UA87439C2 - Турбореактивный двигатель с высокой степенью двухконтурности - Google Patents

Турбореактивный двигатель с высокой степенью двухконтурности

Info

Publication number
UA87439C2
UA87439C2 UAA200500996A UAA200500996A UA87439C2 UA 87439 C2 UA87439 C2 UA 87439C2 UA A200500996 A UAA200500996 A UA A200500996A UA A200500996 A UAA200500996 A UA A200500996A UA 87439 C2 UA87439 C2 UA 87439C2
Authority
UA
Ukraine
Prior art keywords
turbojet
bypass ratio
large bypass
casing
jacket
Prior art date
Application number
UAA200500996A
Other languages
English (en)
Ukrainian (uk)
Inventor
Брюно Бетен
Сантос Нельсон Дос
Жеремі Фер
Фабьєнн Лакорр
Жан-Луї Пікар
Original Assignee
Снекма
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 Снекма filed Critical Снекма
Publication of UA87439C2 publication Critical patent/UA87439C2/ru

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/68—Reversers mounted on the engine housing downstream of the fan exhaust section
    • 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
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within

Landscapes

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

Abstract

Турбореактивный двигатель содержит, по меньшей мере, вентилятор, компрессор, камеру сгорания, турбину и жесткий цилиндрический кожух, присоединенный одним концом, который находится выше по потоку, к промежуточному корпусу, и концом, который находится ниже по потоку, к корпусу выхлопного сопла, кожух для распределения нагрузки между промежуточным корпусом и корпусом выхлопного сопла.
UAA200500996A 2004-02-05 2005-02-03 Турбореактивный двигатель с высокой степенью двухконтурности UA87439C2 (ru)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0401083A FR2866070B1 (fr) 2004-02-05 2004-02-05 Turboreacteur a fort taux de dilution

Publications (1)

Publication Number Publication Date
UA87439C2 true UA87439C2 (ru) 2009-07-27

Family

ID=34746421

Family Applications (1)

Application Number Title Priority Date Filing Date
UAA200500996A UA87439C2 (ru) 2004-02-05 2005-02-03 Турбореактивный двигатель с высокой степенью двухконтурности

Country Status (7)

Country Link
US (1) US7430852B2 (ru)
EP (1) EP1568868B1 (ru)
JP (1) JP4738821B2 (ru)
CA (1) CA2495624C (ru)
FR (1) FR2866070B1 (ru)
RU (1) RU2387864C2 (ru)
UA (1) UA87439C2 (ru)

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US20080072566A1 (en) * 2006-09-27 2008-03-27 Pratt & Whitney Canada Corp. Bleed holes oriented with gaspath and flared for noise reduction
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US7726116B2 (en) * 2006-11-14 2010-06-01 General Electric Company Turbofan engine nozzle assembly and method of operating same
US7673458B2 (en) * 2006-11-14 2010-03-09 General Electric Company Turbofan engine nozzle assembly and method for operating the same
US9126691B2 (en) 2007-05-30 2015-09-08 United Technologies Corporation Access door for gas turbine engine components
FR2919347B1 (fr) * 2007-07-26 2009-11-20 Snecma Enveloppe externe de conduite de soufflante dans une turbomachine.
US8534074B2 (en) * 2008-05-13 2013-09-17 Rolls-Royce Corporation Dual clutch arrangement and method
FR2948636B1 (fr) 2009-07-31 2012-01-13 Airbus Operations Sas Ensemble moteur pour aeronef dont le mat d'accrochage comprend une enveloppe structurale formant delimitation radiale interne du flux secondaire
FR2952126B1 (fr) * 2009-11-04 2011-12-23 Snecma Turbomachine a double flux pour aeronef, comprenant des moyens structuraux de rigidification du carter central
FR2978982B1 (fr) * 2011-08-12 2013-09-20 Snecma Moyens de renfort d'un conduit de soufflante d'une turbomachine
FR3010049B1 (fr) * 2013-09-04 2017-03-31 Snecma Structure de liaison moteur-nacelle a secteurs de virole pivotants
FR3015569B1 (fr) * 2013-12-19 2019-01-25 Safran Aircraft Engines Carter pour un ensemble propulsif
US9797271B2 (en) 2014-04-25 2017-10-24 Rohr, Inc. Access panel(s) for an inner nacelle of a turbine engine
FR3023260B1 (fr) * 2014-07-03 2016-07-15 Aircelle Sa Ensemble propulsif d'aeronef
CN105952540B (zh) * 2016-05-25 2017-07-25 中国科学院工程热物理研究所 一种多级压气机稳定工作裕度调节系统
US9972896B2 (en) * 2016-06-23 2018-05-15 General Electric Company Wireless aircraft engine monitoring system
US11512594B2 (en) 2020-06-05 2022-11-29 General Electric Company System and method for modulating airflow into a bore of a rotor to control blade tip clearance
CN114810416B (zh) * 2022-06-27 2022-09-23 中国航发四川燃气涡轮研究院 一种锯齿形的变循环发动机可调前涵道引射器结构

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Also Published As

Publication number Publication date
CA2495624C (en) 2011-08-23
FR2866070A1 (fr) 2005-08-12
JP4738821B2 (ja) 2011-08-03
EP1568868A2 (fr) 2005-08-31
CA2495624A1 (en) 2005-08-05
US20050172609A1 (en) 2005-08-11
EP1568868A3 (fr) 2006-01-04
RU2005102777A (ru) 2006-07-10
FR2866070B1 (fr) 2008-12-05
EP1568868B1 (fr) 2016-04-27
RU2387864C2 (ru) 2010-04-27
JP2005220905A (ja) 2005-08-18
US7430852B2 (en) 2008-10-07

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