EP1936122B1 - Vanne d'isolation du circuit d'huile dans un moteur d'avion - Google Patents

Vanne d'isolation du circuit d'huile dans un moteur d'avion Download PDF

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Publication number
EP1936122B1
EP1936122B1 EP06447130A EP06447130A EP1936122B1 EP 1936122 B1 EP1936122 B1 EP 1936122B1 EP 06447130 A EP06447130 A EP 06447130A EP 06447130 A EP06447130 A EP 06447130A EP 1936122 B1 EP1936122 B1 EP 1936122B1
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EP
European Patent Office
Prior art keywords
valve
turbomachine
engine
isolation valve
shut
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.)
Active
Application number
EP06447130A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1936122A1 (fr
Inventor
Albert Cornet
Marc Montfort
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.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero 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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to AT06447130T priority Critical patent/ATE462063T1/de
Priority to EP06447130A priority patent/EP1936122B1/fr
Priority to ES06447130T priority patent/ES2342317T3/es
Priority to DE602006013168T priority patent/DE602006013168D1/de
Priority to US11/958,021 priority patent/US8020664B2/en
Publication of EP1936122A1 publication Critical patent/EP1936122A1/fr
Application granted granted Critical
Publication of EP1936122B1 publication Critical patent/EP1936122B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/20—Lubricating arrangements using lubrication pumps

