EP1936122A1 - Absperrventil für den Ölkreislauf in einem Flugzeugmotor - Google Patents

Absperrventil für den Ölkreislauf in einem Flugzeugmotor Download PDF

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Publication number
EP1936122A1
EP1936122A1 EP06447130A EP06447130A EP1936122A1 EP 1936122 A1 EP1936122 A1 EP 1936122A1 EP 06447130 A EP06447130 A EP 06447130A EP 06447130 A EP06447130 A EP 06447130A EP 1936122 A1 EP1936122 A1 EP 1936122A1
Authority
EP
European Patent Office
Prior art keywords
engine
isolation valve
valve
turbomachine
lubrication circuit
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
EP06447130A
Other languages
English (en)
French (fr)
Other versions
EP1936122B1 (de
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 DE602006013168T priority Critical patent/DE602006013168D1/de
Priority to ES06447130T priority patent/ES2342317T3/es
Priority to AT06447130T priority patent/ATE462063T1/de
Priority to EP06447130A priority patent/EP1936122B1/de
Priority to US11/958,021 priority patent/US8020664B2/en
Publication of EP1936122A1 publication Critical patent/EP1936122A1/de
Application granted granted Critical
Publication of EP1936122B1 publication Critical patent/EP1936122B1/de
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.
  • valves In aircraft engines, there are known valves 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 motor or the plane.
  • 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 isolation valve is pneumatically operated and is provided with a device allowing to automatically select as command from among two sources of air under pressure, that which is of higher pressure.
  • the first source of pressure is the air pressure coming from the compressor of the engine.
  • the second source of pressure is the pneumatic control corresponding to a start signal of the engine, 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 from the rest of the engine lubrication circuit and 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 bellows cylinder, 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 shuttle valve 7A, which makes it possible to automatically select 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 Absperrventil für den Ölkreislauf in einem Flugzeugmotor Active EP1936122B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE602006013168T DE602006013168D1 (de) 2006-12-21 2006-12-21 Absperrventil für den Ölkreislauf in einem Flugzeugmotor
ES06447130T ES2342317T3 (es) 2006-12-21 2006-12-21 Valvula de aislamiento del circuito de aceite en un motor de avion.
AT06447130T ATE462063T1 (de) 2006-12-21 2006-12-21 Absperrventil für den ölkreislauf in einem flugzeugmotor
EP06447130A EP1936122B1 (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 (de) 2006-12-21 2006-12-21 Absperrventil für den Ölkreislauf in einem Flugzeugmotor

Publications (2)

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

Family

ID=37909850

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06447130A Active EP1936122B1 (de) 2006-12-21 2006-12-21 Absperrventil für den Ölkreislauf in einem Flugzeugmotor

Country Status (5)

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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8181746B2 (en) * 2008-09-18 2012-05-22 United Technologies Corporation Continuous supply fluid reservoir
US8356694B2 (en) * 2007-08-28 2013-01-22 Pratt & Whitney Recirculating lubrication system with sealed lubrication oil storage
FR3019583A1 (fr) * 2014-04-08 2015-10-09 Snecma Isolation d'un reservoir de fluide combustible relativement a une partie aval de systeme d'alimentation pour turbomachine en cas d'incendie
US10760496B2 (en) 2015-07-31 2020-09-01 Safran Aircraft Engines Isolation of an aircraft turbo engine tank in case of a fire by closing a valve sensitive to the release of an extinguishing agent

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2202387B1 (de) * 2008-12-23 2012-08-22 Techspace Aero S.A. Absperrventil für steuerlosen Ölkreislauf in einem Flugzeugmotor
DE102011012863A1 (de) * 2011-03-03 2012-09-06 Rolls-Royce Deutschland Ltd & Co Kg Ölversorgungssystem für ein Flugtriebwerk
EP2801707B1 (de) * 2013-05-10 2017-07-05 Safran Aero Boosters SA Schmierkreislauf eines Turbotriebwerks mit Überlaufventil für Windmilling
EP3044438B1 (de) 2013-09-13 2018-07-04 United Technologies Corporation Überwachungssystem für schmierölhilfspumpe eines lüfterantriebssystems
DE102015212030A1 (de) * 2015-06-29 2016-12-29 Skf Lubrication Systems Germany Gmbh Vorrichtung zur automatischen Bereitstellung von Schmiermittel
FR3059718B1 (fr) * 2016-12-02 2019-06-21 Safran Aircraft Engines Dispositif hydromecanique de coupure a hysteresis pour systeme de lubrification de turbomachine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4170873A (en) * 1977-07-20 1979-10-16 Avco Corporation Lubrication system
EP1510658A2 (de) 2003-08-14 2005-03-02 United Technologies Corporation Notschmiersystem

Family Cites Families (6)

* 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
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
GB0422241D0 (en) * 2004-10-07 2004-11-10 Rolls Royce Plc Aeroengine oil tank fire protection system

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4170873A (en) * 1977-07-20 1979-10-16 Avco Corporation Lubrication system
EP1510658A2 (de) 2003-08-14 2005-03-02 United Technologies Corporation Notschmiersystem

Cited By (7)

* 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
US8181746B2 (en) * 2008-09-18 2012-05-22 United Technologies Corporation Continuous supply fluid reservoir
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
FR3019583A1 (fr) * 2014-04-08 2015-10-09 Snecma Isolation d'un reservoir de fluide combustible relativement a une partie aval de systeme d'alimentation pour turbomachine en cas d'incendie
WO2015155465A1 (fr) * 2014-04-08 2015-10-15 Snecma Procédé d'isolation d'un reservoir de fluide combustible relativement a une partie aval de systeme d'alimentation pour turbomachine en cas d'incendie et un tel syseme d'alimentation
US10760496B2 (en) 2015-07-31 2020-09-01 Safran Aircraft Engines Isolation of an aircraft turbo engine tank in case of a fire by closing a valve sensitive to the release of an extinguishing agent

Also Published As

Publication number Publication date
US20080264726A1 (en) 2008-10-30
ATE462063T1 (de) 2010-04-15
EP1936122B1 (de) 2010-03-24
US8020664B2 (en) 2011-09-20
ES2342317T3 (es) 2010-07-05
DE602006013168D1 (de) 2010-05-06

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