BRPI0413933A - bocal de exaustão variável com came - Google Patents
bocal de exaustão variável com cameInfo
- Publication number
- BRPI0413933A BRPI0413933A BRPI0413933-0A BRPI0413933A BRPI0413933A BR PI0413933 A BRPI0413933 A BR PI0413933A BR PI0413933 A BRPI0413933 A BR PI0413933A BR PI0413933 A BRPI0413933 A BR PI0413933A
- Authority
- BR
- Brazil
- Prior art keywords
- openings
- exhaust nozzle
- duct
- flaps
- frame
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- B64D33/06—Silencing exhaust or propulsion jets
-
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
-
- 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
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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)
- Control Of Turbines (AREA)
- Supercharger (AREA)
- Exhaust Silencers (AREA)
Abstract
"BOCAL DE EXAUSTãO VARIáVEL COM CAME". Trata-se de um bocal de exaustão (38) que inclui um duto de exaustão (36) com uma saída (46) e uma série de aberturas radiais (48) a montante a partir da mesma. Um quadro radial (58) circunda o duto (36) a montante das aberturas (48). Uma série de flapes (56) são articulados para o quadro (58) para seletivamente cobrir e descobrir as aberturas (48) para controlar o fluxo de exaustão descarregado através das mesmas. Uma barra de união arqueada (66) circunda o duto (36) adjacente ao quadro (58) e inclui os seguidores de came separados de forma circunferencial (68) se engatando com os cames correspondentes (64) afixados com os flapes. Um acionador (70) é unido com a barra (66) para rotação seletiva da mesma entre a primeira e segunda direções opostas para abrir e fechar em forma de pivó os flapes em cima das aberturas (48).
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US49885203P | 2003-08-29 | 2003-08-29 | |
US60/498,852 | 2003-08-29 | ||
PCT/US2004/024197 WO2005024184A2 (en) | 2003-08-29 | 2004-07-27 | Variable cam exhaust nozzle |
Publications (2)
Publication Number | Publication Date |
---|---|
BRPI0413933A true BRPI0413933A (pt) | 2006-10-24 |
BRPI0413933B1 BRPI0413933B1 (pt) | 2018-04-17 |
Family
ID=34272742
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BRPI0413933-0A BRPI0413933B1 (pt) | 2003-08-29 | 2004-07-27 | Bocal de exaustão variável com came |
Country Status (5)
Country | Link |
---|---|
US (1) | US7093793B2 (pt) |
EP (1) | EP1663778B1 (pt) |
BR (1) | BRPI0413933B1 (pt) |
CA (1) | CA2536802C (pt) |
WO (1) | WO2005024184A2 (pt) |
Families Citing this family (44)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7264203B2 (en) * | 2003-10-02 | 2007-09-04 | The Nordam Group, Inc. | Spider actuated thrust reverser |
US7721551B2 (en) * | 2006-06-29 | 2010-05-25 | United Technologies Corporation | Fan variable area nozzle for a gas turbine engine fan nacelle |
US8015797B2 (en) | 2006-09-21 | 2011-09-13 | Jean-Pierre Lair | Thrust reverser nozzle for a turbofan gas turbine engine |
FR2906573B1 (fr) * | 2006-09-29 | 2008-11-21 | Airbus France Sas | Nacelle de reacteur d'aeronef et aeronef comportant une telle nacelle |
US8365515B2 (en) * | 2006-10-12 | 2013-02-05 | United Technologies Corporation | Gas turbine engine with fan variable area nozzle, nacelle assembly and method of varying area of a fan nozzle |
US8286415B2 (en) * | 2006-10-12 | 2012-10-16 | United Technologies Corporation | Turbofan engine having inner fixed structure including ducted passages |
FR2910937B1 (fr) * | 2007-01-02 | 2009-04-03 | Airbus France Sas | Nacelle de reacteur d'aeronef et aeronef comportant une telle nacelle |
US7721549B2 (en) * | 2007-02-08 | 2010-05-25 | United Technologies Corporation | Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system |
US20090067993A1 (en) * | 2007-03-22 | 2009-03-12 | Roberge Gary D | Coated variable area fan nozzle |
