WO2013057553A1 - Aircraft hydraulic air bleed valve system - Google Patents
Aircraft hydraulic air bleed valve system Download PDFInfo
- Publication number
- WO2013057553A1 WO2013057553A1 PCT/IB2012/001993 IB2012001993W WO2013057553A1 WO 2013057553 A1 WO2013057553 A1 WO 2013057553A1 IB 2012001993 W IB2012001993 W IB 2012001993W WO 2013057553 A1 WO2013057553 A1 WO 2013057553A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- air
- aircraft
- signal
- bleed valve
- gyroscope
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K24/00—Devices, e.g. valves, for venting or aerating enclosures
- F16K24/04—Devices, e.g. valves, for venting or aerating enclosures for venting only
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
- F01D17/22—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical
- F01D17/26—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical fluid, e.g. hydraulic
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B21/00—Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
- F15B21/04—Special measures taken in connection with the properties of the fluid
- F15B21/044—Removal or measurement of undissolved gas, e.g. de-aeration, venting or bleeding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K24/00—Devices, e.g. valves, for venting or aerating enclosures
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0318—Processes
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0318—Processes
- Y10T137/0324—With control of flow by a condition or characteristic of a fluid
- Y10T137/0379—By fluid pressure
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/2931—Diverse fluid containing pressure systems
- Y10T137/3115—Gas pressure storage over or displacement of liquid
- Y10T137/3143—With liquid level responsive gas vent or whistle
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/7722—Line condition change responsive valves
- Y10T137/7758—Pilot or servo controlled
- Y10T137/7759—Responsive to change in rate of fluid flow
Definitions
- the exemplary aircraft hydraulic air bleed valve system relates, in general, to an air bleed valve and in particular to an aircraft hydraulic air bleed valve system that utilizes a gyroscope to determine when the aircraft is in a flight mode that is conducive to the bleeding of air from the hydraulic system and then permits the activation of an air vent valve.
- Air bleed valves are used in aircraft hydraulic systems to remove unwanted air from the hydraulic circuit prior to the operation of the high pressure hydraulic system to prevent unexpected and unwanted operational anomalies. Due to certain flight regimes, a traditional air bleed valve cannot be used in certain high performance aircraft, primarily those aircraft used in military applications. High G loads and inverted flight modes do not allow the air in the hydraulic system to be bled when experiencing these flight regimes. Therefore it is necessary to use sensors to determine when there is air in the hydraulic system and then electronically open an air vent valve to discharge the air when the aircraft is flying in a suitable flight mode. Traditional air bleed valves are usually bled when the pilot manually triggers the vent valve circuit.
- Sensors can be used in the air bleed valve such as a light emitting diode and a photoelectric diode to indicate that there is air in the hydraulic system and then send a signal to the pilot that the air vent in the air bleed valve needs to be activated.
- Pub. No. US 2010/0319791 Al to Dirkin et al. disclose such a system.
- the Dirkin system two LEDs and a phototransistor and three transparent windows are used to sense the presence of air. When air is detected by an electronic circuit which is connected to the phototransistor and the LEDs, a signal is sent to the flight deck so that the vent valve can be activated.
- This system is subject to several operational limitations involving clouding of the windows and failure of the phototransistor.
- CONFIRMATION COPY is not controlled by the flight crew or an electronic control system so the air is automatically vented whenever it is present irrespective of the aircraft flight mode. This presents a problem in high performance aircraft since the air cannot be vented in certain flight regimes. Also, this type of air bleed valve is not as reliable or dependable as what is needed in the industry for use in high performance aircraft.
- the exemplary electronically controlled air bleed valve system provides for a robust solution for bleeding air from a hydraulic system whenever the level of air in a reservoir exceeds a set level and the aircraft in which it is installed is in a flight mode that is conducive to the bleeding of air from a fluid reservoir in an accumulator or housing.
- the quantity of excess air in the housing is measured with the use of some type of fluid level sensor such as one that makes use of light emitting diodes and a photoelectric sensor.
- a gyroscope that includes a gyroscope control system is used to determine when the aircraft is in a proper orientation and flight regime for the activation of an air vent valve that is connected to the reservoir in the housing and opens upon receipt of an electrical command signal and vents the excess air outside of the housing and out of the aircraft hydraulic system.
- the exemplary air bleed valve system is particularly adaptable for use in aircraft in that the excess air can be sensed and then vented when the aircraft is in a suitable flight regime independent of the aircraft flight instruments.
