BR112017020475A2 - ?dispositivo para reduzir o ruído de jato de um motor de turbina, e, motor de turbina? - Google Patents
?dispositivo para reduzir o ruído de jato de um motor de turbina, e, motor de turbina?Info
- Publication number
- BR112017020475A2 BR112017020475A2 BR112017020475A BR112017020475A BR112017020475A2 BR 112017020475 A2 BR112017020475 A2 BR 112017020475A2 BR 112017020475 A BR112017020475 A BR 112017020475A BR 112017020475 A BR112017020475 A BR 112017020475A BR 112017020475 A2 BR112017020475 A2 BR 112017020475A2
- Authority
- BR
- Brazil
- Prior art keywords
- turbine engine
- flow
- reducing
- jet noise
- section
- Prior art date
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
- F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
- F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
-
- 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
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- 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
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/306—Mass flow
-
- 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
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)
- Jet Pumps And Other Pumps (AREA)
- Supercharger (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
- Nozzles (AREA)
- Fuel-Injection Apparatus (AREA)
- Testing Of Engines (AREA)
Abstract
a invenção se refere a um dispositivo para reduzir ruído de jato de um motor de turbina, compreendendo uma capota externa (16) provida dentro de uma parede (20) definindo no exterior uma seção anular (22) para o fluxo de uma corrente secundária do motor de turbina, a dita parede da capota externa compreendendo uma pluralidade de circuitos de microjatos (28) cada compreendendo meios (30) para gás de amostra fluir na seção de fluxo na corrente secundária que se abre em um conduto de alimentação (32) único, que por sua vez se abre em uma borda posterior da capota externa através da pelo menos uma grade de ejeção (34) capaz de dividir a corrente de amostra de gás em uma pluralidade de correntes de gás tendo seções diretas com dimensões menores que uma seção direta (d) de um conduto de alimentação.
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1552535A FR3034141B1 (fr) | 2015-03-26 | 2015-03-26 | Dispositif a microjets pour la reduction du bruit de jet d'une turbomachine |
FR1552535 | 2015-03-26 | ||
FR1552536A FR3034142B1 (fr) | 2015-03-26 | 2015-03-26 | Dispositif a grilles d'ejection de microjets pour la reduction du bruit de jet d'une turbomachine |
FR1552536 | 2015-03-26 | ||
PCT/FR2016/050690 WO2016151267A1 (fr) | 2015-03-26 | 2016-03-25 | Dispositif a grilles d'ejection de microjets pour la reduction du bruit de jet d'une turbomachine |
Publications (3)
Publication Number | Publication Date |
---|---|
BR112017020475A2 true BR112017020475A2 (pt) | 2018-07-03 |
BR112017020475B1 BR112017020475B1 (pt) | 2022-03-08 |
BR112017020475B8 BR112017020475B8 (pt) | 2022-03-29 |
Family
ID=55860879
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112017020475A BR112017020475B8 (pt) | 2015-03-26 | 2016-03-25 | Dispositivo para reduzir o ruído de jato de um motor de turbina, e, motor de turbina |
Country Status (8)
Country | Link |
---|---|
US (1) | US10408165B2 (pt) |
EP (1) | EP3274578B1 (pt) |
JP (1) | JP6813497B2 (pt) |
CN (2) | CN107636289A (pt) |
BR (1) | BR112017020475B8 (pt) |
CA (1) | CA2980794C (pt) |
RU (1) | RU2731780C2 (pt) |
WO (1) | WO2016151267A1 (pt) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109424370B (zh) * | 2017-08-21 | 2022-08-09 | 赛峰飞机发动机公司 | 用于收敛-发散型次级喷嘴的加热系统 |
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 |
US11828226B2 (en) | 2022-04-13 | 2023-11-28 | General Electric Company | Compressor bleed air channels having a pattern of vortex generators |
Family Cites Families (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1064675A (en) * | 1962-11-26 | 1967-04-05 | Bristol Siddeley Engines Ltd | Improvements in nozzles for discharge of compressible fluid |
FR1542668A (fr) * | 1967-08-24 | 1968-10-18 | Snecma | Perfectionnements aux silencieux pour tuyères ventilées |
US4068471A (en) * | 1975-06-16 | 1978-01-17 | General Electric Company | Variable cycle engine with split fan section |
US4291782A (en) * | 1979-10-30 | 1981-09-29 | The Boeing Company | Simplified method and apparatus for hot-shield jet noise suppression |
GB2149456B (en) * | 1983-11-08 | 1987-07-29 | Rolls Royce | Exhaust mixing in turbofan aeroengines |
BR0307845B1 (pt) * | 2002-02-22 | 2012-09-18 | bocal de exaustão de misturador duplex. | |
US7010905B2 (en) * | 2003-02-21 | 2006-03-14 | The Nordam Group, Inc. | Ventilated confluent exhaust nozzle |
US7412832B2 (en) * | 2004-03-26 | 2008-08-19 | General Electric Company | Method and apparatus for operating gas turbine engines |
FR2872549B1 (fr) * | 2004-07-05 | 2006-09-22 | Centre Nat Rech Scient Cnrse | Reacteur d'avion equipe d'un dispositif de reduction de bruit des jets propulsifs |
FR2892152B1 (fr) * | 2005-10-19 | 2007-11-23 | Airbus France Sas | Turbomoteur a bruit de jet attenue |
FR2901321B1 (fr) * | 2006-05-18 | 2011-08-12 | Aircelle Sa | Procede d'homogeneisation de l'air en sortie de turboreacteur pour abaisser le bruit genere |
EP2074319B1 (en) * | 2006-10-12 | 2012-08-15 | United Technologies Corporation | Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method |
US7870722B2 (en) * | 2006-12-06 | 2011-01-18 | The Boeing Company | Systems and methods for passively directing aircraft engine nozzle flows |
EP2256327B1 (en) * | 2008-02-25 | 2019-09-04 | IHI Corporation | Noise reducing device, and jet propulsion system |
US8141366B2 (en) * | 2008-08-19 | 2012-03-27 | United Technologies Corporation | Gas turbine engine with variable area fan nozzle |
FR2929337B1 (fr) * | 2008-03-31 | 2012-06-01 | Airbus France | Dispositif a jets secondaires de reduction du bruit genere par un reacteur d'aeronef |
FR2929335B1 (fr) * | 2008-03-31 | 2012-06-01 | Airbus France | Dispositif de reduction du bruit genere par un reacteur d'aeronef a jets de fluide de meme orientation |
FR2929334B1 (fr) * | 2008-03-31 | 2012-06-01 | Airbus France | Dispositif de reduction du bruit genere par reacteur d'aeronef a conduits de fluide coudes |
FR2929336B1 (fr) * | 2008-03-31 | 2012-06-01 | Airbus France | Dispositif a jets plans de reduction du bruit genere par un reacteur d'aeronef |
US9528468B2 (en) * | 2009-10-28 | 2016-12-27 | Ihi Corporation | Noise reduction system |
JP5459317B2 (ja) * | 2009-10-28 | 2014-04-02 | 株式会社Ihi | 騒音低減装置 |
JP5446749B2 (ja) * | 2009-11-09 | 2014-03-19 | 株式会社Ihi | エンジン排気ノズル及び航空機エンジン |
FR2975135B1 (fr) * | 2011-05-12 | 2016-07-22 | Snecma | Cone arriere de turboreacteur tournant a micro-jets |
FR3009027B1 (fr) | 2013-07-26 | 2018-04-06 | Airbus Operations | Ensemble turbomachine d'aeronef a bruit de jet attenue. |
-
2016
- 2016-03-25 CN CN201680028220.2A patent/CN107636289A/zh active Pending
- 2016-03-25 JP JP2017550486A patent/JP6813497B2/ja active Active
- 2016-03-25 CN CN202210372426.4A patent/CN114687887A/zh active Pending
- 2016-03-25 CA CA2980794A patent/CA2980794C/fr active Active
- 2016-03-25 US US15/561,359 patent/US10408165B2/en active Active
- 2016-03-25 WO PCT/FR2016/050690 patent/WO2016151267A1/fr active Application Filing
- 2016-03-25 BR BR112017020475A patent/BR112017020475B8/pt active IP Right Grant
- 2016-03-25 EP EP16719444.8A patent/EP3274578B1/fr active Active
- 2016-03-25 RU RU2017134269A patent/RU2731780C2/ru active
Also Published As
Publication number | Publication date |
---|---|
WO2016151267A1 (fr) | 2016-09-29 |
CN107636289A (zh) | 2018-01-26 |
RU2731780C2 (ru) | 2020-09-08 |
CA2980794C (fr) | 2023-01-24 |
CN114687887A (zh) | 2022-07-01 |
US20180080408A1 (en) | 2018-03-22 |
CA2980794A1 (fr) | 2016-09-29 |
JP6813497B2 (ja) | 2021-01-13 |
BR112017020475B1 (pt) | 2022-03-08 |
RU2017134269A (ru) | 2019-04-05 |
EP3274578A1 (fr) | 2018-01-31 |
RU2017134269A3 (pt) | 2019-09-11 |
EP3274578B1 (fr) | 2019-05-01 |
BR112017020475B8 (pt) | 2022-03-29 |
JP2018514680A (ja) | 2018-06-07 |
US10408165B2 (en) | 2019-09-10 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B06U | Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette] | ||
B09A | Decision: intention to grant [chapter 9.1 patent gazette] | ||
B16A | Patent or certificate of addition of invention granted [chapter 16.1 patent gazette] |
Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 25/03/2016, OBSERVADAS AS CONDICOES LEGAIS. |
|
B16C | Correction of notification of the grant [chapter 16.3 patent gazette] |
Free format text: REF. RPI 2670 DE 08/03/2022 QUANTO AO ENDERECO. |