BR0106243A - Junta carvilhada para discos de rotores e método de redução de gradientes térmicos na mesma - Google Patents

Junta carvilhada para discos de rotores e método de redução de gradientes térmicos na mesma

Info

Publication number
BR0106243A
BR0106243A BR0106243-3A BR0106243A BR0106243A BR 0106243 A BR0106243 A BR 0106243A BR 0106243 A BR0106243 A BR 0106243A BR 0106243 A BR0106243 A BR 0106243A
Authority
BR
Brazil
Prior art keywords
channel
tube
screw
thermal gradients
rotor discs
Prior art date
Application number
BR0106243-3A
Other languages
English (en)
Other versions
BR0106243B1 (pt
Inventor
Jason Francis Pepi
Todd Alan Ebert
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BR0106243A publication Critical patent/BR0106243A/pt
Publication of BR0106243B1 publication Critical patent/BR0106243B1/pt

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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)

Abstract

"JUNTA CARVILHADA PARA DISCOS DE ROTORES E MéTODO DE REDUçãO DE GRADIENTES TéRMICOS NA MESMA". Tensão de disco de rotor é reduzida em uma junta carvilhada (52) para conexão de discos de rotor adjacentes em um motor de turbina a gás (10). A junta carvilhada (52) inclui um furo de parafuso (70) formado no primeiro disco de rotor (40) e um tubo (82) disposto no furo de parafuso (70) de modo que um canal (84) é definido entre o tubo (82) e o furo de parafuso (70). Um parafuso (66) é disposto no tubo (82) de modo que uma abertura (88) é definida entre o parafuso (66) e o tubo (82). A abertura (88) isola termicamente o parafuso (66) do fluido quente no canal (84). Uma primeira passagem (96) proporciona comunicação de fluido entre o canal (84) e uma cavidade dianteira e uma segunda passagem (98) proporciona comunicação de fluido entre o canal (84) e uma cavidade traseira. Fluido quente passando através do canal (84) reduz gradientes térmicos no primeiro disco de rotor (40). O tubo (82) protege termicamente o parafuso (66) do fluido quente para minimizar crescimento térmico diferencial.
BRPI0106243-3A 2000-12-22 2001-12-21 junta cavilhada para conexão de primeiro e segundo componentes. BR0106243B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/747,872 US6428272B1 (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
BR0106243A true BR0106243A (pt) 2002-08-13
BR0106243B1 BR0106243B1 (pt) 2010-07-13

Family

ID=25007012

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0106243-3A BR0106243B1 (pt) 2000-12-22 2001-12-21 junta cavilhada para conexão de primeiro e segundo componentes.

Country Status (6)

Country Link
US (1) US6428272B1 (pt)
EP (1) EP1217169B1 (pt)
JP (1) JP4100902B2 (pt)
BR (1) BR0106243B1 (pt)
CA (1) CA2364768C (pt)
DE (1) DE60129403T2 (pt)

