GB2174824A - Control systems for gas turbine engines - Google Patents
Control systems for gas turbine engines Download PDFInfo
- Publication number
- GB2174824A GB2174824A GB08511597A GB8511597A GB2174824A GB 2174824 A GB2174824 A GB 2174824A GB 08511597 A GB08511597 A GB 08511597A GB 8511597 A GB8511597 A GB 8511597A GB 2174824 A GB2174824 A GB 2174824A
- Authority
- GB
- United Kingdom
- Prior art keywords
- valve
- servo
- control
- control unit
- control valves
- 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
Links
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
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
-
- 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
- F15B13/00—Details of servomotor systems ; Valves for servomotor systems
- F15B13/02—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors
- F15B13/06—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with two or more servomotors
- F15B13/07—Fluid distribution or supply devices characterised by their adaptation to the control of servomotors for use with two or more servomotors in distinct sequence
Abstract
The invention simplifies arrangements for controlling on/off control valves (21 to 24) in a gas turbine engine by means of an electronic control unit (27) coupled to a fluid servo power system (31). Essentially, a servo valve (33) controlled by the electronic control unit (27) temporarily connects the servo power system (31) to a source (41) of high pressure air, thereby passing a pulse of high pressure air to a motor driven multiplex valve (35), which again is actuated by signals from the electronic control unit (27). The multiplex valve (35) is utilised to distribute each pressure pulse as it arrives to any one of a number of control valves (21 to 24) as designated by the electronic control unit (27). The pressure pulses operate the control valves into their 'on' or 'off' positions as the case may be, the control valves being of the latching type (Figure 3, not shown) so that each stays in the position to which a pressure pulse has driven it until the next pressure pulse arrives. <IMAGE>
Description
SPECIFICATION
Control systems for gas turbine engines
The present invention relates to control systems for gas turbine aeroengines in which operation of a plurality of control valves for aiding control and management of various systems in a gas turbine aeroengine is scheduled by means of the engine's electronic control unit which monitors and controls the overall operation of the engine.
On/off control valves of various sorts are increasingly used in modern gas turbine aeroengines to help control operation of the various systems comprising the engine. Such valves may, for example, control bleeding-off of air from one or more compressor stages to help combat surge in the airflow through the stages, and may also control circulation of compressed air from the compressor to the turbine for cooling purposes or for powering of pneumatically actuated mechanisms. In addition there could well be the need for one or more on/ off control valves to control oil or air flows to heat exchanger modules.
The present state-of-the-art practice is that each control valve is, say, pneumatically operated through its own solenoid/ type sevo valve by a compressed air servo supply, which is piped to the control valve through the solenoid-type servo valve. Each servo valve is connected to receive control signals from the engine's electronic control unit and when a control signal is received, the servo valve is actuated and compressed air is then passed to the control valve to operate it. The electronic control unit schedules operation of the control valves in accordance with information it receives from sensors concerning the condition of the engine and from manual inputs from the flight station.
Solenoid-type servo valves are heavy and quite expensive items of equipment for their size and it would be desireable if an aeroengine incorporating several control valves could be made lighter and less expensive by reducing the number of servo/ valves required.
The present invention achieves such a result by providing means whereby a single servo valve can operate all the control valves.
According to the present invention a control system for a gas turbine aeroengine comprises a plurality of control valves for controlling a plurality of systems in the aeroengine, and an electronic control unit adapted to schedule opening and closing of the control valves in accordance with data inputs to the electronic control unit, the control system further comprising fluid servo supply means for supplying fluid servo power to operate the control valves, the fluid servo supply means incorporating::
an electrically actuated servo-valve connected to a source of pressurised fluid and also connected to the electronic control control unit for receiving actuating signals therefrom, whereby upon receipt of an actuating signal the servo-valve temporarily connects said source of pressurised fluid to said fluid servo supply means thereby to input a pressure pulse to the fluid servo supply means for operating at least one of said control valves; and
an electrically actuated multiplexing valve having a single input port connected to the servo-valve, and a plurality of output ports, each output port being connected to at least one corresponding control valve, the multiplexing valve also being connected to receive actuating signals from the electronic control unit, whereby upon receipt of an actuating signal / which actuating signal designates a selected one of the output ports - the multiplexing valve connects at least one control valve corresponding to said selected output port to the servo valve to enable operation of the at least one control valve upon receipt of the pressure pulse, the control valves being of a latching type such that upon receipt of a pressure pulse they remain in the "on' state or the "of' state until receipt of a further pressure pulse.