Definitions

  • the present invention relates to a closure and isolation valve located at the outlet of the oil tank of an aircraft engine and to its pneumatic control system.
  • turbomachines in general, and in particular those, like turboprop engines, which are likely to have a total stop, or a very low residual speed of the rotation shaft. , after shutdown of the engine in flight and with the exception of those equipped with an electric starter.
  • oil systems may have valves for different purposes.
  • Valves regulating the supply of oil into the equipment to be lubricated are known in the event of failure of one of the components of the lubrication circuit, thus avoiding irreparable damage to the engine.
  • the oil circuit comprises in parallel an emergency lubrication system with an oil tank whose inputs and outputs are regulated by valves.
  • the Inlet and outlet valves are open and the oil in the tank is continuously renewed and supplies, in addition to the circuit, the equipment to be lubricated.
  • the pressure drop in the circuit causes the closing of the inlet valve, and the tank empties, via the outlet valve, thus allowing the equipment to be powered anyway.
  • the tank is empty at a reduced speed compared to the normal operating mode so as to feed the equipment for as long as possible until the tank has been completely emptied.
  • the solenoid type outlet valve cycles with an open position and a closed position or is only partially open.
  • Valves are also known to close the oil circuit at the engine stop, to prevent leakage through the pump (anti-siphon function). Valves are also known to close the oil circuit during an accidental shutdown of the engine in flight, to protect the equipment in case of fire in the engine.
  • shut-off valve having a function of closing and isolating the oil circuit, being in the form of an electrically controlled valve.
  • a shut-off valve having a function of closing and isolating the oil circuit, being in the form of an electrically controlled valve.
  • such a valve has only a fire function, but not anti-leakage, the latter function being provided by other organs.
  • the presence of an oil circuit interruption valve, type anti-siphon valve is indeed also necessary during the normal shutdown of the engine, the closure thereof to prevent the tank from closing. oil will empty through the circuit to the low points of the engine.
  • a valve of the aforementioned type requires not only a source of electrical power, but also control logic at the engine or the aircraft.
  • the control computer is saturated in some aircraft or nonexistent when the regulation is servo-mechanical.
  • the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
  • the object of the invention is to provide a single isolation valve ensuring the dual anti-fire and anti-siphon function, operated at each stop and starting of the engine, following a normal stopping or stopping of the engine in flight.
  • the present invention relates to a turbomachine comprising an air compressor and a lubrication circuit comprising an oil reservoir, said oil reservoir being able to be isolated from the rest of the lubrication circuit by means of an isolation valve comprising a pneumatic control for maintaining the valve in the open and closed position when the turbine engine is in operation respectively and kept at a standstill, and for respectively closing and opening the valve during the stopping and starting of the turbomachine, said valve of insulation being characterized in that it is provided with a device for automatically selecting as command, among two sources of pressurized air, the one which is higher pressure.
  • the first source of pressure is the air pressure coming from the compressor.
  • the second pressure source is the pneumatic control corresponding to a start signal of the turbomachine, in particular the control air pressure of a pneumatic motor starter.
  • the isolation valve is controlled by one or the other of the two pressurized air sources, via a shuttle valve, whose two inlet doors are respectively connected to said two sources of pressure. pressurized air and the outlet door is connected to the isolation valve.
  • the isolation valve is a flapper valve provided with a bellows jack.
  • the invention finds a particularly suitable application when the turbomachine is a turboprop.
  • the isolation valve makes it particularly advantageous to isolate the oil reservoir on the one hand from the rest of the turboprop lubrication circuit and on the other hand from the rest of the lubrication circuit.
  • a turboprop reduction gearbox a turboprop reduction gearbox.
  • the figure 1 is a schematic view of the control system of a pneumatic valve closing the oil tank outlet in an aircraft engine, according to the present invention.
  • the system proposed according to the invention and represented on the figure 1 uses the pneumatic energy, for example that generated by the compressor 3 or that supplying the starter 8, to open an isolation valve 7 of the oil tank 1, closed at rest, ensuring both the protection of the circuit of oil in case of fire and an anti-siphon function.
  • the isolation valve 7 is advantageously a valve valve connected to a jack bellows, which ensures its tightness while minimizing friction.
  • the valve 7 is actuated either by the air pressure supplying the starter 9 or by that of the compressor 10, according to the position of a "shuttle" valve or incorporated 7A shuttle valve , which automatically selects the source of the highest pressure.
  • This shuttle valve has two input gates connected in this case respectively to the air pressure supplying the starter and that of the compressor and an output port connected to the isolation valve 7. A ball shuttle between the two seats corresponding to the two entrance doors, the seat corresponding to the highest pressure being free.
  • isolation valve 7 is open either when the engine is running or at the start. It is closed at rest or during a failure of the engine pressure in flight.
  • the shuttle valve 7A can be advantageously adjusted without bias or with a bias to pass the starting transients of the engine.
  • the isolation valve 7 closes as soon as there is no more air pressure, under the action of a return spring 7B.
  • the oil tank is put in communication with the equipment of the lubrication circuit of the engine 2, via the pipe 4A and the pump 4 and, via the pipe 6A and the pump 6, with the reduction box ( power gear box ) 5, which has in this case exposed its own lubrication circuit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
  • General Details Of Gearings (AREA)
EP06447130A 2006-12-21 2006-12-21 Vanne d'isolation du circuit d'huile dans un moteur d'avion Active EP1936122B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
AT06447130T ATE462063T1 (de) 2006-12-21 2006-12-21 Absperrventil für den ölkreislauf in einem flugzeugmotor
EP06447130A EP1936122B1 (fr) 2006-12-21 2006-12-21 Vanne d'isolation du circuit d'huile dans un moteur d'avion
ES06447130T ES2342317T3 (es) 2006-12-21 2006-12-21 Valvula de aislamiento del circuito de aceite en un motor de avion.
DE602006013168T DE602006013168D1 (de) 2006-12-21 2006-12-21 Absperrventil für den Ölkreislauf in einem Flugzeugmotor
US11/958,021 US8020664B2 (en) 2006-12-21 2007-12-17 Isolation valve for the oil circuit of an airplane engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06447130A EP1936122B1 (fr) 2006-12-21 2006-12-21 Vanne d'isolation du circuit d'huile dans un moteur d'avion

Publications (2)

Publication Number Publication Date
EP1936122A1 EP1936122A1 (fr) 2008-06-25
EP1936122B1 true EP1936122B1 (fr) 2010-03-24

