WO1997017255A1 - Systeme de commande d'helice transsonique coaxiale et a pas reversible - Google Patents

Systeme de commande d'helice transsonique coaxiale et a pas reversible Download PDF

Info

Publication number
WO1997017255A1
WO1997017255A1 PCT/RU1997/000002 RU9700002W WO9717255A1 WO 1997017255 A1 WO1997017255 A1 WO 1997017255A1 RU 9700002 W RU9700002 W RU 9700002W WO 9717255 A1 WO9717255 A1 WO 9717255A1
Authority
WO
WIPO (PCT)
Prior art keywords
valve
channel
chamber
ρeveρsa
control system
Prior art date
Application number
PCT/RU1997/000002
Other languages
English (en)
Russian (ru)
Inventor
Leonid Evgenievich Plakhov
Jury Nikolaevich Vronsky
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 AU15605/97A priority Critical patent/AU1560597A/en
Publication of WO1997017255A1 publication Critical patent/WO1997017255A1/fr

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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof

Definitions

  • the invention is subject to aviation technology, in particular to systems 5 of which are equipped with propeller-driven gas turbines.
  • PREVIOUS UZH ⁇ It is known to ensure high efficiency and negative impact.
  • the indicated negative effects can be minimized by avoiding changing the angle of installation of the blades with a speed of 10 times more than in case of performing a reversal by a traditional way.
  • Fig. 3 - parts of D and ⁇ control systems shown in Fig. 1, located in the control and participating in the control of the front fans.
  • the control system with a real reversible rotor (Fig. 1) is based on a unit that is identical to that located in its front part, which is independent of the rest.
  • Regulate (part C), in turn, consists of identical units D and
  • Part disproportionate of the control system in Fig. 1 is not shown completely from the conditions of the elimination of the image (without vaults and valves).
  • a further description of the system is based on the control of the front fans. Control of the rear rotor screw is a similar process.
  • FIG. 2 introduced the oil pump of 20 fans, an additional number of 21 large steps, valve 22 of the oil pump of the fan is connected, 22 ⁇ ⁇ 97/17255 ⁇ / ⁇ 97 / 00002
  • Fig. 2 shows an arrangement located at hub 1 of the blade 34 with a finger 35, interconnected with the brake 3, oil 36, at the same time, it is installed on the 24th, aforementioned 24, 23, aforementioned 23, on the 10th, 23, 23, 8,
  • selective valve 39 selective valve 39, split valves 40, 41 and 42, filter 43, reduced valve 44 and 45 nozzle.
  • a channel for 46 large steps a channel for 47 small steps and a channel for 48 step steps are also shown.
  • the 45-jets are designed to limit oil drainage and quick-release solenoid valves 16, 18 and 32.
  • a working fluid (hereinafter referred to as the oil) of low pressure is supplied to channel 49 at the inlet to the oil pump 1 1 (Fig. 3), after which there is a high oil pressure of 51 cm.
  • step 2 When high pressure is applied, step 2 is placed on and off through step 3 and finger 35 and the finger 34 is moved to increase the angle of installation.
  • L ⁇ as ⁇ 34 us ⁇ an ⁇ vi ⁇ sya on ug ⁇ l, s ⁇ ve ⁇ s ⁇ vuyuschy ⁇ avn ⁇ vesn ⁇ y chas ⁇ e v ⁇ ascheniya vin ⁇ ven ⁇ ilya ⁇ a.
  • the simultaneous high pressure on channels 71 and 72 is as large as the area above the 30 prisoner by switching the channels of large and small steps. ⁇