Preferably, the control valves incorporate valve position sensor means connected to the electronic control unit to indicate to the unit whether the control valve is latched in the "of' state or the "on' state.
The fluid servo supply means is preferably of the pneumatic type, the source of pressurised fluid being the high pressure compressor of the engine, but alternatively the fluid servo supply means could be of the hydraulic type.
Embodiments of the invention will now be described by way of example only with reference to the accompanying drawings, in which:
Figure 1 schematically illustrates a prior art arrangement for controling control valves in a gas turbine aeroengine;
Figure 2 schematically illustrates an embodiment of the present invention; and
Figure 3 schematically illustrates a control valve of the latching type for use in the embodiment of
Figure 2.
Refering to Figure 1, there is shown an arrangement in which several control valves 1,2,3, etc., which control the operation of various subsystems in an aeroengine (not shown) are pneumatically operated by a pneumatic servo supply system 5 comprising solenoid actuated servo valves 7,8,9 connected by suitable piping 11, 12,13 to the control valves, each control valve being operated by means of its own servo valve in a one-to-one relationship. The servo valves 7,8,9 receive actuating signals from the engine's electronic control unit 15 and operate the control valves by connecting them to a source of high pressure compressed air 17, which conveniently is the high pressure compressor of the aeroengine.The control valves are selected for operation by the electronic control unit 15, which receives inputs of data 19 representing engine conditions and manual control settings in the aircraft's flight station, and by referring to a schedule of valve settings against engine conditions, decides which servo valve should be actuated to operate the corresponding control valve and thereby control operation of the aeroengine adequately.
Typical examples of systems controlled by the above-mentioned control valves are compressor air bleeds for combatting surge, distribution of compressor air for turbine cooling or turbine blade tip clearance control, and heat exchangers involving cooling of oil by means of fuel or air.
Referring now to Figure 2, there is shown the different arrangement of the invention. In it a number of control valves 21 to 24 etc., again control a variety of systems in the aeroengine (not shown).
As before, an electronic control unit 27 is programed to schedule opening and closing of the control valves in accordance with data inputs 29, actuai operation of the control valves being accomplished by a pneumatic servo supply system 31 which supplies pneumatic power to operate the control valves.
Besides the pneumatic connections in the form of pipes to transmit the pneumatic power, the pneumatic servo supply system 31 incorporates two main units, namely a solenoid actuated servo valve 33, which receives command signals on line 34 from electronic control unit 27, and a multiplexing valve 35 comprising fixed input and output sides 35a and b respectively, and a middle portion 35c which is rotatable relative to the input and output sides, being driven by a stepper motor 37 which in turin receives command signals on line 39 from the electronic control unit 27.
The servo valve 33 is connected to a source of compressed air 41 such as the high pressure compressor of the aeroengine, and upon receipt of an actuating command signal from the electronic control unit 27, its solenoid operates to temporarily connect the rest of the pneumatic servo supply system 31 to the source 41 of compressed air. The connection to the compressed air source 41 is temporary becuase the required inputs to the pneumatic servo supply system are pressure pulses for operating the control valves 21 to 24. Thus, when the solenoid of servo-valve 33 is actuated, the solenoid power circuit is switched off after a short time interval and a spring or other suitable mechanism immediateiy biasses the servo valve back to the "off' position.
