EP1456505A1 - Thermally loaded component - Google Patents
Thermally loaded componentInfo
- Publication number
- EP1456505A1 EP1456505A1 EP02779098A EP02779098A EP1456505A1 EP 1456505 A1 EP1456505 A1 EP 1456505A1 EP 02779098 A EP02779098 A EP 02779098A EP 02779098 A EP02779098 A EP 02779098A EP 1456505 A1 EP1456505 A1 EP 1456505A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- deflection
- thermally loaded
- loaded component
- cooling
- parts
- 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.)
- Withdrawn
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
- 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
- Y10T29/49341—Hollow blade with cooling passage
-
- 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
- Y10T29/4998—Combined manufacture including applying or shaping of fluent material
- Y10T29/49988—Metal casting
- Y10T29/49989—Followed by cutting or removing material
Definitions
- the invention is based on a thermally loaded component according to the preamble of the first claim.
- blades are known in which cooling fluid is conducted from the trailing edge region of the blade to the leading edge region via cooling channels formed by partition walls and then blown out via openings in the blade head. In order to cool the trailing edge area of the bucket sufficiently, you blow air out of the rear edge of the blade. Deflection vanes are arranged in order to divert the cooling fluid into the cooling channels.
- deflection blades are often arranged in the region of the deflection channels.
- these deflection blades are very fragile and difficult to manufacture using the casting process, even with large components such as for large blades of stationary gas turbines.
- tensions can form in the cast body because the inner, relatively small-sized parts and the outer parts have different cooling rates. In individual cases, these tensions can lead to cracks in the internal structures, which means that the cast part cannot be used. If the defects are not noticed, the cast part can break during use and e.g. with blades, additional blades and destroy the turbine.
- the invention is based on the object of avoiding problems with previously known means for deflecting the cooling fluid in a thermally loaded component with at least one cooling channel of the type mentioned at the outset and nevertheless enabling efficient cooling.
- the deflection device consists of two mutually spaced deflection parts over the height of the cooling channel.
- the advantages of the invention can be seen, inter alia, in the fact that the function of the deflection device with respect to previously known deflection blades is not impaired by the inventive design of the deflection device.
- the primary function of the deflection device the prevention of pressure losses and the avoidance of a separation of the cooling fluid flow after the deflection channel is further guaranteed.
- the deflecting parts according to the invention are arranged in cooling ducts of blades of heat engines.
- FIG. 1 shows a partial longitudinal section through a blade of a turbine.
- FIG. 4 shows a cross section through a deflection device according to the invention
- Fig. 5 shows a cross section through a further inventive
- FIG. 1 shows a blade 10 of a turbomachine, consisting of a blade 1 and a blade root 11, with which the blade 10 can be mounted on a rotor or stator, not shown.
- a platform 12 is usually arranged between the airfoil 1 and the airfoil 11 and shields the airfoil and thus the rotor or stator from the fluids flowing around the airfoil.
- the airfoil 1 has a leading edge region 3, a trailing edge region 4, a suction-side wall 5 and a pressure-side wall 6 (see FIG. 3a), the suction-side and the pressure-side wall being connected to one another in the region of the leading edge 3 and the trailing edge 4, as a result of which a cavity 2 is formed.
- the front edge region 3 is first acted upon by the fluids flowing around the airfoil 1.
- the cavity 2 extends essentially in the radial direction through the blade 10 and serves as a cooling fluid passage for a cooling fluid 20.
- essentially radially extending partition walls 8 are arranged in the cavity 2 in order to generate cooling channels 21.
- These cooling channels 21 are connected by deflection channels 22, which are designed in such a way that the pressure loss during the deflection is minimal and the heat transfer is as homogeneous as possible in order to avoid local hot zones.
- additional deflection devices such as deflection blades 9, are arranged in the region of the deflection channels 22.
- deflecting blades 9 can be designed as desired according to FIGS. 2a, 2b and 2c, e.g. with regard to thickness along the blade, the radius of curvature etc. and must be adapted to the conditions in the deflection channel 22.
- 3a, 3b and 4 show the deflection vane according to the invention consisting of a first deflection part 9a on the suction side and an opposite second deflection part 9b on the pressure side of the vane.
- the deflection parts 9a and 9b are at a distance ⁇ from one another, which can be up to 30% of the height 23 of the cooling channel 21 at the location of the deflection parts.
- the design of the deflecting parts 9a and 9b according to the invention does not impair the function of the deflecting device with respect to previously known deflecting blades.
- the primary function of the deflection vane is the prevention of pressure losses and the avoidance of a separation of the cooling fluid flow 20 after the deflection channel 22.
