CN106471214A - The blade of gas turbine and the method manufacturing described blade - Google Patents
The blade of gas turbine and the method manufacturing described blade Download PDFInfo
- Publication number
- CN106471214A CN106471214A CN201580004412.5A CN201580004412A CN106471214A CN 106471214 A CN106471214 A CN 106471214A CN 201580004412 A CN201580004412 A CN 201580004412A CN 106471214 A CN106471214 A CN 106471214A
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- CN
- China
- Prior art keywords
- entrance
- blade
- outlet
- flow
- passage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
Abstract
A kind of blade for gas turbine (2) has elongate body (18) and cooling circuit (28), and cooling circuit (28) is supplied with cooling fluid and comprises first passage (29) and at least one second channel (30) being at least partially disposed in described main body (18)；First passage (29) has first entrance (32) and first outlet (33)；Second channel (30) has the second entrances (35) different from first entrance (32) and at least one second outlet (36) different with first outlet (33).
Description
Technical field
The present invention relates to the blade of gas turbine and the method manufacturing described blade.
In particular it relates to be installed in electric station be used for producing the stator vane of the gas turbine of electric energy.
Background technology
The stator vane of gas turbine is generally limited by the elongate body that inside is provided with cooling circuit.Cooling fluid,
The air typically extracted out from the machine set compressor producing energy, flows through cooling circuit.
In the gas turbine stator vane of known type, the air flowing through cooling circuit substantially has two functions：Cold
But function and sealing function.
Refrigerating function is implemented by multiple Cooling Holes that cooling circuit supplies by what the main body along blade was arranged；Sealing
Function is implemented by the sealing opening being formed on the track ring being connected with the anchor portion of blade；Described sealing opening is by cold
But loop supply.Described opening is arranged to fill by stator vane, track ring and rotor using the air from cooling circuit
The cavity being formed, and prevent the hot gas released in the turbine from occupying described cavity.
But, the air stream being provided to described cavity is typically not enough to the entrance stoping hot gas, in gas turbine
Obvious shortcoming is had on the reliability of efficiency and internal passages of gas turbine components.
Content of the invention
Therefore, one of target of the present invention be produce for gas turbine blade, it does not have referred to herein go out existing
The shortcoming of technology；Specifically, one of target of the present invention is to produce to make in the way of cheap and simple in terms of function with construction
Sealing and the optimized gas-turbine blade of refrigerating function.
According to described target, the present invention relates to a kind of blade for gas turbine, it includes：
Main body；
Cooling circuit, it is supplied with cooling fluid, and comprise to be at least partially disposed in described main body first is led to
Road and at least one second channel；First passage has first entrance and first outlet；Second channel has with first entrance not
Same second entrance and at least one second outlet different from first outlet.
In this way, the presence with two kinds of different passages of entrance independently allows to be each passed through first
The regulation of cooling fluid stream of outlet and second outlet and optimization.
Thus, for example, in the design phase it is possible to determine the size of the entrance of two kinds of passages, thus obtain it is each passed through
The predetermined amount of flow of the cooling fluid of first outlet and second outlet.
According to a preferred embodiment of the invention, blade includes being connected to main body and being suitable in use be connected to combustion gas
First anchor portion of the stator case of turbine；And be connected to main body and be suitable in use be connected to gas turbine
Second anchor portion of respective track ring；First entrance and second entrance are formed in the first anchor portion；First outlet
It is formed in the second anchor portion and second outlet is formed along main body.
For anchoring to the anchor portion of stator case and the presence determination for anchoring to the anchor portion of track ring
The stator vane of gas turbine.This has two kinds of different passages presence permissions of respective independent inlets in this case
Adjust and optimize sealing stream flow and the cooling stream flow of cooling fluid, therefore prevent by stator vane, track ring and rotor institute
The cavity limiting is filled by the hot gas of release in turbine.
According to a preferred embodiment of the invention, first passage connects with second channel.
In this way, can also be adjusted respectively by determining the size of the connecting portion between first passage and second channel
The first outlet that throttled and the stream of second outlet.
According to a preferred embodiment of the invention, the first connecting pipe is configured to have variable cross section.By this way, even
The size determination in adapter road is simplified.
According to a preferred embodiment of the invention, blade is included in the region be disposed in one of first entrance and second entrance
And be configured to reduce at least one metering plate of the flow section of first entrance or second entrance.
By this way, the stream entering first or second channel may be adjusted further.Thereby it is also possible to adjust stream respectively
Cross the flow value of first outlet and second outlet.For example, on connecting pipe between first and second passages or in the first He
In the case of there is manufacturing defect on the entrance and exit of second channel, described scheme is very useful.
According to preferred embodiment, metering plate has at least one first hole.By this way it is also possible to pass through determination first
The size in hole adjusts the stream entering first or second channel.
According to preferred embodiment, metering plate is formed so that the first hole has variable cross section.
By this way, the regulation entering the stream of first or second channel is simplified.
It is also an object of the present invention to provide a kind of manufacture method of gas-turbine blade, it ensures the heat in turbine
Expanding gas do not invade the cavity being limited by stator vane and rotor.
According to described target, the present invention relates to a kind of manufacture method of gas-turbine blade, it includes step：
Form the blade with cooling circuit, cooling circuit includes a first passage and at least one second channel；The
One passage has first entrance and first outlet；Second channel have different from the second entrance of first entrance and at least one the
Two outlets；
There is provided predetermined cooling fluid flow to first entrance and second entrance；
Detection respectively flows through the flow of the cooling fluid of first outlet and second outlet；
The flow flowing through the cooling fluid of first outlet and second outlet is compared with respective reference value；
Reduce the flow section of one of first entrance and second entrance.
Because methods described is it is possible to correct any manufacture mistake, thus ensureing that the inflation gas in turbine are not invaded
Enter the cavity being limited by stator vane and rotor.
Brief description
By the description of the non-limiting example below with reference to accompanying drawing, further features and advantages of the present invention will
It is made apparent from, wherein：
Fig. 1 is the schematic diagram of a part for the gas turbine comprising the blade according to the present invention, for the sake of clarity, part
Part is cut open and part is removed；
Fig. 2 is the sectional view of the blade according to Fig. 1 of the present invention, and for the sake of clarity, part is removed；
Fig. 3 is the axonometric chart of the details of the blade of Fig. 1, and for the sake of clarity, part is cut open and part quilt
Remove.
Specific embodiment
In FIG, reference 1 represents the gas turbine 2 for the electric station (in order to concisely not shown) producing electric energy
A part.
Electric station is known type, and include inner side have the compressor (not shown) of air stream, fuel and be derived from
The combustor of the air of compressor, gas turbine 2 and be mechanically connected to the axle of gas turbine 2 and compressor and be connected to
The electromotor (not shown) of power distribution network (not shown).
Gas turbine 2 extend along longitudinal axis A and include stator 4 and around axis A rotation rotor 5 (in Fig. 1 all parts
Be illustrated).
Stator 4 includes：Around axis A along the whole length of gas turbine 2 extend and be static stator case 7 (in Fig. 1
It is shown partially), the multiple track rings 8 supporting centered on axis A, by stator case 7 and being sequentially arranged along axis A,
And multiple stator vane 10.Stator vane 10 is divided into and multiple arrange and be radially disposed with regard to axis A.Each stator vane
10 are fixed to stator case 7 and respective track ring 8.
Rotor 5 includes being connected to multiple rotor rings 12 each other, thus limit around axis A rotation single element,
And it is divided into multiple multiple rotor blades 13 arranging and being radially disposed with regard to axis A.
Each rotor blade 13 has a free end 14 and an end 15 being connected to corresponding rotor 12.
Track ring 8 extends around rotor ring 12, and is spaced apart, so that the radial alignment of rotor blade 13 and stator vane
10 radial alignment replaces along axis A.
Multiple rotor rings 12, track ring 8 and stator case 7 define inflation channel 16, from combustor hot gas from
In flow through.
Each stator vane 10 includes elongated main body 18, the first anchor portion 19 and the second anchor portion 21, elongated
The respective axis that main body 18 radially extends B with regard to axis A extends, and the first anchor portion 19 is connected to of main body 18
End 20, and it is connected to stator case 7 in use, the second anchor portion 21 is connected to the contrary with end 20 of main body 18
An end 22 and be connected to respective track ring 8 in use.
In use, when connected, the second anchor portion 21 of adjacent stator blades 10 and respective track ring 8 limit
Annular seal space 23.
Track ring 8 has multiple sealing openings 24, their companies of establishing between the annular chamber 25 of annular seal space 23 and opening
Logical.Annular chamber 25 is by track ring 8, the anchor portion 21 of the stator vane being connected to track ring 8 and the vicinity in track ring 8
Rotor ring 12 limit.
Referring to Fig. 2, each stator vane 10 also includes the cooling circuit 28 being supplied with cooling fluid.
Cooling circuit 28 includes at least one first cooling duct 29, preferably bends to U-shaped, and the second cooling duct
30.
Therefore, the first cooling duct 29 is by being substantially parallel to axis B and mainly stretch into the Liang Ge branch 31 in main body 18 limit
Fixed.
Second cooling duct 29 is generally mainly stretched in main body 18 along axis B.
First cooling duct 29 has the first entrance 32 being formed in the first anchor portion 19 and is formed on second
First outlet 33 in anchor portion 21.
Second cooling duct 30 has the second entrance 35 being formed in the first anchor portion 19 and along main body 18 quilt
The multiple outlet openings 36 being formed.
First entrance 32 and second entrance 35 are substantially arranged side-by-side.
First cooling duct 29 and the second cooling duct 30 are preferably connected.
Specifically, two connecting pipes 37, two connecting pipes are passed through in the first cooling duct 29 and the second cooling duct 30
37 are preferably parallel and extend perpendicular to axis B.
In the first modification having been not shown, there is plural connecting pipe.
In the second modification having been not shown, the first cooling duct 29 and the second cooling duct 30 are passed through rightly to be determined
The singular association pipeline of size is connected.
In the 3rd modification having been not shown, one or more between the first cooling duct 29 and the second cooling duct 30
The flow section of connecting pipe is adjustable, such as by using being connected to the connecting pipe with variable cross section opening
Metering plate, or any other can block the device in the section of coupled connecting pipe.
Referring to Fig. 3, be formed on the second entrance 35 of the second cooling duct 30 on the first anchor portion 19 preferably by
It is connected to the metering plate 40 being configured to the flow section reducing second entrance 35.
In non-limiting embodiments described and illustrated herein, metering plate 40 has two holes 41 and has to enter with second
The essentially identical shape in mouthfuls 35 section.The connection of metering plate 40 to second entrance 35 determines the flow section of second entrance 35
Reduction.Hole 41 is by rightly sizing, thus the flow section required for obtaining reduces.
Preferably, metering plate 40 is soldered to the first anchor portion 19.
In the first modification having been not shown, metering plate has a single flow orifice.
In the second modification having been not shown, there is more than two flow orifice.
In the 3rd modification having been not shown, metering plate is shaped to limit one or more has scalable flow section
Hole.For example, metering plate can have the mobile structure being configured to the one or more holes partially or even wholly closing metering plate
Part.Alternatively, metering plate is by can be connected to each other and be shaped to jointly limit the Part I of variable cross section opening and second
Divide and limit.For example, Part I and Part II geometrically can be connected in multiple positions, thus limiting variable cross section opening.
In other modifications, described plate does not have hole and is fully closed coupled entrance, thus reducing by 100% enter
Mouth flow.
Referring to Fig. 1, in cooling circuit 28, the cooling fluid of circulation is preferably derived from and suctions out loop 41 (by schematically
Illustrate) air, suction out loop and be configured to extract out air supply the air to be formed on from generating set compressor
Multiple bore of stators 43 in stator case 7.By first entrance 32 and second entrance 35, each bore of stator 43 is complete with same column
The cooling circuit 28 of portion's stator vane connects.
The cooling circuit 28 of each stator vane 10 passes through first entrance 32 and second entrance 35 receives from respective fixed
Total air mass flow QTOT in sub- chamber 43, and cooling air delivery QR is passed through to carry along multiple outlet openings 36 that main body 18 is formed
Supply inflation channel 26, seal gas flow QS is supplied to annular seal space 23 by first outlet 33.
In design phase, first entrance 32 and second entrance 35, first outlet 33, outlet opening 36 and connecting pipe 37 are determined
Size, so that sealing flow QS and cooling flow QR are equal to respective reference value.
But, blade passes through casting and is manufactured, and the presence of manufacturing defect does not ensure to seal flow QS and cooling flow
The reference value of QR is truly observed.
In order to avoid this problem, a kind of manufacture method is used, and it includes carrying out performance survey on the blade just having produced
Examination, the sealing flow QS flowing out first outlet 33 during testing and cooling flow QR passing through outlet opening 36 are detected.
If sealing flow QS and/or cooling flow QR do not reflect reference value, described manufacture method provides first
The reduction of the flow section of both one of entrance 32 and second entrance 35 or entrance 32 and 35.
Specifically, methods described passes through appropriately to be determined that the connection of the metering plate 40 of size provides the flowing of second entrance 35
The reduction in section.
The size of metering plate 40 additionally aids and adjusts further to the air supply of the second cooling duct 30, and therefore adjusts
The flow QR of section cooling air.
It should be understood that if sealing flow QS and cooling flow QR reflect reference value, metering plate 40 is not used.
Finally, blade described herein and method are made with change and change without deviating from scope of the following claims
It is obvious.
Claims (18)
1. a kind of blade for gas turbine (2), it includes：
Main body (18)；
Cooling circuit (28), it is supplied with cooling fluid, and comprises be at least partially disposed in described main body (18)
One passage (29) and at least one second channel (30)；First passage (29) has first entrance (32) and first outlet (33)；
Second channel (30) has the second entrances (35) different from first entrance (32), and at least one is different from first outlet (33)
Second outlet (36).
2. blade according to claim 1, it includes being connected to main body (18) and being suitable in use be connected to combustion
First anchor portion (19) of the stator case (7) of air turbine (2)；First entrance (32) and second entrance (35) are formed on
In one anchor portion (19).
3. blade according to claim 1 and 2, it includes being connected to main body (18) and being suitable in use be connected to
Second anchor portion (21) of the respective track ring (8) of gas turbine (2)；First outlet (33) is formed on the second anchor portion
Divide in (21).
4. the blade according to any one of aforementioned claim, wherein, second outlet (36) is along main body (18) by shape
Become.
5. the blade according to any one of aforementioned claim, wherein, first passage (29) and second channel (30) are
It is in fluid communication.
6. blade according to claim 5, wherein, first passage (29) and second channel (30) pass through at least one first
Connecting pipe (37) is connected.
7. blade according to claim 6, wherein, first passage (29) and second channel (30) pass through at least one second
Connecting pipe (37) is connected.
8. the blade according to claim 6 or 7, wherein, the first connecting pipe (37) is configured to have variable cross section.
9. the blade according to claim 7 or 8, wherein, the first connecting pipe and the second connecting pipe (37) are essentially identical.
10. the blade according to any one of aforementioned claim, it includes being connected to first entrance (32) and/or
Two entrances (35) simultaneously are configured to reduce at least one of the flow section of first entrance (32) and/or second entrance (35) respectively
Metering plate (40).
11. blades according to claim 10, wherein, metering plate (40) has at least one first hole (41).
12. blades according to claim 11, wherein, it is variable that metering plate (40) is configured such that the first hole (41) has
Section.
13. blades according to claim 12, wherein, metering plate (40) includes at least one mobile member, and it is configured
To close at least first hole (41) at least in part.
14. blades according to claim 12, wherein, metering plate (40) includes to be connected to each other and being shaped to jointly limit
Surely there is the Part I at least first hole (41) and the Part II of variable cross section.
15. blades according to claim 14, wherein, Part I is connected in multiple geometry of positions with Part II,
To limit first hole (41) with variable cross section.
A kind of 16. manufacture methods of the blade (10) of gas turbine (2), it includes step：
Manufacture has a blade (10) of cooling circuit (28), cooling circuit (28) include first passage (29) and at least one second
Passage (30)；First passage (29) has first entrance (32) and first outlet (33)；Second channel (30) has different from
The second entrance (35) of one entrance (32) and at least one second outlet (36) different from first outlet (33)；
There is provided predetermined cooling fluid flow (QTOT) to first entrance (32) and second entrance (35)；
The first flow (QS) of the cooling fluid of first outlet (33) is flow through in detection；
The second flow (QR) of the cooling fluid of second outlet (36) is flow through in detection；
The first flow (QS) of cooling fluid and second flow (QR) are compared with respective reference value；
Reduce the flow section of at least one in first entrance (32) and second entrance (35).
17. methods according to claim 16, wherein, reduce at least one in first entrance (32) and second entrance (35)
The step of flow section include for metering plate (40) being connected in first entrance (32) and second entrance (35) at least one
Step.
18. methods according to claim 16 or 17, wherein, the step of manufacture blade (10) includes manufacture wherein first and leads to
The step of the blade (10) that road (29) and second channel (30) are connected to each other by least one first connecting pipe (37).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ITMI20140033 | 2014-01-13 | ||
| ITMI2014A000033 | 2014-01-13 | ||
| PCT/IB2015/050247 WO2015104695A1 (en) | 2014-01-13 | 2015-01-13 | Blade for a gas turbine and method for manufacturing said blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106471214A true CN106471214A (en) | 2017-03-01 |
| CN106471214B CN106471214B (en) | 2019-04-02 |
Family
ID=50159392
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201580004412.5A Active CN106471214B (en) | 2014-01-13 | 2015-01-13 | The blade of gas turbine and the method for manufacturing the blade |
Country Status (4)
| Country | Link |
|---|---|
| EP (1) | EP3094822B1 (en) |
| KR (1) | KR20160125952A (en) |
| CN (1) | CN106471214B (en) |
| WO (1) | WO2015104695A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110043328A (en) * | 2018-12-17 | 2019-07-23 | 中国航发沈阳发动机研究所 | A kind of cooled change geometry low-pressure turbine guide vane |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FI125111B (en) | 2013-11-19 | 2015-06-15 | Kemira Oyj | A method for analyzing a sample comprising first and second anticaking agents |
| JP6791777B2 (en) * | 2017-02-10 | 2020-11-25 | 三菱パワー株式会社 | Geothermal turbine |
| EP3663522B1 (en) * | 2018-12-07 | 2021-11-24 | ANSALDO ENERGIA S.p.A. | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
| EP3816402B1 (en) * | 2019-11-04 | 2023-01-04 | ANSALDO ENERGIA S.p.A. | Stator assembly for a gas turbine and gas turbine comprising said stator assembly |
| EP4019742A1 (en) * | 2020-12-23 | 2022-06-29 | ANSALDO ENERGIA S.p.A. | A sealing assembly for a vane set of a gas turbine engine and gas turbine engine comprising such a sealing assembly |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6186741B1 (en) * | 1999-07-22 | 2001-02-13 | General Electric Company | Airfoil component having internal cooling and method of cooling |
| US20090185893A1 (en) * | 2008-01-22 | 2009-07-23 | United Technologies Corporation | Radial inner diameter metering plate |
| US20100054915A1 (en) * | 2008-08-28 | 2010-03-04 | United Technologies Corporation | Airfoil insert |
| WO2010139766A1 (en) * | 2009-06-04 | 2010-12-09 | Ansaldo Energia S.P.A. | Turbine blade |
-
2015
- 2015-01-13 WO PCT/IB2015/050247 patent/WO2015104695A1/en active Application Filing
- 2015-01-13 CN CN201580004412.5A patent/CN106471214B/en active Active
- 2015-01-13 KR KR1020167021096A patent/KR20160125952A/en not_active Application Discontinuation
- 2015-01-13 EP EP15707775.1A patent/EP3094822B1/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6186741B1 (en) * | 1999-07-22 | 2001-02-13 | General Electric Company | Airfoil component having internal cooling and method of cooling |
| US20090185893A1 (en) * | 2008-01-22 | 2009-07-23 | United Technologies Corporation | Radial inner diameter metering plate |
| US20100054915A1 (en) * | 2008-08-28 | 2010-03-04 | United Technologies Corporation | Airfoil insert |
| WO2010139766A1 (en) * | 2009-06-04 | 2010-12-09 | Ansaldo Energia S.P.A. | Turbine blade |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110043328A (en) * | 2018-12-17 | 2019-07-23 | 中国航发沈阳发动机研究所 | A kind of cooled change geometry low-pressure turbine guide vane |
| CN110043328B (en) * | 2018-12-17 | 2021-10-22 | 中国航发沈阳发动机研究所 | Cooled variable-geometry low-pressure turbine guide vane |
Also Published As
| Publication number | Publication date |
|---|---|
| KR20160125952A (en) | 2016-11-01 |
| CN106471214B (en) | 2019-04-02 |
| EP3094822A1 (en) | 2016-11-23 |
| EP3094822B1 (en) | 2021-10-06 |
| WO2015104695A1 (en) | 2015-07-16 |
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