EP1164253B1 - Système de ventilation d'une paire de plates-formes d'aubes juxtaposées - Google Patents
Système de ventilation d'une paire de plates-formes d'aubes juxtaposées Download PDFInfo
- Publication number
- EP1164253B1 EP1164253B1 EP01401534A EP01401534A EP1164253B1 EP 1164253 B1 EP1164253 B1 EP 1164253B1 EP 01401534 A EP01401534 A EP 01401534A EP 01401534 A EP01401534 A EP 01401534A EP 1164253 B1 EP1164253 B1 EP 1164253B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- platforms
- bosses
- pair
- gas
- holes
- 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
Links
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
-
- 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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Definitions
- the subject of this invention is a system of ventilation of a pair of paddles juxtaposed.
- Ventilation systems found in turbomachines usually serve to blow a stream of gas on a portion of structure carried to a different temperature of this gas to protect it overheating or, in some cases applications, to adjust its thermal expansion and perform a game adjustment that improves performance flow of the machine.
- the invention can be regarded as a improvement of the system described in the patent French Pat. No. 2,758,855, where the sealing pieces are metal folders formed of sheet metal which rests under the underside of the platforms and that the forces centrifuges produced on the blades during the operation of the machine press against platforms.
- the sheet is provided with holes that through the ventilation gas to reach the platforms; these holes open into collecting dimples dug into the platforms and which constitute ends of coils, that is to say sinuous ducts, still dug in the platforms and that the vent gases must walk to reach the vents crossing the platforms. Heat exchange is accomplished by convection. However, it was concluded that this provision was not efficient enough.
- US Patent 5,513,955 discloses an associated sealing piece convection cooling systems as well. This provision, however, is not efficient enough either.
- the object of the invention is therefore to improve the sealing liner in sheet metal or metal plate to increase the heat exchange that is indebted to gas without compromising the watertightness and obtaining a satisfactory damping of the vibrations paddles.
- the shirt is provided with bosses at the location of the holes, chambers being formed between platforms and bosses, and the vent holes opening into the bedrooms. It follows from this that the ventilation gas going through the holes of the shirt is blown towards platforms at a speed that increases the exchange of heat thanks to the impact against the platforms which is realized.
- the bosses elongate parallel to a junction of the platforms of to each encompass several holes or several vents; he is also advantageous that the vent holes make respectively facing the holes to facilitate the flow of ventilation gases.
- FIG. 1 is a front view of a pair of blades
- FIG. 2 is a perspective view of the system.
- the blades envisaged in the invention may be turbine blades, in particular first stage of a high-pressure turbine, which are subject to very high temperatures in the room neighboring combustion, and which are inserted into grooves of a disc 1. They include a foot 2 engaged in a groove of the disc 1, a stilt 3, and a blade 4 placed in the vein of flow of the gases of combustion 5 and which constitutes the useful part of dawn. In addition, they include a platform 6 substantially in an arc and which extends around the junction of the stilt 3 and the blade 4. The platforms 6 of a pair of neighboring blades are juxtaposed leaving only a gap 7 between them, which joins the vein 5 to a cavity 8 delimited by the platforms 6 and stilts 3 adjacent blades and by the disk 1. This gap 7 is closed by a sealing piece consisting here of a jacket 9 in metal sheet disposed in the cavity 8 and covering the underside of the platforms 6 and the gap 7 from one stilt 3 to another.
- Fresh ventilation gas is blown in the cavity 8 by a conduit such as 10 dug to through foot 2 and stilt 3 of one of the blades neighboring or through an inter-vane hole upstream of the 8.
- the gas is ordinarily sourced from compressors or turbine. But as possibilities to build the duct circuit 10 are numerous and have been extensively described elsewhere, we will not recall them here.
- Orifices of vent 11 cross platforms 6 to places on which to wear the cooling while allowing the gas to leave the cavity 8 and join the vein 5.
- the shirt 9 is provided with holes 12 respectively facing the venting ports 11; in addition, bosses 13 are trained on the shirt 9 at the locations of these holes 12 to form chambers 14 between them and the platforms 6.
- Figure 2 shows that the bosses 13 have a longitudinal extension parallel to gap 7 to encompass multiple orifices Ventilation 11 and holes 12.
- bosses The purpose of the bosses is that the ventilation gas passing through the holes 12 and blown to the platforms 6 cools them by impact, more strongly than in the design previous where the cooling was carried out by convection.
