CA2355428C - Blisk - Google Patents

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Publication number
CA2355428C
CA2355428C CA002355428A CA2355428A CA2355428C CA 2355428 C CA2355428 C CA 2355428C CA 002355428 A CA002355428 A CA 002355428A CA 2355428 A CA2355428 A CA 2355428A CA 2355428 C CA2355428 C CA 2355428C
Authority
CA
Canada
Prior art keywords
blades
airfoils
row
blisk
splitter
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 - Fee Related
Application number
CA002355428A
Other languages
English (en)
French (fr)
Other versions
CA2355428A1 (en
Inventor
David Andrew Goshorn
David William Crall
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of CA2355428A1 publication Critical patent/CA2355428A1/en
Application granted granted Critical
Publication of CA2355428C publication Critical patent/CA2355428C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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)
CA002355428A 2000-10-31 2001-08-16 Blisk Expired - Fee Related CA2355428C (en)

Applications Claiming Priority (2)

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

Publications (2)

Publication Number Publication Date
CA2355428A1 CA2355428A1 (en) 2002-04-30
CA2355428C true CA2355428C (en) 2007-05-08

Family

ID=24821046

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002355428A Expired - Fee Related CA2355428C (en) 2000-10-31 2001-08-16 Blisk

Country Status (7)

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

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US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
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US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
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US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor 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
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
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WO2006059968A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
EP1825111B1 (en) 2004-12-01 2011-08-31 United Technologies Corporation Counter-rotating compressor case for a tip turbine engine
US8468795B2 (en) * 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
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WO2006059974A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
DE602004019710D1 (de) 2004-12-01 2009-04-09 United Technologies Corp Fernbetätigung für eine verstellbare stufe eines verdichters für einen turbinenmotor
WO2006059996A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
EP1825177B1 (en) 2004-12-01 2012-01-25 United Technologies Corporation Inflatable bleed valve for turbine engine and method of controlling bleed air
WO2006059988A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
WO2006059978A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Cantilevered tip turbine engine
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
DE602004028297D1 (de) * 2004-12-01 2010-09-02 United Technologies Corp Umfangsbrennkammer für spitzenturbinenmotor
WO2006059989A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
WO2006059985A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Axial compressor for tip turbine engine
WO2006059971A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
EP1831521B1 (en) 2004-12-01 2008-08-20 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
WO2006059973A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine with a heat exchanger
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
WO2006059979A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
WO2006110123A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006059997A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Annular turbine ring rotor
US8087885B2 (en) * 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
WO2006059987A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Particle separator 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
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
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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
EP3052760B1 (en) 2013-10-03 2019-04-10 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
EP3012411B1 (en) * 2014-10-23 2025-05-21 RTX 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
US10670037B2 (en) * 2017-11-21 2020-06-02 General Electric Company Turbofan engine's fan blade and setting method thereof
US10619483B2 (en) * 2017-11-21 2020-04-14 United Technologies Corporation Partially shrouded gas turbine engine fan
US11060406B2 (en) * 2019-10-11 2021-07-13 Pratt & Whitney Canada Corp. Rotor for gas turbine engine
CN111810430B (zh) * 2020-08-05 2025-08-08 太仓欣华盈电子有限公司 涡轮增压风扇
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
US12247516B2 (en) 2022-09-29 2025-03-11 General Electric Company Counter-rotating gas turbine engines including turbine sections with separable torque frames
US12409945B2 (en) * 2023-02-23 2025-09-09 ESS 2 Tech, LLC Fluid accelerator
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CN119802010A (zh) * 2023-10-09 2025-04-11 中国航发商用航空发动机有限责任公司 风扇出口导叶、风扇出口导叶组件及其装配方法
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Also Published As

Publication number Publication date
BR0104895A (pt) 2002-07-30
EP1201878B1 (en) 2006-06-21
DE60120875D1 (de) 2006-08-03
CA2355428A1 (en) 2002-04-30
EP1201878A3 (en) 2003-06-18
DE60120875T2 (de) 2007-01-18
JP5138138B2 (ja) 2013-02-06
JP2002180996A (ja) 2002-06-26
EP1201878A2 (en) 2002-05-02
US6454535B1 (en) 2002-09-24
ES2265397T3 (es) 2007-02-16

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Legal Events

Date Code Title Description
EEER Examination request
MKLA Lapsed

Effective date: 20180816