resistance is small, and the special construction of vane tip can have under conditions of no integral shroud
Effect reduces blade tip clearance, improves turbine efficiency.
Description of the drawings：
Fig. 1 is the three dimensional structure 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 of mudhole in the present invention.
Specific embodiment：
With reference to each figure, a kind of Gas Turbine without hat gaseous film control rotor blade, including tenon root 1, stretch root 2, listrium 3 and
Blade profile 4, tenon root 1 are connect with blade profile 4 by stretching 2 transition of root, and blade profile 4 is equipped with air film hole 6, and 4 top of blade profile is equipped with leaf top boss
5；The blade interior forms the first ante-chamber 14, the second ante-chamber 13, the first back cavity 15, the second back cavity 16 and trailing edge and splits seam 10, the
Coarse rib 8, the metal isolation board between the first ante-chamber 14 and the second ante-chamber 13 by being integrated with blade are equipped in one ante-chamber 14
Isolation, metal isolation board are equipped with the impact throttling 11 not less than 1 row, and the first back cavity 15 and the second back cavity 16 are isolated by metal
Plate forms inverted U-shaped cavity, and coarse rib 8 is disposed in the first back cavity 15, turbulence columns 9 are equipped in the second back cavity 16；It is described
4 top of blade profile be equipped with mudhole 12；First ante-chamber 14, the second ante-chamber 13, the first back cavity 15, the second back cavity 16 and trailing edge split seam
10 form the cooling channel structure of rotor blade, and wherein first via cold air enters the first ante-chamber 14 along 1 bottom of tenon root, through impact
Throttle orifice 11 enters the second ante-chamber 13, then spray by the air film hole 6 of leading edge locus after distributing；Second road cold air is along tenon root 1
Position enters the first back cavity 15, and position enters the second back cavity 16 after the turning of U-shaped cavity, is finally distributed according to resistance along trailing edge and splits seam 10
Channel outflow；First ante-chamber 14, the second ante-chamber 13, the first back cavity 15, the second back cavity 16 and trailing edge, which are split seam 10 and formd, to be turned
The cooling circulation part spraying thermal barrier coating of blades, spraying adhesive layer prevents thermal barrier coating from taking off between thermal barrier coating and metal
It falls, blade cooling channel can prevent the blade interior in high salt point of working environment from corroding with metallic cementation erosion resistant coating；The leaf
Top boss 5 is designed for semi-closed structure, and molded line smoothly transits with blade profile 4, leaf pressure on top surface surface side near trailing edge without boss,
The boss uses built-up welding boss structure, and pressure face is not closed close to trailing edge position；Second ante-chamber 13 and the second back cavity 16
Plug 7 is equipped with, convenient for removing inner runner core, the position is a cavity in hot investment casting, cast blade off-type core
When, the lysate of coolant flow channel core is flowed out from the cavity, and after having taken off core, which is closed using plug 7；Second ante-chamber 13
Non- air film hole site can also arrange coarse rib 8, and in 2~3 exhaust fenestras 6 of leading edge locus arrangement of the second ante-chamber 13；The
By-pass prot can be arranged on metal isolation board between one back cavity 15 and the second back cavity 16, to distribute the cold air in the second back cavity 16；
The turbulence columns 9 are arranged in a manner that mistake is arranged in the second back cavity 16, turbulence columns 9 and coarse rib 8, for enhanced heat exchange；
The shape that the trailing edge splits seam 10 may be designed as the rectangle with rounded corner, circle, the zigzag with rounded corner；The blowdown
Hole 12 is arranged in each flow path vane tip position, and mudhole 12 is blocked by leaf top boss 5, washes away influence to avoid high-speed fuel gas
Filth-discharging effect, mudhole 12 are discharged dust using centrifugal force.