- the deflecting parts can be designed as desired, as shown in FIGS. 2a, 2b and 2c and described above for the deflecting vane.
- the function of the deflection parts namely the prevention of pressure losses and the avoidance of separation of the cooling fluid flow 20 after the deflection channel 22, is maintained.
- the distance ⁇ was achieved by arranging a weak point in the deflection vane due to a narrowing or notch 24 in the casting mold.
- the deflection vane breaks into two parts after the casting process during cooling and the resulting shrinkage, and thus produces the two deflection parts 9a and 9b with the spacing ⁇ .
- the distance ⁇ and its shape can be set by the design of the notch 24.
- Such deflection parts can generally be arranged in curvatures of cooling channels of thermally loaded components in order to avoid the problems described above.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH22512001 | 2001-12-10 | ||
CH225101 | 2001-12-10 | ||
PCT/CH2002/000661 WO2003054356A1 (en) | 2001-12-10 | 2002-12-04 | Thermally loaded component |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1456505A1 true EP1456505A1 (en) | 2004-09-15 |
Family
ID=4568221
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02779098A Withdrawn EP1456505A1 (en) | 2001-12-10 | 2002-12-04 | Thermally loaded component |
Country Status (4)
Country | Link |
---|---|
US (1) | US7137784B2 (en) |
EP (1) | EP1456505A1 (en) |
AU (1) | AU2002342500A1 (en) |
WO (1) | WO2003054356A1 (en) |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102005012803A1 (en) * | 2005-03-19 | 2006-09-21 | Alstom Technology Ltd. | Rotor blade for gas turbine stage, has whirling effect producing structures, which are formed as elevated sections on inner wall surfaces of coolant duct and enclose narrow gap, where duct is defined by side walls of blade sheet |
US7303376B2 (en) * | 2005-12-02 | 2007-12-04 | Siemens Power Generation, Inc. | Turbine airfoil with outer wall cooling system and inner mid-chord hot gas receiving cavity |
US7955053B1 (en) | 2007-09-21 | 2011-06-07 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine cooling circuit |
EP2143883A1 (en) * | 2008-07-10 | 2010-01-13 | Siemens Aktiengesellschaft | Turbine blade and corresponding casting core |
US8985940B2 (en) * | 2012-03-30 | 2015-03-24 | Solar Turbines Incorporated | Turbine cooling apparatus |
US9228439B2 (en) * | 2012-09-28 | 2016-01-05 | Solar Turbines Incorporated | Cooled turbine blade with leading edge flow redirection and diffusion |
US20140093388A1 (en) * | 2012-09-28 | 2014-04-03 | Solar Turbines Incorporated | Cooled turbine blade with leading edge flow deflection and division |
JP2018512535A (en) * | 2015-03-17 | 2018-05-17 | シーメンス エナジー インコーポレイテッド | Turbine blade with unconstrained flow diverting guide structure |
KR101691095B1 (en) * | 2015-04-20 | 2016-12-29 | 연세대학교 산학협력단 | Structure of discrete guide vane in the internal cooling channel to control local cooling performance on internal surface |
DE102015112643A1 (en) * | 2015-07-31 | 2017-02-02 | Wobben Properties Gmbh | Wind turbine rotor blade |
US10012092B2 (en) | 2015-08-12 | 2018-07-03 | United Technologies Corporation | Low turn loss baffle flow diverter |
US10184341B2 (en) | 2015-08-12 | 2019-01-22 | United Technologies Corporation | Airfoil baffle with wedge region |
US10450874B2 (en) * | 2016-02-13 | 2019-10-22 | General Electric Company | Airfoil for a gas turbine engine |
US10718219B2 (en) * | 2017-12-13 | 2020-07-21 | Solar Turbines Incorporated | Turbine blade cooling system with tip diffuser |
US10774657B2 (en) | 2018-11-23 | 2020-09-15 | Raytheon Technologies Corporation | Baffle assembly for gas turbine engine components |
EP3862537A1 (en) * | 2020-02-10 | 2021-08-11 | General Electric Company Polska sp. z o.o. | Cooled turbine nozzle and nozzle segment |
CN111852574A (en) * | 2020-07-27 | 2020-10-30 | 北京全四维动力科技有限公司 | Turbine blade and gas turbine comprising same |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1223308A2 (en) * | 2000-12-16 | 2002-07-17 | ALSTOM (Switzerland) Ltd | Cooling of a turbo machine component |