- the exemplary system is mounted at the highest point where the air in the hydraulic system is collected and will bleed excess air even during flight so long as the aircraft is in a suitable flight regime or mode. " Thus, the system will bleed air at appropriate times and will not result in leakage of the hydraulic oil from a reservoir during flight.
- the gyroscope used in the exemplary air bleed system can be a standalone unit and electrically connected to the air vent valve controller or it can be physically integrated with the air vent controller in one package.
- the gyroscope can be any type of known gyroscope including what is known as a laser ring gyro so long as it can determine the aircraft orientation or flight mode to determine if the aircraft is in an orientation or flight mode that is suitable for the venting of the excess air from the aircraft hydraulic system.
- the gyroscope control system generates an electronic signal when the aircraft excess air can be vented and transmits this to another part of the system such as to an air vent valve controller.
- the gyroscope control system can simply send a signal representation of the aircraft's orientation or flight mode to another circuit or controller and that unit can determine if the aircraft is in an orientation and flight mode suitable for the venting of excess air.
- the air vent valve controller is electrically connected to the air vent valve and to the liquid level sensor in addition to the gyroscope control system.
- the liquid level sensor generates an electrical signal that represents the level of the hydraulic oil in the housing and hence, the quantity of excess air residing above the oil can be calculated. Once the excess air reaches a given quantity and the aircraft is in a suitable orientation and flight mode as determined by the gyroscope, then the air vent valve can be activated and the excess air is purged from the aircraft hydraulic system.
- FIG. 1 is a cross-sectional view of the exemplary aircraft air bleed valve system
- FIG. 2 is an alternative functional block diagram of the exemplary aircraft air bleed valve system
- FIG. 3 is a second alternative functional block diagram of the exemplary aircraft air bleed valve system.
- FIG. 1 of the drawings a cross-sectional view of the exemplary aircraft air bleed valve system 10 is shown.
- the air bleed valve system 10 includes an accumulator housing 12 which has a reservoir 24 for containing a quantity of hydraulic oil 22 and a varying quantity of excess air 30.
- a liquid level sensor 20 which is positioned to sense the level of the hydraulic oil 22 in the reservoir 24 and is electrically connected to an air bleed valve controller 14.
- the air vent valve 32 is vented outside of the housing 12 and can be opened and closed in response to an activation signal.
- the air vent valve 32 is also electrically connected to the air bleed valve controller 14.
- the air bleed valve controller 14 can be a separate electronic circuit or it can be integrated with the liquid level sensor 20.
- the liquid level sensor 20 can use a photoelectric sensor such as a phototransistor and light emitting diodes LEDs to measure the level of the hydraulic oil 22 within the reservoir 24.
- a photoelectric sensor such as a phototransistor and light emitting diodes LEDs
- other types of liquid level sensing systems can be used such as one the uses liquid contact sensors such as acoustic wave sensors. Since the volume of the reservoir 24 is known, the quantity of the excess air 30 can then be determined based on the measured level of the hydraulic oil 22 in the housing 12.
- a quantity of excess air 30 is shown residing above the hydraulic oil 22.
- the electronically activated air vent valve 32 is mounted to the top section of the reservoir 24 which remains closed until a signal is generated by the air bleed valve controller 14 to cause it to open. Upon opening, the air vent valve 32 vents the excess air 30 to the outside of the housing 12.
- the vent valve 32 can be a solenoid or a stepper motor or any other type of opening and closing valve whose state is electronically controlled.
- a gyroscope 16 is shown whose operation is electronically controlled by a gyroscope control system 18.
- the gyroscope 16 can be any type of know gyroscope system such as a laser ring gyroscope.
- the gyroscope 16 is used to determine the flight regime and orientation of the aircraft in which it resides and the gyroscope control system 18 generates this information and then transmits it to the air bleed valve controller 14 or processes it and generates a aircraft mode signal when the excess air can be bled from the aircraft by opening the air vent valve 32.
- the gyroscope control system 18 and the air bleed valve controller 14 and the liquid level sensor 20 electronics can be integrated into various packages or it can all be integrated into one package and connected to the aircraft electrical power supply.
- the operation of the exemplary aircraft air valve system 10 is electronically controlled according to the signals generated by the gyroscope control system 18 which generates an aircraft mode signal, and the liquid level sensor 20 which generates a liquid level signal.
- the air bleed valve controller 14 processes these signals and generates an activation signal that is sent to the air vent valve 32 when the excess air, if present in a sufficient quantity, can be vented out of the reservoir 24.
- the gyroscope control system 18 processes the signals generated by the gyroscope 16 and generates a separate aircraft mode signal that is transmitted to the air bleed valve controller 14.
