CN108999646A - Blade for gas turbine and the electric power generating device including the blade - Google Patents
Blade for gas turbine and the electric power generating device including the blade Download PDFInfo
- Publication number
- CN108999646A CN108999646A CN201810580811.1A CN201810580811A CN108999646A CN 108999646 A CN108999646 A CN 108999646A CN 201810580811 A CN201810580811 A CN 201810580811A CN 108999646 A CN108999646 A CN 108999646A
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- China
- Prior art keywords
- cooling
- pressure side
- wall
- absorption
- leading edge
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Classifications
-
- 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
- F01D5/187—Convection cooling
-
- 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
- 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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to the blade for gas turbine and including the electric power generating device of the blade.It for the blade of gas turbine (5), is equipped with airfoil (18), with leading edge (27), rear (28), on the pressure side (24) and absorption side (25)；The airfoil (18) include outer wall (35) and substantially by outer wall (35) surround inner wall (36)；And it is equipped with cooling device (29) comprising at least partly cooling path (31a) along the absorption side that side (25) limit between outer wall (35) and inner wall (36) is drawn；Drawing side cooling path (31a), there is at least one to draw side entrance (40) and at least one absorption side tapping equipment (41)；It draws side entrance (40) and is arranged closer to rear (28) compared to side tapping equipment (41) are drawn.
Description
Priority
This application claims the priority for the European Patent Application No. 17174866.8 that on June 7th, 2017 submits, the disclosure of which is logical
It crosses and is incorporated by.
Technical field
The present invention relates to the blade for gas turbine and be related to include the blade electric power generating device.Specifically,
The present invention relates to the improved coolings of the blade of gas turbine.Preferably, electric power generating device is connected to power grid.
Background technique
During the operation of electric energy generating device, the blade of gas turbine is commonly exposed to the hot gas from combustion chamber
Stream.
The temperature of the hot gas flowed in gas turbine influences the performance of equipment.Specifically, the performance of equipment with
Turbine interior flowing hot gas increased temperature and increase.
However, the increase of the temperature of the hot gas flowed in gas turbine is limited by the thermal resistance for constituting the material of blade.
In order to overcome this limitation, in recent years, the cooling system for blade has been used.In general, being mentioned from compressor
It takes or the cooling air from dedicated cooling air source is driven through blade.
The example of blade equipped with cooling system discloses in file US 8,231,349 or EP 2107215.
It will lead to excessive heat power loss in the blade of gas turbine however, a large amount of cooling airs are introduced into.
Summary of the invention
Therefore object of the invention is to provide the blade with optimization cooling system, can improve the thermal resistance of blade, allows
The temperature of the gas flowed in gas turbine further increases and reduces heat power loss, thus so as to improve equipment
Energy.
According to the present invention, the blade for gas turbine is provided, comprising:
Airfoil, have leading edge, rear, on the pressure side with draw side；Airfoil include outer wall and substantially by outer wall surround in
Wall；With
Cooling device comprising the cooling path in absorption side at least partly limited between outer wall and inner wall along absorption side；It inhales
Taking the cooling path in side to have, at least one draws side entrance and at least one draws side tapping equipment；Side entrance is drawn compared to absorption
Side tapping equipment is arranged closer to rear.
In this way, cooling fluid is relative to the hot gas working fluid in inflation channel along the stream for drawing the cooling path in side
The reverse flow of stream.The solution improves heat exchanger effectiveness, because as the heat transfer that reverse flow obtains is handed over higher than concurrent flow
It changes.Because cooling efficiency increases, lower cooling fluid flow rate can be extracted for cooling blade.This leads to the aobvious of device efficiency
It writes and increases, because cooling fluid is usually extracted from the compressor of equipment.
Further, since draw the claimed structure in the cooling path in side, to draw side cold when it is travelled across for cooling fluid
But path and then by close to up-front absorptions side tapping equipment discharge when be heated.In this way, the cooling fluid of heating is arranged
It is put into hot gas working fluid stream, reduces heat power loss.
A kind of preferred embodiment according to the present invention, drawing the cooling path in side includes multiple in fluid communication and and arranging
The absorption side cooling chamber set；Multiple absorption side cooling chambers include drawing side entrance room, are cooling near the absorption side of rear
Room, and side drain chamber is drawn, it is near up-front absorption side cooling chamber；Drawing side entrance room includes drawing side entrance and suction
Taking side drain chamber includes drawing side tapping equipment.
A kind of preferred embodiment according to the present invention, airfoil have pedestal and tip；Multiple absorption sides cooling chamber is basic
The direction that upper edge is advanced from pedestal towards tip extends.
A kind of preferred embodiment according to the present invention, at least one is drawn side cooling chamber and is equipped at least one turbulator.This
Sample improves the cooling efficiency for drawing the cooling path in side.
A kind of preferred embodiment according to the present invention, cooling device include on the pressure side cool down path, be limited to inner wall and
Between outer wall and at least partly along on the pressure side extending；On the pressure side cooling down path includes at least one pressure side entrance and at least one
A on the pressure side tapping equipment；On the pressure side tapping equipment is arranged closer to rear compared to pressure side entrance.