- the shirt 9 substantially marries the surface lower platforms 6 out bosses 12, except perhaps at the extremities, which can be curved. It is flexible enough to sit well under the platforms 6, with some pressure, when centrifugal forces from the rotation of the disk 1 are applied to it, and then contribute to dampen their vibrations.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0007611 | 2000-06-15 | ||
FR0007611A FR2810365B1 (fr) | 2000-06-15 | 2000-06-15 | Systeme de ventilation d'une paire de plates-formes d'aubes juxtaposees |
US09/883,948 US6457935B1 (en) | 2000-06-15 | 2001-06-20 | System for ventilating a pair of juxtaposed vane platforms |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1164253A1 EP1164253A1 (fr) | 2001-12-19 |
EP1164253B1 true EP1164253B1 (fr) | 2005-03-02 |
Family
ID=26212467
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01401534A Expired - Lifetime EP1164253B1 (fr) | 2000-06-15 | 2001-06-14 | Système de ventilation d'une paire de plates-formes d'aubes juxtaposées |
Country Status (4)
Country | Link |
---|---|
US (1) | US6457935B1 (ja) |
EP (1) | EP1164253B1 (ja) |
JP (1) | JP4047560B2 (ja) |
FR (1) | FR2810365B1 (ja) |
Families Citing this family (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10332561A1 (de) * | 2003-07-11 | 2005-01-27 | Rolls-Royce Deutschland Ltd & Co Kg | Gekühltes Turbinenlaufrad, insbesondere Hochdruckturbinenlaufrad für ein Flugtriebwerk |
GB2411697B (en) * | 2004-03-06 | 2006-06-21 | Rolls Royce Plc | A turbine having a cooling arrangement |
US7198467B2 (en) * | 2004-07-30 | 2007-04-03 | General Electric Company | Method and apparatus for cooling gas turbine engine rotor blades |
US20060056968A1 (en) * | 2004-09-15 | 2006-03-16 | General Electric Company | Apparatus and methods for cooling turbine bucket platforms |
US7186089B2 (en) * | 2004-11-04 | 2007-03-06 | Siemens Power Generation, Inc. | Cooling system for a platform of a turbine blade |
GB2420162A (en) * | 2004-11-16 | 2006-05-17 | Cross Mfg Company | A seal arrangement for sealing between turbine blades |
US20060269409A1 (en) * | 2005-05-27 | 2006-11-30 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade having a platform, a method of forming the moving blade, a sealing plate, and a gas turbine having these elements |
GB0523106D0 (en) | 2005-11-12 | 2005-12-21 | Rolls Royce Plc | A cooliing arrangement |
DE502006006344D1 (de) * | 2006-10-16 | 2010-04-15 | Siemens Ag | Turbinenschaufel für eine Turbine mit einem Kühlmittelkanal |
US8240981B2 (en) * | 2007-11-02 | 2012-08-14 | United Technologies Corporation | Turbine airfoil with platform cooling |
FR2927357B1 (fr) * | 2008-02-12 | 2013-09-20 | Snecma | Dispositif d'amortissement des vibrations entre deux aubes de roue aubagee de turbomachine |
JP5129633B2 (ja) * | 2008-03-28 | 2013-01-30 | 三菱重工業株式会社 | 冷却通路用カバーおよび該カバーの製造方法ならびにガスタービン |
GB0806893D0 (en) * | 2008-04-16 | 2008-05-21 | Rolls Royce Plc | A damper |
US8240987B2 (en) * | 2008-08-15 | 2012-08-14 | United Technologies Corp. | Gas turbine engine systems involving baffle assemblies |
US8292587B2 (en) * | 2008-12-18 | 2012-10-23 | Honeywell International Inc. | Turbine blade assemblies and methods of manufacturing the same |
ES2542159T3 (es) | 2009-03-09 | 2015-07-31 | Ge Avio S.R.L. | Rotor para turbomáquinas |
EP2282014A1 (de) * | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Rinförmiger Strömungskanalabschnitt für eine Turbomaschine |
US8356978B2 (en) * | 2009-11-23 | 2013-01-22 | United Technologies Corporation | Turbine airfoil platform cooling core |
WO2011084040A2 (en) * | 2010-01-05 | 2011-07-14 | Alibi Akhmejanov | The method of sealing of moving elements and the device for its realization |
US8814517B2 (en) * | 2010-09-30 | 2014-08-26 | General Electric Company | Apparatus and methods for cooling platform regions of turbine rotor blades |
US8777568B2 (en) * | 2010-09-30 | 2014-07-15 | General Electric Company | Apparatus and methods for cooling platform regions of turbine rotor blades |
GB201016597D0 (en) | 2010-10-04 | 2010-11-17 | Rolls Royce Plc | Turbine disc cooling arrangement |
US8641368B1 (en) * | 2011-01-25 | 2014-02-04 | Florida Turbine Technologies, Inc. | Industrial turbine blade with platform cooling |
