ES2175623T3 - Forro de entrada de aire a un motor con amortiguador de ruido y dispositivo anti-hielo combinados. - Google Patents
Forro de entrada de aire a un motor con amortiguador de ruido y dispositivo anti-hielo combinados.Info
- Publication number
- ES2175623T3 ES2175623T3 ES98306935T ES98306935T ES2175623T3 ES 2175623 T3 ES2175623 T3 ES 2175623T3 ES 98306935 T ES98306935 T ES 98306935T ES 98306935 T ES98306935 T ES 98306935T ES 2175623 T3 ES2175623 T3 ES 2175623T3
- Authority
- ES
- Spain
- Prior art keywords
- lining
- engine
- shock absorber
- acoustic layer
- air entry
- 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.)
- Expired - Lifetime
Links
- 239000006096 absorbing agent Substances 0.000 title 1
- 230000035939 shock Effects 0.000 title 1
- 239000012530 fluid Substances 0.000 abstract 4
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/04—Boundary layer controls by actively generating fluid flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/14—Boundary layer controls achieving noise reductions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
-
- 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
- B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
-
- 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
- Y02T50/10—Drag reduction
-
- 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)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
DE ACUERDO CON ESTA INVENCION, EN UN VEHICULO AEREO CON UN TURBOMOTOR QUE INCLUYE UN CONDUCTO DE ENTRADA QUE RECIBE EL FLUJO DE AIRE ENTRANTE Y QUE ESTA DEFINIDO POR UNA SUPERFICIE INTERIOR Y UN MORRO EN D DEL TURBOMOTOR, SE DISPONE UN FORRO PARA EL CONDUCTO DE ENTRADA CON EL FIN DE OBTENER UN MEJOR RENDIMIENTO ACUSTICO, ANTIHIELO Y DE RESISTENCIA AERODINAMICA. EL FORRO ESTA DOTADO DE UNA CAPA ACUSTICA PERMEABLE HECHA PARA QUE ATENUE EL SONIDO Y DEFINA EL MORRO EN D. EL FORRO TAMBIEN ESTA DOTADO DE UN DISPOSITIVO INYECTOR DE FLUIDO PRESURIZADO. ESTE DISPOSITIVO ESTA EN COMUNICACION LIBRE CON LA CAPA ACUSTICA PERMEABLE Y ESTA CREADO PARA INYECTAR EL FLUIDO A TRAVES DE LA CAPA ACUSTICA PERMEABLE EN EL MORRO EN D Y REDUCIR LA RESISTENCIA DEL FLUJO DE AIRE ENTRANTE. EL DISPOSITIVO INYECTOR DE FLUIDO PRESURIZADO ADEMAS ESTA CREADO PARA INYECTAR FLUIDO A TRAVES DE LA CAPA ACUSTICA PERMEABLE A UNA TEMPERATURA SUFICIENTE PARA QUE EJERZA UNA FUNCION ANTIHIELO EN EL MORRO EN D.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/962,863 US5841079A (en) | 1997-11-03 | 1997-11-03 | Combined acoustic and anti-ice engine inlet liner |
Publications (1)
Publication Number | Publication Date |
---|---|
ES2175623T3 true ES2175623T3 (es) | 2002-11-16 |
Family
ID=25506437
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
ES98306935T Expired - Lifetime ES2175623T3 (es) | 1997-11-03 | 1998-08-28 | Forro de entrada de aire a un motor con amortiguador de ruido y dispositivo anti-hielo combinados. |
Country Status (4)
Country | Link |
---|---|
US (1) | US5841079A (es) |
EP (1) | EP0913326B1 (es) |
DE (1) | DE69805035T2 (es) |
ES (1) | ES2175623T3 (es) |
Families Citing this family (83)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6371411B1 (en) | 1999-11-23 | 2002-04-16 | The Boeing Company | Method and apparatus for aircraft inlet ice protection |
US6688558B2 (en) | 1999-11-23 | 2004-02-10 | The Boeing Company | Method and apparatus for aircraft inlet ice protection |