- the aircraft mode signal can represent the orientation and flight mode of the aircraft or it can represent that the aircraft is in an orientation and flight mode of the aircraft that is suitable for the venting of the excess air 30 and the air vent valve 32 can be opened if there is sufficient excess air 30 present in the reservoir 24 as determined within the air bleed valve controller 14 using software algorithms.
- the quantity of the excess air 30 is determined either within the liquid level sensor 20 or within the air bleed valve controller 14.
- the exemplary air bleed system 10 provides for the automatic determination of the quantity of excess air 30 in the aircraft hydraulic system and then the automatic bleeding of that excess air 30 only when the aircraft is in a suitable orientation and flight mode.
- FIG. 2 of the drawings an alternative functional block diagram of the exemplary air bleed valve system 10 is shown.
- This functional block diagrams illustrates how the electronic software operates within the air bleed valve systems 10.
- This air valve bleed system 10' is mounted within an aircraft structure and controls the removal of excess air from the aircraft hydraulic system.
- An aircraft electrical power supply 40 is connected to the gyroscope 16 through the gyroscope control system 18 and provides electrical power to other circuits as well, such as the liquid level sensor 20 and the air bleed valve controller 14.
- the gyroscope 16 can be what is known as a laser ring gyroscope or any other type of electrically powered or otherwise powered device that can detect when the aircraft is in a flight regime that will allow for the venting of the excess air 30 out of the reservoir 24.
- the gyroscope control system 18 processes the signals generated by the gyroscope 16 and then generates either an aircraft signal that represents the orientation and/or flight mode of the aircraft that is sent to the air valve controller which is part of the liquid level sensor 20 or it can generate a aircraft signal that represents when the aircraft is in an orientation and flight mode that is conducive to the venting of the excess air 30.
- the liquid level sensor 20 generates a level signal that is transmitted to the air valve bleed controller 14. By knowing the level of the hydraulic fluid 22 in the reservoir 24, the quantity of excess air 30 can be calculated. If the quantity of excess air 30 exceeds a pre-determined level for a pre-determined length of time, and the aircraft is determined to be in a suitable orientation and flight mode, then the liquid level sensor 20 generates an activation signal that is sent to the air vent valve 32 to open it and allow the excess air to be vented outside of the aircraft hydraulic system.
- the gyroscope control system 18 can be physically attached to the gyroscope 16 or it can be located elsewhere in the aircraft and only electrically connected to the gyroscope 16. Likewise, the air bleed valve controller 14 can be separated out from the liquid level sensor 20 as shown in FIG. 1 and made a separate unit or it can be made a physical part of the gyroscope controller 18. The physical packaging of the electronics is up to the designer and offers extreme flexibility.
- FIG. 3 of the drawings a second alternative functional diagram of the exemplary aircraft air bleed system 10 is shown.
- This functional block diagram illustrates how the electronic software operates within the air bleed valve system 10.
- the aircraft electrical power supply 40 supplies electrical power to the liquid level sensor 20 and to the gyroscope 16 and to the gyroscope control system 18 and to the air bleed control system which is integrated into the liquid level sensor 20.
- the level of the hydraulic oil 22 in the reservoir 24 is measured by the liquid level sensor 20.
- the liquid level sensor 20 is shown having one or more LEDs that reflect off the top of the hydraulic oil and the amplitude of the reflected light is measured by a photo detector.
- the output of the photo detector is sent to a circuit that calculates the quantity of the excess air based on the level of the hydraulic oil and the volume of the reservoir 24. This level signal is then sent to the gyroscope system controller 18.
- the gyroscope system controller 18 interfaces with the gyroscope 16 and process the output of the gyroscope 16 to determine the orientation and flight mode of the aircraft.
- the gyroscope 16 operating in conjunction with the gyroscope control system 18 determines when the aircraft is in a suitable orientation and flight mode to permit the excess air to be safely vented out of the reservoir 24 through the air vent valve 32.
- the gyroscope control system 18 send an activation signal to the air vent valve 32 to cause it to open and vent the excess air 30 out of the aircraft hydraulic system.
