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WO1997017253A1 - Helice a pas variable et procede de mesure de la position angulaire de ses pales - Google Patents

Helice a pas variable et procede de mesure de la position angulaire de ses pales Download PDF

Info

Publication number
WO1997017253A1
WO1997017253A1 PCT/RU1996/000366 RU9600366W WO9717253A1 WO 1997017253 A1 WO1997017253 A1 WO 1997017253A1 RU 9600366 W RU9600366 W RU 9600366W WO 9717253 A1 WO9717253 A1 WO 9717253A1
Authority
WO
WIPO (PCT)
Prior art keywords
fact
blades
propeller
beτa
air screw
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.)
Ceased
Application number
PCT/RU1996/000366
Other languages
English (en)
Russian (ru)
Inventor
Valery Antonovich Poddubsky
Jury Mikhailovich Gnidkin
Alexandr Nikolaevich Kashirov
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.)
Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpriyatie 'aerosila'
Original Assignee
Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpriyatie 'aerosila'
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 Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpriyatie 'aerosila' filed Critical Otkrytoe Aktsionernoe Obschestvo 'nauchno-Proizvodstvennoe Predpriyatie 'aerosila'
Priority to AU13227/97A priority Critical patent/AU1322797A/en
Publication of WO1997017253A1 publication Critical patent/WO1997017253A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • B64C11/40—Blade pitch-changing mechanisms fluid, e.g. hydraulic automatic