GB0016149D0 (en) * | 2000-06-30 | 2000-08-23 | Short Brothers Plc | A noise attenuation panel |
FR2820715B1 (fr) | 2001-02-15 | 2003-05-30 | Eads Airbus Sa | Procede de degivrage d'un capot d'entree d'air de moteur a reaction et dispositif pour sa mise en oeuvre |
FR2820716B1 (fr) | 2001-02-15 | 2003-05-30 | Eads Airbus Sa | Procede de degivrage par circulation forcee d'un fluide, d'un capot d'entree d'air de moteur a reaction et dispositif pour sa mise en oeuvre |
US6910659B2 (en) | 2002-10-22 | 2005-06-28 | The Boeing Company | Method and apparatus for liquid containment, such as for aircraft fuel vessels |
FR2847304B1 (fr) * | 2002-11-18 | 2005-07-01 | Airbus France | Nacelle de reacteur d'aeronef a attenuation acoustique |
US7175136B2 (en) | 2003-04-16 | 2007-02-13 | The Boeing Company | Method and apparatus for detecting conditions conducive to ice formation |
EP1623104A1 (de) * | 2003-05-15 | 2006-02-08 | Alstom Technology Ltd | Vorrichtung zur schalldämpfung in einem strömungskanal |
US7588212B2 (en) | 2003-07-08 | 2009-09-15 | Rohr Inc. | Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip |
ATE445210T1 (de) | 2003-08-20 | 2009-10-15 | Boeing Co | Verfahren und systeme zur erkennung von vereisungsbedingungen |
US8070994B2 (en) | 2004-06-18 | 2011-12-06 | Zephyros, Inc. | Panel structure |
US7337875B2 (en) * | 2004-06-28 | 2008-03-04 | United Technologies Corporation | High admittance acoustic liner |
US20060032983A1 (en) * | 2004-07-19 | 2006-02-16 | Brand Joseph H | Foreign object damage tolerant nacelle anti-icing system |
DE102004061036B4 (de) * | 2004-12-18 | 2008-10-30 | Daimler Ag | Windschutz für Cabriolets |
US7431196B2 (en) | 2005-03-21 | 2008-10-07 | The Boeing Company | Method and apparatus for forming complex contour structural assemblies |
US7429166B2 (en) * | 2005-12-20 | 2008-09-30 | General Electric Company | Methods and apparatus for gas turbine engines |
GB0608236D0 (en) * | 2006-04-26 | 2006-06-07 | Rolls Royce Plc | Aeroengine noise reduction |
US7959412B2 (en) * | 2006-09-29 | 2011-06-14 | General Electric Company | Wind turbine rotor blade with acoustic lining |
US7797944B2 (en) | 2006-10-20 | 2010-09-21 | United Technologies Corporation | Gas turbine engine having slim-line nacelle |
US7870721B2 (en) | 2006-11-10 | 2011-01-18 | United Technologies Corporation | Gas turbine engine providing simulated boundary layer thickness increase |
EP1925551A1 (en) * | 2006-11-24 | 2008-05-28 | GKN Aerospace Transparency Systems (Luton) Limited | Ice protection system with noise abatement |
FR2912781B1 (fr) * | 2007-02-20 | 2009-04-10 | Airbus France Sas | Revetement pour le traitement acoustique integrant la fonction de traitement du givre avec de l'air chaud |
EP2140120A2 (fr) * | 2007-02-20 | 2010-01-06 | AIRBUS France | Procede de realisation d'un revetement pour le traitement acoustique incorporant une structure alveolaire avec une forme complexe et revetement pour le traitement acoustique ainsi obtenu |
US8408491B2 (en) * | 2007-04-24 | 2013-04-02 | United Technologies Corporation | Nacelle assembly having inlet airfoil for a gas turbine engine |
US8657567B2 (en) * | 2007-05-29 | 2014-02-25 | United Technologies Corporation | Nacelle compartment plenum for bleed air flow delivery system |
