WO2005005785A1 - Gekühlte schaufel für eine gasturbine - Google Patents
Gekühlte schaufel für eine gasturbine Download PDFInfo
- Publication number
- WO2005005785A1 WO2005005785A1 PCT/EP2004/051309 EP2004051309W WO2005005785A1 WO 2005005785 A1 WO2005005785 A1 WO 2005005785A1 EP 2004051309 W EP2004051309 W EP 2004051309W WO 2005005785 A1 WO2005005785 A1 WO 2005005785A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- cooling
- bores
- flow
- cooling channel
- Prior art date
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
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/185—Two-dimensional patterned serpentine-like
-
- 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
- F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle
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 e.g. known from US-A-4,278,400.
- FIG. 1 shows a basic configuration of such a shovel with a shroud.
- the blade 10 comprises an airfoil 11 which merges downwards into a blade root 12 via a blade shaft 25. At the upper end, the airfoil 11 merges into a shroud section 21 which, in the case of a complete shroud, together with the shroud sections of the other
- Blades form a closed, ring-shaped shroud.
- the airfoil 11 has a leading edge 19, which is flown by the hot gas, and a rear edge 20.
- a plurality of radial cooling channels 13, 14 and 15 are arranged, which are connected to one another in terms of flow by deflection regions 17, 18 and one Form a serpentine with several turns (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 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 rear edge 20.
- the rear edge 20 of the blade 10 can therefore be below certain excessive operating temperatures of the cooling medium and the blade material or metal.
- the resulting mismatch of the metal temperature over the axial length of the blade can lead to high temperature creep and consequently to the deformation of the trailing edge 20.
- the secondary effect of the trailing edge deformation is a tilting of the shroud segments 21 in the axial, radial and circumferential direction.
- the tilting of the shroud segments 21 can lead to the gaps between individual shroud segments opening and the entry of high-temperature hot gas into the shroud cavity.
- the temperatures of the shroud metal can rise significantly and quickly cause the shroud to creep and ultimately lead to the high-temperature failure of the shroud.
- This known type of multiple supply with cooling medium has various disadvantages: the injector changes the pressure conditions and flow conditions in the cooling ducts massively compared to the configuration with single supply through the entrance of the cooling duct at the front edge. In particular, a balance must be found between the cooling medium flowing out at the front edge for film cooling and the cooling medium drawn in by the injector. This requires a completely new design of the blade cooling, which is difficult to adapt to changing requirements.
- the injector principle and the associated negative pressure generation are not suitable for blades without film cooling of the leading edge and blades with a cooled shroud.
- the object is achieved by the entirety of the features of claim 1.
- the essence of the invention is that the additional flow is supplied via bores which run transversely through the blade or the blade shaft and are directly or indirectly connected to the deflection region.
- the pressure and the temperature of the additional flow supplied through the core opening are the same as for the main flow flowing into the main cooling inlet.
- the holes can open directly into the deflection area. However, they can also open into a radially extending channel below the deflection area, which is connected to the deflection area.
- a first preferred embodiment of the invention is characterized in that a radially oriented core opening is provided in the blade root and that the bores run through the blade shaft and open into the core opening.
- At least two bores lying opposite one another are provided which run obliquely upward in the direction of flow and each form an angle between 30 ° and 90 ° with the vertical.
- the bores are staggered in the radial and axial directions, the bores having a predetermined inner diameter, the radial distance of the bores, standardized to the inner diameter, in the range between 1 and 4, the axial distance, standardized to the inner diameter, in the range is between 0 and 3, and the radial distance of the upper bore from the second deflection area, normalized to the inside diameter, is in the range between 1 and 4.
- second means are provided which ensure that the main flow of the cooling medium through the first cooling channel remains essentially unchanged despite the addition of the additional flow.
- the second means comprise additional outlet openings which are arranged between the main cooling inlet and the second deflection area and through which a partial flow of the main flow of the cooling medium emerges.
- the blade has a shroud section at the upper end and the additional outlet openings are bores arranged in the shroud section. This also enables significantly improved cooling of the shroud.