In this way, cooling fluid is relative to the hot gas working fluid in inflation channel along the stream in path is on the pressure side cooled down
Stream concurrent flow.
A kind of preferred embodiment according to the present invention, on the pressure side cooling down path includes multiple on the pressure side cooling chambers, is in
Fluid communication and along being on the pressure side arranged side by side between the inner walls and the outer；Plurality of on the pressure side cooling chamber includes pressure side entrance
Room, be near up-front on the pressure side cooling chamber and at least one on the pressure side drain chamber, be near rear on the pressure side
Cooling chamber；On the pressure side inlet chamber includes pressure side entrance and on the pressure side drain chamber includes at least one on the pressure side tapping equipment.
A kind of preferred embodiment according to the present invention, cooling device include the cooling path of leading edge comprising are limited by inner wall
Center of inside cooling chamber and the leading edge cooling chamber arranged between the inner walls and the outer in edge；Center of inside cooling chamber is with before
Edge cooling chamber is in fluid communication；The cooling path of leading edge includes at least one leading edge entrance and at least one leading edge tapping equipment；
Leading edge tapping equipment is arranged to compare leading edge entrance closer to leading edge.
A kind of preferred embodiment according to the present invention, cooling device include the cooling path of rear, by be arranged in rear and
The rear cooling chamber drawn between side entrance for drawing the cooling path in side limits.
A kind of preferred embodiment according to the present invention, the cooling path of rear includes at least one rear entrance and at least one
Rear tapping equipment；Rear tapping equipment is arranged on the pressure side and is configured to guidance stream towards rear.
A kind of preferred embodiment according to the present invention draws side tapping equipment and extends through outer wall and including multiple ingates
Hole, at least one export public sealing and multiple interface channels, interface channel each of be configured to connect corresponding hole and
Export public sealing.
In addition, it is another object of the present invention to provide the equipment generated for electric power with improved power efficiency.
According to the target, equipment the present invention relates to being generated for electric power, including at least one gas turbine, along vertical
To axis extension and at least one including being circumferentially spaced and extending radially outward from the corresponding supporting disk of gas turbine
Arrange blade；At least one of blade of the row has the claimed type in any one of claim 1-10.
A kind of preferred embodiment according to the present invention, equipment include at least one compressor, are connected to by absorption pipeline
Gas turbine, the absorption pipeline are configured to extract cooling air from compressor and are supplied to the cooling dress of at least one blade
It sets.
Detailed description of the invention
The present invention describes referring now to the drawings, some non-limiting embodiments of drawing illustration, wherein:
Fig. 1 is the schematic transverse view of electric power generating device according to the present invention, part of removal and part in order to clear
In cross-sectional form；
Fig. 2 is the schematic transverse view of the blade according to the present invention for gas turbine, part of to remove in order to clear
And part is in cross-sectional form；
Fig. 3 is the perspective schematic view of the first details of the blade of Fig. 2, part of to remove in order to clear and partially with section
Form；
Fig. 4 is the top sectional view of the first details of the blade of Fig. 2；
Fig. 5 is the amplification schematic sectional view of the second details of blade according to the present invention.
Fig. 6 is the schematic sectional view along the second details of the plane VI-VI indicated in Fig. 5；
Fig. 7 is schematically cutting for the second details for the plane VI-VI that edge according to another embodiment of the present invention indicates in Fig. 5
Face figure.
Specific embodiment
In Fig. 1, reference label 1 instruction for electric energy generate gas turbine equipment, including compressor 3, burner 4,
Gas turbine 5 and generator 7, the mechanical output supplied by turbine 5 is converted into be connected to power generation to be supplied to via switch 9
The electrical power of the power grid 8 of machine 7.
Unshowned variant schemes, which provides, is used for equipment 1, has combination cyclical patterns and in addition to gas turbine 5 and power generation
Machine 7 also includes steamturbine.
Axis A extends and is equipped with axis 10 (also extending along axis A), compressor 3 and generator 7 gas turbine 5 along longitudinal direction
It is connected to the axis 10.
Gas turbine 5 includes inflation channel 12, wherein the hot gas working fluid from burner 4 is flowed along direction D.
Inflation channel 12 has section, increases radially along axis A along direction D.
Multiple grades 13 that axis A is spaced apart along longitudinal direction are disposed in inflation channel 12.Each grade 13 includes fixed blade
Row and rotating vane row's (not illustrated in Fig. 1).Each row includes the week extended radially outward from corresponding supporting disk
The blade being spaced apart to ground.
The blade 15 of the grade 13 of gas turbine 5 is demonstrated by Fig. 2.
Preferably, blade 15 is rotating vane, it is clear that it is can also be applied to stator vane.
Blade 15 includes root 17, airfoil 18 and platform 20.
