DE602006006077D1 - Mantelstromtriebwerk mit Vorrichtung zur Unterdrückung des Strahllärms - Google Patents

Mantelstromtriebwerk mit Vorrichtung zur Unterdrückung des Strahllärms

Info

Publication number
DE602006006077D1
DE602006006077D1 DE602006006077T DE602006006077T DE602006006077D1 DE 602006006077 D1 DE602006006077 D1 DE 602006006077D1 DE 602006006077 T DE602006006077 T DE 602006006077T DE 602006006077 T DE602006006077 T DE 602006006077T DE 602006006077 D1 DE602006006077 D1 DE 602006006077D1
Authority
DE
Germany
Prior art keywords
annular surfaces
outlet orifice
section
stream
jet noise
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
DE602006006077T
Other languages
English (en)
Inventor
Alain Porte
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of DE602006006077D1 publication Critical patent/DE602006006077D1/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
    • 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
    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • 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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/48—Corrugated nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/024—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising cooling means

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)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Pipe Accessories (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Percussion Or Vibration Massage (AREA)
DE602006006077T 2005-09-12 2006-09-01 Mantelstromtriebwerk mit Vorrichtung zur Unterdrückung des Strahllärms Active DE602006006077D1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0509260A FR2890696B1 (fr) 2005-09-12 2005-09-12 Turbomoteur a bruit de jet attenue
PCT/FR2006/002016 WO2007031618A1 (fr) 2005-09-12 2006-09-01 Procede pour attenuer le bruit de jet d’un turbomoteur a double flux

Publications (1)

Publication Number Publication Date
DE602006006077D1 true DE602006006077D1 (de) 2009-05-14

Family

ID=36337535

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602006006077T Active DE602006006077D1 (de) 2005-09-12 2006-09-01 Mantelstromtriebwerk mit Vorrichtung zur Unterdrückung des Strahllärms

Country Status (11)

Country Link
US (1) US7621371B2 (de)
EP (1) EP1934456B1 (de)
JP (1) JP4686607B2 (de)
CN (1) CN101263295B (de)
AT (1) ATE427418T1 (de)
BR (1) BRPI0616528A2 (de)
CA (1) CA2619292C (de)
DE (1) DE602006006077D1 (de)
FR (1) FR2890696B1 (de)
RU (1) RU2387862C2 (de)
WO (1) WO2007031618A1 (de)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7963099B2 (en) * 2007-05-21 2011-06-21 General Electric Company Fluted chevron exhaust nozzle
US7926285B2 (en) * 2007-07-18 2011-04-19 General Electric Company Modular chevron exhaust nozzle
FR2920035B1 (fr) * 2007-08-17 2013-09-06 Airbus France Turbomoteur a emission de bruit reduite pour aeronef
FR2923270B1 (fr) * 2007-11-06 2014-01-31 Airbus France Turbomoteur a tuyere de flux froid adaptee
FR2930972B1 (fr) * 2008-05-07 2012-11-30 Airbus France Turbomachine a double flux pour aeronef a emission de bruit reduite
FR2960028B1 (fr) * 2010-05-12 2016-07-15 Snecma Dispositif pour attenuer le bruit emis par le jet d'un moteur de propulsion d'un aeronef.
FR2966435B1 (fr) * 2010-10-25 2013-04-26 Aircelle Sa Nacelle de turboreacteur a section de sortie de ventilation adaptable
FR2977567B1 (fr) 2011-07-07 2014-12-26 Airbus Operations Sas Procede de refroidissement d'un plancher de protection thermique d'un carenage aerodynamique arriere d'un mat d'accrochage d'un ensemble propulsif d'aeronef
EP2837795B1 (de) 2013-08-14 2019-05-01 Ansaldo Energia IP UK Limited Verbesserte Ansauganordnung in Gasturbinenkraftwerk
FR3028020B1 (fr) * 2014-10-29 2016-11-11 Snecma Panneau d'echange thermique et de reduction de bruit ameliore pour une turbomachine
US10040560B2 (en) * 2015-09-30 2018-08-07 The Boeing Company Trailing edge core compartment vent for an aircraft engine
EP3555429B1 (de) * 2017-01-19 2020-07-15 Siemens Aktiengesellschaft Abgassystem für einen gasturbinenmotor
US11053888B2 (en) * 2017-11-01 2021-07-06 The Boeing Company Fan cowl with a serrated trailing edge providing attached flow in reverse thrust mode
CN110454298A (zh) * 2019-07-26 2019-11-15 中国航发沈阳发动机研究所 一种具有降噪功能的排气装置
US11685539B2 (en) * 2019-09-27 2023-06-27 Rohr, Inc. Passive internal compartment exhaust for an aircraft propulsion system
US20220195960A1 (en) * 2020-12-21 2022-06-23 Rohr, Inc. Gas turbine engine exhaust chevrons