- FIG. 1 shows in longitudinal section the configuration of a cooled gas turbine blade with multiple supply of the cooling medium and cooled cover band according to a preferred embodiment of the invention
- FIG. 2 shows the foot region of the blade from FIG. 1 in an enlarged view with two bores for supplying the additional cooling medium flow; 3, 4 each show a section through the base of the blade from FIG. 2 in a plane perpendicular to the section plane of FIG. 2 through one of the two bores for supplying the additional coolant flow;
- FIGS. 1, 2 shows a top view of the shroud section of the blade from FIGS. 1, 2;
- FIG. 6-8 different sections through the shroud area of the blade from Fig. 1, 2 along the parallel sectional planes A-A, B-B and C-C shown in Fig. 5.
- FIGS. 1 to 4 A preferred embodiment of a cooled gas turbine blade with multiple supply of the cooling medium according to the invention is shown in FIGS. 1 to 4.
- the main flow of the cooling medium in the area of the blade shaft 25 enters the cooling channel 13 from below through a main cooling inlet 16 and partly passes through openings in the shroud section 21 (bores 27,..., 29 in FIGS. 5 to 8) and partly along the rear edge 20 again (see the arrows drawn in FIG. 1 on the shroud section 21 and on the rear edge 20).
- Additional cooling medium is supplied through the blade shaft 25 and a core opening 24 present in the blade root by means of two bores 22, 23.
- the bores 22, 23 are - as can be clearly seen from FIGS. 2 to 4 - staggered in the radial and in the axial direction and lie opposite one another (FIGS. 3, 4).
- the bores 22, 23 are inclined at an angle between 30 ° and 90 ° to the vertical, whereby they run obliquely upwards in the direction of flow (from the outside inwards).
- the bores 22, 23 end in the core opening 24 in the blade root 12. They are thus incorporated in the area of the blade 10 that serves to support and remove the cast core and is therefore available anyway.
- the bores 22, 23 can also extend further up and open directly into the deflection area 18. Furthermore, it is conceivable to provide a radially arranged quartz rod instead of the core opening, which ensures a connection of the bores to the deflection area.
- the purpose of the multiple supply of cooling medium is to introduce cooler cooling medium directly into the rear edge area of the blade 10. This introduction takes place in such a way that the main flow of the cooling medium supplied through the main cooling inlet 16 is prevented or blocked as little as possible.
- the axial distance x between the bores 22 and 23 is, normalized to the diameter d of the bores 22, 23, preferably in a range of x / d between 0 and 3 (see FIG. 2).
- the radial distance y between the bores 22 and 23 is, normalized to the diameter d, preferably in a range of y / d between 1 and 4 (see FIG. 2).
- the distance of the upper bore 22 normalized to d from the second inner deflection area 18 is preferably in a range of 1 / d between 1 and 4 (FIG. 2).
- further bores 27, 28, 29 are provided in the shroud section 21 of the blade (FIGS. 5 to 8).
- the purpose of these additional bores 27, 28, 29 is to ensure that the mass flow of the cooling medium in the front cooling channel 13 remains largely unchanged despite the supply of the additional cooling medium through the bores 23, 24.
- the cooling medium emerging through the bores 27, 28, 29 serves to actively cool the shroud section.
- 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 bores 27, 28, 29 are positioned and dimensioned on the shroud section 21 in such a way that an uneven beam penetration into the main stream of the shroud cavity takes place.
- the cooling medium has the same pressure and the same temperature. There is therefore a mixture of the cooling medium main flow with the additional flow within the deflection region 18, which leaves the pressure and the flow rate largely unchanged.
- the main flow is deflected by approximately 135 °.
- the additional flow is then advantageously supplied at a point of the deflection area 18 where a deflection of approximately 90 ° has already taken place. If - starting from a blade configuration without multiple supply of the cooling medium - bores 22, 23 and 27,..., 29 are provided in the region of the blade root 12 and in the shroud section 21 according to FIG. 1, the cooling in the region is provided the trailing edge 20 is significantly improved without the main cooling flow and thus the cooling of the remaining blade being changed. Active cooling of the shroud section 21 is also obtained.