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA 2850426 CA2850426A1 (en) | 2011-10-17 | 2012-10-09 | Aircraft hydraulic air bleed valve system |
CN201280050840.8A CN103890321A (en) | 2011-10-17 | 2012-10-09 | Aircraft hydraulic air bleed valve system |
BR112014009351A BR112014009351A2 (en) | 2011-10-17 | 2012-10-09 | air bleed valve system for an aircraft hydraulic system and method for bleeding excess air from an aircraft hydraulic system |
EP12787497.2A EP2769057A1 (en) | 2011-10-17 | 2012-10-09 | Aircraft hydraulic air bleed valve system |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/274,384 | 2011-10-17 | ||
US13/274,384 US8833695B2 (en) | 2011-10-17 | 2011-10-17 | Aircraft hydraulic air bleed valve system |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013057553A1 true WO2013057553A1 (en) | 2013-04-25 |
Family
ID=47189978
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/IB2012/001993 WO2013057553A1 (en) | 2011-10-17 | 2012-10-09 | Aircraft hydraulic air bleed valve system |
Country Status (6)
Country | Link |
---|---|
US (2) | US8833695B2 (en) |
EP (1) | EP2769057A1 (en) |
CN (1) | CN103890321A (en) |
BR (1) | BR112014009351A2 (en) |
CA (1) | CA2850426A1 (en) |
WO (1) | WO2013057553A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8833695B2 (en) * | 2011-10-17 | 2014-09-16 | Eaton Corporation | Aircraft hydraulic air bleed valve system |
US9904296B2 (en) * | 2014-04-01 | 2018-02-27 | Honeywell International Inc. | Controlling flow in a fluid distribution system |
WO2016138309A1 (en) | 2015-02-26 | 2016-09-01 | Eaton Corporation | Bleed valve arrangements; and methods |
US10563784B2 (en) | 2016-02-24 | 2020-02-18 | Eaton Intelligent Power Limited | Pressurized fluid system including an automatic bleed value arrangement; components; and, methods |
BE1026218B1 (en) * | 2018-04-19 | 2019-11-21 | Safran Aero Boosters S.A. | LEVEL MEASURING DEVICE FOR TURBOMACHINE OIL RESERVOIR |
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GB1092997A (en) * | 1965-02-24 | 1967-11-29 | British Aircraft Corp Ltd | Improvements relating to hydraulic servo systems |
US4204457A (en) * | 1976-12-30 | 1980-05-27 | Parker-Hannifin Corporation | Device for controlling hydraulic motors |
US4524793A (en) | 1983-10-14 | 1985-06-25 | Pall Corporation | Automatic reservoir bleed valve |
US4813446A (en) | 1987-04-06 | 1989-03-21 | Pall Corporation | Automatic pressurized reservoir bleed valve |
US20100319791A1 (en) | 2008-03-31 | 2010-12-23 | William Dirkin | Automotive air bleed valve for a closed hydraulic system |
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-
2011
- 2011-10-17 US US13/274,384 patent/US8833695B2/en active Active
-
2012
- 2012-10-09 CA CA 2850426 patent/CA2850426A1/en not_active Abandoned
- 2012-10-09 WO PCT/IB2012/001993 patent/WO2013057553A1/en active Application Filing
- 2012-10-09 BR BR112014009351A patent/BR112014009351A2/en not_active IP Right Cessation
- 2012-10-09 CN CN201280050840.8A patent/CN103890321A/en active Pending
- 2012-10-09 EP EP12787497.2A patent/EP2769057A1/en not_active Withdrawn
-
2014
- 2014-08-19 US US14/462,782 patent/US20140352791A1/en not_active Abandoned
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2451575A (en) * | 1946-02-20 | 1948-10-19 | Adel Prec Products Corp | Hydraulic selector valve |
GB1092997A (en) * | 1965-02-24 | 1967-11-29 | British Aircraft Corp Ltd | Improvements relating to hydraulic servo systems |
US4204457A (en) * | 1976-12-30 | 1980-05-27 | Parker-Hannifin Corporation | Device for controlling hydraulic motors |
US4524793A (en) | 1983-10-14 | 1985-06-25 | Pall Corporation | Automatic reservoir bleed valve |
US4813446A (en) | 1987-04-06 | 1989-03-21 | Pall Corporation | Automatic pressurized reservoir bleed valve |
US20100319791A1 (en) | 2008-03-31 | 2010-12-23 | William Dirkin | Automotive air bleed valve for a closed hydraulic system |
Also Published As
Publication number | Publication date |
---|---|
CA2850426A1 (en) | 2013-04-25 |
BR112014009351A2 (en) | 2017-04-18 |
US8833695B2 (en) | 2014-09-16 |
US20130092245A1 (en) | 2013-04-18 |
CN103890321A (en) | 2014-06-25 |
EP2769057A1 (en) | 2014-08-27 |
US20140352791A1 (en) | 2014-12-04 |
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