BR0104895A - Disco provido de pás - Google Patents

Disco provido de pás

Info

Publication number
BR0104895A
BR0104895A BR0104895-3A BR0104895A BR0104895A BR 0104895 A BR0104895 A BR 0104895A BR 0104895 A BR0104895 A BR 0104895A BR 0104895 A BR0104895 A BR 0104895A
Authority
BR
Brazil
Prior art keywords
paddle
disc
row
paddles
airfoils
Prior art date
Application number
BR0104895-3A
Other languages
English (en)
Inventor
David Andrew Goshorn
David William Crall
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 BR0104895A publication Critical patent/BR0104895A/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ceramic Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

"DISCO PROVIDO DE PáS". Um disco provido de pás (20) ou disco provido de pás para uso em um motor turboreator (10). O disco provido de pás (20) inclui um disco anular (60), uma carreira interna de pás (70) incluindo uma pluralidade de aerofólios (72) circunferentemente espaçados integralmente formados com o disco (60), um divisor anular (80) integralmente formado com a carreira interna de pás (70) e circundando as extremidades (76) da pluralidade de aerofólios (72) do mesmo, e uma carreira externa de pás (90) incluindo uma pluralidade de aerofólios (92) circunferentemente espaçados integralmente formados com o divisor (80). Existem mais aerofólios na carreira externa de pás (90) do que na carreira interna de pás (70).
BR0104895-3A 2000-10-31 2001-10-31 Disco provido de pás BR0104895A (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/702,394 US6454535B1 (en) 2000-10-31 2000-10-31 Blisk

Publications (1)

Publication Number Publication Date
BR0104895A true BR0104895A (pt) 2002-07-30

Family

ID=24821046

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0104895-3A BR0104895A (pt) 2000-10-31 2001-10-31 Disco provido de pás

Country Status (7)

Country Link
US (1) US6454535B1 (pt)
EP (1) EP1201878B1 (pt)
JP (1) JP5138138B2 (pt)
BR (1) BR0104895A (pt)
CA (1) CA2355428C (pt)
DE (1) DE60120875T2 (pt)
ES (1) ES2265397T3 (pt)

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WO2006060013A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
WO2006059980A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Diffuser aspiration for a tip turbine engine
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
EP1825111B1 (en) 2004-12-01 2011-08-31 United Technologies Corporation Counter-rotating compressor case for a tip turbine engine
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
EP1825117B1 (en) 2004-12-01 2012-06-13 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
EP1825116A2 (en) * 2004-12-01 2007-08-29 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006059994A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
DE602004032186D1 (de) 2004-12-01 2011-05-19 United Technologies Corp Turbinenschaufelgruppe eines Fanrotors sowie Verfahren zur Montage einer solchen Gruppe
WO2006059972A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
DE602004016065D1 (de) 2004-12-01 2008-10-02 United Technologies Corp Variable gebläseeinlassleitschaufelanordnung, turbinenmotor mit solch einer anordnung und entsprechendes steuerverfahren
US8104257B2 (en) * 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US8087885B2 (en) * 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
EP1825126B1 (en) * 2004-12-01 2011-02-16 United Technologies Corporation Vectoring transition duct for turbine engine
EP1828591B1 (en) * 2004-12-01 2010-07-21 United Technologies Corporation Peripheral combustor for tip turbine engine
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
WO2006060012A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
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
WO2006059971A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
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
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
EP1825112B1 (en) 2004-12-01 2013-10-23 United Technologies Corporation Cantilevered tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
EP1841960B1 (en) 2004-12-01 2011-05-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
WO2006059977A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and corresponding orepating method
WO2006059997A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Annular turbine ring rotor
WO2006062497A1 (en) 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
US7537430B2 (en) * 2005-11-11 2009-05-26 General Electric Company Stacked reaction steam turbine rotor assembly
US7578655B1 (en) * 2006-05-20 2009-08-25 Florida Turbine Technologies, Inc. Composite gas turbine fan blade
US7758303B1 (en) * 2006-07-31 2010-07-20 General Electric Company FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween
US7736450B2 (en) * 2006-09-29 2010-06-15 General Electric Company Varying fluence as a function of thickness during laser shock peening
US8356469B1 (en) 2007-04-05 2013-01-22 The United States Of America As Represented By The Secretary Of The Air Force Gas turbine engine with dual compression rotor
FR2914943B1 (fr) * 2007-04-13 2011-04-01 Snecma Aube de soufflante
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
CA2643587A1 (en) * 2008-11-10 2010-05-10 Organoworld Inc. Turbine annular axial rotor
US8667774B2 (en) 2009-08-05 2014-03-11 The Boeing Company Coannular ducted fan
ITMI20120569A1 (it) * 2012-04-06 2013-10-07 Franco Tosi Meccanica S P A Stadio rotorico di turbina assiale a rapporto corda/passo migliorato
US20140169972A1 (en) * 2012-12-17 2014-06-19 United Technologies Corporation Fan with integral shroud
US20160245087A1 (en) * 2013-10-03 2016-08-25 Franco Tosi Meccanica S.P.A. Rotor stage of axial turbine with improved chord/pitch ratio
WO2015057544A1 (en) * 2013-10-16 2015-04-23 United Technologies Corporation Auxiliary power unit impeller blade
US10119403B2 (en) * 2014-02-13 2018-11-06 United Technologies Corporation Mistuned concentric airfoil assembly and method of mistuning same
EP3012411A1 (en) * 2014-10-23 2016-04-27 United Technologies Corporation Integrally bladed rotor having axial arm and pocket
US20160208613A1 (en) * 2015-01-15 2016-07-21 United Technologies Corporation Gas turbine engine integrally bladed rotor
US10563516B2 (en) * 2016-07-06 2020-02-18 General Electric Company Turbine engine and method of assembling
US10415403B2 (en) * 2017-01-13 2019-09-17 Rolls-Royce North American Technologies Inc. Cooled blisk for gas turbine engine
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
GB2561837A (en) * 2017-04-24 2018-10-31 Hieta Tech Limited Turbine rotor, turbine, apparatus and method
US10619483B2 (en) * 2017-11-21 2020-04-14 United Technologies Corporation Partially shrouded gas turbine engine fan
US10670037B2 (en) * 2017-11-21 2020-06-02 General Electric Company Turbofan engine's fan blade and setting method thereof
US11060406B2 (en) * 2019-10-11 2021-07-13 Pratt & Whitney Canada Corp. Rotor for gas turbine engine
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
BE1030046B1 (fr) * 2021-12-17 2023-07-17 Safran Aero Boosters Roue mobile a plusieurs rangees d’aubes
CN114542510A (zh) * 2022-02-23 2022-05-27 中国航发沈阳发动机研究所 一种自适应变循环发动机风扇转子结构
BE1030473B1 (fr) * 2022-04-21 2023-11-27 Safran Aero Boosters Rotor a plusieurs rangees d’aubes

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Also Published As

Publication number Publication date
US6454535B1 (en) 2002-09-24
EP1201878A3 (en) 2003-06-18
JP2002180996A (ja) 2002-06-26
JP5138138B2 (ja) 2013-02-06
EP1201878A2 (en) 2002-05-02
DE60120875T2 (de) 2007-01-18
DE60120875D1 (de) 2006-08-03
CA2355428C (en) 2007-05-08
ES2265397T3 (es) 2007-02-16
CA2355428A1 (en) 2002-04-30
EP1201878B1 (en) 2006-06-21

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 7A E 8A ANUIDADE(S).

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: REFERENTE AO DESPACHO 8.6 PUBLICADO NA RPI 2029 DE 24/11/2009.