EP1228293A1 - Turbine blade and method for producing a turbine blade - Google Patents
Turbine blade and method for producing a turbine bladeInfo
- Publication number
- EP1228293A1 EP1228293A1 EP00969567A EP00969567A EP1228293A1 EP 1228293 A1 EP1228293 A1 EP 1228293A1 EP 00969567 A EP00969567 A EP 00969567A EP 00969567 A EP00969567 A EP 00969567A EP 1228293 A1 EP1228293 A1 EP 1228293A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- cooling gas
- throttle device
- flow
- throttle
- 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
Links
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C21/00—Flasks; Accessories therefor
- B22C21/12—Accessories
- B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49339—Hollow blade
- Y10T29/49341—Hollow blade with cooling passage
Definitions
- the invention relates to a turbine blade, in particular a gas turbine blade, with a head, a foot and an airfoil area and with an inner channel system made up of individual channels, through which cooling gas can be passed on a flow path within the turbine blade and with a throttle device influencing the flow of the cooling gas. direction, wherein in the channels cooling gas from the foot area through the airfoil area to the head area and is diverted in the opposite direction, and with outlet openings for the discharge of the cooling gas from the turbine blade, which are arranged on the downstream side of the turbine blade, and the invention relates to a method for Production of a turbine blade with the features of the preamble of claim 10.
- the action fluid is heated to a high temperature.
- a cooling gas flows through the guide vanes and rotor blades closest to the combustion chamber so that they can withstand the high temperatures prevailing there, which in some cases lie above critical values for the material used to manufacture the turbine blade.
- the temperature on and within the turbine blade is lowered by the cooling gas, so that the mechanical stability and thus the functionality of the turbine blade is ensured under these conditions.
- an outer wall of the turbine blade, around which an action fluid flows surrounds a meandering channel system, which repeats the cooling gas from a foot area to a head area of the turbine blade and again leads back to the foot area.
- the area of the cooling gas introduction is referred to as the leading edge area and the area of the cooling gas discharge is referred to as the leading edge area.
- a plurality of outlet openings are provided in the outlet edge area, which connect the duct system of the turbine blade to an outer space through which the action fluid flows.
- the object of the present invention is therefore to provide a turbine blade having the features mentioned at the beginning with a throttle device for adjusting the flow of the cooling gas without influencing the flow of the cooling gas on the To design the leading edge and - as a sub-task - to provide a structurally simple and also individually adaptable method for producing such a turbine blade.
- the object is achieved in that the throttle device is arranged upstream of the outlet openings in the rear region of the flow path.
- the flow of the cooling gas can be throttled without adverse effects on the flow of the cooling gas.
- the flow at the leading edge is largely undisturbed.
- the throttling occurs only in a rear area of the flow path.
- the cooling gas flow has left most of its path behind and has already fulfilled the tasks of heat dissipation, which are linked to a sufficient flow rate.
- the pressure difference between the first cooling chamber and the surrounding hot action fluid is maintained, so that no hot gas can enter the blade, which would lead to severe damage. Reliable cooling of the turbine blade is thus ensured.
- the consumption of cooling gas is minimized. It is only necessary to use as much cooling gas for the turbine blade as is absolutely necessary to prevent overheating. In this way, an optimal cooling of the turbine blade and at the same time a good efficiency of the turbine are obtained.
- the opening can be a passage opening due to the casting process, but also a bsw after casting in the turbine blade. act opening made by drilling.
- the location of the throttle device can be better adapted to the model and casting-dependent needs.
- the sub-task directed towards the production of a turbine blade is achieved in that, after the casting process, a throttle device influencing the flow of the cooling gas is introduced in the rear region of the flow path, upstream of the outlet openings, and is set up in a production-related through-opening while measuring the flow of the cooling gas. that a predetermined value of a flow parameter of the cooling gas is reached and then the throttle device is permanently attached in the throttle position.
- This procedure means that a certain cooling gas restriction does not have to be taken into account during the casting process itself. This facilitates the casting process, simplifies the molds and reduces waste.
- An opening caused by the casting for example caused by a connection of the casting core to the casting outer jacket that holds the core in position, can be used in this way.
- the throttle device closes the feedthrough opening. This saves an otherwise necessary work step.
