ES2136528A1 - Mejoras en la patente de invencion n. 9401114, presentada el 20 de mayo de 1994, relativa a: perfeccionamientos en toberas aximetricas de geometria variable y orientacion del flujo destinadas a propulsores de turbina de gas. - Google Patents

Mejoras en la patente de invencion n. 9401114, presentada el 20 de mayo de 1994, relativa a: perfeccionamientos en toberas aximetricas de geometria variable y orientacion del flujo destinadas a propulsores de turbina de gas.

Info

Publication number
ES2136528A1
ES2136528A1 ES009602744A ES9602744A ES2136528A1 ES 2136528 A1 ES2136528 A1 ES 2136528A1 ES 009602744 A ES009602744 A ES 009602744A ES 9602744 A ES9602744 A ES 9602744A ES 2136528 A1 ES2136528 A1 ES 2136528A1
Authority
ES
Spain
Prior art keywords
variable area
vectorable nozzle
engines
plane
biarticulated
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.)
Granted
Application number
ES009602744A
Other languages
English (en)
Other versions
ES2136528B1 (es
Inventor
Urruela Jose Rivacoba
Garate Kepa M Aldecoa-Otalora
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.)
Sener Ingenieria y Sistemas SA
Original Assignee
Sener Ingenieria y Sistemas SA
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 Sener Ingenieria y Sistemas SA filed Critical Sener Ingenieria y Sistemas SA
Priority to ES009602744A priority Critical patent/ES2136528B1/es
Priority to CA002204078A priority patent/CA2204078C/en
Priority to AT97500118T priority patent/ATE229619T1/de
Priority to DE69717778T priority patent/DE69717778T2/de
Priority to EP97500118A priority patent/EP0851110B1/en
Priority to US08/990,341 priority patent/US6067793A/en
Publication of ES2136528A1 publication Critical patent/ES2136528A1/es
Application granted granted Critical
Publication of ES2136528B1 publication Critical patent/ES2136528B1/es
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/008—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector in any rearward direction
    • 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
    • F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
  • Nozzles (AREA)
  • On-Site Construction Work That Accompanies The Preparation And Application Of Concrete (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Abstract

Mejoras en la patente de invención Nº. 9401114, presentada el 20 de mayo de 1.994, relativa a: Perfeccionamientos en toberas axisimétricas de geometría variable y orientación del flujo destinadas a propulsores de turbina de gas. La tobera comprende medios de gobierno, para regular el área de garganta A{sub,8 y vectorizar el empuje, compuestos por tres anillos concéntricos con el eje longitudinal (14) del propulsor, uno interno (8), uno intermedio (7) y uno externo (6), y por una pluralidad de actuadores lineales (9); incluyendo el anillo externo (6) dos segmentos de anillo (6a-6b) biarticulados entre sí que tiene limitada su capacidad de basculamiento a un solo plano y, por tanto, pueden vectorizar el empuje únicamente en el plano de cabeceo del avión. De aplicación en propulsores de aviones birreactores.
ES009602744A 1996-12-26 1996-12-26 Perfeccionamientos en toberas axisimetricas de geometria variable y orientacion del flujo destinadasa propulsores de turbina de gas Expired - Fee Related ES2136528B1 (es)

Priority Applications (6)

Application Number Priority Date Filing Date Title
ES009602744A ES2136528B1 (es) 1996-12-26 1996-12-26 Perfeccionamientos en toberas axisimetricas de geometria variable y orientacion del flujo destinadasa propulsores de turbina de gas
CA002204078A CA2204078C (en) 1996-12-26 1997-04-30 Improvements in axisymmetric nozzles of variable geometry and orientation of the flow, which are intended for gas turbine engines
AT97500118T ATE229619T1 (de) 1996-12-26 1997-07-04 Schwenkdüse mit veränderlichem querschnitt für ein strahltriebwerk
DE69717778T DE69717778T2 (de) 1996-12-26 1997-07-04 Schwenkdüse mit veränderlichem Querschnitt für ein Strahltriebwerk
EP97500118A EP0851110B1 (en) 1996-12-26 1997-07-04 Variable area vectorable nozzle
US08/990,341 US6067793A (en) 1996-12-26 1997-12-15 Variable geometry axisymmetric nozzle with 2-d thrust vectoring intended for a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ES009602744A ES2136528B1 (es) 1996-12-26 1996-12-26 Perfeccionamientos en toberas axisimetricas de geometria variable y orientacion del flujo destinadasa propulsores de turbina de gas