The input side 35a of motor-driven multi-plexing valve 35 has a single input port which is connected via pipe 43 to the servo valve 33 for receipt of the pneumatic pressure pulses. The output side 35b of valve 35 has a number of output ports connected in one-to-one correspondence with the control valves 21 to 24 to convey the pressure pulses to them, though of course there is no reason why one output port could not be connected to two or more control valves if it is necessary or desireable to operate two such control valves simultaneously.
Upon receipt of an actuating command signal from the electronic control unit 27, the stepper motor 37 indexes the rotatable middle portion 35c of the multiplexing valve 35 round by an amount designated by the command signal so that drillings (not shown) in the rotatable portion connect the input port to a selected one of the output ports. In this way, a control valve corresponding to the selected output port is connected to the servo valve by the multiplexing valve to enable operation of the control valve by the pressure pulse. Of course, the electronic control unit ensures that the multiplexing valve is indexed by the stepping motor to connect the appropriate control valve to the servo valve before the servo valve is actuated to supply the pressure pulse.
In order to ensure satisfactory operation of control valves 21 to 24, it is preferable to provide a feed-back signal of their state ("on' or "off') to the electronic control unit so that if one fails to operate properly, the electronic control unit 27 could repeatedly actuate the servo-valve 33 to apply pressure pulses to the control valve in an effort to correct the situation. Such feedback is shown in
Figure 2, where the control valves are provided with position sensors such as microswitches or proximity capacitance switches 45 to 48 which complete a circuit when the control valves are in the "on' position, the resulting voltage signal being sent to the electronic control unit 27 on line 51.
Because the pneumatic servo supply system utilises pressure pulses to operate the control valves 21 to 24, rather than continuously applied pressure, the control valves 21 to 24 must be of the latching type, i.e. having been operated by a pressure pulse into the on or off position, they must remain in that position until operated again by a subsequent pressure pulse. A typical schematic design for such a control valve is shown in Figure 3, the valve in this particular case being used to control a compressor bleed system.
The control valve 21 of Figure 3 is a spool valve and is shown in the open position, in which the bleed air 61 from the compressor 63 of the aeroengine is allowed to exit through a slot 64 in compressor casing 65, past the end of the valve and out through an orifice 67 provided in a casing 69 containing the valve.
Valve 21 comprises a valve body 71, with a stepped axisymmetric internal bore 73, and a spool 75 with annular ribs 77 and 79 which cooperate with corresponding step surfaces 81,83 of stepped bore 73 to define three annular chambers 85 to 87.
Valve body 71 includes passages 91 to 94 and spool 75 includes passage 95 and 96 which by supplying air at various pressures to the annular chambers 85 to 87, enable the spool 75 to move axially to open or close orifice 67 in valve casing 69.
High pressure pulses from the pneumatic servo supply system 31 (Figure 2) are applied to operate the control valve 21 by mean of valve body passages 92 and 94, but in order to ensure that the valve spool 75 stays positively latched in the desired position after a pressure pulse has been removed, the valve is also supplied with air at a constant low pressure through valve body passages 91 and 93, this constant low pressure being much lower than the maximum value reached by the pressure pulses. Conveniently, the constant low pressure may be provided by a throttle offtake from the low pressure compressor of the aeroengine and the high pressure pulses may be supplied from the high pressure compressor. The pressure of bleed air 61 is intermediate the high pulse pressure and low constant pressure.
The spool 75 of valve 21 is latched in its open position by the spring force of a helical compression spring 99 acting between step surface C of bore 73 and surface A of rib 77 assisted by the axial force exerted on the spool due to the pressure in annular chamber 86 acting on the surface A of annular rib 77, chamber 86 receiving low pressure air from passage 91. The pressure in chamber 86 also acts on surface B of rib 79 to produce an axial force on the spool which is opposite to those acting on surface A of rib 77. However, the chamber 87 is also connected to the low pressure supply through passage 93, and therefore the pressure force on surface A of rib 79 cancels out that on surface B.