FR2917067B1 (fr) * | 2007-06-08 | 2009-08-21 | Airbus France Sas | Revetement pour le traitement acoustique integrant la fonction de traitement du givre avec de l'air chaud |
US8402739B2 (en) * | 2007-06-28 | 2013-03-26 | United Technologies Corporation | Variable shape inlet section for a nacelle assembly of a gas turbine engine |
GB0713526D0 (en) * | 2007-07-12 | 2007-08-22 | Rolls Royce Plc | An acoustic panel |
US9004399B2 (en) * | 2007-11-13 | 2015-04-14 | United Technologies Corporation | Nacelle flow assembly |
FR2924407B1 (fr) * | 2007-12-03 | 2010-05-14 | Airbus France | Systeme de sortie d'air pour un bord d'attaque d'aeronef |
US7900872B2 (en) * | 2007-12-12 | 2011-03-08 | Spirit Aerosystems, Inc. | Nacelle inlet thermal anti-icing spray duct support system |
US8192147B2 (en) * | 2007-12-14 | 2012-06-05 | United Technologies Corporation | Nacelle assembly having inlet bleed |
US8186942B2 (en) * | 2007-12-14 | 2012-05-29 | United Technologies Corporation | Nacelle assembly with turbulators |
FR2925463B1 (fr) * | 2007-12-21 | 2010-04-23 | Airbus France | Structure pour le traitement acoustique plus particulierement adaptee a une entree d'air d'une nacelle d'aeronef |
ITTO20080142A1 (it) * | 2008-02-28 | 2009-08-29 | Alenia Aeronautica Spa | Presa d'aria, in particolare per un espulsore di chaff per velivolo |
US8052089B2 (en) * | 2008-11-03 | 2011-11-08 | The Boeing Company | Anti-icing apparatus for honeycomb structures |
US8100364B2 (en) * | 2009-01-15 | 2012-01-24 | Textron Innovations Inc. | Anti-icing piccolo tube standoff |
US9003760B2 (en) * | 2009-02-03 | 2015-04-14 | Airbus Operations Sas | Acoustic processing panel, more particularly adapted for an air intake in an aircraft nacelle |
FR2951436B1 (fr) * | 2009-10-15 | 2011-12-09 | Airbus Operations Sas | Mat d'accrochage de turbomoteur d'aeronef a canalisations d'air chaud concentriques |
FR2953811B1 (fr) * | 2009-12-15 | 2012-03-16 | Airbus Operations Sas | Panneau pour une entree d'air d'une nacelle d'aeronef assurant un traitement acoustique et un traitement du givre optimises |
FR2954279B1 (fr) * | 2009-12-18 | 2014-08-22 | Airbus Operations Sas | Entree d'air d'une nacelle d'aeronef integrant des moyens d'injection en air chaud pour le traitement du givre optimises |
US8382039B2 (en) * | 2009-12-30 | 2013-02-26 | MRA Systems Inc. | Turbomachine nacelle and anti-icing system and method therefor |
FR2961175B1 (fr) * | 2010-06-14 | 2013-01-04 | Aircelle Sa | Nacelle de turboreacteur |
JP5582927B2 (ja) * | 2010-08-30 | 2014-09-03 | 三菱重工業株式会社 | 航空機の防除氷システム及びこれを備える航空機 |
US8974177B2 (en) | 2010-09-28 | 2015-03-10 | United Technologies Corporation | Nacelle with porous surfaces |
US8876038B2 (en) * | 2010-10-05 | 2014-11-04 | Urban Aeronautics Ltd. | Ducted fan for VTOL vehicles with system and method to reduce roll moments |
US9310079B2 (en) * | 2010-12-30 | 2016-04-12 | Rolls-Royce North American Technologies, Inc. | Combustion liner with open cell foam and acoustic damping layers |
FR2980775B1 (fr) * | 2011-10-03 | 2014-07-11 | Airbus Operations Sas | Nacelle d'aeronef comportant un panneau pour le traitement acoustique integrant des canaux d'air chaud et au moins une chambre de stabilisation |
FR2980776B1 (fr) | 2011-10-03 | 2014-08-22 | Airbus Operations Sas | Nacelle d'aeronef comportant un panneau pour le traitement acoustique integrant des canaux d'air chaud et au moins un canal annulaire |
FR2981049B1 (fr) | 2011-10-07 | 2014-04-11 | Aircelle Sa | Procede de fabrication d'un panneau d'absorption acoustique |
GB201121887D0 (en) | 2011-12-20 | 2012-02-01 | Rolls Royce Plc | Intake liner for a gas turbine engine |
GB201121889D0 (en) * | 2011-12-20 | 2012-02-01 | Rolls Royce Plc | Active flow control intake for a gas turbine engine |
US8640820B2 (en) * | 2012-01-11 | 2014-02-04 | Polytechnic Institute Of New York University | High-speed jet noise reduction via fluidic injection |
US8998144B2 (en) * | 2012-02-06 | 2015-04-07 | Textron Innovations Inc. | Thermal insulation barrier for an aircraft de-icing heater |
US20140263837A1 (en) * | 2013-03-12 | 2014-09-18 | Spirit Aerosystems, Inc. | Nacelle inlet thermal anti-ice spray duct |
FR3023538B1 (fr) | 2014-07-11 | 2016-07-15 | Aircelle Sa | Levre avant de nacelle de turboreacteur comportant des percages d’air chaud en amont de panneaux acoustiques |
GB2531808A (en) | 2014-11-03 | 2016-05-04 | Short Brothers Plc | Methods and precursors for manufacturing a perforated composite part |
GB201511454D0 (en) * | 2015-06-30 | 2015-08-12 | Rolls Royce Plc | Aircraft engine nacelle |
US10486821B2 (en) | 2015-07-07 | 2019-11-26 | The Boeing Company | Jet engine anti-icing and noise-attenuating air inlets |
US9815558B2 (en) | 2015-12-09 | 2017-11-14 | King Fahd University Of Petroleum And Minerals | Anti-icing apparatus and system |
US10823060B2 (en) * | 2015-12-18 | 2020-11-03 | Raytheon Technologies Corporation | Gas turbine engine with short inlet, acoustic treatment and anti-icing features |
GB201600180D0 (en) * | 2016-01-06 | 2016-02-17 | Rolls Royce Plc | Gas turbine engine |
JP2017136893A (ja) * | 2016-02-01 | 2017-08-10 | 三菱航空機株式会社 | 防氷装置、及び、航空機 |
GB2547049B (en) | 2016-02-08 | 2019-12-25 | Gkn Aerospace Services Ltd | Integrated heater |
FR3050763B1 (fr) | 2016-04-28 | 2018-04-13 | Safran Aircraft Engines | Dispositif de circulation d'air pour une turbomachine comportant un systeme de derivation d'air chaud vers un echangeur de chaleur |
US11485486B2 (en) * | 2016-05-18 | 2022-11-01 | The University Of Toledo | Active flow control for ducted fans and fan-in-wing configurations |
EP3428062A1 (en) * | 2017-07-11 | 2019-01-16 | Airbus Operations GmbH | A leading edge structure for a flow control system of an aircraft |
FR3072365B1 (fr) * | 2017-10-12 | 2020-11-13 | Safran Aircraft Engines | Attenuation acoustique sur une paroi de turbomachine |
FR3074776B1 (fr) | 2017-12-13 | 2020-02-28 | Safran Nacelles | Levre d’entree d’air de nacelle pour turboreacteur |
US11053848B2 (en) | 2018-01-24 | 2021-07-06 | General Electric Company | Additively manufactured booster splitter with integral heating passageways |
FR3092620B1 (fr) | 2019-02-08 | 2021-03-05 | Safran Nacelles | Entrée d'air d'une nacelle de turboréacteur d'aéronef comportant des ouvertures de ventilation d’un flux d’air chaud de dégivrage |
FR3092619B1 (fr) * | 2019-02-08 | 2021-03-19 | Safran Nacelles | Entrée d'air d'une nacelle de turboréacteur d'aéronef comportant des ouvertures de ventilation d’un flux d’air chaud de dégivrage |
FR3095420B1 (fr) | 2019-04-26 | 2023-04-21 | Safran Nacelles | Entrée d’air de nacelle et nacelle comportant une telle entrée d’air |
FR3095417B1 (fr) | 2019-04-26 | 2021-09-24 | Safran Nacelles | Entrée d’air de nacelle et nacelle comportant une telle entrée d’air |
FR3095418B1 (fr) | 2019-04-26 | 2021-09-24 | Safran Nacelles | Entrée d’air de nacelle et nacelle comportant une telle entrée d’air |
US11577843B2 (en) * | 2019-11-05 | 2023-02-14 | Rohr, Inc. | Thermal anti-icing system with non-circular piccolo tube |
CN110979693A (zh) * | 2019-11-18 | 2020-04-10 | 西安京东天鸿科技有限公司 | 防除冰系统、无人机及控制方法 |
FR3103520B1 (fr) | 2019-11-27 | 2022-07-29 | Safran Nacelles | Entrée d’air et procédé de dégivrage d'une entrée d'air d’une nacelle d'un turboréacteur d'aéronef |
US11577844B2 (en) * | 2020-03-12 | 2023-02-14 | Rohr, Inc. | Variable diameter piccolo tube for anti-icing system |
CN113982755B (zh) * | 2020-07-27 | 2023-05-12 | 中国航发商用航空发动机有限责任公司 | 防冰喷嘴、防冰装置和航空发动机 |
EP4074602A1 (en) * | 2021-04-13 | 2022-10-19 | Airbus Operations GmbH | Piccolo tube for de-icing an airfoil structure of an aircraft, de-icing system and airfoil structure |
US20240077018A1 (en) * | 2022-09-02 | 2024-03-07 | Rohr, Inc. | Thermal anti-icing system for an aircraft propulsion system |
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US3853428A (en) * | 1972-01-27 | 1974-12-10 | Bolt Beranek & Newman | Foil structures with reduced sound generation |
US3821999A (en) * | 1972-09-05 | 1974-07-02 | Mc Donnell Douglas Corp | Acoustic liner |
US3820628A (en) * | 1972-10-02 | 1974-06-28 | United Aircraft Corp | Sound suppression means for rotating machinery |
US3917193A (en) * | 1974-01-21 | 1975-11-04 | Boeing Co | Boundary layer control and anti-icing apparatus for an aircraft wing |
US3933327A (en) * | 1974-08-30 | 1976-01-20 | Rohr Industries, Inc. | Aircraft anti-icing plenum |
US4240250A (en) * | 1977-12-27 | 1980-12-23 | The Boeing Company | Noise reducing air inlet for gas turbine engines |
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IL78786A0 (en) * | 1985-06-03 | 1986-08-31 | Short Brothers Plc | Duct for hot air |
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US5114100A (en) * | 1989-12-29 | 1992-05-19 | The Boeing Company | Anti-icing system for aircraft |
GB9300545D0 (en) * | 1993-01-13 | 1993-03-10 | Hurel Dubois Uk Ltd | Carbon fibre panels |
US5423658A (en) * | 1993-11-01 | 1995-06-13 | General Electric Company | Active noise control using noise source having adaptive resonant frequency tuning through variable ring loading |
US5415522A (en) * | 1993-11-01 | 1995-05-16 | General Electric Company | Active noise control using noise source having adaptive resonant frequency tuning through stress variation |
US5498127A (en) * | 1994-11-14 | 1996-03-12 | General Electric Company | Active acoustic liner |
US5590849A (en) * | 1994-12-19 | 1997-01-07 | General Electric Company | Active noise control using an array of plate radiators and acoustic resonators |
-
1997
- 1997-11-03 US US08/962,863 patent/US5841079A/en not_active Expired - Fee Related
-
1998
- 1998-08-28 ES ES98306935T patent/ES2175623T3/es not_active Expired - Lifetime
- 1998-08-28 EP EP98306935A patent/EP0913326B1/en not_active Expired - Fee Related
- 1998-08-28 DE DE69805035T patent/DE69805035T2/de not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP0913326A3 (en) | 1999-05-19 |
DE69805035D1 (de) | 2002-05-29 |
US5841079A (en) | 1998-11-24 |
EP0913326A2 (en) | 1999-05-06 |
DE69805035T2 (de) | 2002-11-14 |
EP0913326B1 (en) | 2002-04-24 |
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