Definitions

  • the invention is subject to aeronautical engineering and, in particular, to air propellers of varying pitch and to appliances that allow for the installation of stationary
  • Izves ⁇ en v ⁇ zdushny vin ⁇ s ⁇ de ⁇ zhaschy gid ⁇ me ⁇ anizm changes ugl ⁇ v us ⁇ an ⁇ v ⁇ i l ⁇ as ⁇ ey with ⁇ shnem, s ⁇ e ⁇ lennym with me ⁇ anizm ⁇ m ⁇ b ⁇ a ⁇ n ⁇ y communication and chas ⁇ ny da ⁇ chi ⁇ , ⁇ as ⁇ l ⁇ zhenny on ⁇ lantse ⁇ edu ⁇ a dviga ⁇ elya over ⁇ veri ⁇ m ⁇ iv ⁇ bledeni ⁇ eln ⁇ y sis ⁇ emy vin ⁇ a [Pa ⁇ en ⁇
  • s ⁇ de ⁇ zhaschy gid ⁇ me ⁇ anizm changes ugl ⁇ v us ⁇ an ⁇ v ⁇ i l ⁇ as ⁇ ey with ⁇ shnem, s ⁇ e ⁇ lennym with me ⁇ anizm ⁇ m ⁇ b ⁇ a ⁇ n ⁇ y communication v ⁇ lyuchayuschim masl ⁇ dayuschuyu be ⁇ a- ⁇ ub ⁇ u and vzaim ⁇ deys ⁇ vuyuschy her linear da ⁇ chi ⁇ ugl ⁇ v ⁇ g ⁇ ⁇ l ⁇ zheniya l ⁇ as ⁇ ey [Pa ⁇ en ⁇ ⁇ eli ⁇ b ⁇ i ⁇ anii
  • the measurement accuracy is reduced, which depends on the size of the measured transmissions of the oil-supplying beta-tube.
  • a separate linear sensor is required; the presence of a screw also increases the value of the standard power supply.
  • the linear sensor assembly which is sufficiently extended in the axial direction, increases the long dimensions of the screw and the power unit as a whole.
  • the pulse signals of the signals are transmitted to the microprocessor to determine the angular position of the components at the momentary shift of the pulse signals.
  • a particular part of the system is often generated by a pulse signal received by a consumer receiving a product from a household broadcasting machine.
  • the range of changes in the volume of the oil supply of the beta-pipe to the selected installation angle is limited by the range of installation angles.
  • the inventive group of inventions complies with the requirement of unity of the invention, a large group of various inventions of a single invention ⁇ ⁇ 97/17253 ⁇ 96 / 00366
  • an eruptive finger of 11 is a step by step, all in all, a 5-step
  • the internal process 14 is made up of two parts: the left - mobile and the fixed - stationary in the left direction. Parts of the internal appliances are connected to the other by radial slots, which is equipped with a fixed motion gear.
  • P ⁇ s ⁇ yann ⁇ e vzaim ⁇ deys ⁇ vie sh ⁇ i ⁇ a 17 ⁇ tsev ⁇ y ⁇ ve ⁇ n ⁇ s ⁇ yu 16 ⁇ aza 16 ⁇ i ⁇ ebuem ⁇ y ⁇ l ⁇ n ⁇ s ⁇ i s ⁇ y ⁇ a in vyb ⁇ ann ⁇ m in ⁇ e ⁇ vale ⁇ ab ⁇ chi ⁇ ugl ⁇ v ⁇ ( ⁇ ⁇ s) d ⁇ ( ⁇ t ⁇ ⁇ a ⁇ eys + (5-10 g ⁇ ad)) ⁇ bes ⁇ echivayu ⁇ ⁇ ⁇ 97/17253 ⁇ 96 / 00366
  • P ⁇ i e ⁇ m, external ⁇ ess ⁇ a 13 za ⁇ i ⁇ si ⁇ vannaya ⁇ ⁇ e ⁇ emescheny in ⁇ sev ⁇ m na ⁇ avlenii ⁇ dshi ⁇ ni ⁇ ami 27 and 28 are offset in ⁇ luchae ⁇ ugl ⁇ v ⁇ e ⁇ uzhn ⁇ m na ⁇ avlenii ⁇ n ⁇ si ⁇ eln ⁇ vnu ⁇ enney ⁇ ess ⁇ y 14, ⁇ . ⁇ . sh ⁇ i ⁇ 17 ⁇ e ⁇ emeschae ⁇ sya in vin ⁇ vy ⁇ ⁇ aza ⁇ 18 vyzyvae ⁇ ⁇ azv ⁇ outer ⁇ ess ⁇ y 13.
  • na ⁇ im ⁇ b ⁇ az ⁇ m - ⁇ azhd ⁇ mu ⁇ l ⁇ zheniyu ⁇ shnya 5 and 15 na ⁇ nechni ⁇ a masl ⁇ dayuschey be ⁇ a- ⁇ ub ⁇ i s ⁇ ve ⁇ s ⁇ vue ⁇ ⁇ edelenny ⁇ azv ⁇ in ⁇ uzhn ⁇ m na ⁇ avlenii v ⁇ aschayuscheg ⁇ sya indu ⁇ a 9, the outer s ⁇ e ⁇ lenn ⁇ g ⁇ ⁇ ess ⁇ y 13 ⁇ n ⁇ si ⁇ eln ⁇ v ⁇ aschayuscheg ⁇ sya indu ⁇ a 10 s ⁇ e ⁇ lenn ⁇ g ⁇ with ne ⁇ dvizhn ⁇ y in ⁇ sev ⁇ m na ⁇ avlenii chas ⁇ yu vnu ⁇ enney ⁇ ess ⁇ y 14.
  • Pulse signals from sensors 7 and 8, having a temporal offset of the friends, is a simple device. ⁇ bsche ⁇ a, na ⁇ ime ⁇ , ele ⁇ nny mi ⁇ tsess ⁇ for ⁇ ⁇ 97/17253 ⁇ 7 ⁇ 96 / 00366

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)

Abstract

Cette invention se rapporte au domaine de l'aéronautique et concerne plus particulièrement une hélice à pas variable. La particularité de cette hélice tient au fait qu'elle comprend des ressorts concentriques et des transmissions du moment rotatif qui entrent en interaction avec une conduite d'alimentation en huile du côté opposé au piston, ceci afin d'assurer de manière cinématique ladite interaction dans l'intervalle des angles de fonctionnement des pales. Le ressort interne est relié cinématiquement et dans le sens axial à la conduite d'alimentation en huile, tandis que le ressort externe peut effectuer un déplacement angulaire et circulaire par rapport au ressort interne, ce déplacement s'effectuant à l'aide de la paire d'hélice comprenant un doigt et une gorge d'hélice. Les ressorts sont reliés entre eux dans le sens circulaire par un ressort hélicoïdal, et comportent des inducteurs entrant en interaction avec des capteurs de fréquence, ce qui permet de mesurer la position angulaire des pales. La particularité de ce procédé de mesure de la position angulaire des pales tient au fait que le signal d'impulsion du capteur est obtenu par la transformation des déplacements en translation de la conduite bêta d'alimentation en huile, en des déplacements en rotation de l'inducteur. La plage de mesure des déplacements de la conduite d'alimentation en huile est limitée par l'intervalle choisi des angles de calage des pales lors du fonctionnement.
PCT/RU1996/000366 1996-10-17 1996-12-30 Helice a pas variable et procede de mesure de la position angulaire de ses pales Ceased WO1997017253A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU13227/97A AU1322797A (en) 1996-10-17 1996-12-30 Variable pitch air propeller and method of measuring the angular position of the propeller blades

