EP1644614B1 - Gekühlte schaufel für eine gasturbine - Google Patents

Gekühlte schaufel für eine gasturbine Download PDF

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Publication number
EP1644614B1
EP1644614B1 EP04766104.6A EP04766104A EP1644614B1 EP 1644614 B1 EP1644614 B1 EP 1644614B1 EP 04766104 A EP04766104 A EP 04766104A EP 1644614 B1 EP1644614 B1 EP 1644614B1
Authority
EP
European Patent Office
Prior art keywords
blade
vane
cooling
cooling duct
bores
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.)
Expired - Lifetime
Application number
EP04766104.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1644614A1 (de
Inventor
Shailendra Naik
Sacha Parneix
Ulrich Rathmann
Helene Saxer-Felici
Stefan Schlechtriem
Beat Von Arx
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1644614A1 publication Critical patent/EP1644614A1/de
Application granted granted Critical
Publication of EP1644614B1 publication Critical patent/EP1644614B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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 for example from the document US-A-4,278,400 known.
  • Fig. 1 is a basic configuration of such 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, the blade 11 merges 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 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 by deflection regions 17, 18 with each other fluidly and a serpentine with form a plurality of turns (see the flow arrows in the cooling channels 13, 14, 15 of the 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 with increasing temperature through the cooling channels and reaches the highest temperature in the last cooling channel 15 of the trailing edge 20.
  • the trailing edge 20 of the blade 10 may 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.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention consists in that the additional flow is supplied via bores running transversely through the blade or the blade shank and which 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 here as in the main flow flowing into the main cooling inlet.
  • Through the supply via the holes a mixture of the two streams is achieved, which leads to a significantly improved cooling of the trailing edge of the blade.
  • the holes can open directly into the deflection area. But you can also open into a radially extending channel below the deflection, which is in communication with the deflection.
  • 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 opposing bores are provided which extend obliquely upward in the flow direction and each include an angle between 30 ° and 90 ° with the vertical.
  • the holes are arranged staggered in the radial and axial directions, wherein the holes have a predetermined inner diameter, the radial distance of the holes, normalized to the inner diameter, in the range between 1 and 4, the axial distance, normalized to the inner diameter, in the range is between 0 and 3, and the radial distance of the upper bore of the second deflection region, normalized to the inner 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 substantially unchanged despite the clogging of the additional flow.
  • the second means comprise additional outlet openings, which are arranged between the main cooling inlet and the second deflection region, 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.
  • 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 to 4 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 partially passes through openings in the shroud section 21 (bores 27, Fig. 5 to 8 ) 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).
  • Additional cooling medium is supplied through the blade shank 25 and a core opening 24 provided in the blade root by means of two bores 22, 23.
  • the holes 22, 23 are - as from the Fig. 2 to 4 is clearly recognizable - staggered in the radial and in the axial direction and are opposite each other ( Fig. 3, 4 ).
  • the bores 22, 23 are inclined at an angle between 30 ° and 90 ° to the vertical, wherein they extend in the flow direction (from outside to inside) obliquely upward.
  • the holes 22, 23 terminate in the core opening 24 in the blade root 12. They are thus incorporated in the region of the blade 10, the serves for supporting and removing the casting core and thus is present anyway.
  • the bores 22, 23 can also extend further upwards and open directly into the deflection region 18. Furthermore, it is conceivable to provide a radially arranged quartz rod instead of the core opening, which ensures a connection of the bores with the deflection region.
  • the purpose of the multiple feed of cooling medium is to introduce cooler cooling medium directly into the trailing edge region of the blade 10. This introduction takes place in such a way that the main flow of the cooling medium supplied by the main cooling inlet 16 is hindered or blocked as little as possible.
  • the axial distance x between the holes 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 holes 22 and 23 is normalized to the diameter d, preferably in a range of y / d between 1 and 4 (see Fig. 2 ).
  • the normalized to d distance of the upper bore 22 from the second inner deflection region 18 is preferably in a range of l / d between 1 and 4 ( Fig. 2 ).
  • 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 such that uneven beam penetration into the main flow of the shroud cavity occurs.
  • the cooling medium has the same pressure and the same temperature. Therefore, there is 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. In the deflection 18 there is a deflection of the main flow by about 135 °.
  • the additional flow is then advantageously fed at a point of the deflection region 18, where a deflection of approximately 90 ° has already taken place.
  • the blade does not have a shroud through which a part of the cooling medium flow exits, it is necessary to widen the cross section of the second cooling channel 15 in such a way that it takes into account the additional flow mixed in the second deflection region 18.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04766104.6A 2003-07-12 2004-06-30 Gekühlte schaufel für eine gasturbine Expired - Lifetime EP1644614B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10331635.3A DE10331635B4 (de) 2003-07-12 2003-07-12 Gekühlte Schaufel für eine Gasturbine
PCT/EP2004/051309 WO2005005785A1 (de) 2003-07-12 2004-06-30 Gekühlte schaufel für eine gasturbine

Publications (2)

Publication Number Publication Date
EP1644614A1 EP1644614A1 (de) 2006-04-12
EP1644614B1 true EP1644614B1 (de) 2013-08-28

Family

ID=33560081

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04766104.6A Expired - Lifetime EP1644614B1 (de) 2003-07-12 2004-06-30 Gekühlte schaufel für eine gasturbine

Country Status (11)

Country Link
US (1) US7264445B2 (zh)
EP (1) EP1644614B1 (zh)
KR (2) KR101146158B1 (zh)
CN (1) CN1849439B (zh)
AR (1) AR046072A1 (zh)
CA (1) CA2531754C (zh)
DE (1) DE10331635B4 (zh)
ES (1) ES2436750T3 (zh)
MX (1) MXPA06000402A (zh)
TW (1) TWI338075B (zh)
WO (1) WO2005005785A1 (zh)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
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 (en) * 2009-03-23 2010-10-06 Alstom Technology Ltd Gas turbine
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

Family Cites Families (14)

* Cited by examiner, † Cited by third party
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
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
GB1268911A (en) 1969-09-26 1972-03-29 Rolls Royce Improvements in or relating to blades
GB1551678A (en) * 1978-03-20 1979-08-30 Rolls Royce Cooled rotor blade for a gas turbine engine
US4278400A (en) * 1978-09-05 1981-07-14 United Technologies Corporation Coolable rotor blade
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
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
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
US6491496B2 (en) * 2001-02-23 2002-12-10 General Electric Company Turbine airfoil with metering plates for refresher holes

Also Published As

Publication number Publication date
US20060177310A1 (en) 2006-08-10
MXPA06000402A (es) 2006-04-05
WO2005005785A1 (de) 2005-01-20
DE10331635B4 (de) 2014-02-13
ES2436750T3 (es) 2014-01-07
CN1849439A (zh) 2006-10-18
CA2531754C (en) 2012-10-09
KR101146158B1 (ko) 2012-05-25
EP1644614A1 (de) 2006-04-12
TW200508478A (en) 2005-03-01
KR20110134505A (ko) 2011-12-14
KR20060030114A (ko) 2006-04-07
AR046072A1 (es) 2005-11-23
CA2531754A1 (en) 2005-01-20
DE10331635A1 (de) 2005-02-03
US7264445B2 (en) 2007-09-04
TWI338075B (en) 2011-03-01
CN1849439B (zh) 2010-12-08

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