US9759087B2 (en) | 2007-08-08 | 2017-09-12 | Rohr, Inc. | Translating variable area fan nozzle providing an upstream bypass flow exit |
CN101939528B (zh) * | 2007-08-08 | 2013-07-24 | 罗尔股份有限公司 | 具有旁通流的面积可调风扇喷嘴 |
US8006479B2 (en) | 2007-10-15 | 2011-08-30 | United Technologies Corporation | Thrust reversing variable area nozzle |
US8091827B2 (en) | 2007-11-16 | 2012-01-10 | The Nordam Group, Inc. | Thrust reverser door |
US8052086B2 (en) | 2007-11-16 | 2011-11-08 | The Nordam Group, Inc. | Thrust reverser door |
US8051639B2 (en) | 2007-11-16 | 2011-11-08 | The Nordam Group, Inc. | Thrust reverser |
US7735778B2 (en) * | 2007-11-16 | 2010-06-15 | Pratt & Whitney Canada Corp. | Pivoting fairings for a thrust reverser |
US8052085B2 (en) | 2007-11-16 | 2011-11-08 | The Nordam Group, Inc. | Thrust reverser for a turbofan gas turbine engine |
US8172175B2 (en) | 2007-11-16 | 2012-05-08 | The Nordam Group, Inc. | Pivoting door thrust reverser for a turbofan gas turbine engine |
US7762086B2 (en) * | 2008-03-12 | 2010-07-27 | United Technologies Corporation | Nozzle extension assembly for ground and flight testing |
US8240126B2 (en) * | 2008-03-22 | 2012-08-14 | Pratt & Whitney Rocketdyne, Inc. | Valve system for a gas turbine engine |
US9267463B2 (en) * | 2008-03-25 | 2016-02-23 | United Technologies Corp. | Gas turbine engine systems involving variable nozzles with flexible panels |
US8356483B2 (en) * | 2008-04-10 | 2013-01-22 | United Technologies Corp | Gas turbine engine systems involving variable nozzles with sliding doors |
US8127530B2 (en) | 2008-06-19 | 2012-03-06 | The Nordam Group, Inc. | Thrust reverser for a turbofan gas turbine engine |
US8317129B1 (en) * | 2009-03-25 | 2012-11-27 | The Boeing Company | Universal convergent nozzle and distinct nozzle aperture |
US8403256B1 (en) | 2009-03-25 | 2013-03-26 | The Boeing Company | Swept-wing powered-lift aircraft |
US8322655B1 (en) | 2009-03-25 | 2012-12-04 | The Boeing Company | Twin-boom empennage |
US8353478B1 (en) | 2009-03-25 | 2013-01-15 | The Boeing Company | Blended wing aircraft |
US8167249B1 (en) | 2009-03-25 | 2012-05-01 | The Boeing Company | Controllable upper surface blown nozzle |
US8382045B2 (en) | 2009-07-21 | 2013-02-26 | The Boeing Company | Shape-changing control surface |
US8844262B2 (en) * | 2009-12-29 | 2014-09-30 | Rolls-Royce North American Technologies, Inc. | Exhaust for a gas turbine engine |
FR2959488B1 (fr) * | 2010-04-28 | 2012-05-18 | Aircelle Sa | Nacelle pour moteur d'aeronef a inverseur de poussee a grilles et a tuyere adaptative |
US8549834B2 (en) | 2010-10-21 | 2013-10-08 | United Technologies Corporation | Gas turbine engine with variable area fan nozzle |
US8967952B2 (en) | 2011-12-22 | 2015-03-03 | United Technologies Corporation | Gas turbine engine duct blocker that includes a duct blocker rotor with a plurality of roller elements |
US9011082B2 (en) | 2011-12-22 | 2015-04-21 | United Technologies Corporation | Gas turbine engine duct blocker with rotatable vane segments |
GB201220378D0 (en) * | 2012-11-13 | 2012-12-26 | Rolls Royce Plc | A gas turbine engine exhaust nozzle |
WO2014143267A1 (en) | 2013-03-15 | 2014-09-18 | United Technologies Corporation | Gas turbine engine with low fan noise |
US9488130B2 (en) | 2013-10-17 | 2016-11-08 | Honeywell International Inc. | Variable area fan nozzle systems with improved drive couplings |
US10969015B2 (en) * | 2017-10-19 | 2021-04-06 | The Boeing Company | Seal system for variable geometry gaps in aircraft systems |
US11258333B2 (en) * | 2019-07-29 | 2022-02-22 | Aurora Flight Sciences Corporation | Propulsor system with integrated passive cooling |
GB2588653A (en) * | 2019-10-31 | 2021-05-05 | Rolls Royce Plc | An exhaust nozzle |