When a high pressure pulse arrives at the valve through passages 92 and 94, the outlet of passage 92 is obturated by rib 79, but the outlet of passage 94 communicates with chamber 85 through the passage 95 in the spool 75. Hence the pulse pressure in chamber 85 is high and the resulting impulsive axial force on surface B of rib 77 moves the spool quickly over towards the closed position. As the spool moves over to the closed position the rib 77 obturates the outlet of passage 91, the rib 79 opens the outlet of passage 92, and the passage 96 in the spool 75 communicates with chamber 85, causing it experience the pressure of compressor bleed air 61.By the time the spool 75 has moved to uncover passage 92, the high pressure pulse has died away, but the spool continues moving to positively engage with its seating 97 in valve casing 69 and seal off the flow of bleed air 61 because the bleed air pressure in chamber 85 acting on surface
B of rib 77 overcomes the spring force and the lower pressure in chamber 87 acting on surface A of rib 79. When the valve is closed, chamber 85 continues to experience bleed air pressure because of passages 96 in the base of valve body 75, and therefore while the engine continues operating the valve 21 remains latched in the closed position until the next high pressure pulse arrives through passages 92 and 94. When this occurs, passage 94 is obturated by the valve body 75, but passage 92 communicates with chamber 86 and the resulting high pulse pressure on surface A of rib 77, plus the force exerted by compression spring 99, result in the valve body 75 moving back to the latched open position shown in Figure 3.
Claims (6)
1. A control system for a gas turbine engine, comprising a plurality of control valves for controling a plurality of systems in the aeroengine, and an electronic control unit adapted to schedule opening and closing of the control valves in accordance with data inputs to the electronic control unit, the control system further comprising fluid servo supply means for supplying fluid servo power to operate the control valves, the fluid servo supply means incorporating::
an electrically actuated servo-valve connected to a source of pressurised fluid and also connected to the electronic control unit for receiving actuating signals therefrom, whereby upon receipt of an actuating signal the servo-valve temporarily connects said source of pressurised fluid to said fluid servo supply means thereby to input a pressure pulse to the fluid servo supply means for operating at least one of the control valves; and
an electrically actuated multiplexing valve having a single input port connected to the servo-valve, and a plurality of output ports, each output port being connected to at least one corresponding control valve, the multiplexing valve also being connected to receive actuating signals from the electronic control unit, whereby upon receipt of an actuating signal - which actuating signal designates a selected one of the output ports - the multi/ plexing valve connects at least one control valve, corresponding to said selected output port, to the servo-valve to enable operation of the at least one control valve upon receipt of the pressure pulse, the control valves being of a latching type such that upon receipt of a pressure pulse they remain in the position to which they are driven by the pressure pulse until receipt of a further pressure pulse.
2. A control system according to claim 1 in which the control valves incorporate valve position sensor means connected to the electronic control unit to indicate to the unit in what position each control valve is latched.
3. A control system according to claim 1 or claim 2 in which the fluid servo supply means is of the pneumatic type.
4. A control system according to claim 3 in which the source of pressurised fluid is the high pressure compressor of the engine.
5. A control system for a gas turbine engine substantially as described in this specification with reference to and as illustrated by Figure 2 of the accompanying drawings.