Root 17 is configured to couple to the supporting disk (illustrating not in the drawings) of gas turbine 5.Specifically, disk has multiple
Axial seat is circumferentially spaced and is engaged by the corresponding root 17 of rotating vane 15.
Airfoil 18 extends from root 17 and is equipped with the pedestal 21 and the tip 22 that are attached to root 17, radial in use
Ground is relative to pedestal 21.
Airfoil 18 is fully accommodated in the aerodynamic profile in inflation channel 12 and limiting rotating vane 15.
Airfoil 18 has recessed on the pressure side 24 (preferably visible in figures 3 and 4) and convex absorption side 25, exists in use
Between leading edge 27 and rear 28 axially extend and between pedestal 21 and tip 22 radially.
Leading edge 27 is arranged in 28 upstream of rear along the direction D of the hot working fluid in inflation channel 12.
Platform 20 is arranged between root 17 and airfoil 18.
Blade 15 is equipped with cooling device 29.Cooling device 29 includes multiple feed paths 30 being produced in root 17 and more
A cooling path 31 (being illustrated not in Fig. 2 and preferably visible in figures 3 and 4) being produced in airfoil 18.
Feed path 30 is supplied with the cooling fluid from cooling fluid source 32.
Preferably, cooling fluid source 32 is a part of compressor 3.It is shown in FIG. 1 and is exclusively used in cooling air from pressure
The absorption of contracting machine 3 and the absorption pipeline 33 for being connected to gas turbine 5.
Preferably, each feed path 30 is attached to corresponding cooling path 31.According to a kind of unshowned variant schemes,
Each feed path may be coupled to more than one cooling path.
In disclosed herein and diagram non-limiting embodiment, feed path 30 is four and cooling path 31 is four
It is a.
With reference to Fig. 3, cooling device 29 includes the cooling path 31a in absorption side for being primarily devoted to draw the cooling of side 25, main
It is exclusively used in the cooling road of leading edge on the pressure side cooling down path 31b, the cooling for being primarily devoted to leading edge 27 of on the pressure side 24 cooling
The cooling path 31d of rear of diameter 31c and the cooling for being primarily devoted to rear 28.
For dotted line for schematically indicating cooling path 31a, imaginary point line is on the pressure side cold for schematically indicating in Fig. 3
But path 31b, dotted line is for schematically indicating the cooling path 31c of leading edge, and solid line is for schematically indicating the cooling road of rear
Diameter 31d.
Airfoil 18 includes outer wall 35 and inner wall 36.
Outer wall 35 at least partially defines the aerodynamic profile of blade 15 and has exterior face 37, in use
It is arranged to contact with the hot gas working fluid flowed in inflation channel 12.
Inner wall 36 is surrounded by outer wall 35 and can have cooling and structure function.
Specifically, inner wall 36 limits center of inside cooling chamber 38, comes from corresponding feed path 30 in use by it
Cooling fluid flowed as will be described in detail below.
The cooling path 31a in side is drawn to be limited between inner wall 36 and outer wall 35 and at least partly extend along absorption side 25.
Drawing the cooling path 31a in side includes at least one entrance 40 (preferably visible in Fig. 2) and at least one discharge
Device 41.
Entrance 40 is arranged closer to rear 28 compared to tapping equipment 41.
In disclosed herein and diagram non-limiting embodiment, drawing the cooling path 31a in side includes an entrance 40,
At pedestal 21 by being located at airfoil 18 and in limiting with the hole of the fluid communication of the corresponding feed path 30 of root 17.
In disclosed herein and diagram non-limiting embodiment, drawing the cooling path 31a in side includes a tapping equipment
41, it will be explained in detail below.
In more detail, drawing the cooling path 31a in side includes multiple absorption sides cooling chamber 42, in fluid communication and along suction
Side 25 is taken to be arranged side by side between inner wall 36 and outer wall 35.
Each of side cooling chamber 42 is drawn substantially to extend along the direction advanced from pedestal 21 towards tip 22.
Multiple absorption sides cooling chamber 42 includes drawing side entrance room 42a, is the absorption side cooling chamber near rear 28
42；It is the absorption side cooling chamber 42 near leading edge 27 with absorption side drain chamber 42b.
Absorption side entrance room 42a includes entrance 40 and absorption side drain chamber 42b includes tapping equipment 41.
In disclosed herein and diagram non-limiting embodiment, drawing the cooling path 31a in side includes that three absorption sides are cold
But room 42.In other words, only one is disposed between absorption side entrance room 42a and absorption side drain chamber 42b to draw among side
Room 42c.
Preferably, side drain chamber 42b is drawn to be connected among absorption side by the bending section (not shown) at tip 22
Room 42c and medial compartment 42c are connected to by the bending section (not shown) at pedestal 21 draws side drain chamber 42b.
In use, the cooling fluid of the corresponding feed path 30 from root 17 is flowed along side entrance room 41a is drawn,
Along drawing, side drain chamber 42b is drawn on the edge side medial compartment 42c and the tapping equipment 41 by drawing side drain chamber 42b exits.