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL98695C (de) * 1952-07-25
BE533443A (de) * 1953-11-26
US4826106A (en) * 1987-02-18 1989-05-02 Grumman Aerospace Corporation Advanced composite aircraft cowl
GB2289921A (en) * 1994-06-03 1995-12-06 A E Harris Limited Nozzle for turbofan aeroengines
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
AU2002211367A1 (en) * 2000-10-02 2002-04-15 Rohr, Inc. Apparatus, method and system for gas turbine engine noise reduction
GB0105349D0 (en) * 2001-03-03 2001-04-18 Rolls Royce Plc Gas turbine engine exhaust nozzle
GB2372779A (en) * 2001-03-03 2002-09-04 Rolls Royce Plc Gas turbine engine nozzle with noise reducing tabs
US6532729B2 (en) * 2001-05-31 2003-03-18 General Electric Company Shelf truncated chevron exhaust nozzle for reduction of exhaust noise and infrared (IR) signature
EP1438494B1 (de) * 2001-10-23 2017-01-04 THE NORDAM GROUP, Inc. Konfluente düse mit veränderlichem auslass
US6971229B2 (en) * 2003-02-26 2005-12-06 The Nordam Group, Inc. Confluent exhaust nozzle
US7093423B2 (en) * 2004-01-20 2006-08-22 General Electric Company Methods and apparatus for operating gas turbine engines

Also Published As

Publication number Publication date
EP1934456B1 (de) 2009-04-01
FR2890696B1 (fr) 2010-09-17
CN101263295A (zh) 2008-09-10
US7621371B2 (en) 2009-11-24
BRPI0616528A2 (pt) 2011-06-21
JP2009508038A (ja) 2009-02-26
WO2007031618A1 (fr) 2007-03-22
RU2008114303A (ru) 2009-10-20
RU2387862C2 (ru) 2010-04-27
CN101263295B (zh) 2012-05-09
CA2619292C (fr) 2013-04-30
JP4686607B2 (ja) 2011-05-25
CA2619292A1 (fr) 2007-03-22
ATE427418T1 (de) 2009-04-15
FR2890696A1 (fr) 2007-03-16
EP1934456A1 (de) 2008-06-25
US20080202847A1 (en) 2008-08-28

Similar Documents

Publication Publication Date Title
DE602006006077D1 (de) Mantelstromtriebwerk mit Vorrichtung zur Unterdrückung des Strahllärms
ATE420024T1 (de) Mit vorkühler versehenes turbogebläse
EP1921291A3 (de) Gasturbinenmotor mit simulierter Außenschichtverdickung
EP2017826A3 (de) Akustikplatte
EP1719950A3 (de) Magergemisch-Direkteinspritzdüse für Gasturbinen
EP2527739A3 (de) System und Verfahren zur Flussteuerung in einem Gasturbinenmotor
BR112012008685A2 (pt) conjunto de um motor com turbina a gás e de uma nacela
EP1927729A3 (de) Verfahren und System zur Rekuperativen Kühlung von Turbinenleitschaufel und Mantel-Anordnung
GB2468669C (en) A flow discharge device
EP2527742A3 (de) System und Verfahren zur Strömungssteuerung in einem Gasturbinenmotor
FR2904604B1 (fr) Element de structure d'un aeronef
FR2898870B1 (fr) Structure de virole d'entree d'air
WO2010019175A3 (en) Transition duct for gas turbine combustor with inlet and outlet circumferentially offset
WO2011066368A3 (en) Nacelle assembly for a variable area fan nozzle of a gas turbine engine
EP2184480A3 (de) Gasturbinenmotor mit Schubdüse mit veränderlichem Querschnitt und Verfahren zum Betreiben eines derartigen Gasturbinenmotors
RU2007104966A (ru) Устройство для охлаждения сопла первого контура турбореактивного двухконтурного двигателя
BRPI0821023A2 (pt) Nacela para motor turbojato.
EP2228602A3 (de) Brennkammerwandkühlsystem
EP1930550A3 (de) Systeme zur Kühlung von Integralturbinendüsen und deren Ummantelungsanordnungen
EP1674660A3 (de) Turbinenkomponente mit Aufprallkühlung und Schmutztrennung
EP1998027A3 (de) Gasturbine mit einem Plenum innerhalb einer Triebwerksgondel und einem Zapfluftsystem
WO2015130384A3 (en) Fan nacelle inlet flow control
WO2008045051A3 (en) Gas turbine nacelle comprising a passive boundary lazer bleed system and method of controlling turbulent airflow
BRPI0814918A2 (pt) "nacela para um motor a jato e aeronave"
RU2007146996A (ru) Способ снижения шумовой эмиссии в задней части турбореактивного двигателя и усовершенствованный турбореактивный двигатель

Legal Events

Date Code Title Description
8364 No opposition during term of opposition
R082 Change of representative

Ref document number: 1934456

Country of ref document: EP

Representative=s name: MEISSNER & MEISSNER, 14199 BERLIN, DE