Family

ID=37909850

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06447130A Active EP1936122B1 (fr) 2006-12-21 2006-12-21 Vanne d'isolation du circuit d'huile dans un moteur d'avion

Country Status (5)

Country Link
US (1) US8020664B2 (es)
EP (1) EP1936122B1 (es)
AT (1) ATE462063T1 (es)
DE (1) DE602006013168D1 (es)
ES (1) ES2342317T3 (es)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8602165B2 (en) 2008-09-18 2013-12-10 United Technologies Corporation Continuous supply fluid reservoir

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8356694B2 (en) * 2007-08-28 2013-01-22 Pratt & Whitney Recirculating lubrication system with sealed lubrication oil storage
EP2202387B1 (fr) * 2008-12-23 2012-08-22 Techspace Aero S.A. Vanne d'isolation du circuit d'huile sans commande dans un moteur d'avion
DE102011012863A1 (de) * 2011-03-03 2012-09-06 Rolls-Royce Deutschland Ltd & Co Kg Ölversorgungssystem für ein Flugtriebwerk
EP2801707B1 (fr) * 2013-05-10 2017-07-05 Safran Aero Boosters SA Circuit de lubrification de turbomachine avec vanne anti-siphon pour windmilling
WO2015076903A2 (en) 2013-09-13 2015-05-28 United Technologies Corporation Fan drive gear system auxiliary pump monitoring system
FR3019583B1 (fr) * 2014-04-08 2019-09-13 Safran Aircraft Engines Isolation d'un reservoir de fluide combustible relativement a une partie aval de systeme d'alimentation pour turbomachine en cas d'incendie
DE102015212030A1 (de) * 2015-06-29 2016-12-29 Skf Lubrication Systems Germany Gmbh Vorrichtung zur automatischen Bereitstellung von Schmiermittel
FR3039591B1 (fr) 2015-07-31 2017-08-25 Snecma Isolation d'un reservoir de turbomachine d'aeronef en cas d'incendie par fermeture d'une vanne sensible a la liberation d'un agent extincteur
FR3059718B1 (fr) * 2016-12-02 2019-06-21 Safran Aircraft Engines Dispositif hydromecanique de coupure a hysteresis pour systeme de lubrification de turbomachine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2688229A (en) * 1948-07-30 1954-09-07 Niles Bement Pond Co Fuel and speed control for internalcombustion engines
US2666490A (en) * 1950-05-03 1954-01-19 United Aircraft Corp Auxiliary drive for propeller pitch control
US4170873A (en) * 1977-07-20 1979-10-16 Avco Corporation Lubrication system
US4452037A (en) * 1982-04-16 1984-06-05 Avco Corporation Air purge system for gas turbine engine
US4531694A (en) * 1982-10-18 1985-07-30 Soloy Conversions, Ltd. Turbine engine drive and mounting assembly for fixed wing aircraft
DE3714990A1 (de) * 1987-05-06 1988-12-01 Mtu Muenchen Gmbh Propfan-turbotriebwerk
US7387189B2 (en) 2003-08-14 2008-06-17 United Technologies Corp. Emergency lubrication system
GB0422241D0 (en) * 2004-10-07 2004-11-10 Rolls Royce Plc Aeroengine oil tank fire protection system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8602165B2 (en) 2008-09-18 2013-12-10 United Technologies Corporation Continuous supply fluid reservoir
US8997935B2 (en) 2008-09-18 2015-04-07 United Technologies Corporation Continuous supply fluid reservoir

Also Published As

Publication number Publication date
US20080264726A1 (en) 2008-10-30
ATE462063T1 (de) 2010-04-15
ES2342317T3 (es) 2010-07-05
EP1936122A1 (fr) 2008-06-25
US8020664B2 (en) 2011-09-20
DE602006013168D1 (de) 2010-05-06

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