DE602004018045D1 - Gebläseschaufelanordnung für ein tip-turbinentriebwerk und montageverfahren - Google Patents

Gebläseschaufelanordnung für ein tip-turbinentriebwerk und montageverfahren

Info

Publication number
DE602004018045D1
DE602004018045D1 DE602004018045T DE602004018045T DE602004018045D1 DE 602004018045 D1 DE602004018045 D1 DE 602004018045D1 DE 602004018045 T DE602004018045 T DE 602004018045T DE 602004018045 T DE602004018045 T DE 602004018045T DE 602004018045 D1 DE602004018045 D1 DE 602004018045D1
Authority
DE
Germany
Prior art keywords
assembly
turbine engine
fan shaft
tip turbine
shaft assembly
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.)
Active
Application number
DE602004018045T
Other languages
English (en)
Inventor
Gabriel L Suciu
James W Norris
Craig A Nordeen
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Publication of DE602004018045D1 publication Critical patent/DE602004018045D1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • 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
    • F02K3/068—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 being characterised by a short axial length relative to the diameter
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
DE602004018045T 2004-12-01 2004-12-01 Gebläseschaufelanordnung für ein tip-turbinentriebwerk und montageverfahren Active DE602004018045D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2004/040212 WO2006060012A1 (en) 2004-12-01 2004-12-01 Tip turbine engine comprising turbine blade clusters and method of assembly

Publications (1)

Publication Number Publication Date
DE602004018045D1 true DE602004018045D1 (de) 2009-01-08

Family

ID=35462394

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602004018045T Active DE602004018045D1 (de) 2004-12-01 2004-12-01 Gebläseschaufelanordnung für ein tip-turbinentriebwerk und montageverfahren

Country Status (4)

Country Link
US (1) US7874802B2 (de)
EP (1) EP1834067B1 (de)
DE (1) DE602004018045D1 (de)
WO (1) WO2006060012A1 (de)

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EP1828567B1 (de) 2004-12-01 2011-10-12 United Technologies Corporation Diffusor-ansaugung für einen spitzenturbinenmotor
WO2006059968A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
EP1831521B1 (de) 2004-12-01 2008-08-20 United Technologies Corporation Variable gebläseeinlassleitschaufelanordnung, turbinenmotor mit solch einer anordnung und entsprechendes steuerverfahren
WO2006060001A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Fan rotor assembly for a 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
WO2006059996A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
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US8347500B2 (en) * 2008-11-28 2013-01-08 Pratt & Whitney Canada Corp. Method of assembly and disassembly of a gas turbine mid turbine frame
US8245518B2 (en) * 2008-11-28 2012-08-21 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US8347635B2 (en) * 2008-11-28 2013-01-08 Pratt & Whitey Canada Corp. Locking apparatus for a radial locator for gas turbine engine mid turbine frame
US20100132377A1 (en) * 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Fabricated itd-strut and vane ring for gas turbine engine
US8061969B2 (en) * 2008-11-28 2011-11-22 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
US20100132371A1 (en) * 2008-11-28 2010-06-03 Pratt & Whitney Canada Corp. Mid turbine frame system for gas turbine engine
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US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
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WO2006060001A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Fan rotor assembly for a tip turbine engine
WO2006059996A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a 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
EP1828567B1 (de) 2004-12-01 2011-10-12 United Technologies Corporation Diffusor-ansaugung für einen spitzenturbinenmotor
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

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US20070292270A1 (en) 2007-12-20
EP1834067B1 (de) 2008-11-26
EP1834067A1 (de) 2007-09-19
WO2006060012A1 (en) 2006-06-08
US7874802B2 (en) 2011-01-25

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