ES289449U - Pala de rotor perfeccionada. - Google Patents

Pala de rotor perfeccionada.

Info

Publication number
ES289449U
ES289449U ES1984289449U ES289449U ES289449U ES 289449 U ES289449 U ES 289449U ES 1984289449 U ES1984289449 U ES 1984289449U ES 289449 U ES289449 U ES 289449U ES 289449 U ES289449 U ES 289449U
Authority
ES
Spain
Prior art keywords
airfoil
rotor blade
section
rotorcraft
airfoil section
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
ES1984289449U
Other languages
English (en)
Other versions
ES289449Y (es
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of ES289449U publication Critical patent/ES289449U/es
Application granted granted Critical
Publication of ES289449Y publication Critical patent/ES289449Y/es
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/463—Blade tips
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/02—Formulas of curves

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Rotary Pumps (AREA)
  • Acyclic And Carbocyclic Compounds In Medicinal Compositions (AREA)
  • Paper (AREA)
  • Mechanical Operated Clutches (AREA)

Abstract

Pala de rotor perfeccionada, especialmente para vehículos accionados por este sistema, del tipo que comprenden un eje de giro del cual se extiende la pala del rotor formado la envergadura de la misma; dicha para tiene una parte extrema que comprende el último treinta por ciento de la envergadura (30 %) y posee una sección aerodinámica con un borde de ataque, un borde de salida, una superficie superior comprendida entre dichos bordes de ataque y de salida una superficie inferior que se extiende entre el borde de ataque y el borde de salida, una cuerda de longitud c comprendida entre el borde de ataque y el de salida; dicha cuerda sirve de eje de referencia para medir una coordenada paralelamente a la cuerda, estando dicha coordenada expresa en función de la longitud c, caracterizada por comprender: una sección aerodinámica en la parte extrema de la pala del rotor, con un grosor y entre la superficie superior y la superficie inferior, a lo largo de una linea perpendicular a la cuerda, la relación de grosores entre la superficie inferior y1 y la superficie superior y, medidos a partir de la cuerda, oscila entre el cincuenta y el setenta por ciento **fórmula** ; el grosor t tiene un valor máximo que se halle entre el seis y el once por ciento de la longitud c **fórmula**, la sección aerodinámica comprende una zona del borde de ataque, una zona de la cuerda central y una zona del borde de salida, estando la superficie aerodinámica caracterizada por una gruesa zona del borde de ataque que se extiende desde el borde de ataque hasta aproximadamente el veinte or ciento de la cuerda (20 % C), la cual se halla sumamente combada, alcanzado su valor máximo de comba en el extremo de la zona del borde de ataque, la zona del borde de ataque tiene superficies superior e inferior que se curvan hacia la cuerda, con una curvatura en cada superficie superior disminuye en una proporción casi constante sobre la parte media de la zona del borde de ataque, a fin de reducir el máximo número mach localen la superficie superior en ángulos de ataque positivos, y la curvatura de la superficie inferior disminuye en rápida proporción entre el borde de ataque y el uno que es aproximadamente tres veces la proporción de disminución de comba y grosor en la zona de la cuerda central; la zona del borde de salida concluye con un repliegue del borde de salida que tiene un remate plano entre el noventa y siete y medio por ciento de la cuerpo (97, 5 % C) y el borde de salida:
ES1984289449U 1983-04-18 1984-04-17 Pala de rotor perfeccionada. Expired ES289449Y (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/485,788 US4569633A (en) 1983-04-18 1983-04-18 Airfoil section for a rotor blade of a rotorcraft

Publications (2)

Publication Number Publication Date
ES289449U true ES289449U (es) 1986-11-16
ES289449Y ES289449Y (es) 1987-07-16

Family

ID=23929440

Family Applications (1)

Application Number Title Priority Date Filing Date
ES1984289449U Expired ES289449Y (es) 1983-04-18 1984-04-17 Pala de rotor perfeccionada.

Country Status (11)

Country Link
US (1) US4569633A (es)
JP (1) JPH0717236B2 (es)
AU (1) AU560133B2 (es)
CA (1) CA1220463A (es)
DE (1) DE3414334C2 (es)
ES (1) ES289449Y (es)
FR (1) FR2544279B1 (es)
GB (1) GB2138374B (es)
IL (1) IL71531A (es)
IT (1) IT1175830B (es)
SE (1) SE452298B (es)