In other words, cooling fluid is relative to having in inflation channel 12 along the stream for drawing the cooling path 31a in side
The reverse flow of the stream of the hot gas working fluid of direction D.
The cross section for drawing side cooling chamber 42 is tapered between 10% to 30% along the direction of coolant flow, to control cooling
The pressure of agent and to control across tapping equipment 41 discharge stream consistency.In addition, the control of the pressure of coolant reduces
Drawing the friction loss in side cooling chamber 42.
Path 31b is on the pressure side cooled down to be limited between inner wall 36 and outer wall 35 and at least partly extend along on the pressure side 24.
On the pressure side cooling down path 31b includes at least one entrance 44 (preferably visible in Fig. 2) and at least one discharge
Device 45.
Tapping equipment 45 is arranged closer to rear 28 compared to entrance 44.
In disclosed herein and diagram non-limiting embodiment, on the pressure side cooling down path 31b includes an entrance 44,
At pedestal 21 by being located at airfoil 18 and in limiting with the hole of 30 fluid communication of corresponding feed path of root 17.
In disclosed herein and diagram non-limiting embodiment, on the pressure side cooling down path 31b includes two tapping equipments
45, it will be described in later.
In more detail, on the pressure side cooling down path 31b includes multiple on the pressure side cooling chamber 47, in fluid communication and along pressure
Power side 24 is arranged side by side between inner wall 36 and outer wall 35.
On the pressure side each of cooling chamber 47 substantially extends along the direction advanced from pedestal 21 towards tip 22.
Multiple on the pressure side cooling chambers 47 include on the pressure side inlet chamber 47a, are the on the pressure side cooling chambers near leading edge 27
47；It is near on the pressure side cooling chamber 47 of rear 28 at least one on the pressure side drain chamber 47b.
On the pressure side inlet chamber 47a includes entrance 44 and on the pressure side drain chamber 47b includes at least one tapping equipment 45.
In disclosed herein and diagram non-limiting embodiment, on the pressure side cooling down path 31b includes three on the pressure side cold
But the on the pressure side inlet chamber 47a and two subsequent drain chamber 47b of room 47: one, wherein being each equipped at least one tapping equipment
45。
In use, the cooling fluid of the corresponding feed path 30 from root 17 is flowed along on the pressure side inlet chamber 47a,
Along the neighbouring on the pressure side on the pressure side drain chamber 47b of inlet chamber 47a and along the on the pressure side drain chamber 47b flowing near rear 28 and
It is exited by two tapping equipments 45 of on the pressure side drain chamber 47b.
Preferably, on the pressure side inlet chamber 47a is connected to by the bending section (not shown) at tip 22 adjacent on the pressure side
The on the pressure side drain chamber 47b of the on the pressure side drain chamber 47b of inlet chamber 47a and neighbouring on the pressure side inlet chamber 47a pass through in pedestal 21
The bending section (not shown) at place is connected to the on the pressure side drain chamber 47b near rear.
In other words, cooling fluid is square relative to having in inflation channel 12 along the stream on the pressure side cooling down path 31b
To the concurrent flow of the stream of the hot gas working fluid of D.
On the pressure side the cross section of cooling chamber 47 is tapered between 10% to 30% along the direction of coolant flow, to control cooling
The pressure of agent and to control across tapping equipment 45 discharge stream consistency.In addition, the control of the pressure of coolant reduces
Friction loss on the pressure side cooling chamber 47.
The cooling path 31c of leading edge by center of inside cooling chamber 38 and by leading edge 27 be arranged in inner wall 36 and outer wall 35 it
Between leading edge cooling chamber 49 limit.Center of inside cooling chamber 38 is in by least one connection hole 50 with leading edge cooling chamber 49
Fluid communication.
Preferably, center of inside cooling chamber 38 is attached at leading edge 27 via the web of perforation, and the web is in leading edge 27
Place connection blade 15 on the pressure side 24 and draw side 25.
The axis in each connection hole 50 is preferably directed towards the corresponding part of exterior face of the leading edge 27 relative to outer wall 35
It is tilted with angle beta.Preferably, angle beta is at least equal to 20 °.
Preferably, at least two radial direction rows and leading edge cooling chamber 49 of the center of inside cooling chamber 38 by connecting hole 50
In fluid communication.Preferably, a row connects connection hole 50 stagger arrangement of the hole 50 relative to another row.
Center of inside cooling chamber 38 and the substantially edge of leading edge cooling chamber 49 are prolonged from pedestal 21 towards the direction that tip 22 is advanced
It stretches.
The cooling path 31c of leading edge includes at least one entrance 51 (preferably visible in Fig. 2) and at least one discharge dress
Set 53.
Tapping equipment 53 is arranged closer to leading edge 27 compared to entrance 51.
In disclosed herein and diagram non-limiting embodiment, the cooling path 31c of leading edge includes an entrance 51, by
The hole that corresponding feed path 30 at the pedestal 21 of airfoil 18 and with root 17 is in fluid communication limits.