- the blade does not have a shroud through which a part of the cooling medium flow exits, it is necessary to expand the cross section of the second cooling channel 15 so that it takes into account the additional flow mixed in the second deflection area 18.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2004800260342A CN1849439B (zh) | 2003-07-12 | 2004-06-30 | 用于燃气轮机的被冷却的叶片 |
MXPA06000402A MXPA06000402A (es) | 2003-07-12 | 2004-06-30 | Alabe o paleta enfriada para turbina de gas. |
EP04766104.6A EP1644614B1 (de) | 2003-07-12 | 2004-06-30 | Gekühlte schaufel für eine gasturbine |
KR1020067000708A KR101146158B1 (ko) | 2003-07-12 | 2004-06-30 | 가스 터빈용 피냉각 블레이드 또는 베인 |
CA2531754A CA2531754C (en) | 2003-07-12 | 2004-06-30 | Cooled blade or vane for a gas turbine |
ES04766104.6T ES2436750T3 (es) | 2003-07-12 | 2004-06-30 | Pala refrigerada para una turbina de gas |
US11/330,268 US7264445B2 (en) | 2003-07-12 | 2006-01-12 | Cooled blade or vane for a gas turbine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10331635.3 | 2003-07-12 | ||
DE10331635.3A DE10331635B4 (de) | 2003-07-12 | 2003-07-12 | Gekühlte Schaufel für eine Gasturbine |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/330,268 Continuation US7264445B2 (en) | 2003-07-12 | 2006-01-12 | Cooled blade or vane for a gas turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005005785A1 true WO2005005785A1 (de) | 2005-01-20 |
Family
ID=33560081
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2004/051309 WO2005005785A1 (de) | 2003-07-12 | 2004-06-30 | Gekühlte schaufel für eine gasturbine |
Country Status (11)
Country | Link |
---|---|
US (1) | US7264445B2 (de) |
EP (1) | EP1644614B1 (de) |
KR (2) | KR101146158B1 (de) |
CN (1) | CN1849439B (de) |
AR (1) | AR046072A1 (de) |
CA (1) | CA2531754C (de) |
DE (1) | DE10331635B4 (de) |
ES (1) | ES2436750T3 (de) |
MX (1) | MXPA06000402A (de) |
TW (1) | TWI338075B (de) |
WO (1) | WO2005005785A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101586477B (zh) * | 2008-05-23 | 2011-04-13 | 中国科学院工程热物理研究所 | 一种具有射流冲击作用的扰流挡板强化传热装置 |
CH699999A1 (de) | 2008-11-26 | 2010-05-31 | Alstom Technology Ltd | Gekühlte schaufel für eine gasturbine. |
EP2236746A1 (de) * | 2009-03-23 | 2010-10-06 | Alstom Technology Ltd | Gasturbine |
US8545170B2 (en) * | 2009-10-27 | 2013-10-01 | General Electric Company | Turbo machine efficiency equalizer system |
US20130052035A1 (en) * | 2011-08-24 | 2013-02-28 | General Electric Company | Axially cooled airfoil |
US9032733B2 (en) | 2013-04-04 | 2015-05-19 | General Electric Company | Turbomachine system with direct header steam injection, related control system and program product |
KR102230700B1 (ko) * | 2017-09-12 | 2021-03-23 | 한국기계연구원 | 가스 터빈용 블레이드 |
KR20200021594A (ko) | 2018-08-21 | 2020-03-02 | 이재진 | 어린이 보호구역 차단기 |
KR20200069876A (ko) | 2018-12-07 | 2020-06-17 | 연세대학교 산학협력단 | 냉각 성능 향상을 위한 단락요철 구조를 포함하는 가스터빈 블레이드 |
CN112969337B (zh) * | 2021-02-01 | 2023-01-06 | 中节能宁夏新能源股份有限公司 | 超算数据中心冷却方法 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB817660A (en) * | 1955-05-27 | 1959-08-06 | Bristol Aero Engines Ltd | Improvements in or relating to blades for gas turbines |
US3719431A (en) * | 1969-09-26 | 1973-03-06 | Rolls Royce | Blades |
US4177010A (en) * | 1977-01-04 | 1979-12-04 | Rolls-Royce Limited | Cooled rotor blade for a gas turbine engine |
US4278400A (en) * | 1978-09-05 | 1981-07-14 | United Technologies Corporation | Coolable rotor blade |
GB2250548A (en) * | 1990-12-06 | 1992-06-10 | Rolls Royce Plc | Cooled turbine aerofoil blade |