- the method of manufacture is very similar for different blade types if the casting core is held in its position relative to the casting outer shell during the casting process by means of a guide bracket in the foot area of the turbine blade, and a throttle device is inserted into the through opening caused by the holder. This simplifies the manufacturing process, reduces the conversion time and the number of parts to be used when manufacturing different types of turbine blades.
- a particularly simple and easily reproducible manufacturing process with low material costs is provided in that the measurement of the cooling gas flow takes place after the insertion of plugs with different throttle projections, and that the plug is welded in that causes a predetermined flow of the cooling gas.
- the throttle projection is also predetermined.
- the plug can be approximately the same by model measurement for turbine blades of the same series. This lowers the manufacturing costs because work steps are simplified or eliminated.
- An individual adjustment of the cooling air flow is possible in that a stopper with a throttle screw, which has a throttle protrusion protruding into the flow path, is inserted into the lead-through opening caused by the casting production, and in that the flow rate is measured under The screw is adjusted, which is then caulked in the desired throttle position.
- the screw position can be changed continuously while the measurement is running. This allows a very precise setting that is adapted to the cooling requirements.
- the caulking of the screw ensures a secure fastening without damaging the material of the turbine blade. For a series of turbine blades that have approximately the same cooling requirements and the same internal structure of the cooling channels, a setting of the screw previously determined in an exemplary cooling flow measurement can be marked and adjusted. The plug with the set screw is then inserted directly into the turbine blade and the screw is caulked.
- FIG. 1 a longitudinal section through a foot area of a turbine blade with throttle device
- FIG. 2 a longitudinal section through a foot area with a stopper
- FIG. 3 a perspective top view of a base area of a turbine blade with a plug
- FIG. 4 a longitudinal section through a base area with a plug and a throttle screw
- Fig. 6 a casting mold with a casting core.
- the channel system 5 shows a longitudinal section through a base area 2 and part of a channel system 5 of a gas-cooled turbine blade 1.
- the channel system 5 is located essentially in the blade area 3 of the turbine blade 1. It has an inlet opening 22 at the base area 2, at the beginning of the flow path 6 of the cooling gas, through which cooling gas is introduced into the channel system 5, and outlet openings 8 in the outflow region 21 of the turbine blade 1, through which the cooling gas at the end of its flow path 6 leaves the channel system 5.
- the cooling gas is guided along its flow path 6 in a meandering manner in the channels 12, which are separated from one another by intermediate walls 21, from the foot area 2 to the head area (not shown) and again to the foot area 2.
- the channels 12 are connected to one another by reversal points 13 which adjoin the foot region 2 or the head region.
- FIG. 2 shows a longitudinal section through the base region 2 of a turbine blade with a throttling plug 20.
- the plug 20 is held in a through opening 10 by means of a shoulder 26.
- the plug 20 has a throttle projection 17, with which the cooling gas flow can be reduced in the inserted state.
- the stopper 20 is on the last reversing parts 13 before the cooling gas emerges from the duct system
- the flow path 6 is divided into two partial flow paths at the reversal point 13 by means of a curved guide rib 18, a first cooling gas partial flow path 23 which is directly adjacent to the foot region 2 and a second cooling gas partial flow path 24 which is separated by the guide rib 18.
- the cooling gas partial flows passed through are after passing _J t P 1 o L ⁇ o L ⁇ o L ⁇ cn H 1 ddi P. cn ⁇ hh 3 dd cn d> ⁇ j ⁇ Hi ⁇ tSJ 3 SD hh cn i Pi Hi ⁇ rt d hj cn i rr>.
- Pi Pi cn o 3 3 N 3 3 ET P- SD: 3 SD d Es ⁇ - ⁇ oo Hj ⁇ - i ET rt P. ⁇ ⁇ d hi ⁇ 3 • n 3 i iQ rt «rt o ⁇ - • ⁇ Pi ⁇ ⁇ - hh ⁇ - dd ⁇ - IQ to t cn ET rt ⁇ Pi SD d P ⁇ ( Q ⁇ - d 3 ⁇ 3 h- 1 SD ⁇ - ⁇ - ⁇ 3 3 i 3 rt oo rt 3 SD ET ⁇ cn ⁇ ta SD ET 3 cn d cn m ⁇ 3 dd iQ P ) ( Q ⁇ iQ 3 m Hi H!