In non-limiting embodiment disclosed herein, the cooling path 31c of leading edge includes multiple tapping equipments 53, later
It will be described in.Preferably, tapping equipment 53 is at least three: at least one tapping equipment 53, court guided towards leading edge 27
To at least one tapping equipment 53 for drawing at least one tapping equipment 53 that side 25 guides and direction on the pressure side 24 guidance.
In more detail, leading edge cooling chamber 49 includes tapping equipment 53, while center of inside cooling chamber 38 includes entrance 51.
Preferably, the tapping equipment 53 in leading edge cooling chamber 49 is relative to connection 50 stagger arrangement of hole.
In use, the cooling fluid of the corresponding feed path 30 from root 17 is flowed along center of inside cooling chamber 38
It is dynamic, connection hole 50 is passed through, flows along leading edge cooling chamber 49 and is exited by the tapping equipment 53 of leading edge cooling chamber 49.
In other words, cooling fluid is relative to having direction D in inflation channel 12 along the stream of the cooling path 31c of leading edge
Hot gas working fluid stream concurrent flow.
The cooling path 31d of rear is cold by the rear being arranged between rear 28 and the entrance 40 of the cooling path 31a in absorption side
But room 55 limits.
Rear cooling chamber 55 substantially extends along the direction advanced from pedestal 21 towards tip 22.
The cooling path 31d of rear includes at least one entrance 57 (preferably visible in Fig. 2) and at least one discharge dress
Set 58.
Tapping equipment 58 is arranged in and on the pressure side on 24 and is configured to guidance stream towards rear 28.
In disclosed herein and diagram non-limiting embodiment, the cooling path 31d of rear includes an entrance 57, by
It is located in the hole restriction that the corresponding feed path 30 at the pedestal 21 of airfoil 18 and with root 17 is in fluid communication.
In disclosed herein and diagram non-limiting embodiment, the cooling path 31d of rear includes a tapping equipment 58,
It will be described in later.
In more detail, rear cooling chamber 55 includes tapping equipment 58 and entrance 57.
In use, the cooling fluid of the corresponding feed path 30 from root 17 flows and leads to along rear cooling chamber 55
Tapping equipment 58 is crossed to exit towards rear 28.
Absorption side cooling chamber 42, on the pressure side cooling chamber 47, leading edge cooling chamber 49 and rear cooling chamber 55 can optionally be set
There is at least one turbulator to improve cooling effect.
Specifically, drawing side cooling chamber 42, on the pressure side cooling chamber 47 and rear cooling chamber 55 may include being limited by flank
Turbulator, flank is prominent from least one inside face of corresponding room and the direction of the cooling fluid relative to portion indoors at
Angle.Preferably, three of the turbulator from corresponding room neighbouring inside faces are prominent.
Leading edge cooling chamber 49 may include multiple by limiting from least one inside face flank outstanding of leading edge cooling chamber 49
Turbulator.The flank has trapezoidal molding section.Preferably, the turbulator is relative at least in leading edge cooling chamber 49
Two inside faces on cooling device 53 inlet hole stagger arrangement arrange, correspondingly closest on the pressure side 24 and draw side
25。
Preferably, the cooling fluid flowed in cooling path 31a, 31b, 31c, 31d mainly has from pedestal 21 to point
End 22 or from tip 22 to the radial direction of pedestal 21, while the cooling fluid master flowed in cooling path 31a, 31b, 31c
Have from pedestal 21 to tip 22 or from tip 22 to the radial direction of pedestal 21.The cooling flowed in cooling path 31c
Fluid mainly has in center of inside cooling chamber 38 from pedestal 21 to the radial direction at tip 22, while in leading edge cooling chamber 49
Middle cooling stream mainly has the axial direction from connection hole 50 to tapping equipment 53.
Preferably, draw side cooling chamber 42, on the pressure side cooling chamber 47, leading edge cooling chamber 49 and rear cooling chamber 55 are rectangular
Shape shape and there is the height/width ratio that is preferably incorporated in range 4-6.
The shape of tapping equipment is illustrated in figs. 5 and 6.
Preferably, the tapping equipment 41 for drawing the cooling path 31a in side, the tapping equipment 45 on the pressure side cooling down path 31b, preceding
The tapping equipment 53 of the cooling path 31c of edge and the tapping equipment 58 of the cooling path 31d of rear illustrate in figs. 5 and 6 with all
Structure.
According to a kind of variant schemes (not shown), at least one of tapping equipment 41 45 53 58 has in Figures 5 and 6
The structure of middle diagram.
Tapping equipment 45 is illustrated only in figs. 5 and 6.However, because the structure base of the tapping equipment 41 53 58 retained
It is equal to the structure of tapping equipment 45 in sheet, consideration below can also be considered to be for tapping equipment 41 53 58
Effect.
Tapping equipment 45 extends through outer wall 35 to outer wall 35 from the corresponding inside face on the pressure side discharging cooling chamber 47b
Exterior face 37.