The turbine rotor blade main body is processed by hot investment casting, and wherein air film hole 6, trailing edge split seam 10 and mudhole 12 is equal
Using electric machining, leaf roof construction built-up welding processing.Tenon root 1 is the connecting portion of blade and the turbine disk, needs to meet in design strong
Spend criterion；It is the transition structure between tenon root 1 and blade profile to stretch root 2, stretches the outside of root 2 and can reduce high temperature combustion by cold air cooling
The heat that gas is transmitted to 1 position of tenon root；Listrium 3 ensures flow passage of the combustion gas according to design；Blade profile position needs to meet pneumatic
It is required that and intensity requirement.Vane tip is semiclosed boss structure, and molded line and the blade profile of leaf top boss 5 should smoothly transit, and is protected
Good aerodynamic characteristic is demonstrate,proved, the structure size of boss should determine that boss is by the way of built-up welding according to pneumatic, intensity resultant effect
Processing, material and airfoil portion split-phase are same.First ante-chamber, 14 channel arrangement coarse rib 8 angle can be it is horizontal, can also
It is with angle, the coarse rib 8 with angle is in pressure surface side and suction surface side interlaced arrangement, sectional dimension, the length of coarse rib 8
Degree, angle, spacing distance, quantity determine that geometric parameter will also combine hot investment casting according to heat transfer and the resultant effect of flow resistance
Precision.Be isolated between first ante-chamber 14 and the second ante-chamber 13 by metal isolation board, metal isolation board and blade be it is integrated,
A row or multi-row impact orifice structure is set on metal isolation board, size second ante-chamber 13 of adjusting in 11 holes that throttled by impact
Distribution of the interior cold air along blade radial can also adjust the cold air flow of the first ante-chamber 14 and the second ante-chamber 13, impact throttle orifice
11 size is determined by the result that pipe network flow resistance calculates.Second ante-chamber, 13 non-air film hole site can also arrange coarse rib 8, slightly
The geometric parameter of rough rib 8 is determined that the second ante-chamber 13 arranges 2~3 exhaust membranes in leading edge locus by the resultant effect to conduct heat with flow resistance
Hole 6, cold air are covered each by blade pressure face and suction surface position after being sprayed along air film hole 6, high-temperature fuel gas, air film, 6 number is isolated
Amount, angle, aperture are obtained by flowing and Calculation of Heat Transfer optimization, and film hole structure is obtained by way of electric machining.After first
Chamber 15 arranges coarse rib Final 8ization heat exchange, and the geometric parameter of coarse rib 8 determines that method is identical with the first ante-chamber 14, the first back cavity 15
Inverted u-shaped structure is formed with the second back cavity 16, two chambers are separated by metal isolation board, metal isolation board is one with blade
, by-pass prot can be arranged on metal isolation board, the cold air in the second back cavity 16 is distributed, turbulence columns 9 is arranged in the second back cavity 16,
Cold air turbulivity in increase chamber, enhancing heat transfer effect, multiple rows of flow-disturbing, 9 structure types arranged using mistake, the distribution of turbulence columns 9,
Diameter, quantity are determined by conducting heat with the resultant effect of flow resistance.Trailing edge split seam 10 shape have the rectangle with rounded corner, circle,
Zigzag with rounded corner, trailing edge splits the shape of seam 10 and geometric parameter is determined by exchanging heat with the resultant effect of flow resistance, in addition
It must also consider the intensity of core during casting, circular trailing edge is split crack structure and obtained by way of electric machining, remaining shape
Structure is processed by hot investment casting.Mudhole 12 is arranged in each flow path vane tip position, and mudhole 12 should be blocked by boss,
High-speed fuel gas is avoided to wash away influence filth-discharging effect, the geometric parameter of mudhole 12 is determined according to two principles：Through mudhole 12
The air conditioning quantity of outflow cannot be too many, and the size of mudhole 12 must assure that dust can be discharged smoothly.Plug 7 is in hot investment casting
One cavity, during cast blade off-type core, the lysate of coolant flow channel core is flowed out from the cavity, after having taken off core, the position
It is closed using stopper structure.In order to further reduce the metal temperature of rotor blade, thermal barrier coating is sprayed in blade flow passage component.
Adhesive layer is sprayed between thermal barrier coating and metal prevents thermal barrier coating from coming off.Blade cooling channel can ooze non-corrosive metal (NCM) layer,
Prevent the blade interior in high salt point of working environment from corroding.
First via cold air enters from the middle part of blade, then flows to blade inlet edge air film hole 6, is conducive to improve the utilization of cold air
Rate；First via orifice structure can adjust the cold air flow point of the total flow for flowing to air film cold air and air film along blade height
Cloth advantageously reduces blade metallic portion temperature gradient；The U-shaped structure on the second tunnel had not only improved the utilization rate of cold air, but also avoided
Cold air resistance is too big；The mudhole 12 on leaf top can be blocked to avoid cooling structure by dust, and 5 semi-closed structure of leaf top boss can
To mitigate blade quality, reduce blade tip clearance, efficiency is improved under the premise of reliability is ensured.Plug 7 is conducive to interior during casting
Cold runner ceramic core is detached with metal, improves blade yield rate.The advantages of rotor blade cooling structure is cold air utilization rate height,
Resistance is small, and the special construction of vane tip can effectively reduce blade tip clearance under conditions of no integral shroud, improve turbine effect
Rate.The structure of the present invention is simple, reasonable design, and cold air utilization rate is high, energy-efficient, and manufacture is at low cost, is easy to push away on a large scale
Wide and use.