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU96120111 1996-10-17
RU96120111A RU2099242C1 (ru) 1996-10-17 1996-10-17 Воздушный винт изменяемого шага и способ измерения углового положения его лопастей

Publications (1)

Publication Number Publication Date
WO1997017253A1 true WO1997017253A1 (fr) 1997-05-15

Family

ID=20186355

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1996/000366 Ceased WO1997017253A1 (fr) 1996-10-17 1996-12-30 Helice a pas variable et procede de mesure de la position angulaire de ses pales

Country Status (3)

Country Link
AU (1) AU1322797A (fr)
RU (1) RU2099242C1 (fr)
WO (1) WO1997017253A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3354562A1 (fr) * 2017-01-30 2018-08-01 Ge Avio S.r.l. Dispositif d'écrasement de palier de transfert

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2276218C1 (ru) * 2004-12-22 2006-05-10 Владимир Александрович Маркин Газоструйная машина
FR2911644B1 (fr) * 2007-01-23 2012-06-01 Snecma Turbopropulseur comportant une helice formee de pales a orientation reglable.
FR2928977B1 (fr) * 2008-03-21 2010-04-09 Snecma Systeme d'helices contrarotatives disposant d'un dispositif de mise en drapeau des pales d'helices
CN107044301B (zh) * 2016-12-13 2022-02-11 惠阳航空螺旋桨有限责任公司 用于螺旋桨贝塔管的锁紧装置
US10577078B2 (en) * 2017-04-24 2020-03-03 General Electric Company Systems and methods for electronic measurement of propeller blade angle

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4097189A (en) * 1976-09-20 1978-06-27 Hartzell Propeller, Inc. Aircraft propeller and blade pitch control system
EP0311277A2 (fr) * 1987-10-03 1989-04-12 Dowty Rotol Limited Dispositif pour pale d'hélice
US4863347A (en) * 1987-10-03 1989-09-05 Dowty Rotol Limited Bladed rotor assemblies
US5174718A (en) * 1991-08-12 1992-12-29 United Technologies Corporation Blade pitch change control system
GB2260821A (en) * 1991-10-25 1993-04-28 United Technologies Corp LVDT for propeller pitch change system
RU2030327C1 (ru) * 1991-06-28 1995-03-10 Гордеев Виктор Федорович Система флюгирования воздушного винта изменяемого шага

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4097189A (en) * 1976-09-20 1978-06-27 Hartzell Propeller, Inc. Aircraft propeller and blade pitch control system
EP0311277A2 (fr) * 1987-10-03 1989-04-12 Dowty Rotol Limited Dispositif pour pale d'hélice
US4863347A (en) * 1987-10-03 1989-09-05 Dowty Rotol Limited Bladed rotor assemblies
RU2030327C1 (ru) * 1991-06-28 1995-03-10 Гордеев Виктор Федорович Система флюгирования воздушного винта изменяемого шага
US5174718A (en) * 1991-08-12 1992-12-29 United Technologies Corporation Blade pitch change control system
GB2260821A (en) * 1991-10-25 1993-04-28 United Technologies Corp LVDT for propeller pitch change system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
TEKHNICHESKOE OPISANIE, 1959, GOSUDARSTVENNOE IZDATELSTVO OBORONNOI PROMYSHLENNOSTI (Moscow), "Aviatsionny Turbovintovoi Dvigatel AI-20", pages 103-112. *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3354562A1 (fr) * 2017-01-30 2018-08-01 Ge Avio S.r.l. Dispositif d'écrasement de palier de transfert
WO2018138295A1 (fr) * 2017-01-30 2018-08-02 Ge Avio S.R.L. Dispositif de pliage de support de transfert
CN110300702A (zh) * 2017-01-30 2019-10-01 通用电气阿维奥有限责任公司 传动轴承伸缩装置
US11161598B2 (en) 2017-01-30 2021-11-02 Ge Avio S.R.L. Transfer bearing collapsing device

Also Published As

Publication number Publication date
AU1322797A (en) 1997-05-29
RU2099242C1 (ru) 1997-12-20

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