With reference to Fig. 6, tapping equipment 45 includes multiple inlet holes 60, exports public sealing 61 and multiple interface channels 63,
Each of interface channel is configured to connect corresponding hole 60 and exports public sealing 61.
Preferably, inlet hole 60 is equivalent each other.
Preferably, the distributed number of inlet hole 60 is in from 5 to 10.
Preferably, inlet hole 60 is spaced apart with spacing-hole diameter ratio of from 3 to 6 distributions.
Preferably, interface channel 63 is equivalent each other.
Interface channel 63 is diverged to towards public sealing 61 is exported.In other words, interface channel 63 has public towards exporting
The area of passage that sealing 61 gradually increases.
The increase of the area of passage is since the entrance zone, threshold zone 65 of interface channel 63 and in the exit zone of interface channel 63 66
Place terminates.The entrance zone, threshold zone 65 of each interface channel 63 is contacted with corresponding inlet hole 60, and each interface channel 63 go out
Mouth region section 66 is contacted with public sealing 61 is exported.
Preferably, interface channel 63 is diverged to towards the public sealing 61 in outlet with diverging to angle ψ, is limited to interface channel inclination
Between the extension of the wall of wall and entrance zone, threshold zone 65；Preferably, angle ψ is diverged to be included between 5 ° and 10 °.
The area of passage of inlet hole 60 is constant.
Preferably visible such as in Fig. 5, the area of passage of inlet hole 60 is less than the entrance of corresponding interface channel 63
The area of passage of section 65.
In disclosed herein and diagram non-limiting example, the access face of the entrance zone, threshold zone 65 of corresponding interface channel 63
Product is greater than the area of passage of inlet hole 60 with 10-20%.
In addition, entrance zone, threshold zone 65 and outlet in disclosed herein and diagram non-limiting example, in interface channel 63
Area ratio between section 66 is included between 3.5 to 5.
Preferably, inlet hole 60 is substantially right in the corresponding inside face on the pressure side discharging cooling chamber 47b along direction F
Together.Preferably, inlet hole 60 and the compartment of terrain arrangement that is equal to each other.
Preferably, public sealing 61 is exported substantially along the direction alignment for being parallel to direction F.
Direction F is substantially the straight line that tip 22 is extended to from the pedestal 21 of airfoil 18.
With reference to Fig. 5, tapping equipment 45 extends along main shaft G, and the exterior face 37 relative to outer wall is tilted with angle [alpha].
The angle [alpha] preferably ° distribution from 25 ° to 35.
In other words, the public sealing 61 of inlet hole 60 and interface channel 63 and outlet is along the institute such as in the cross section of Fig. 5
The main shaft G shown extends.
The depth DH of inlet hole 60 is the 10-20% of the total depth Dtot of outer wall 35；Wherein, depth DH and depth Dtot
The two is measured along main shaft G.
Preferably, the ratio between the depth DH of inlet hole 60 and the diameter d of inlet hole is from 1 to 2 distribution.
The depth DC of interface channel 63 is the 50%-70% of the total depth Dtot of outer wall 35；Wherein, depth DC and depth Dtot
The two is measured along main shaft G.
Preferably, the ratio between the depth DC of interface channel 63 and the diameter d of inlet hole is from 2 to 4 distributions.
Export public sealing 61 depth DS be outer wall 35 total depth Dtot 20-30%；Wherein, depth DS and depth
Both Dtot are measured along main shaft G.
Preferably, the ratio between the diameter d of the depth DS and inlet hole that export public sealing 61 is from 1 to 4 distribution.
Obviously, inclined angle [alpha] and along main shaft G measurement outer wall 35 total depth for tapping equipment 41 45 53
Each of 58 can be different.
In disclosed herein and diagram non-limiting example, the angle [alpha] of tapping equipment 58 is equal to or more than tapping equipment
45 angle [alpha].
In use, it is divided from the cooling fluid on the pressure side discharging cooling chamber 47b accordingly by multiple inlet holes 60,
It flow in corresponding interface channel 63 and is combined at public sealing 61 exporting.The single wide and uniform stream of cooling fluid from
It exports public sealing 61 to exit, as also indicated by the arrow in Fig. 6.
The presence of multiple inlet holes 60 of the area of passage with restriction have adjusted exited by tapping equipment 45 it is cold
But the flow rate of fluid.
The presence for exporting public sealing 61 improves film cooling effect, because the exterior face 37 of outer wall 35 is by wide and uniform
Cooling stream overlapping (or being covering, lapping, i.e. lap).
Due to increased cooling efficiency, the cooling air of lower quantity is required for blade.Due to this, gas turbine
Whole efficiency increase.
Another embodiment of tapping equipment 145 is illustrated in Fig. 7.The identical ginseng of cooling device 45 for Figures 5 and 6
It examines label and is also used in and be used to indicate similar or equivalent part in Fig. 7.
According to the embodiment, tapping equipment 145 includes at least two discharge groups 146.