- ⁇ rt 3 ET 3 p- 3 3 ⁇ - ⁇ cn • ⁇ - ⁇ d m rt ⁇
- Hi ⁇ Hi ⁇ - o 3 3 ⁇ ⁇ er d E ⁇ ) ET ⁇ - ⁇ m ⁇ d IQ Pi 3 Hi ⁇ • er) ⁇ - ⁇ - ⁇ 3 ⁇ cn 3 ⁇ ET
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00969567A EP1228293B1 (en) | 1999-11-12 | 2000-10-30 | Method for producing a turbine blade |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99122577 | 1999-11-12 | ||
EP99122577A EP1099825A1 (en) | 1999-11-12 | 1999-11-12 | Turbine blade and production method therefor |
PCT/EP2000/010678 WO2001036790A1 (en) | 1999-11-12 | 2000-10-30 | Turbine blade and method for producing a turbine blade |
EP00969567A EP1228293B1 (en) | 1999-11-12 | 2000-10-30 | Method for producing a turbine blade |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1228293A1 true EP1228293A1 (en) | 2002-08-07 |
EP1228293B1 EP1228293B1 (en) | 2005-02-16 |
Family
ID=8239379
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99122577A Withdrawn EP1099825A1 (en) | 1999-11-12 | 1999-11-12 | Turbine blade and production method therefor |
EP00969567A Expired - Lifetime EP1228293B1 (en) | 1999-11-12 | 2000-10-30 | Method for producing a turbine blade |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99122577A Withdrawn EP1099825A1 (en) | 1999-11-12 | 1999-11-12 | Turbine blade and production method therefor |
Country Status (6)
Country | Link |
---|---|
US (1) | US6631561B1 (en) |
EP (2) | EP1099825A1 (en) |
JP (1) | JP4474085B2 (en) |
CN (1) | CN1312381C (en) |
DE (1) | DE50009560D1 (en) |
WO (1) | WO2001036790A1 (en) |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7216694B2 (en) * | 2004-01-23 | 2007-05-15 | United Technologies Corporation | Apparatus and method for reducing operating stress in a turbine blade and the like |
US7137782B2 (en) * | 2004-04-27 | 2006-11-21 | General Electric Company | Turbulator on the underside of a turbine blade tip turn and related method |
US7210906B2 (en) * | 2004-08-10 | 2007-05-01 | Pratt & Whitney Canada Corp. | Internally cooled gas turbine airfoil and method |
EP1869289B1 (en) * | 2005-04-11 | 2014-12-03 | Alstom Technology Ltd | Guide vane support |
EP1843007A1 (en) * | 2006-04-06 | 2007-10-10 | Siemens Aktiengesellschaft | Turbine blade with separate closing element |
EP2003291B1 (en) | 2007-06-15 | 2017-08-09 | Ansaldo Energia Switzerland AG | Cast turbine blade and method of manufacture |
EP2476863A1 (en) * | 2011-01-14 | 2012-07-18 | Siemens Aktiengesellschaft | Turbine blade for a gas turbine |
EP2628900A1 (en) | 2012-02-14 | 2013-08-21 | Siemens Aktiengesellschaft | Turbine vane with a throttling element |
US8985940B2 (en) | 2012-03-30 | 2015-03-24 | Solar Turbines Incorporated | Turbine cooling apparatus |
US9546554B2 (en) | 2012-09-27 | 2017-01-17 | Honeywell International Inc. | Gas turbine engine components with blade tip cooling |
US9670797B2 (en) * | 2012-09-28 | 2017-06-06 | United Technologies Corporation | Modulated turbine vane cooling |
EP2826955A1 (en) | 2013-07-15 | 2015-01-21 | Siemens Aktiengesellschaft | Cast turbine airfoil with opening closed with a plug and method for closing an opening of a cast turbine airfoil |
EP2832953A1 (en) * | 2013-07-29 | 2015-02-04 | Siemens Aktiengesellschaft | Turbine blade |
CN103586634A (en) * | 2013-11-01 | 2014-02-19 | 哈尔滨汽轮机厂有限责任公司 | Method for manufacturing flow diversion core of hollow turbine stator blades of gas turbine |
EP2918775A1 (en) | 2014-03-11 | 2015-09-16 | Siemens Aktiengesellschaft | Method for closing an opening of a turbine blade and plug suited for same |