Claims (1)
1. a kind of Gas Turbine is without hat gaseous film control rotor blade, it is characterised in that：The blade includes tenon root（1）, stretch root
（2）, listrium（3）And blade profile（4）, tenon root（1）With blade profile（4）By stretching root（2）Transition connects, blade profile（4）It is equipped with air film hole
（6）, blade profile（4）Top is equipped with leaf top boss（5）；The blade interior forms the first ante-chamber（14）, the second ante-chamber（13）, first
Back cavity（15）, the second back cavity（16）And trailing edge splits seam（10）, the first ante-chamber（14）It is interior to be equipped with coarse rib（8）, the first ante-chamber（14）
With the second ante-chamber（13）Between be isolated by the metal isolation board being integrated with blade, metal isolation board is equipped with not less than 1 row
Impact throttle orifice（11）, the first back cavity（15）With the second back cavity（16）Inverted U-shaped cavity is formd by metal isolation board,
First back cavity（15）Inside it is disposed with coarse rib（8）, the second back cavity（16）It is interior to be equipped with turbulence columns（9）；The blade profile（4）Top is set
There is mudhole（12）；First ante-chamber（14）, the second ante-chamber（13）, the first back cavity（15）, the second back cavity（16）And trailing edge
Split seam（10）Form the cooling channel structure of rotor blade, wherein first via cold air is along tenon root（1）Bottom enters the first ante-chamber
（14）, through impacting throttle orifice（11）Enter the second ante-chamber after distribution（13）, then the air film hole for passing through leading edge locus（6）It sprays；The
Two road cold air are along tenon root（1）Position enters the first back cavity（15）, enter the second back cavity after the turning of U-shaped cavity（16）, finally press
It is distributed according to resistance along trailing edge and splits seam（10）Channel outflow；First ante-chamber（14）, the second ante-chamber（13）, the first back cavity
（15）, the second back cavity（16）And trailing edge splits seam（10）The cooling duct part spraying thermal barrier coating of the rotor blade formed,
Adhesive layer is sprayed between thermal barrier coating and metal prevents thermal barrier coating from coming off, and blade cooling channel metallic cementation erosion resistant coating prevents
Blade interior is corroded in high salt point of working environment；The leaf top boss（5）It is designed for semi-closed structure, molded line and blade profile
（4）It smoothly transits, leaf pressure on top surface surface side is near trailing edge without boss；Second ante-chamber（13）And second back cavity（16）On
Equipped with plug（7）, convenient for removing inner runner core, in hot investment casting, the position is a cavity, cast blade off-type core
When, the lysate of coolant flow channel core is flowed out from the cavity, and after having taken off core, which uses plug（7）Closing；Described
Two ante-chambers（13）The non-coarse rib of air film hole location arrangements（8）, and in the second ante-chamber（13）Leading edge locus arrange 2~3 rows
Air film hole（6）；First back cavity（15）With the second back cavity（16）Between metal isolation board on arrange by-pass prot, with distribution
Second back cavity（16）Interior cold air；The turbulence columns（9）The second back cavity is arranged in a manner that mistake is arranged（16）It is interior；Described
Trailing edge splits seam（10）Shape be designed as the rectangle with rounded corner, circle, the zigzag with rounded corner；The mudhole（12）
It is arranged in each flow path vane tip position, mudhole（12）By leaf top boss（5）It blocks, washes away influence to avoid high-speed fuel gas
Filth-discharging effect, mudhole（12）Dust is discharged using centrifugal force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610193629.1A CN105673089B (en) | 2016-03-31 | 2016-03-31 | A kind of Gas Turbine is without hat gaseous film control rotor blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Publication Number | Publication Date |
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| CN105673089A CN105673089A (en) | 2016-06-15 |
| CN105673089B true CN105673089B (en) | 2018-06-29 |
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| CN201610193629.1A Active 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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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114215607A (en) * | 2021-11-29 | 2022-03-22 | 西安交通大学 | Turbine blade leading edge rotational flow cooling structure |
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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 |
| CN111022127B (en) * | 2019-11-29 | 2021-12-03 | 大连理工大学 | Turbine blade trailing edge curved exhaust split structure |
| 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 |
| CN112459849B (en) * | 2020-10-27 | 2022-08-30 | 哈尔滨广瀚燃气轮机有限公司 | Cooling structure for turbine blade of gas turbine |
| 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 |
| CN115126547B (en) * | 2022-05-29 | 2023-05-12 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine movable blade trailing edge structure for suction side exhaust |
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| CN105673089A (en) | 2016-06-15 |
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