In disclosed herein and diagram non-limiting example, tapping equipment 145 includes three discharge groups 146.
Each discharge group 146 includes multiple inlet holes 160, exports public sealing 161 and multiple interface channels 163,
In be each configured to connect corresponding hole 160 and export public sealing 161.
Specifically, each interface channel 163 has entrance zone, threshold zone 165 and exit zone 166；Each interface channel 163
Entrance zone, threshold zone 165 is contacted with corresponding inlet hole 160 and the public seam of the exit zone 166 of each interface channel 163 and outlet
Mouth 161 contacts.The area of passage of each inlet hole 160 is preferably less than the entrance zone, threshold zone 165 of corresponding interface channel 163
The area of passage, similar to the embodiment illustrated in Fig. 6.
In disclosed herein and diagram non-limiting example, each discharge group 146 includes three inlet holes 160, goes out
The public sealing 161 of mouth and three interface channels 163, wherein being each configured to connect corresponding hole 160 and exporting public sealing
161。
Every group 146 of inlet hole 160 is spaced apart each other at equal intervals.
Discharge group 146 is separated from each other.Preferably, discharge group 146 is spaced apart each other at equal intervals.
In use, it is drawn from the cooling fluid on the pressure side discharging cooling chamber 47b accordingly by multiple inlet holes 160
Point, it flows in corresponding interface channel 163 and is combined at public sealing 161 exporting.It is disclosed herein and diagram unrestricted
Property example in, three of cooling fluid uniform streams are exited from exporting public sealing 161, as also by the arrow instruction in Fig. 7
Like that.
Finally, it is therefore clear that modifications and variations can be made to blade described herein and gas turbine, without departing from such as existing
The scope of the present invention defined in the appended claims.
Claims (12)
1. the blade that one kind is used for gas turbine (5), comprising:
Airfoil (18), with leading edge (27), rear (28), on the pressure side (24) and absorption side (25)；The airfoil (18)
Including outer wall (35) and substantially by the inner wall (36) of the outer wall (35) encirclement；With
Cooling device (29) comprising at least partly along the absorption side (25) in the outer wall (35) and the inner wall (36)
Between the absorption side that limits it is cooling path (31a)；Cooling path (31a) there is at least one to draw side entrance for the absorption side
(40) and at least one draws side tapping equipment (41)；The absorption side entrance (40) compares the absorption side tapping equipment (41)
It is arranged closer to the rear (28).
2. blade according to claim 1, which is characterized in that the absorption side cooling path (31a) includes multiple be in
Fluid communication and the absorption side cooling chamber (42) being arranged side by side；The multiple absorption side cooling chamber (42) includes drawing side entrance room
(42a) is the absorption side cooling chamber near the rear (28), and draws side drain chamber (42b), is near described
The absorption side cooling chamber of leading edge (27)；The absorption side entrance room (42a) includes the absorption side entrance (40) and the absorption
Side drain chamber (42b) includes the absorption side tapping equipment (41).
3. blade according to claim 2, which is characterized in that the airfoil (18) has pedestal (21) and tip
(22)；It is the multiple to draw side cooling chamber (42) substantially along the direction advanced from the pedestal (21) towards the tip (22)
Extend.
4. blade according to claim 2 or 3, which is characterized in that at least one is drawn side cooling chamber (42) and is equipped at least
One turbulator.
5. blade according to any one of the preceding claims, which is characterized in that the cooling device (29) includes pressure
Side is cooling path (31b), is limited between the inner wall (36) and the outer wall (35) and at least partly along the pressure
Side (24) extends；It is described on the pressure side cool down path (31b) include at least one pressure side entrance (44) and at least one on the pressure side
Tapping equipment (45)；The on the pressure side tapping equipment (45) is arranged closer to the rear compared to the pressure side entrance (44)
(28)。
6. blade according to claim 5, which is characterized in that on the pressure side cool down path (31b) includes multiple pressure
Side cooling chamber (47), in fluid communication and along on the pressure side (24) between the inner wall (36) and the outer wall (35)
It is arranged side by side；Wherein, the multiple on the pressure side cooling chamber (47) includes on the pressure side inlet chamber (47a), is before described
The on the pressure side cooling chamber (47) of edge (27) and at least one on the pressure side drain chamber (47b), are near the rear (28)
On the pressure side cooling chamber (47)；The on the pressure side inlet chamber (47a) includes pressure side entrance (44) and the on the pressure side drain chamber
(47b) includes at least one on the pressure side tapping equipment (45).
7. blade according to any one of the preceding claims, which is characterized in that the cooling device (29) includes leading edge
Cooling path (31c) comprising the center of inside cooling chamber (38) that is limited by the inner wall (36) and at the leading edge (27)
The leading edge cooling chamber (49) arranged between the inner wall (36) and the outer wall (35)；The center of inside cooling chamber (38) with
The leading edge cooling chamber (49) is in fluid communication；The leading edge cooling path (31c) includes at least one leading edge entrance (51)
With at least one leading edge tapping equipment (53)；The leading edge tapping equipment (53) is arranged to more lean on compared to the leading edge entrance (51)
The nearly leading edge (27).