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FR2866057B1 (fr) * 2004-02-06 2006-04-28 Snecma Moteurs Dispositif d'equilibrage d'un disque de rotor, disque equipe d'un tel dispositif, et rotor ayant un tel disque
DE102004016244B4 (de) * 2004-04-02 2007-08-23 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
FR2908153B1 (fr) * 2006-11-07 2011-05-13 Snecma Dispositif d'accrochage d'un distributeur (8) d'une turbine, turbine les comportant, et moteur d'aeronef en etant equipe
US8240988B2 (en) * 2008-03-26 2012-08-14 Siemens Energy, Inc. Fastener assembly with cyclone cooling
FR2935429B1 (fr) * 2008-08-26 2011-11-25 Snecma Aubage fixe de turbomachine a masse reduite et turbomachine comportant au moins un tel aubage fixe
DE102008060571A1 (de) * 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Montagevorrichtung für ein Rotorsystem einer Axial-Strömungsmaschine
US8186939B2 (en) * 2009-08-25 2012-05-29 Pratt & Whitney Canada Corp. Turbine disc and retaining nut arrangement
US8727695B2 (en) * 2009-12-09 2014-05-20 Rolls-Royce Corporation Chamfer-fillet gap for thermal management
US9863250B2 (en) * 2010-02-24 2018-01-09 United Technologies Corporation Fastener aperture having an elongated geometry
GB201108842D0 (en) * 2011-05-26 2011-07-06 Rolls Royce Plc A vortex reducer
US8932011B2 (en) * 2011-10-06 2015-01-13 United Technologies Corporation Shaft assembly for a gas turbine engine
US8932022B2 (en) 2012-02-03 2015-01-13 Pratt & Whitney Canada Corp. Fastening system for fan and shaft interconnection
US9004871B2 (en) * 2012-08-17 2015-04-14 General Electric Company Stacked wheel assembly for a turbine system and method of assembling
US9593590B2 (en) 2013-03-01 2017-03-14 Siemens Energy, Inc. Active bypass flow control for a seal in a gas turbine engine
EP2964898B1 (en) 2013-03-06 2019-01-16 Rolls-Royce North American Technologies, Inc. Gas turbine engine with soft mounted pre-swirl nozzle
US10465519B2 (en) 2013-10-17 2019-11-05 Pratt & Whitney Canada Corp. Fastening system for rotor hubs
DE102013226490A1 (de) 2013-12-18 2015-06-18 Rolls-Royce Deutschland Ltd & Co Kg Gekühlte Flanschverbindung eines Gasturbinentriebwerks
US9771802B2 (en) * 2014-02-25 2017-09-26 Siemens Energy, Inc. Thermal shields for gas turbine rotor
US10001061B2 (en) * 2014-06-06 2018-06-19 United Technologies Corporation Cooling system for gas turbine engines
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
DE102014222060A1 (de) * 2014-10-29 2016-05-04 Siemens Aktiengesellschaft Schraubenbolzen, Gehäuse für eine Turbine, Turbine sowie Verfahren zur Montage eines Gehäuses einer Turbine
US20170107902A1 (en) * 2015-10-19 2017-04-20 General Electric Company Systems and Methods for Wheel Space Temperature Management
US10336459B2 (en) * 2016-02-01 2019-07-02 Bell Helicopter Textron Inc. Clamped splines for aircraft engine mount assemblies
DE102017214058A1 (de) 2017-08-11 2019-02-14 MTU Aero Engines AG Rotor für eine Turbomaschine
US11428104B2 (en) 2019-07-29 2022-08-30 Pratt & Whitney Canada Corp. Partition arrangement for gas turbine engine and method
US11352903B2 (en) * 2020-01-20 2022-06-07 Raytheon Technologies Corporation Rotor stack bushing with adaptive temperature metering for a gas turbine engine
US11293294B2 (en) 2020-05-22 2022-04-05 Raytheon Technologies Corporation Speed-controlled conditioning valve for high pressure compressor

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Also Published As

Publication number Publication date
CA2364768C (en) 2007-09-11
DE60129403T2 (de) 2008-04-17
EP1217169B1 (en) 2007-07-18
EP1217169A3 (en) 2004-01-07
JP4100902B2 (ja) 2008-06-11
BR0106243B1 (pt) 2010-07-13
CA2364768A1 (en) 2002-06-22
US20020081199A1 (en) 2002-06-27
US6428272B1 (en) 2002-08-06
DE60129403D1 (de) 2007-08-30
EP1217169A2 (en) 2002-06-26
JP2002242605A (ja) 2002-08-28

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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 21/12/2001, OBSERVADAS AS CONDICOES LEGAIS.

B24C Patent annual fee: request for for restoration

Free format text: REFERENTE A 10A E 11A ANUIDADES.

B24E Patent annual fee: resolution cancelled

Free format text: REFERENTE A DESPACHO 24.3 NA RPI 2183 DE 06/11/2012.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time

Free format text: REFERENTE A 16A ANUIDADE.

B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)