US5813835A (en) * | 1991-08-19 | 1998-09-29 | The United States Of America As Represented By The Secretary Of The Air Force | Air-cooled turbine blade |
US20020119045A1 (en) * | 2001-02-23 | 2002-08-29 | Starkweather John Howard | Turbine airfoil with metering plates for refresher holes |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB855058A (en) * | 1957-02-22 | 1960-11-30 | Rolls Royce | Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines |
US4775296A (en) * | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US4761116A (en) * | 1987-05-11 | 1988-08-02 | General Electric Company | Turbine blade with tip vent |
US5403159A (en) * | 1992-11-30 | 1995-04-04 | United Technoligies Corporation | Coolable airfoil structure |
JP3238344B2 (ja) | 1997-02-20 | 2001-12-10 | 三菱重工業株式会社 | ガスタービン静翼 |
JPH10280904A (ja) * | 1997-04-01 | 1998-10-20 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却動翼 |
US6524847B2 (en) * | 2000-06-23 | 2003-02-25 | E. I. Du Pont De Nemours And Company | Composting system |
-
2003
- 2003-07-12 DE DE10331635.3A patent/DE10331635B4/de not_active Expired - Fee Related
-
2004
- 2004-06-30 MX MXPA06000402A patent/MXPA06000402A/es active IP Right Grant
- 2004-06-30 WO PCT/EP2004/051309 patent/WO2005005785A1/de active Application Filing
- 2004-06-30 KR KR1020067000708A patent/KR101146158B1/ko not_active IP Right Cessation
- 2004-06-30 ES ES04766104.6T patent/ES2436750T3/es active Active
- 2004-06-30 CA CA2531754A patent/CA2531754C/en not_active Expired - Fee Related
- 2004-06-30 CN CN2004800260342A patent/CN1849439B/zh active Active
- 2004-06-30 KR KR1020117025895A patent/KR20110134505A/ko not_active Application Discontinuation
- 2004-06-30 EP EP04766104.6A patent/EP1644614B1/de active Active
- 2004-07-08 AR ARP040102433A patent/AR046072A1/es not_active Application Discontinuation
- 2004-07-12 TW TW093120792A patent/TWI338075B/zh not_active IP Right Cessation
-
2006
- 2006-01-12 US US11/330,268 patent/US7264445B2/en not_active Expired - Fee Related
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB817660A (en) * | 1955-05-27 | 1959-08-06 | Bristol Aero Engines Ltd | Improvements in or relating to blades for gas turbines |
US3719431A (en) * | 1969-09-26 | 1973-03-06 | Rolls Royce | Blades |
US4177010A (en) * | 1977-01-04 | 1979-12-04 | Rolls-Royce Limited | Cooled rotor blade for a gas turbine engine |
US4278400A (en) * | 1978-09-05 | 1981-07-14 | United Technologies Corporation | Coolable rotor blade |
GB2250548A (en) * | 1990-12-06 | 1992-06-10 | Rolls Royce Plc | Cooled turbine aerofoil blade |
US5813835A (en) * | 1991-08-19 | 1998-09-29 | The United States Of America As Represented By The Secretary Of The Air Force | Air-cooled turbine blade |
US20020119045A1 (en) * | 2001-02-23 | 2002-08-29 | Starkweather John Howard | Turbine airfoil with metering plates for refresher holes |
Also Published As
Publication number | Publication date |
---|---|
KR101146158B1 (ko) | 2012-05-25 |
MXPA06000402A (es) | 2006-04-05 |
EP1644614A1 (de) | 2006-04-12 |
US7264445B2 (en) | 2007-09-04 |
DE10331635A1 (de) | 2005-02-03 |
EP1644614B1 (de) | 2013-08-28 |
US20060177310A1 (en) | 2006-08-10 |
CA2531754C (en) | 2012-10-09 |
AR046072A1 (es) | 2005-11-23 |
CN1849439B (zh) | 2010-12-08 |
TWI338075B (en) | 2011-03-01 |
CN1849439A (zh) | 2006-10-18 |
CA2531754A1 (en) | 2005-01-20 |
DE10331635B4 (de) | 2014-02-13 |
ES2436750T3 (es) | 2014-01-07 |
KR20060030114A (ko) | 2006-04-07 |
TW200508478A (en) | 2005-03-01 |
KR20110134505A (ko) | 2011-12-14 |
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