FR2974387B1 (fr) * | 2011-04-19 | 2015-11-20 | Snecma | Roue de turbine pour une turbomachine |
RU2460886C1 (ru) * | 2011-04-26 | 2012-09-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Ротор турбины |
US8734111B2 (en) * | 2011-06-27 | 2014-05-27 | General Electric Company | Platform cooling passages and methods for creating platform cooling passages in turbine rotor blades |
FR2981132B1 (fr) * | 2011-10-10 | 2013-12-06 | Snecma | Ensemble pour turbomachine a refroidissement de disque |
FR2981979B1 (fr) * | 2011-10-28 | 2013-11-29 | Snecma | Roue de turbine pour une turbomachine |
US8840370B2 (en) | 2011-11-04 | 2014-09-23 | General Electric Company | Bucket assembly for turbine system |
US8870525B2 (en) | 2011-11-04 | 2014-10-28 | General Electric Company | Bucket assembly for turbine system |
US8845289B2 (en) | 2011-11-04 | 2014-09-30 | General Electric Company | Bucket assembly for turbine system |
CN103982250B (zh) * | 2014-05-12 | 2015-07-22 | 天津大学 | 具有冷却功能的金属橡胶减振器 |
JP6422308B2 (ja) * | 2014-11-05 | 2018-11-14 | 三菱日立パワーシステムズ株式会社 | シール構造を備えたガスタービン |
US10030523B2 (en) * | 2015-02-13 | 2018-07-24 | United Technologies Corporation | Article having cooling passage with undulating profile |
US10066488B2 (en) * | 2015-12-01 | 2018-09-04 | General Electric Company | Turbomachine blade with generally radial cooling conduit to wheel space |
DE102016104957A1 (de) * | 2016-03-17 | 2017-09-21 | Rolls-Royce Deutschland Ltd & Co Kg | Kühleinrichtung zur Kühlung von Plattformen eines Leitschaufelkranzes einer Gasturbine |
RU2695160C2 (ru) * | 2017-06-06 | 2019-07-22 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" | Устройство демпфирования колебаний ротора газотурбинного двигателя |
EP3438410B1 (en) | 2017-08-01 | 2021-09-29 | General Electric Company | Sealing system for a rotary machine |
US20190085706A1 (en) * | 2017-09-18 | 2019-03-21 | General Electric Company | Turbine engine airfoil assembly |
FR3094034B1 (fr) * | 2019-03-20 | 2021-03-19 | Safran Aircraft Engines | Chemise tubulaire de ventilation pour un distributeur de turbomachine |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB612097A (en) * | 1946-10-09 | 1948-11-08 | English Electric Co Ltd | Improvements in and relating to the cooling of gas turbine rotors |
GB1259750A (en) * | 1970-07-23 | 1972-01-12 | Rolls Royce | Rotor for a fluid flow machine |
JPS6022002A (ja) * | 1983-07-18 | 1985-02-04 | Hitachi Ltd | タ−ボ機械の翼構造 |
GB2195403A (en) * | 1986-09-17 | 1988-04-07 | Rolls Royce Plc | Improvements in or relating to sealing and cooling means |
US4767260A (en) * | 1986-11-07 | 1988-08-30 | United Technologies Corporation | Stator vane platform cooling means |
US4902198A (en) * | 1988-08-31 | 1990-02-20 | Westinghouse Electric Corp. | Apparatus for film cooling of turbine van shrouds |
US5075621A (en) | 1988-12-19 | 1991-12-24 | International Business Machines Corporation | Capacitor power probe |
US5281097A (en) * | 1992-11-20 | 1994-01-25 | General Electric Company | Thermal control damper for turbine rotors |
GB2280935A (en) * | 1993-06-12 | 1995-02-15 | Rolls Royce Plc | Cooled sealing strip for nozzle guide vane segments |
FR2726323B1 (fr) * | 1994-10-26 | 1996-12-13 | Snecma | Ensemble d'un disque rotatif et d'aubes, notamment utilise dans une turbomachine |
US5573375A (en) * | 1994-12-14 | 1996-11-12 | United Technologies Corporation | Turbine engine rotor blade platform sealing and vibration damping device |
US5513955A (en) * | 1994-12-14 | 1996-05-07 | United Technologies Corporation | Turbine engine rotor blade platform seal |
FR2758855B1 (fr) * | 1997-01-30 | 1999-02-26 | Snecma | Systeme de ventilation des plates-formes des aubes mobiles |
-
2000
- 2000-06-15 FR FR0007611A patent/FR2810365B1/fr not_active Expired - Fee Related
-
2001
- 2001-06-14 EP EP01401534A patent/EP1164253B1/fr not_active Expired - Lifetime
- 2001-06-14 JP JP2001180380A patent/JP4047560B2/ja not_active Expired - Lifetime
- 2001-06-20 US US09/883,948 patent/US6457935B1/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
FR2810365A1 (fr) | 2001-12-21 |
JP2002021503A (ja) | 2002-01-23 |
FR2810365B1 (fr) | 2002-10-11 |
US6457935B1 (en) | 2002-10-01 |
EP1164253A1 (fr) | 2001-12-19 |
JP4047560B2 (ja) | 2008-02-13 |
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