Families Citing this family (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4744728A (en) * 1986-09-03 1988-05-17 United Technologies Corporation Helicopter blade airfoil
USRE33589E (en) * 1986-09-03 1991-05-14 United Technologies Corporation Helicopter blade airfoil
US4776531A (en) * 1986-09-05 1988-10-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration High lift, low pitching moment airfoils
US4830574A (en) * 1988-02-29 1989-05-16 United Technologies Corporation Airfoiled blade
FR2628062B1 (fr) * 1988-03-07 1990-08-10 Aerospatiale Pale pour helice carenee a hautes performances, helice carenee multipale pourvue de telles pales et agencement de rotor de queue a helice carenee pour aeronef a voilure tournante
GB2220712B (en) * 1988-07-13 1992-12-09 Rolls Royce Plc Open rotor blading
US4941803A (en) * 1989-02-01 1990-07-17 United Technologies Corporation Airfoiled blade
US5137427A (en) * 1990-12-20 1992-08-11 United Technologies Corporation Quiet tail rotor
GB9112835D0 (en) * 1991-06-14 1992-05-27 Westland Helicopters Helicopter rotor blades
DE4128627C2 (de) * 1991-08-26 1994-06-23 Mannesmann Ag Verfahren zur Veränderung der Geschwindigkeit eines Fahrzeuges und Fahrzeug zur Durchführung dieses Verfahrens
JP3544711B2 (ja) * 1994-08-02 2004-07-21 富士重工業株式会社 回転翼航空機の回転翼羽根
FR2765187B1 (fr) 1997-06-25 1999-08-27 Onera (Off Nat Aerospatiale) Profil de pale pour voilure tournante d'aeronef et pale pour voilure tournante presentant un tel profil
JP3189251B2 (ja) * 1999-03-12 2001-07-16 株式会社コミュータヘリコプタ先進技術研究所 回転翼機のロータブレード
US20020005458A1 (en) * 2000-06-09 2002-01-17 Carter Jay W. Airfoil suitable for forward and reverse flow
US6522993B1 (en) * 2001-09-14 2003-02-18 General Electric Company Method and system for marking surface deviations on a three dimensional surface
US7014142B2 (en) * 2004-02-03 2006-03-21 The Boeing Company Low-drag rotor/wing flap
US7547193B2 (en) * 2005-07-22 2009-06-16 Sikorsky Aircraft Corporation Rotor blade assembly with high pitching moment airfoil section for a rotary wing aircraft
EA015948B1 (ru) * 2009-07-20 2011-12-30 Феликс Мубаракович Давлетшин Лопасть вентилятора градирни
EA015947B1 (ru) * 2009-07-20 2011-12-30 Феликс Мубаракович Давлетшин Лопасть вентилятора градирни
EA015884B1 (ru) * 2009-07-20 2011-12-30 Феликс Мубаракович Давлетшин Лопасть вентилятора градирни (варианты)
EA015966B1 (ru) * 2009-07-20 2012-01-30 Феликс Мубаракович Давлетшин Лопасть вентилятора градирни (варианты)
EA015968B1 (ru) * 2009-10-12 2012-01-30 Феликс Мубаракович Давлетшин Лопасть вентилятора градирни
US9284050B2 (en) * 2011-12-09 2016-03-15 Sikorsky Aircraft Corporation Airfoil for rotor blade with reduced pitching moment
EP3112258B1 (en) * 2015-07-03 2017-09-13 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Airfoils for rotor blades of rotary wing aircrafts
JP6626527B2 (ja) * 2018-04-27 2019-12-25 川崎重工業株式会社 回転翼航空機用ブレード翼型、このブレード翼型を有するブレード、およびこのブレードを備える回転翼航空機
KR102594866B1 (ko) 2018-05-10 2023-10-30 조비 에어로, 인크. 전기 틸트로터 항공기
CN108468620A (zh) * 2018-06-01 2018-08-31 天津超算科技有限公司 叶片翼型及风力发电机
US10710741B2 (en) 2018-07-02 2020-07-14 Joby Aero, Inc. System and method for airspeed determination
WO2020061085A1 (en) 2018-09-17 2020-03-26 Joby Aero, Inc. Aircraft control system
JP7275272B2 (ja) 2018-12-07 2023-05-17 ジョビー エアロ，インコーポレイテッド 航空機制御システム及び方法
EP3891066A4 (en) 2018-12-07 2022-08-10 Joby Aero, Inc. ROTATING AIRFORCE AND DESIGN METHOD THEREFORE
CN109878757B (zh) * 2019-03-03 2022-03-29 西北工业大学 一种适用于超声速靶机兼顾多速域性能的新概念翼型
KR102652792B1 (ko) 2019-04-23 2024-03-29 조비 에어로, 인크. 배터리 열 관리 시스템 및 방법
US11952912B2 (en) * 2022-08-24 2024-04-09 General Electric Company Turbine engine airfoil

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728045A (en) * 1971-09-22 1973-04-17 United Aircraft Corp Helicopter blade
GB1450965A (en) * 1973-12-28 1976-09-29 Boeing Co Rotor blades for rotorcraft
US4142837A (en) * 1977-11-11 1979-03-06 United Technologies Corporation Helicopter blade
CA1141738A (fr) * 1979-08-10 1983-02-22 Jacques Gallot Profil de pale voilure tournante d'aeronef
US4314795A (en) * 1979-09-28 1982-02-09 The Boeing Company Advanced airfoils for helicopter rotor application
FR2490586A1 (fr) * 1980-09-24 1982-03-26 Aerospatiale Profil de pale pour voilure tournante d'aeronef
US4412664A (en) * 1982-06-25 1983-11-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Family of airfoil shapes for rotating blades

Also Published As

Publication number Publication date
US4569633A (en) 1986-02-11
DE3414334C2 (de) 1998-04-09
SE8402124D0 (sv) 1984-04-16
IT1175830B (it) 1987-07-15
FR2544279A1 (fr) 1984-10-19
AU2689284A (en) 1984-10-25
GB8408406D0 (en) 1984-05-10
GB2138374A (en) 1984-10-24
DE3414334A1 (de) 1984-10-25
SE8402124L (sv) 1984-10-19
CA1220463A (en) 1987-04-14
IT8420612A1 (it) 1985-10-18
ES289449Y (es) 1987-07-16
AU560133B2 (en) 1987-04-02
FR2544279B1 (fr) 1986-01-17
SE452298B (sv) 1987-11-23
JPS59206298A (ja) 1984-11-22
JPH0717236B2 (ja) 1995-03-01
IL71531A (en) 1990-11-29
GB2138374B (en) 1986-10-15
IT8420612A0 (it) 1984-04-18

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Effective date: 20030505