  • the valve cover 22 is connected to the oil pump of the ventilator and is connected to the drain channels 64 and 48 after the quick release of 17 steps.
  • U ⁇ azanny ⁇ la ⁇ an ⁇ d deys ⁇ viem efforts ⁇ uzhiny ⁇ e ⁇ emeschae ⁇ sya vve ⁇ ⁇ s ⁇ edinyae ⁇ ⁇ and drain 62 and 63.
  • valve 22 goes down and discharges through channels 63 and 64 and increases the high pressure of the oil pump 20 and increases the speed of the fan.
  • connection of channels 46 and 47 to the receiver 12 of the power switch must be in operation at a standstill when it is in a malfunctioning state
  • the higher wiring of channels ensures that the rotational speed of the fan is maintained at the same speed as the rotational speed of the fan. This is as follows.
  • a 12-hour wake-up device by activating the load of the 13 load cells is switched off and a high-pressure oil outlet from the 51-channel Za ⁇ em, vys ⁇ e pressure che ⁇ ez lower ⁇ as ⁇ ch ⁇ u z ⁇ l ⁇ ni ⁇ a 30 ⁇ anal 60, a bottom ⁇ as ⁇ ch ⁇ u z ⁇ l ⁇ ni ⁇ a 14 ⁇ s ⁇ u ⁇ ae ⁇ in ⁇ anal 47 step mal ⁇ g ⁇ and further - in ⁇ l ⁇ s ⁇ 5 mal ⁇ g ⁇ step ⁇ i e ⁇ m, ⁇ l ⁇ s ⁇ 4 b ⁇ lsh ⁇ g ⁇ step s ⁇ bschae ⁇ sya s ⁇ sliv ⁇ m ( ⁇ u ⁇ ⁇ zhdeniya oil ⁇ ⁇ analam and elemen ⁇ am
  • the systems for this case are described above for the description of the direct mode).
  • the cam 10 By accessing the camshaft, the cam 10 is interrupted by a quick release of 23 and the latter is driven by the rear axle.
  • the high pressure from channel 48 is increased through the pressure release valve 28, the upper air outlet is disconnected 23 and the air outlet is 68.
  • gaining access to a prisoner 26 exits from the repertoire on channel 83, through a lower separation zone 23 is communicated with a disengaged person.
  • Fan operation is performed with a single engine at a standstill after the command has been turned on to turn on the fan pump (it is not used on the drawer). (The original use of the elements of the system when describing the mode of operation is compatible with the operation of the mode of direct traction).
  • the control valve is 40 and the channel is 51 to the filter 43.
  • the oil is supplied to the reduced valve 44, which is limited by the maximum pressure in the system.
  • ⁇ chischenn ⁇ e ⁇ il ⁇ m 43 masl ⁇ ⁇ ⁇ analu 52 ⁇ dv ⁇ di ⁇ sya ⁇ z ⁇ l ⁇ ni ⁇ u 14 ⁇ lyuge ⁇ a and ⁇ a ⁇ zhe ⁇ ⁇ analu 88 che ⁇ ez ⁇ as ⁇ ch ⁇ u sele ⁇ n ⁇ g ⁇ ⁇ la ⁇ ana 39, ⁇ ⁇ analu 89 che ⁇ ez ⁇ as ⁇ edeli ⁇ elny ⁇ la ⁇ an 41, ⁇ ⁇ analu 90 che ⁇ ez ⁇ as ⁇ ch ⁇ u z ⁇ l ⁇ ni ⁇ a 15 vyv ⁇ da of ⁇ lyuge ⁇ a, ⁇ ⁇ analu 91 Sovereign over the landlord 14 flueugra. Moving down, the aforementioned greenhouse will connect through the upper quick channel 52 to
  • step 2 will be moved to the right and through the step 3 to move the blade in the direction of increasing the angle of installation.
  • One oil from a small area of 5 small steps will be displaced to the drain by channel 57 through valve 7, channel 58, by-pass valve 25, channel 59, and external reset
  • Movement 2 will, in addition, continue to move downward at 23 cam 10, and the corner of the fence should be located at the same time.
  • the area of 4 large steps on channel 56 is communicated with the drains through the lower landlord 26.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)

