IT1213376B - Turbina a gas in modalita'propulsore a turbogetto con costruttiva multialbero e due correnti. - Google Patents

Turbina a gas in modalita'propulsore a turbogetto con costruttiva multialbero e due correnti.

Info

Publication number
IT1213376B
IT1213376B IT8622288A IT2228886A IT1213376B IT 1213376 B IT1213376 B IT 1213376B IT 8622288 A IT8622288 A IT 8622288A IT 2228886 A IT2228886 A IT 2228886A IT 1213376 B IT1213376 B IT 1213376B
Authority
IT
Italy
Prior art keywords
turbine
currents
shaft construction
jet
jet turbine
Prior art date
Application number
IT8622288A
Other languages
English (en)
Other versions
IT8622288A0 (it
Inventor
Claus Burkhardt
Original Assignee
Mtu Muenchen Gmbh
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 Mtu Muenchen Gmbh filed Critical Mtu Muenchen Gmbh
Publication of IT8622288A0 publication Critical patent/IT8622288A0/it
Application granted granted Critical
Publication of IT1213376B publication Critical patent/IT1213376B/it

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F02K3/06—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 with front fan
    • 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
IT8622288A 1985-11-19 1986-11-11 Turbina a gas in modalita'propulsore a turbogetto con costruttiva multialbero e due correnti. IT1213376B (it)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19853540943 DE3540943A1 (de) 1985-11-19 1985-11-19 Gasturbinenstrahltriebwerk in mehr-wellen-zweistrom-bauweise

Publications (2)

Publication Number Publication Date
IT8622288A0 IT8622288A0 (it) 1986-11-11
IT1213376B true IT1213376B (it) 1989-12-20

Family

ID=6286342

Family Applications (1)

Application Number Title Priority Date Filing Date
IT8622288A IT1213376B (it) 1985-11-19 1986-11-11 Turbina a gas in modalita'propulsore a turbogetto con costruttiva multialbero e due correnti.

Country Status (5)

Country Link
US (1) US4841726A (it)
DE (2) DE3540943A1 (it)
FR (1) FR2590320B1 (it)
GB (1) GB2183296B (it)
IT (1) IT1213376B (it)

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DE102009010647A1 (de) * 2009-02-26 2010-09-02 Rolls-Royce Deutschland Ltd & Co Kg Laufspalteinstellungssystem einer Fluggasturbine
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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
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DE102011106961A1 (de) * 2011-07-08 2013-01-10 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbinentriebwerk mit Kühlelementen am Kerntriebwerksgehäuse
JP5478576B2 (ja) * 2011-09-20 2014-04-23 株式会社日立製作所 ガスタービン
DE102012100646B4 (de) * 2012-01-26 2017-03-16 Saxess Holding Gmbh Turbinen- und Generatorgehäuse
EP2696040B1 (de) 2012-08-09 2017-03-15 MTU Aero Engines AG Strömungsleitanordnung zur Kühlung des Niederdruckturbinengehäuses eines Gasturbinenstrahltriebwerk
US9828880B2 (en) * 2013-03-15 2017-11-28 General Electric Company Method and apparatus to improve heat transfer in turbine sections of gas turbines
DE102015215144B4 (de) * 2015-08-07 2017-11-09 MTU Aero Engines AG Vorrichtung und Verfahren zum Beeinflussen der Temperaturen in Innenringsegmenten einer Gasturbine
DE102015217078A1 (de) * 2015-09-07 2017-03-09 MTU Aero Engines AG Vorrichtung zum Begrenzen eines Strömungskanals einer Strömungsmaschine
US10138752B2 (en) 2016-02-25 2018-11-27 General Electric Company Active HPC clearance control
US10697314B2 (en) 2016-10-14 2020-06-30 Rolls-Royce Corporation Turbine shroud with I-beam construction
FR3058459B1 (fr) * 2016-11-04 2018-11-09 Safran Aircraft Engines Dispositif de refroidissement pour une turbine d'une turbomachine
US10774664B2 (en) * 2017-06-08 2020-09-15 General Electric Company Plenum for cooling turbine flowpath components and blades
FR3067751B1 (fr) * 2017-06-15 2019-07-12 Safran Aircraft Engines Dispositif de refroidissement d'un carter annulaire externe de turbine
DE102017117291A1 (de) * 2017-07-31 2019-01-31 Rolls-Royce Deutschland Ltd & Co Kg Luftführungsvorrichtung in einem Flugzeugtriebwerk
US10612466B2 (en) * 2017-09-11 2020-04-07 United Technologies Corporation Gas turbine engine active clearance control system using inlet particle separator
US10557365B2 (en) 2017-10-05 2020-02-11 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having reaction load distribution features
GB201718234D0 (en) 2017-11-03 2017-12-20 Rolls Royce Plc Cooling Arrangement for a turbine casing of a gas turbine engine
US10718267B2 (en) * 2017-12-14 2020-07-21 Rolls-Royce Corporation Turbine engine cooling with substantially uniform cooling air flow distribution
FR3082551B1 (fr) * 2018-06-13 2021-01-08 Airbus Operations Sas Systeme de propulsion d'un aeronef comportant une structure interieure fixe presentant une fente d'evacuation
FR3098549B1 (fr) * 2019-07-11 2021-07-09 Safran Aircraft Engines Systeme de refroidissement pour carter de turbomachine
US11149563B2 (en) 2019-10-04 2021-10-19 Rolls-Royce Corporation Ceramic matrix composite blade track with mounting system having axial reaction load distribution features
US11614037B2 (en) * 2021-01-26 2023-03-28 General Electric Company Method and system for bleed flow power generation
US11821326B2 (en) * 2021-04-27 2023-11-21 General Electric Company Turbine containment system
US11702951B1 (en) * 2022-06-10 2023-07-18 Pratt & Whitney Canada Corp. Passive cooling system for tip clearance optimization
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Also Published As

Publication number Publication date
IT8622288A0 (it) 1986-11-11
DE3546839C2 (de) 1995-05-04
US4841726A (en) 1989-06-27
FR2590320B1 (fr) 1993-08-27
DE3540943C2 (it) 1992-01-23
DE3540943A1 (de) 1987-05-21
GB8627581D0 (en) 1986-12-17
GB2183296A (en) 1987-06-03
GB2183296B (en) 1989-10-04
FR2590320A1 (fr) 1987-05-22

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Legal Events

Date Code Title Description
TA Fee payment date (situation as of event date), data collected since 19931001

Effective date: 19971031