FR2986832B1 - Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante. - Google Patents

Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.

Info

Publication number
FR2986832B1
FR2986832B1 FR1351152A FR1351152A FR2986832B1 FR 2986832 B1 FR2986832 B1 FR 2986832B1 FR 1351152 A FR1351152 A FR 1351152A FR 1351152 A FR1351152 A FR 1351152A FR 2986832 B1 FR2986832 B1 FR 2986832B1
Authority
FR
France
Prior art keywords
convergent
divergent tube
defining
divergent
tube
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
FR1351152A
Other languages
English (en)
Other versions
FR2986832A1 (fr
Inventor
Julien Szydlowski
Guillaume Bodard
Matthieu Leyko
Jonathan Langridge
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1351152A priority Critical patent/FR2986832B1/fr
Publication of FR2986832A1 publication Critical patent/FR2986832A1/fr
Application granted granted Critical
Publication of FR2986832B1 publication Critical patent/FR2986832B1/fr
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
    • 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
    • A—HUMAN NECESSITIES
    • A45—HAND OR TRAVELLING ARTICLES
    • A45D—HAIRDRESSING OR SHAVING EQUIPMENT; EQUIPMENT FOR COSMETICS OR COSMETIC TREATMENTS, e.g. FOR MANICURING OR PEDICURING
    • A45D34/00—Containers or accessories specially adapted for handling liquid toiletry or cosmetic substances, e.g. perfumes
    • A—HUMAN NECESSITIES
    • A45—HAND OR TRAVELLING ARTICLES
    • A45D—HAIRDRESSING OR SHAVING EQUIPMENT; EQUIPMENT FOR COSMETICS OR COSMETIC TREATMENTS, e.g. FOR MANICURING OR PEDICURING
    • A45D40/00—Casings or accessories specially adapted for storing or handling solid or pasty toiletry or cosmetic substances, e.g. shaving soaps or lipsticks
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/60—Structure; Surface texture
    • F05B2250/61—Structure; Surface texture corrugated
    • F05B2250/611—Structure; Surface texture corrugated undulated
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/20—Purpose of the control system to optimize the performance of a machine
    • 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
    • Y10T29/49826—Assembling or joining

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
FR1351152A 2012-02-10 2013-02-11 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante. Active FR2986832B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1351152A FR2986832B1 (fr) 2012-02-10 2013-02-11 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1251289A FR2986831A1 (fr) 2012-02-10 2012-02-10 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.
FR1351152A FR2986832B1 (fr) 2012-02-10 2013-02-11 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.

Publications (2)

Publication Number Publication Date
FR2986832A1 FR2986832A1 (fr) 2013-08-16
FR2986832B1 true FR2986832B1 (fr) 2016-12-09

Family

ID=47998900

Family Applications (2)

Application Number Title Priority Date Filing Date
FR1251289A Withdrawn FR2986831A1 (fr) 2012-02-10 2012-02-10 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.
FR1351152A Active FR2986832B1 (fr) 2012-02-10 2013-02-11 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.

Family Applications Before (1)

Application Number Title Priority Date Filing Date
FR1251289A Withdrawn FR2986831A1 (fr) 2012-02-10 2012-02-10 Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.

Country Status (3)

Country Link
US (1) US9249755B2 (fr)
FR (2) FR2986831A1 (fr)
GB (1) GB2500466B (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10190536B2 (en) * 2012-09-17 2019-01-29 Pratt & Whitney Canada Corp. Turbine exhaust case mixer of gas turbine with variable thickness
FR3008739B1 (fr) * 2013-07-18 2017-03-24 Snecma Tuyere d'une turbomachine equipee de chevrons a face interne non axi-symetrique.
FR3010454B1 (fr) 2013-09-10 2024-02-16 Snecma Arriere corps de turboreacteur a flux melanges comportant un melangeur a lobes et des chevrons a surface interne non axisymetrique
FR3010453B1 (fr) 2013-09-10 2017-12-29 Snecma Arriere corps de turboreacteur comportant une tuyere equipee d'un systeme d'inversion de poussee qui integre une couronne de chevrons antibruit
US10094332B2 (en) * 2014-09-03 2018-10-09 The Boeing Company Core cowl for a turbofan engine
GB2542287B (en) * 2014-09-03 2018-11-28 Boeing Co Core cowl for a turbofan engine
FR3070184B1 (fr) 2017-08-21 2019-08-23 Safran Aircraft Engines Systeme de diffusion d'air chaud au col d'une tuyere secondaire convergente-divergente
FR3070185B1 (fr) * 2017-08-21 2019-08-23 Safran Aircraft Engines Systeme de radiateur chauffant pour tuyere secondaire convergente-divergente
FR3070186B1 (fr) * 2017-08-21 2021-06-11 Safran Aircraft Engines Tuyere secondaire modifiee acoustique
EP3447271B1 (fr) * 2017-08-21 2020-09-30 Safran Aircraft Engines Système de chauffage pour tuyère secondaire convergente-divergente
CN109977592A (zh) * 2019-04-08 2019-07-05 涂常青 一种横截面积等差锥体流线型结构的设计方法
US20230167783A1 (en) * 2021-12-01 2023-06-01 General Electric Company Propulsion system for a gas turbine engine
US11920539B1 (en) * 2022-10-12 2024-03-05 General Electric Company Gas turbine exhaust nozzle noise abatement