Publications (2)

Publication Number Publication Date
ES2136528A1 true ES2136528A1 (es) 1999-11-16
ES2136528B1 ES2136528B1 (es) 2000-05-01

Family

ID=8297157

Family Applications (1)

Application Number Title Priority Date Filing Date
ES009602744A Expired - Fee Related ES2136528B1 (es) 1996-12-26 1996-12-26 Perfeccionamientos en toberas axisimetricas de geometria variable y orientacion del flujo destinadasa propulsores de turbina de gas

Country Status (6)

Country Link
US (1) US6067793A (es)
EP (1) EP0851110B1 (es)
AT (1) ATE229619T1 (es)
CA (1) CA2204078C (es)
DE (1) DE69717778T2 (es)
ES (1) ES2136528B1 (es)

Cited By (1)

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CN113982777A (zh) * 2021-11-10 2022-01-28 南京航空航天大学 一种可线性化控制的双喉道气动矢量喷管

Families Citing this family (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2792366B1 (fr) * 1999-04-15 2005-08-19 Snecma Tuyere d'ejection axisymetrique, convergente divergente et orientable
EP1052395B1 (en) * 1999-05-13 2004-07-07 Industria de Turbo Propulsores S.A. Exit area control mechanism for convergent divergent nozzles
FR2796422B1 (fr) * 1999-07-12 2001-09-07 Snecma Tuyere d'ejection de turboreacteur axisymetrique, convergente divergente a deviation de jet
US6622472B2 (en) * 2001-10-17 2003-09-23 Gateway Space Transport, Inc. Apparatus and method for thrust vector control
US20040244633A1 (en) * 2003-05-08 2004-12-09 Witmer Warner H. Cats-constrained airplane transportation system
DE102004056127A1 (de) * 2004-11-20 2006-05-24 SCHÄFER, Alexander Auf Düsenantrieb
US7721551B2 (en) * 2006-06-29 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle
EP3495650B8 (en) * 2006-10-17 2021-04-14 Raytheon Technologies Corporation Method of varying an annular fan exit area of a gas turbine engine
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
US7861535B2 (en) * 2007-09-24 2011-01-04 United Technologies Corporation Self-aligning liner support hanger
CN102083688B (zh) * 2008-05-07 2013-12-11 安泰克有限公司 具有推力控制遮罩的流体动力设备
US8549834B2 (en) 2010-10-21 2013-10-08 United Technologies Corporation Gas turbine engine with variable area fan nozzle
RU2445486C1 (ru) * 2010-11-26 2012-03-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Плоское сопло турбореактивного двигателя
RU2445487C1 (ru) * 2010-12-02 2012-03-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Плоское сопло турбореактивного двигателя
RU2451812C1 (ru) * 2010-12-24 2012-05-27 Открытое акционерное общество Авиамоторный научно-технический комплекс "Союз" Поворотное круглое осесимметричное реактивное сопло воздушно-реактивного двигателя
US9249732B2 (en) 2012-09-28 2016-02-02 United Technologies Corporation Panel support hanger for a turbine engine
US9243515B2 (en) 2012-09-28 2016-01-26 United Technologies Corporation Support hanger for flexibly connecting a plurality of panels
WO2014197030A2 (en) * 2013-03-12 2014-12-11 United Technologies Corporation Expanding shell flow control device
WO2015000028A1 (en) * 2013-07-01 2015-01-08 Entecho Pty Ltd An aerodynamic lifting device
CN105756807A (zh) * 2014-12-19 2016-07-13 中国航空工业集团公司沈阳发动机设计研究所 一种新式喷管
US9951717B2 (en) 2015-04-15 2018-04-24 Hamilton Sundstrand Corporation Asymmetric load compensation system
CN106499543B (zh) * 2016-09-26 2017-12-26 南京航空航天大学 一种排气喷管推力矢量控制与面积调节的装置
US10669020B2 (en) * 2018-04-02 2020-06-02 Anh VUONG Rotorcraft with counter-rotating rotor blades capable of simultaneously generating upward lift and forward thrust
GB2588651A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588652A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588653A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
CN111271194B (zh) * 2020-03-06 2023-07-18 南京理工大学 一种滚珠丝杠驱动的推力矢量多轴摆动喷管
CN111322912A (zh) * 2020-03-06 2020-06-23 南京理工大学 一种滚珠丝杠协同驱动的推力矢量全轴摆动喷管
CN112177795B (zh) * 2020-09-18 2021-08-20 中国航发四川燃气涡轮研究院 一种轴对称矢量喷管外密封片对中机构
CN112412654B (zh) * 2020-11-05 2022-09-20 中国航发四川燃气涡轮研究院 一种螺杆调节式二元矢量喷管结构及调节方法
CN113374595B (zh) * 2021-05-27 2022-04-22 南京航空航天大学 一种椭圆形喉道偏移式气动矢量喷管的设计方法
CN113982778B (zh) * 2021-09-22 2023-05-26 西安交通大学 一种用于变循环航空发动机的二维可调后涵道引射器
EP4180332A1 (en) * 2021-11-11 2023-05-17 Airbus Defence and Space GmbH Fuselage for an aircraft with fuselage-integrated tailplane
US11772809B2 (en) 2021-11-27 2023-10-03 Airbus Defence and Space GmbH Fuselage for an aircraft with fuselage-integrated tailplane
CN114251188B (zh) * 2021-12-22 2023-04-07 北京航空航天大学 一种基于自适应变循环发动机的喷管结构及其操作方法
CN114776469A (zh) * 2022-04-14 2022-07-22 中国航发沈阳发动机研究所 一种轴对称喷管
PL443524A1 (pl) * 2023-01-18 2023-07-10 Politechnika Świętokrzyska Układ napędowy bezzałogowego statku powietrznego