Family Cites Families (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US612250A (en) * | 1898-10-11 | Heinrich von der linde | ||
US3171631A (en) * | 1962-12-05 | 1965-03-02 | Gen Motors Corp | Turbine blade |
GB1188401A (en) | 1966-02-26 | 1970-04-15 | Gen Electric | Cooled Vane Structure for High Temperature Turbines |
US3628885A (en) | 1969-10-01 | 1971-12-21 | Gen Electric | Fluid-cooled airfoil |
US3804551A (en) | 1972-09-01 | 1974-04-16 | Gen Electric | System for the introduction of coolant into open-circuit cooled turbine buckets |
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 |
US4474532A (en) * | 1981-12-28 | 1984-10-02 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US4775296A (en) * | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US5232343A (en) * | 1984-05-24 | 1993-08-03 | General Electric Company | Turbine blade |
GB2165315B (en) * | 1984-10-04 | 1987-12-31 | Rolls Royce | Improvements in or relating to hollow fluid cooled turbine blades |
JPS62228603A (en) | 1986-03-31 | 1987-10-07 | Toshiba Corp | Gas turbine blade |
GB9014762D0 (en) | 1990-07-03 | 1990-10-17 | Rolls Royce Plc | Cooled aerofoil vane |
EP0475658A1 (en) | 1990-09-06 | 1992-03-18 | General Electric Company | Turbine blade airfoil with serial impingement cooling through internal cavity-forming ribs |
US5695321A (en) * | 1991-12-17 | 1997-12-09 | General Electric Company | Turbine blade having variable configuration turbulators |
JP3666602B2 (en) | 1992-11-24 | 2005-06-29 | ユナイテッド・テクノロジーズ・コーポレイション | Coolable airfoil structure |
US5403159A (en) | 1992-11-30 | 1995-04-04 | United Technoligies Corporation | Coolable airfoil structure |
GB9402442D0 (en) | 1994-02-09 | 1994-04-20 | Rolls Royce Plc | Cooling air cooled gas turbine aerofoil |
JP3137527B2 (en) | 1994-04-21 | 2001-02-26 | 三菱重工業株式会社 | Gas turbine blade tip cooling system |
US5498126A (en) | 1994-04-28 | 1996-03-12 | United Technologies Corporation | Airfoil with dual source cooling |
US5599166A (en) | 1994-11-01 | 1997-02-04 | United Technologies Corporation | Core for fabrication of gas turbine engine airfoils |
US5842829A (en) * | 1996-09-26 | 1998-12-01 | General Electric Co. | Cooling circuits for trailing edge cavities in airfoils |
US5931638A (en) | 1997-08-07 | 1999-08-03 | United Technologies Corporation | Turbomachinery airfoil with optimized heat transfer |
US5902093A (en) | 1997-08-22 | 1999-05-11 | General Electric Company | Crack arresting rotor blade |
US6220817B1 (en) | 1997-11-17 | 2001-04-24 | General Electric Company | AFT flowing multi-tier airfoil cooling circuit |
DE19860788A1 (en) | 1998-12-30 | 2000-07-06 | Abb Alstom Power Ch Ag | Coolable blade for a gas turbine |
DE19921644B4 (en) | 1999-05-10 | 2012-01-05 | Alstom | Coolable blade for a gas turbine |
US6257831B1 (en) * | 1999-10-22 | 2001-07-10 | Pratt & Whitney Canada Corp. | Cast airfoil structure with openings which do not require plugging |
US6254347B1 (en) * | 1999-11-03 | 2001-07-03 | General Electric Company | Striated cooling hole |
-
2002
- 2002-12-04 EP EP02779098A patent/EP1456505A1/en not_active Withdrawn
- 2002-12-04 WO PCT/CH2002/000661 patent/WO2003054356A1/en not_active Application Discontinuation
- 2002-12-04 AU AU2002342500A patent/AU2002342500A1/en not_active Abandoned
-
2004
- 2004-06-10 US US10/864,532 patent/US7137784B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1223308A2 (en) * | 2000-12-16 | 2002-07-17 | ALSTOM (Switzerland) Ltd | Cooling of a turbo machine component |
Also Published As
Publication number | Publication date |
---|---|
AU2002342500A1 (en) | 2003-07-09 |
US7137784B2 (en) | 2006-11-21 |
US20050042096A1 (en) | 2005-02-24 |
WO2003054356A1 (en) | 2003-07-03 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20040607 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: PARNEIX, SACHA Inventor name: TSCHUOR, REMIGI Inventor name: HALL, KENNETH |
|
17Q | First examination report despatched |
Effective date: 20070625 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: ANSALDO ENERGIA IP UK LIMITED |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20180703 |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F01D 5/18 20060101AFI20030710BHEP |