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5120004A (en) * 1990-02-05 1992-06-09 Rohr, Inc. Split door thrust reverser for fan jet aircraft engines
US5884472A (en) * 1995-10-11 1999-03-23 Stage Iii Technologies, L.C. Alternating lobed mixer/ejector concept suppressor
US6082635A (en) * 1996-06-12 2000-07-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Undulated nozzle for enhanced exit area mixing
US6360528B1 (en) * 1997-10-31 2002-03-26 General Electric Company Chevron exhaust nozzle for a gas turbine engine
DE50012958D1 (de) * 1999-03-05 2006-07-27 Rolls Royce Deutschland Blütenmischer für ein zweikreis-strahltriebwerk
US6658839B2 (en) * 2002-02-28 2003-12-09 The Boeing Company Convergent/divergent segmented exhaust nozzle
US20040244357A1 (en) * 2003-06-05 2004-12-09 Sloan Mark L. Divergent chevron nozzle and method
GB0505246D0 (en) * 2005-03-15 2005-04-20 Rolls Royce Plc Engine noise
FR2885955B1 (fr) * 2005-05-18 2007-06-22 Airbus France Sas Procede pour reduire les emissions sonores a l'arriere d'un turbomoteur et turbomoteur ainsi perfectionne.
US7543452B2 (en) 2005-08-10 2009-06-09 United Technologies Corporation Serrated nozzle trailing edge for exhaust noise suppression
US7966824B2 (en) 2006-08-09 2011-06-28 The Boeing Company Jet engine nozzle exit configurations and associated systems and methods
FR2914020B1 (fr) * 2007-03-23 2009-04-24 Airbus France Sas Procede pour reduire les emissions sonores a l'arriere d'un turbomoteur et turbomoteur perfectionne par le procede
US7963099B2 (en) * 2007-05-21 2011-06-21 General Electric Company Fluted chevron exhaust nozzle
US8356468B2 (en) * 2009-06-12 2013-01-22 The Boeing Company Gas turbine engine nozzle configurations
FR2979673B1 (fr) * 2011-09-01 2013-08-23 Snecma Procede de melange de flux dans un turboreacteur double flux et sortie moteur de mise en oeuvre

Also Published As

Publication number Publication date
FR2986832A1 (fr) 2013-08-16
FR2986831A1 (fr) 2013-08-16
GB2500466B (en) 2019-05-29
GB2500466A (en) 2013-09-25
US20130206865A1 (en) 2013-08-15
GB201302344D0 (en) 2013-03-27
US9249755B2 (en) 2016-02-02

Similar Documents

Publication Publication Date Title
FR2986832B1 (fr) Procede pour definir la forme d'une tuyere convergente-divergente d'une turbomachine et tuyere convergente-divergente correspondante.
MA44381A (fr) Format d'anticorps hétérodimères multispécifiques
FR3003422B1 (fr) Procede de tatouage de la partie textuelle d'un document
FR2987031B1 (fr) Aeronef a voilure muni d'un rotor arriere, et procede pour optimiser le fonctionnement d'un rotor arriere
BRPI1106091A2 (pt) "método de solda."
FR2992676B1 (fr) Plateforme inter-aubes pour une soufflante, rotor d'une soufflante et procede de fabrication associe
FR2970030B1 (fr) Procede d'etancheite de rebord entre etages d'une turbine
FR3039063B1 (fr) Procede d'enrichissement en pongamol d'huile de karanja
FR3002675B1 (fr) Procede pour faciliter l approche d une plateforme
FR2982236B1 (fr) Pylone d'accrochage pour turbomachine
FR3021993B1 (fr) Procede de dimensionnement d'une turbomachine
FR2994698B1 (fr) Procede d'aplanissement des bords d'un coupon de matiere souple a decouper
FR2994587B1 (fr) Allumeur bimodal et procede d'injection bimodale pour allumeur de moteur-fusee
FR2994538B1 (fr) Outillage pour le dessablage d'une turbomachine
FR2987085B1 (fr) Procede de securisation du fonctionnement d'une turbomachine
FR2946555B1 (fr) Procede de reduction de diametre d'un orifice.
BR112015000887A2 (pt) unidade de luva, e, método de acionar uma unidade de luva instalada na tubulação de produção".
FR2989609B1 (fr) Support d'usinage pour un secteur de distribution de turbomachine
BR112013005073A2 (pt) Processo para produção de 2-metil-1,4- naftoquinona
FR2980234B1 (fr) Aube pour turbomachine avec lechettes d'etancheite
FR2992720B1 (fr) Procede pour determiner le moment resistant aerodynamique d'une roue
IT1403920B1 (it) Composti fotosensibilizzanti "metal free".
FR2971830B1 (fr) Detecteur de presence d'un liquide.
FR2997107B1 (fr) Entrainement de secours pour une machine de construction et procede de fonctionnement de l'entrainement de secours
FR2995634B1 (fr) Tube d'echappement pour un tube de degazage d'une turbomachine

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

RM Correction of a material error

Effective date: 20160404

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

PLFP Fee payment

Year of fee payment: 9

PLFP Fee payment

Year of fee payment: 10

PLFP Fee payment

Year of fee payment: 11

PLFP Fee payment

Year of fee payment: 12