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4978071A (en) * 1989-04-11 1990-12-18 General Electric Company Nozzle with thrust vectoring in the yaw direction
EP0595753A1 (en) * 1992-10-27 1994-05-04 Sener, Ingenieria Y Sistemas, S.A. Divergent slave petal for variable geometry exhaust nozzles
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4175385A (en) * 1977-12-12 1979-11-27 General Electric Company Thrust reverser for an asymmetric aircraft exhaust nozzle
US4994660A (en) * 1989-04-11 1991-02-19 Hitachi, Ltd. Axisymmetric vectoring exhaust nozzle
ES2075782B1 (es) * 1992-02-20 1998-03-16 Sener Ing & Sist Tobera orientable de geometria variable para turbinas de gas.
US5351888A (en) * 1993-05-14 1994-10-04 General Electric Company Multi-axis vectorable exhaust nozzle
ES2105929B1 (es) * 1993-11-23 1998-05-01 Sener Ing & Sist Tobera axisimetrica orientable de geometria variable para propulsores de turbina de gas.
ES2136475B1 (es) * 1994-05-20 2000-05-16 Sener Ing & Sist Perfeccionamientos en toberas axisimetricas de geometria variable y orientacion del flujo destinadas a propulsores de turbina de gas.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4978071A (en) * 1989-04-11 1990-12-18 General Electric Company Nozzle with thrust vectoring in the yaw direction
EP0595753A1 (en) * 1992-10-27 1994-05-04 Sener, Ingenieria Y Sistemas, S.A. Divergent slave petal for variable geometry exhaust nozzles
US5511376A (en) * 1993-08-31 1996-04-30 United Technologies Corporation Axisymmetric vectoring nozzle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113982777A (zh) * 2021-11-10 2022-01-28 南京航空航天大学 一种可线性化控制的双喉道气动矢量喷管

Also Published As

Publication number Publication date
CA2204078C (en) 2004-04-20
DE69717778T2 (de) 2003-09-18
ES2136528B1 (es) 2000-05-01
US6067793A (en) 2000-05-30
ATE229619T1 (de) 2002-12-15
DE69717778D1 (de) 2003-01-23
CA2204078A1 (en) 1998-06-26
EP0851110B1 (en) 2002-12-11
EP0851110A3 (en) 1999-10-13
EP0851110A2 (en) 1998-07-01

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