BR0106233A - União aparafusada para discos de rotor e processo de reduzir gradientes térmicos no mesmo - Google Patents

União aparafusada para discos de rotor e processo de reduzir gradientes térmicos no mesmo

Info

Publication number
BR0106233A
BR0106233A BR0106233-6A BR0106233A BR0106233A BR 0106233 A BR0106233 A BR 0106233A BR 0106233 A BR0106233 A BR 0106233A BR 0106233 A BR0106233 A BR 0106233A
Authority
BR
Brazil
Prior art keywords
screw
screw hole
encounter
channel
rotor discs
Prior art date
Application number
BR0106233-6A
Other languages
English (en)
Other versions
BR0106233B1 (pt
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 filed Critical
Publication of BR0106233A publication Critical patent/BR0106233A/pt
Publication of BR0106233B1 publication Critical patent/BR0106233B1/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
    • F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
    • F16B35/041—Specially-shaped shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B39/00—Locking of screws, bolts or nuts
    • F16B39/01—Locking of screws, bolts or nuts specially adapted to prevent loosening at extreme temperatures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
    • F16B5/0275—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread the screw-threaded element having at least two axially separated threaded portions

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

"UNIãO APARAFUSADA PARA DISCOS DE ROTOR E PROCESSO DE REDUZIR GRADIENTES TéRMICOS NO MESMO". Tensão de furo de parafuso em discos de rotor que tem uniões aparafusadas é reduzida passando ar do trajeto de escoamento secundário relativamente quente (tal como o ar de descarga do compressor) através de cada furo de parafuso 70 para aquecer o disco 40 a partir de dentro do furo de parafuso 70. Fazendo assim, a distribuição de temperatura na área do furo de parafuso 70 é feita mais uniforme e a tensão é reduzida de maneira dramática. A união aparafusada 50 inclui um furo de parafuso 70 formado em um primeiro disco de rotor 40, um parafuso 66 colocado no furo de parafuso 70 de tal modo que um canal 84 é definido entre o parafuso 66 e o furo de parafuso 70. Uma primeira porca 74, ou encontro, é ligada a uma primeira extremidade do parafuso 66 e uma segunda porca 76, õu encontro, é ligada a uma segunda extremidade do parafuso 66. Uma primeira passagem 86 associada com o primeiro encontro 74 fornece comunicação direta com o canal 84, e uma segunda passagem 88 associada com o segundo encontro 76 fornece comunicação direta com o canal 84, permitindo com isto que o fluido relativamente quente passe através do canal 84 durante operação do motor.
BRPI0106233-6A 2000-12-22 2001-12-20 união aparafusada para conectar primeiro e segundo componentes, motor de turbina a gás e processo de reduzir gradientes térmicos. BR0106233B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/747,873 US6422812B1 (en) 2000-12-22 2000-12-22 Bolted joint for rotor disks and method of reducing thermal gradients therein

Publications (2)

Publication Number Publication Date
BR0106233A true BR0106233A (pt) 2002-08-20
BR0106233B1 BR0106233B1 (pt) 2010-09-08

Family

ID=25007019

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0106233-6A BR0106233B1 (pt) 2000-12-22 2001-12-20 união aparafusada para conectar primeiro e segundo componentes, motor de turbina a gás e processo de reduzir gradientes térmicos.

Country Status (6)

Country Link
US (1) US6422812B1 (pt)
EP (1) EP1217231B1 (pt)
JP (1) JP4100903B2 (pt)
BR (1) BR0106233B1 (pt)
CA (1) CA2364931C (pt)
DE (1) DE60140170D1 (pt)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8186939B2 (en) * 2009-08-25 2012-05-29 Pratt & Whitney Canada Corp. Turbine disc and retaining nut arrangement
FR2961250B1 (fr) * 2010-06-14 2012-07-20 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine a l'aval du cone d'entrainement
US9004871B2 (en) * 2012-08-17 2015-04-14 General Electric Company Stacked wheel assembly for a turbine system and method of assembling
GB2505475B (en) * 2012-08-31 2015-11-18 Lappeenranta University Of Technology Compressing a laminated stack in an electrical machine
WO2014189589A2 (en) 2013-03-06 2014-11-27 Rolls-Royce North American Technologies, Inc. Gas turbine engine with soft mounted pre-swirl nozzle
US9951621B2 (en) 2013-06-05 2018-04-24 Siemens Aktiengesellschaft Rotor disc with fluid removal channels to enhance life of spindle bolt
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
JP6702542B2 (ja) * 2016-04-14 2020-06-03 株式会社東芝 カップリング構造およびカップリング構造用ナット
US11428104B2 (en) 2019-07-29 2022-08-30 Pratt & Whitney Canada Corp. Partition arrangement for gas turbine engine and method
CN115614324B (zh) * 2022-11-22 2023-05-05 中国航发四川燃气涡轮研究院 基于变截面螺栓连接的压气机转子多级轮盘连接结构

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH171459A (de) 1933-02-15 1934-08-31 Sulzer Ag Flanschverbindung, insbesondere für Hohlkörper, welche ein unter hoher Temperatur stehendes Druckmittel enthalten.
DE1218800B (de) * 1961-04-25 1966-06-08 M A N Turbo Ges Mit Beschraenk Gasturbine, insbesondere Kleingasturbine
US3561516A (en) * 1967-02-28 1971-02-09 Robert R Reddy Safety bolt
US4309145A (en) * 1978-10-30 1982-01-05 General Electric Company Cooling air seal
US4247248A (en) * 1978-12-20 1981-01-27 United Technologies Corporation Outer air seal support structure for gas turbine engine
US4887949A (en) * 1988-03-30 1989-12-19 United Technologies Corporation Bolt retention apparatus
US4991390A (en) * 1988-09-26 1991-02-12 Sundstrand Corporation Mounting and cooling turbine nozzle vanes
US5052891A (en) * 1990-03-12 1991-10-01 General Motors Corporation Connection for gas turbine engine rotor elements
US5072785A (en) * 1990-06-12 1991-12-17 United Technologies Corporation Convectively cooled bolt assembly
US5226788A (en) * 1991-12-23 1993-07-13 General Electric Company Turbine heat shield and bolt retainer assembly
US5350278A (en) * 1993-06-28 1994-09-27 The United States Of America As Represented By The Secretary Of The Air Force Joining means for rotor discs
US5511941A (en) * 1995-01-30 1996-04-30 Brandon; Ronald E. Steam turbine shell disassembly method
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly

Also Published As

Publication number Publication date
CA2364931A1 (en) 2002-06-22
US6422812B1 (en) 2002-07-23
JP2002256807A (ja) 2002-09-11
BR0106233B1 (pt) 2010-09-08
JP4100903B2 (ja) 2008-06-11
EP1217231B1 (en) 2009-10-14
CA2364931C (en) 2008-06-17
DE60140170D1 (de) 2009-11-26
EP1217231A1 (en) 2002-06-26
US20020081192A1 (en) 2002-06-27

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 20/12/2001, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time
B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)