8. blade according to any one of the preceding claims, which is characterized in that the cooling device (29) includes rear
Cooling path (31d), by being arranged between the absorption side entrance (40) and the rear (28) of drawing side cooling path (31a)
Rear cooling chamber (55) limit.
9. blade according to claim 8, which is characterized in that after the rear cooling path (31d) includes at least one
Edge entrance (57) and at least one rear tapping equipment (58)；The rear tapping equipment (58) be arranged in it is described on the pressure side (24)
Above and it is configured to guide the stream towards the rear (28).
10. blade according to any one of the preceding claims, which is characterized in that the absorption side tapping equipment (41) is prolonged
Extend through the outer wall (35) and including multiple inlet holes (60;160), at least one exports public sealing (61;161) and it is more
A interface channel (63;163), wherein being each configured to connect corresponding hole (60;160) public sealing (61 is exported with described;
161)。
11. a kind of equipment generated for electric power, including at least one gas turbine (5), axis (A) extends and wraps along longitudinal direction
Include at least row's blade for being circumferentially spaced and extending radially outward from the corresponding supporting disk of the gas turbine (5)
(15)；At least one of blade (15) of the row is the claimed type in any one of preceding claims.
12. equipment according to claim 10, including at least one compressor (3), are connected to by absorption pipeline (33)
The gas turbine (5), the absorption pipeline are configured to extract cooling air from the compressor (3) and be supplied to described
The cooling device (29) of at least one blade (15).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP17174866.8 | 2017-06-07 | ||
| EP17174866.8A EP3412867B8 (en) | 2017-06-07 | 2017-06-07 | Cooled gas turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108999646A true CN108999646A (en) | 2018-12-14 |
Family
ID=59030843
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810580811.1A Pending CN108999646A (en) | 2017-06-07 | 2018-06-07 | Blade for gas turbine and the electric power generating device including the blade |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3412867B8 (en) |
| CN (1) | CN108999646A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10787932B2 (en) * | 2018-07-13 | 2020-09-29 | Honeywell International Inc. | Turbine blade with dust tolerant cooling system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55114806A (en) * | 1979-02-27 | 1980-09-04 | Hitachi Ltd | Gas turbine blade |
| US20030044277A1 (en) * | 2001-08-28 | 2003-03-06 | Snecma Moteurs | Gas turbine blade cooling circuits |
| US7862299B1 (en) * | 2007-03-21 | 2011-01-04 | Florida Turbine Technologies, Inc. | Two piece hollow turbine blade with serpentine cooling circuits |
| US8066483B1 (en) * | 2008-12-18 | 2011-11-29 | Florida Turbine Technologies, Inc. | Turbine airfoil with non-parallel pin fins |
| CN106593543A (en) * | 2016-11-28 | 2017-04-26 | 西北工业大学 | Arched groove gas film cooling structure for turbine blades |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4303374A (en) * | 1978-12-15 | 1981-12-01 | General Electric Company | Film cooled airfoil body |
| US6981846B2 (en) * | 2003-03-12 | 2006-01-03 | Florida Turbine Technologies, Inc. | Vortex cooling of turbine blades |
| US7563073B1 (en) * | 2006-10-10 | 2009-07-21 | Florida Turbine Technologies, Inc. | Turbine blade with film cooling slot |
| EP2107215B1 (en) | 2008-03-31 | 2013-10-23 | Alstom Technology Ltd | Gas turbine airfoil |
| US8366392B1 (en) * | 2009-05-06 | 2013-02-05 | Florida Turbine Technologies, Inc. | Composite air cooled turbine rotor blade |
| US8585365B1 (en) * | 2010-04-13 | 2013-11-19 | Florida Turbine Technologies, Inc. | Turbine blade with triple pass serpentine cooling |
-
2017
- 2017-06-07 EP EP17174866.8A patent/EP3412867B8/en active Active
-
2018
- 2018-06-07 CN CN201810580811.1A patent/CN108999646A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55114806A (en) * | 1979-02-27 | 1980-09-04 | Hitachi Ltd | Gas turbine blade |
| US20030044277A1 (en) * | 2001-08-28 | 2003-03-06 | Snecma Moteurs | Gas turbine blade cooling circuits |
| US7862299B1 (en) * | 2007-03-21 | 2011-01-04 | Florida Turbine Technologies, Inc. | Two piece hollow turbine blade with serpentine cooling circuits |
| US8066483B1 (en) * | 2008-12-18 | 2011-11-29 | Florida Turbine Technologies, Inc. | Turbine airfoil with non-parallel pin fins |
| CN106593543A (en) * | 2016-11-28 | 2017-04-26 | 西北工业大学 | Arched groove gas film cooling structure for turbine blades |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3412867B8 (en) | 2024-02-14 |
| EP3412867A1 (en) | 2018-12-12 |
| EP3412867B1 (en) | 2024-01-03 |
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