EP3081751B1 (en) * | 2015-04-14 | 2020-10-21 | Ansaldo Energia Switzerland AG | Cooled airfoil and method for manufacturing said airfoil |
EP3147455A1 (en) | 2015-09-23 | 2017-03-29 | Siemens Aktiengesellschaft | Turbine vane with a throttling arrangement |
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 |
KR102193940B1 (en) * | 2018-01-22 | 2020-12-22 | 두산중공업 주식회사 | Vane ring assembly, assembly method thereof and gas turbine including the same |
EP3862537A1 (en) * | 2020-02-10 | 2021-08-11 | General Electric Company Polska sp. z o.o. | Cooled turbine nozzle and nozzle segment |
GB202213805D0 (en) * | 2022-09-22 | 2022-11-09 | Rolls Royce Plc | Platform for stator vane |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL32747C (en) * | 1931-01-19 | |||
US2906494A (en) * | 1956-06-12 | 1959-09-29 | Daniel J Mccarty | Heat responsive means for blade cooling |
BE794195A (en) * | 1972-01-18 | 1973-07-18 | Bbc Sulzer Turbomaschinen | COOLED STEERING VANE FOR GAS TURBINES |
BE794194A (en) * | 1972-01-18 | 1973-07-18 | Bbc Sulzer Turbomaschinen | COOLED MOBILE BLADE FOR GAS TURBINES |
IT1096996B (en) * | 1977-07-22 | 1985-08-26 | Rolls Royce | METHOD FOR THE MANUFACTURE OF A BLADE OR BLADE FOR GAS TURBINE ENGINES |
FR2468727A1 (en) * | 1979-10-26 | 1981-05-08 | Snecma | IMPROVEMENT TO COOLED TURBINE AUBES |
GB2078596A (en) * | 1980-06-19 | 1982-01-13 | Rolls Royce | Method of Making a Blade |
US4883404A (en) * | 1988-03-11 | 1989-11-28 | Sherman Alden O | Gas turbine vanes and methods for making same |
US5243759A (en) * | 1991-10-07 | 1993-09-14 | United Technologies Corporation | Method of casting to control the cooling air flow rate of the airfoil trailing edge |
EP0925426A1 (en) * | 1996-09-04 | 1999-06-30 | Siemens Aktiengesellschaft | Turbine blade which can be exposed to a hot gas flow |
US5820774A (en) * | 1996-10-28 | 1998-10-13 | United Technologies Corporation | Ceramic core for casting a turbine blade |
DE19733148C1 (en) * | 1997-07-31 | 1998-11-12 | Siemens Ag | Cooling device for gas turbine initial stage |
JP2002512334A (en) * | 1998-04-21 | 2002-04-23 | シーメンス アクチエンゲゼルシヤフト | Turbine blade |
DE19821770C1 (en) * | 1998-05-14 | 1999-04-15 | Siemens Ag | Mold for producing a hollow metal component |
US6155783A (en) * | 1998-05-20 | 2000-12-05 | Voith Siemens Hydro Power Generation, Inc. | Hollow blade for hydraulic turbine or pump |
JP3666256B2 (en) * | 1998-08-07 | 2005-06-29 | 株式会社日立製作所 | Steam turbine blade manufacturing method |
DE59905944D1 (en) * | 1998-08-31 | 2003-07-17 | Siemens Ag | TURBINE BLADE |
-
1999
- 1999-11-12 EP EP99122577A patent/EP1099825A1/en not_active Withdrawn
-
2000
- 2000-10-30 US US10/129,850 patent/US6631561B1/en not_active Expired - Lifetime
- 2000-10-30 JP JP2001538649A patent/JP4474085B2/en not_active Expired - Fee Related
- 2000-10-30 EP EP00969567A patent/EP1228293B1/en not_active Expired - Lifetime
- 2000-10-30 WO PCT/EP2000/010678 patent/WO2001036790A1/en active IP Right Grant
- 2000-10-30 DE DE50009560T patent/DE50009560D1/en not_active Expired - Lifetime
- 2000-10-30 CN CNB008169950A patent/CN1312381C/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO0136790A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE50009560D1 (en) | 2005-03-24 |
JP4474085B2 (en) | 2010-06-02 |
US6631561B1 (en) | 2003-10-14 |
JP2003515024A (en) | 2003-04-22 |
CN1312381C (en) | 2007-04-25 |
EP1228293B1 (en) | 2005-02-16 |
CN1409800A (en) | 2003-04-09 |
EP1099825A1 (en) | 2001-05-16 |
WO2001036790A1 (en) | 2001-05-25 |
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