Abstract

Cette invention se rapporte au domaine de l'aéronautique et son résultat technique consiste en de plus grandes vitesses d'inversion des pales d'une hélice transsonique lors d'un mode de fonctionnement inverse consistant à passer par le stade de drapeau. Cette invention permet également d'assurer un transfert des pales selon des angles de fonctionnement inverse optimaux, ainsi que leur retour aux angles initiaux, ceci grâce à un piston (2), une chambre (4) de pas élevé, une chambre (5) de pas réduit et une chambre permettant d'exclure le décrochage du flux d'air. Cette invention permet enfin de maintenir une fréquence de rotation équilibrée de l'hélice lors de son mode de fonctionnement inverse. A cette fin, chacun des deux moyeux (1) de l'hélice comprend un mécanisme hydraulique de changement de la position des pales (34), dans la chambre de vidange (6) duquel se trouvent des cames (9) et (10) et un clapet (7) comportant un plongeur (8), ainsi qu'une pompe à huile (20) connectée à une chambre complémentaire (21) et à un clapet (22), et des tiroirs (23, 24, 25, 26). Le régulateur est en outre connecté au mécanisme hydraulique susmentionné par des canaux (33, 46, 47, 48), et comprend une pompe à huile (11), des tiroirs (12, 14, 15, 17) et des clapets électromagnétiques (16, 18), ainsi que des tiroirs (30) et (31) et un clapet électromagnétique (32). La chambre située en amont du clapet (22) est connectée par l'intermédiaire d'un clapet répartiteur (27) au canal (48) et à la sortie du tiroir (24), l'entrée de ce dernier étant connectée au canal (33) et à la chambre de décharge (6). Le canal (46) est connecté à la chambre (4) par l'intermédiaire du tiroir (26), tandis que le canal (47) est connecté à la chambre (5) par l'intermédiaire des tiroirs (26, 27) et du clapet (7). Les tiroirs (23) et (24) sont reliés de manière cinématique aux cames (9) et (10) dont l'emplacement sur le piston (2) définit, respectivement, l'angle de drapeau et la butée de transfert des pales (34). Le canal (33) et la chambre de décharge (6) sont connectés à l'entrée du tiroir (23), le canal (48) et la sortie de la pompe à huile (20) étant également connectés à l'entrée du tiroir (23) par l'intermédiaire du clapet répartiteur (28). Les chambres situées en amont du plongeur (8) et du tiroir (26) sont, quant à elles, connectées à la sortie de ce même tiroir (23). La cavité à ressort du tiroir susmentionné et la chambre située en amont du tiroir (25) sont connectées au canal (33), tandis que la cavité à ressort est reliée par l'intermédiaire du clapet répartiteur (29) au canal (48) et à la sortie du tiroir (24). Les chambres (4) et (5) sont connectées entre elles par l'intermédiaire des clapets (7) et (25).
PCT/RU1997/000002 1996-10-17 1997-01-08 Systeme de commande d'helice transsonique coaxiale et a pas reversible WO1997017255A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU15605/97A AU1560597A (en) 1996-10-17 1997-01-08 System for controlling a coaxial reversing propeller fan

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU96120106 1996-10-17
RU96120106A RU2101212C1 (ru) 1996-10-17 1996-10-17 Система управления соосным реверсивным винтовентилятором

Publications (1)

Publication Number Publication Date
WO1997017255A1 true WO1997017255A1 (fr) 1997-05-15

Family

ID=20186350

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1997/000002 WO1997017255A1 (fr) 1996-10-17 1997-01-08 Systeme de commande d'helice transsonique coaxiale et a pas reversible

Country Status (3)

Country Link
AU (1) AU1560597A (fr)
RU (1) RU2101212C1 (fr)
WO (1) WO1997017255A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10800512B2 (en) 2015-09-03 2020-10-13 General Electric Company System and method for propeller pitch control
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2940247B1 (fr) * 2008-12-19 2011-01-21 Snecma Systeme d'helices contrarotatives entrainees par un train epicycloidal offrant une repartition de couple equilibree entre les deux helices
FR2951696B1 (fr) * 2009-10-22 2011-12-23 Snecma Systeme pour faire varier l'incidence des pales d'une helice de turbomachine pour aeronef, utilisant un moteur electrique sans balai
FR2980770B1 (fr) * 2011-10-03 2014-06-27 Snecma Turbomachine a helice(s) pour aeronef avec systeme pour changer le pas de l'helice.