6. A control system for a gas turbine engine substantially as described in this specification and incorporating a latching control valve substantially as described in this specification with reference to and as illustrated by Figure 3 of the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8511597A GB2174824B (en) | 1985-05-08 | 1985-05-08 | Control systems for gas turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8511597A GB2174824B (en) | 1985-05-08 | 1985-05-08 | Control systems for gas turbine engines |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8511597D0 GB8511597D0 (en) | 1985-06-12 |
| GB2174824A true GB2174824A (en) | 1986-11-12 |
| GB2174824B GB2174824B (en) | 1989-07-19 |
Family
ID=10578784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8511597A Expired GB2174824B (en) | 1985-05-08 | 1985-05-08 | Control systems for gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2174824B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0329477A1 (en) * | 1988-02-17 | 1989-08-23 | General Electric Company | Fluidic multiplexer |
| EP0375372A1 (en) * | 1988-12-19 | 1990-06-27 | Woodward Governor Company | Multiplexed hydraulic control systems |
| EP0380234A1 (en) * | 1989-01-23 | 1990-08-01 | Woodward Governor Company | Multiplexed control systems |
| EP0381361A1 (en) * | 1989-02-01 | 1990-08-08 | Woodward Governor Company | Multiplex control systems |
| EP0410811A2 (en) * | 1989-07-28 | 1991-01-30 | Woodward Governor Company | Hydraulic control system |
| EP0437111A2 (en) * | 1990-01-09 | 1991-07-17 | Woodward Governor Company | Multiplexed hydraulic control systems |
| EP0438925A2 (en) * | 1990-01-22 | 1991-07-31 | Woodward Governor Company | Multiplexed hydraulic control systems |
| US5048394A (en) * | 1989-07-28 | 1991-09-17 | Woodward Governor Company | Multiplexed hydraulic control system with oscillator for multiplexer drive |
| GB2248887A (en) * | 1990-08-22 | 1992-04-22 | Gen Electric | Fluidic multtplexer. |
| FR2698919A1 (en) * | 1992-12-03 | 1994-06-10 | Le Gall Philippe | Control of hydraulic receivers e.g. in agricultural and construction equipment - using distributor having two slide valves, oil flow detector, oil switching unit and control buttons |
| EP0644336A1 (en) * | 1993-09-18 | 1995-03-22 | Lucas Industries Public Limited Company | Multiplexing valve |
| US5996464A (en) * | 1998-12-07 | 1999-12-07 | Woodward Governor Company | Fail safe valve and multiplexed fluid control systems incorporating the same |
| US6158208A (en) * | 1998-12-04 | 2000-12-12 | Woodward Governor Company | Multiplexed fluid control system with pressure transducer feedback |
| US6186045B1 (en) | 1998-12-07 | 2001-02-13 | Woodward Governor Company | Latching valve and a multiplexed hydraulic control system utilizing same |
| EP1688625A1 (en) * | 2005-02-04 | 2006-08-09 | Hispano-Suiza | Control system for a plurality of relief valves of a turbomachine |
| US10094288B2 (en) | 2012-07-24 | 2018-10-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine volute attachment for a gas turbine engine |
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| BRPI1007723A2 (en) | 2009-05-12 | 2018-03-06 | Icr Turbine Engine Corp | gas turbine storage and conversion system |
| WO2011109514A1 (en) | 2010-03-02 | 2011-09-09 | Icr Turbine Engine Corporatin | Dispatchable power from a renewable energy facility |
| US8984895B2 (en) | 2010-07-09 | 2015-03-24 | Icr Turbine Engine Corporation | Metallic ceramic spool for a gas turbine engine |
| WO2012031297A2 (en) | 2010-09-03 | 2012-03-08 | Icr Turbine Engine Corporation | Gas turbine engine configurations |
| US9051873B2 (en) | 2011-05-20 | 2015-06-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine shaft attachment |
-
1985
- 1985-05-08 GB GB8511597A patent/GB2174824B/en not_active Expired
Cited By (30)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0329477A1 (en) * | 1988-02-17 | 1989-08-23 | General Electric Company | Fluidic multiplexer |
| US5090194A (en) * | 1988-02-17 | 1992-02-25 | General Electric Company | Fluidic multiplexer for fluid servomotors in a gas turbine engine |
| EP0375372A1 (en) * | 1988-12-19 | 1990-06-27 | Woodward Governor Company | Multiplexed hydraulic control systems |
| JP2833812B2 (en) | 1989-01-23 | 1998-12-09 | ウッドワード・ガバナー・カンパニー | Liquid flow control device |
| EP0380234A1 (en) * | 1989-01-23 | 1990-08-01 | Woodward Governor Company | Multiplexed control systems |
| JPH02238133A (en) * | 1989-01-23 | 1990-09-20 | Woodward Governor Co | