EP1709298B1 - Gekühlte schaufel für eine gasturbine - Google Patents
Gekühlte schaufel für eine gasturbine Download PDFInfo
- Publication number
- EP1709298B1 EP1709298B1 EP05701516.6A EP05701516A EP1709298B1 EP 1709298 B1 EP1709298 B1 EP 1709298B1 EP 05701516 A EP05701516 A EP 05701516A EP 1709298 B1 EP1709298 B1 EP 1709298B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- cooling
- cooling duct
- inlet
- cooling medium
- 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.)
- Not-in-force
Links
- 238000001816 cooling Methods 0.000 claims description 55
- 239000002826 coolant Substances 0.000 claims description 27
- 239000012530 fluid Substances 0.000 claims 1
- 239000007789 gas Substances 0.000 description 8
- 239000002184 metal Substances 0.000 description 3
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000009291 secondary effect Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- 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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
-
- 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
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- 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
Definitions
- the present invention relates to the field of gas turbine technology. It relates to a cooled blade for a gas turbine according to the preamble of claim 1.
- Such a blade is for example from the document US-A-4,278,400 known.
- Fig. 1 is a basic configuration of a shovel with shroud shown.
- the blade 10 comprises an airfoil 11 that merges downwards over a blade shank 25 into a blade root 12. At the upper end, that is, at the blade tip or blade tip, the blade 11 goes into a shroud portion 21, which forms a closed, annular shroud together with the shroud portions of the other blades at a complete blade ring.
- the airfoil has a span that extends from the blade shank to the blade tip. If the blade is installed in a turbine, the span of the blade is oriented in the radial direction of the turbine cross-section, which is why the direction of the span is hereinafter also referred to as the radial direction.
- the Blade sheet 11 has a front edge 19, which is flowed by the hot gas, and a trailing edge 20.
- a plurality of radial cooling channels 13, 14 and 15 are arranged, which are connected to each other by flow deflection 17, 18 with each other and a Serpentine with several Windings form (see the flow arrows in the cooling channels 13, 14,15 of Fig. 1 ).
- the cooling medium Due to the one-time passage of the cooling medium through the serpentine-like successive cooling channels 13, 14, 15, the cooling medium flows through the cooling channels with increasing temperature and reaches the highest temperature in the last cooling channel 15 of the trailing edge 20.
- the trailing edge 20 of the blade 10 can therefore be excessively high under certain operating conditions Temperatures of the cooling medium and the blade material or metal reach. The resulting mismatch of metal temperature over the axial length of the blade can lead to high temperature creep and consequently deformation of the trailing edge 20.
- a shovel with shroud as in Fig. 1 is shown, there is a tilting of the shroud segments 21 in the axial, radial and circumferential direction as a secondary effect of the trailing edge deformation.
- the tilting of the shroud segments 21 may cause the gaps between individual shroud segments to open and allow the entry of high temperature hot gas into the shroud cavity.
- the temperatures of the shroud metal can increase significantly and quickly induce creep of the shroud and eventually lead to high temperature failure of the shroud.
- an additional flow of cooling medium is diverted directly from the main cooling inlet and via a between the Main cooling inlet and the second deflection region extending opening, in an exemplary embodiment, a bore or an opening made during casting, is fed to the running along the trailing edge of the cooling channel. Since the flow of the cooling medium is diverted through the bypass bore from the main cooling flow and later added again, the cooling medium flow remains unchanged overall.
- An advantageous embodiment of the invention is characterized in that the bore is formed and arranged so that the flowing through the bore cooling medium flows through the second deflection directly into the second cooling channel. This results in a particularly efficient temperature reduction by the bypass flow in the cooling channel of the trailing edge.
- a preferred embodiment of a cooled gas turbine blade with multiple feed of the cooling medium according to the invention is in the Fig. 1 and 2 played.
- the main flow of the cooling medium occurs in the region of the blade shank 25 through a main cooling inlet 16 from below into the cooling channel 13 and passes partially through openings in the shroud section 21 (bores 27, Fig. 3 to 6 ) and partially along the trailing edge 20 again (see the in Fig. 1 Plotted arrows on the shroud portion 21 and at the trailing edge 20).
- a portion of the cooling medium flowing into the main cooling inlet 16 is branched off through a bore 23 and fed via the second deflection region 18 to the cooling channel 15 at the trailing edge.
- the bore 23 is preferably formed and arranged (i.e., obliquely upwardly in the present case) in such a way that the cooling medium flow flowing through it is directed directly into the cooling channel 15 without detours.
- the purpose of the bypass bore 23 is to introduce cooler cooling medium directly into the trailing edge region of the blade 10.
- the shroud portion 21 of the blade 10 further holes 27, 28, 29 are provided ( Fig. 3 to 6 ).
- the cooling medium exiting through the bores 27, 28, 29 serves to actively cool the shroud section 21.
- the cooling bores 27, 28, 29 in the shroud section 21 preferably have an inner diameter in the range between 0.6 mm and 4 mm. All three holes 27,28, 29 are positioned and dimensioned on the shroud portion 21, that an uneven Beam penetration takes place in the main flow of the shroud cavity.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004002327A DE102004002327A1 (de) | 2004-01-16 | 2004-01-16 | Gekühlte Schaufel für eine Gasturbine |
PCT/EP2005/050137 WO2005068783A1 (de) | 2004-01-16 | 2005-01-14 | Gekühlte schaufel für eine gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1709298A1 EP1709298A1 (de) | 2006-10-11 |
EP1709298B1 true EP1709298B1 (de) | 2015-11-11 |
Family
ID=34716622
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05701516.6A Not-in-force EP1709298B1 (de) | 2004-01-16 | 2005-01-14 | Gekühlte schaufel für eine gasturbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US7520724B2 (zh) |
EP (1) | EP1709298B1 (zh) |
CN (1) | CN100408812C (zh) |
DE (1) | DE102004002327A1 (zh) |
TW (1) | TWI356870B (zh) |
WO (1) | WO2005068783A1 (zh) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2898384B1 (fr) * | 2006-03-08 | 2011-09-16 | Snecma | Aube mobile de turbomachine a cavite commune d'alimentation en air de refroidissement |
US7731483B2 (en) * | 2007-08-01 | 2010-06-08 | General Electric Company | Airfoil shape for a turbine bucket and turbine incorporating same |
US7988420B2 (en) * | 2007-08-02 | 2011-08-02 | General Electric Company | Airfoil shape for a turbine bucket and turbine incorporating same |
EP2180141B1 (en) | 2008-10-27 | 2012-09-12 | Alstom Technology Ltd | Cooled blade for a gas turbine and gas turbine having such a blade |
EP2230383A1 (en) | 2009-03-18 | 2010-09-22 | Alstom Technology Ltd | Blade for a gas turbine with cooled tip cap |
WO2013167513A1 (en) | 2012-05-07 | 2013-11-14 | Alstom Technology Ltd | Method for manufacturing of components made of single crystal (sx) or directionally solidified (ds) superalloys |
US10145269B2 (en) | 2015-03-04 | 2018-12-04 | General Electric Company | System and method for cooling discharge flow |
GB201506728D0 (en) * | 2015-04-21 | 2015-06-03 | Rolls Royce Plc | Thermal shielding in a gas turbine |
GB201512810D0 (en) | 2015-07-21 | 2015-09-02 | Rolls Royce Plc | Thermal shielding in a gas turbine |
JP5905631B1 (ja) * | 2015-09-15 | 2016-04-20 | 三菱日立パワーシステムズ株式会社 | 動翼、これを備えているガスタービン、及び動翼の製造方法 |
US10683763B2 (en) | 2016-10-04 | 2020-06-16 | Honeywell International Inc. | Turbine blade with integral flow meter |
US10378363B2 (en) | 2017-04-10 | 2019-08-13 | United Technologies Corporation | Resupply hole of cooling air into gas turbine blade serpentine passage |
US10961854B2 (en) * | 2018-09-12 | 2021-03-30 | Raytheon Technologies Corporation | Dirt funnel squealer purges |
US11021961B2 (en) | 2018-12-05 | 2021-06-01 | General Electric Company | Rotor assembly thermal attenuation structure and system |
US11118462B2 (en) * | 2019-01-24 | 2021-09-14 | Pratt & Whitney Canada Corp. | Blade tip pocket rib |
US11371359B2 (en) | 2020-11-26 | 2022-06-28 | Pratt & Whitney Canada Corp. | Turbine blade for a gas turbine engine |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4278400A (en) * | 1978-09-05 | 1981-07-14 | United Technologies Corporation | Coolable rotor blade |
FR2468727A1 (fr) * | 1979-10-26 | 1981-05-08 | Snecma | Perfectionnement aux aubes de turbine refroidies |
US4775296A (en) * | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US4474532A (en) * | 1981-12-28 | 1984-10-02 | United Technologies Corporation | Coolable airfoil for a rotary machine |
EP0340149B1 (en) * | 1988-04-25 | 1993-05-19 | United Technologies Corporation | Dirt removal means for air cooled blades |
JPH09505655A (ja) * | 1993-11-24 | 1997-06-03 | ユナイテッド テクノロジーズ コーポレイション | 冷却されたタービン用翼型 |
US5915923A (en) * | 1997-05-22 | 1999-06-29 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade |
JPH11241602A (ja) * | 1998-02-26 | 1999-09-07 | Toshiba Corp | ガスタービン翼 |
US6832889B1 (en) * | 2003-07-09 | 2004-12-21 | General Electric Company | Integrated bridge turbine blade |
US6966756B2 (en) * | 2004-01-09 | 2005-11-22 | General Electric Company | Turbine bucket cooling passages and internal core for producing the passages |
US7137780B2 (en) * | 2004-06-17 | 2006-11-21 | Siemens Power Generation, Inc. | Internal cooling system for a turbine blade |
-
2004
- 2004-01-16 DE DE102004002327A patent/DE102004002327A1/de not_active Ceased
-
2005
- 2005-01-14 EP EP05701516.6A patent/EP1709298B1/de not_active Not-in-force
- 2005-01-14 CN CNB2005800023337A patent/CN100408812C/zh not_active Expired - Fee Related
- 2005-01-14 WO PCT/EP2005/050137 patent/WO2005068783A1/de not_active Application Discontinuation
- 2005-01-14 TW TW094101211A patent/TWI356870B/zh not_active IP Right Cessation
-
2006
- 2006-07-10 US US11/483,091 patent/US7520724B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
EP1709298A1 (de) | 2006-10-11 |
WO2005068783A1 (de) | 2005-07-28 |
CN100408812C (zh) | 2008-08-06 |
CN1910343A (zh) | 2007-02-07 |
TW200532096A (en) | 2005-10-01 |
US7520724B2 (en) | 2009-04-21 |
US20060292006A1 (en) | 2006-12-28 |
TWI356870B (en) | 2012-01-21 |
DE102004002327A1 (de) | 2005-08-04 |
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