ES2024761A6 - Montaje de alabes de turbina de plataforma integral con raices de entrada lateral oblicua. - Google Patents

Montaje de alabes de turbina de plataforma integral con raices de entrada lateral oblicua.

Info

Publication number
ES2024761A6
ES2024761A6 ES9000938A ES9000938A ES2024761A6 ES 2024761 A6 ES2024761 A6 ES 2024761A6 ES 9000938 A ES9000938 A ES 9000938A ES 9000938 A ES9000938 A ES 9000938A ES 2024761 A6 ES2024761 A6 ES 2024761A6
Authority
ES
Spain
Prior art keywords
roots
platform
rotor
mounting
turbine blades
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
ES9000938A
Other languages
English (en)
Inventor
Albert Joseph Partington
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Publication of ES2024761A6 publication Critical patent/ES2024761A6/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

MONTAJE DE ALABES DE TURBINA DE PLATAFORMA INTEGRAL CON RAICES DE ENTRADA LATERAL OBLICUA. UN ROTOR DE TURBINA QUE LLEVA GRUPOS (28) DE ALABES CADA UNO CON UNA PLURALIDAD DE HOJAS DE ALABES (34) Y UNA PLATAFORMA COMUN (32), UNA PLURALIDAD DE RAICES (36) SEPARADAS ALLI FORMADAS, CON UNA ACANALADURA (42) ENTRE CADA PAR DE RAICES (36), Y UNA PLURALIDAD DE RESALTOS (14) HABIENDO UNA CANALADURA (16) DE ROTOR ENTRE CADA PAR DE RESALTOS ADYACENTES (14), CARACTERIZADO PORQUE TANTO LAS RAICES (36) DE PLATAFORMA COMO LOS RESALTOS DEL ROTOR ESTAN INCLINADOS CON RESPECTO AL EJE DEL ROTOR, CADA UNA DE LAS ACANALADURAS (16) DEL ROTOR ESTA ALINEADA CON UNA CORRESPONDIENTE DE LAS ACANALADURAS (42) DE PLATAFORMA, ESTANDO DISPUESTOS LOS RESALTOS (14) CONTIGUOS RADIALMENTE A LAS RAICES (36); Y PORQUE UNA PLURALIDAD DE PIEZAS DE CONEXION (44) SON INSERTADAS DENTRO DE LAS ACANALADURAS ALINEADAS (16, 42) DE LA PLATAFORMA (32) Y DEL ROTOR (10) PARA CONECTAR CADA GRUPO INTEGRAL (28) DE ALABES CON EL ROTOR (10).
ES9000938A 1989-04-03 1990-04-02 Montaje de alabes de turbina de plataforma integral con raices de entrada lateral oblicua. Expired - Lifetime ES2024761A6 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/332,187 US4904160A (en) 1989-04-03 1989-04-03 Mounting of integral platform turbine blades with skewed side entry roots

Publications (1)

Publication Number Publication Date
ES2024761A6 true ES2024761A6 (es) 1992-03-01

Family

ID=23297097

Family Applications (1)

Application Number Title Priority Date Filing Date
ES9000938A Expired - Lifetime ES2024761A6 (es) 1989-04-03 1990-04-02 Montaje de alabes de turbina de plataforma integral con raices de entrada lateral oblicua.

Country Status (7)

Country Link
US (1) US4904160A (es)
JP (1) JP2983033B2 (es)
KR (1) KR900016586A (es)
CN (1) CN1046206A (es)
CA (1) CA2013641A1 (es)
ES (1) ES2024761A6 (es)
IT (1) IT1239399B (es)

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US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
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WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7980054B2 (en) * 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
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WO2006059980A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Diffuser aspiration for a tip turbine engine
WO2006059979A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
WO2006059999A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
WO2006059975A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Peripheral combustor for tip turbine engine
WO2006060009A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine blade engine comprising turbine clusters and radial attachment lock arrangement therefor
EP1825113B1 (en) * 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
EP1831519B1 (en) * 2004-12-01 2010-08-04 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
WO2006060003A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
EP1825114B1 (en) * 2004-12-01 2008-08-20 United Technologies Corporation Tip turbine engine with a heat exchanger
WO2006060013A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
DE602004019709D1 (de) * 2004-12-01 2009-04-09 United Technologies Corp Tip-turbinentriebwerk und entsprechendes betriebsverfahren
WO2006059987A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8087885B2 (en) * 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
WO2006060010A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor inlet guide vane for tip turbine engine and corresponding control method
WO2006060014A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Starter generator system for a tip turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
WO2006059978A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Cantilevered tip turbine engine
EP1825117B1 (en) 2004-12-01 2012-06-13 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
WO2006060011A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
WO2006060001A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Fan rotor assembly for a tip turbine engine
EP1828574B1 (en) 2004-12-01 2010-11-03 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
EP1825126B1 (en) * 2004-12-01 2011-02-16 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006062497A1 (en) 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
US7261518B2 (en) * 2005-03-24 2007-08-28 Siemens Demag Delaval Turbomachinery, Inc. Locking arrangement for radial entry turbine blades
JP2007231868A (ja) * 2006-03-02 2007-09-13 Hitachi Ltd 蒸気タービン動翼およびそれを用いた蒸気タービン並びに蒸気タービン発電プラント
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
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ITTO20090522A1 (it) * 2009-07-13 2011-01-14 Avio Spa Turbomacchina con girante a segmenti palettati
US9664056B2 (en) * 2013-08-23 2017-05-30 General Electric Company Turbine system and adapter
WO2016195656A1 (en) * 2015-06-02 2016-12-08 Siemens Aktiengesellschaft Attachment system for a turbine airfoil usable in a gas turbine engine
FR3085420B1 (fr) 2018-09-04 2020-11-13 Safran Aircraft Engines Disque de rotor avec arret axial des aubes, ensemble d'un disque et d'un anneau et turbomachine
FR3092865B1 (fr) 2019-02-19 2021-01-29 Safran Aircraft Engines Disque de rotor avec arret axial des aubes, ensemble d’un disque et d’un anneau et turbomachine

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Also Published As

Publication number Publication date
JPH02283801A (ja) 1990-11-21
IT9019735A1 (it) 1991-09-20
IT9019735A0 (it) 1990-03-20
CN1046206A (zh) 1990-10-17
US4904160A (en) 1990-02-27
IT1239399B (it) 1993-10-20
CA2013641A1 (en) 1990-10-03
KR900016586A (ko) 1990-11-13
JP2983033B2 (ja) 1999-11-29

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Legal Events

Date Code Title Description
FD1A Patent lapsed

Effective date: 19980401