GB2588651A (en) | 2019-10-31 | 2021-05-05 | Rolls Royce Plc | An exhaust nozzle |
US11215140B2 (en) * | 2019-12-18 | 2022-01-04 | Rolls-Royce Deutschland Ltd & Co. Kg | Exhaust nozzle of a gas turbine engine |
CN111846251B (zh) * | 2020-07-10 | 2024-03-19 | 山东太古飞机工程有限公司 | 一种用于发动机进气口、排气及尾喷嘴的防沙保护装置 |
US11867135B1 (en) | 2022-09-14 | 2024-01-09 | Rtx Corporation | Vectoring exhaust nozzle for an aircraft powerplant |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2597253A (en) * | 1945-11-13 | 1952-05-20 | Effie B Melchior | Jet-propulsion nozzle |
GB1418905A (en) | 1972-05-09 | 1975-12-24 | Rolls Royce | Gas turbine engines |
US3779010A (en) | 1972-08-17 | 1973-12-18 | Gen Electric | Combined thrust reversing and throat varying mechanism for a gas turbine engine |
FR2622929A1 (fr) * | 1987-11-05 | 1989-05-12 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a grilles,a section variable d'ejection |
US4922712A (en) | 1988-03-28 | 1990-05-08 | General Electric Company | Thrust reverser for high bypass turbofan engine |
US5076496A (en) * | 1990-02-05 | 1991-12-31 | General Electric Company | Exhaust nozzle flap seal |
FR2676779B1 (fr) | 1991-05-21 | 1994-06-03 | Lair Jean Pierre | Tuyere a section variable. |
US5181676A (en) | 1992-01-06 | 1993-01-26 | Lair Jean Pierre | Thrust reverser integrating a variable exhaust area nozzle |
US5778659A (en) * | 1994-10-20 | 1998-07-14 | United Technologies Corporation | Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems |
FR2727468B1 (fr) | 1994-11-30 | 1996-12-27 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a obstacles aval |
US5655360A (en) | 1995-05-31 | 1997-08-12 | General Electric Company | Thrust reverser with variable nozzle |
DE69514224T2 (de) | 1995-09-13 | 2000-08-10 | Hurel Dubois Avions | Elektrohydraulische Schubumkehrvorrichtung mit zwei Klappen |
GB2308866B (en) * | 1996-01-04 | 1999-09-08 | Rolls Royce Plc | Ducted fan gas turbine engine with secondary duct |
US5826823A (en) * | 1996-02-07 | 1998-10-27 | Rohr, Inc. | Actuator and safety lock system for pivoting door thrust reverser for aircraft jet engine |
FR2757215B1 (fr) * | 1996-12-12 | 1999-01-22 | Hispano Suiza Sa | Inverseur de poussee de turboreacteur a portes comportant des aubes deflectrices associees a la structure fixe |
US6966175B2 (en) * | 2003-05-09 | 2005-11-22 | The Nordam Group, Inc. | Rotary adjustable exhaust nozzle |
-
2004
- 2004-07-26 US US10/899,247 patent/US7093793B2/en active Active
- 2004-07-27 EP EP04786125.7A patent/EP1663778B1/en active Active
- 2004-07-27 CA CA2536802A patent/CA2536802C/en not_active Expired - Fee Related
- 2004-07-27 WO PCT/US2004/024197 patent/WO2005024184A2/en active Application Filing
- 2004-07-27 BR BRPI0413933-0A patent/BRPI0413933B1/pt not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
CA2536802A1 (en) | 2005-03-17 |
EP1663778A4 (en) | 2012-01-11 |
CA2536802C (en) | 2013-02-26 |
EP1663778B1 (en) | 2013-09-25 |
EP1663778A2 (en) | 2006-06-07 |
WO2005024184A3 (en) | 2005-12-29 |
US20050103933A1 (en) | 2005-05-19 |
US7093793B2 (en) | 2006-08-22 |
WO2005024184A2 (en) | 2005-03-17 |
BRPI0413933B1 (pt) | 2018-04-17 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B25G | Requested change of headquarter approved |
Owner name: THE NORDAM GROUP, INC. (US) |
|
B06A | Patent application procedure suspended [chapter 6.1 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] | ||
B21F | Lapse acc. art. 78, item iv - on non-payment of the annual fees in time |
Free format text: REFERENTE A 17A ANUIDADE. |
|
B24J | Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12) |
Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2630 DE 01-06-2021 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013. |