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU67587A1 (ru) * 1942-02-15 1945-11-30 Л.С. Файн Устройство дл реверсировани винта с автоматическим изменением шага
US3901626A (en) * 1972-08-10 1975-08-26 Rolls Royce 1971 Ltd Actuating mechanism for a variable pitch fan or propeller
EP0039496A2 (fr) * 1980-05-06 1981-11-11 Saarbergwerke Aktiengesellschaft Dispositif pour l'ancrage des rails de roulement pour chemins de fer de mines
DE3837994A1 (de) * 1988-11-09 1990-05-10 Mtu Muenchen Gmbh Vorrichtung zur verstellung der rotorschaufeln eines propfan/turboproptriebwerkes
EP0409552A2 (fr) * 1989-07-21 1991-01-23 Dowty Aerospace Gloucester Limited Système de commande d'helices à pas variable
US5141399A (en) * 1990-10-18 1992-08-25 United Technologies Corporation Pitch change control system
GB2260821A (en) * 1991-10-25 1993-04-28 United Technologies Corp LVDT for propeller pitch change system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU67587A1 (ru) * 1942-02-15 1945-11-30 Л.С. Файн Устройство дл реверсировани винта с автоматическим изменением шага
US3901626A (en) * 1972-08-10 1975-08-26 Rolls Royce 1971 Ltd Actuating mechanism for a variable pitch fan or propeller
EP0039496A2 (fr) * 1980-05-06 1981-11-11 Saarbergwerke Aktiengesellschaft Dispositif pour l'ancrage des rails de roulement pour chemins de fer de mines
DE3837994A1 (de) * 1988-11-09 1990-05-10 Mtu Muenchen Gmbh Vorrichtung zur verstellung der rotorschaufeln eines propfan/turboproptriebwerkes
EP0409552A2 (fr) * 1989-07-21 1991-01-23 Dowty Aerospace Gloucester Limited Système de commande d'helices à pas variable
US5141399A (en) * 1990-10-18 1992-08-25 United Technologies Corporation Pitch change control system
GB2260821A (en) * 1991-10-25 1993-04-28 United Technologies Corp LVDT for propeller pitch change system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10800512B2 (en) 2015-09-03 2020-10-13 General Electric Company System and method for propeller pitch control
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Also Published As

Publication number Publication date
AU1560597A (en) 1997-05-29
RU2101212C1 (ru) 1998-01-10

Similar Documents

Publication Publication Date Title
EP1897804B1 (fr) Système et procédé pour commander l'alimentation électrique d'un avion
US3893638A (en) Dual cycle fan jet engine for stol aircraft with augmentor wings
US5170963A (en) VTOL aircraft
US5213471A (en) Propeller pitch control
RU2012512C1 (ru) Комбинированный летательный аппарат
US4514976A (en) Integrated auxiliary power and environmental control unit
US4062185A (en) Method and apparatus for windmill starts in gas turbine engines
US7982328B2 (en) Emergency supply unit with a ram-air turbine adapted to be driven by an air stream and with an energy converter for aircraft
US2320195A (en) Airplane propeller and actuating mechanism therefor
US3045951A (en) Aircraft
CA2105339C (fr) Systeme de commande d'une helice a pas variable, a pleine autorite
US6269627B1 (en) Rapid thrust response control logic for shaft-driven lift fan STOVL engine
US6196801B1 (en) Adjustable propeller unit which can be hydraulically reversed
CN112173078A (zh) 螺旋桨组件和桨距控制单元
WO1997017255A1 (fr) Systeme de commande d'helice transsonique coaxiale et a pas reversible
CN101450714A (zh) 喷气式直升飞机
US3467213A (en) Gas turbine powered air-cushion vehicle with propulsive jet means
US3985094A (en) Series waterjet propulsion pumps for marine vehicles
EP1936173A2 (fr) Système de propulsion de moteur avec un premier et deuxieme conduit d'échappement
US5391055A (en) Propeller pitch change mechanism with impulse turbines
US3940926A (en) Jet propulsion engines
US2652122A (en) Propeller pitch stop system
US11286881B2 (en) Gas turbine engine with reversible heat exchanger
RU2099243C1 (ru) Соосный воздушный винт и способ его управления
US3503572A (en) Vertical take-off and landing aircraft

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AL AM AT AU AZ BB BG BR BY CA CH CN CZ DE DK EE ES FI GB GE HU IL IS JP KE KG KP KR KZ LK LR LS LT LU LV MD MG MK MN MW MX NO NZ PL PT RO RU SD SE SG SI SK TJ TM TR TT UA UG US UZ VN AM AZ BY KG KZ MD RU TJ TM

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): KE LS MW SD SZ UG AT BE CH DE DK ES FI FR GB GR IE IT LU MC NL PT SE BF BJ CF CG CI CM GA

121 Ep: the epo has been informed by wipo that ep was designated in this application
DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

122 Ep: pct application non-entry in european phase
NENP Non-entry into the national phase

Ref country code: CA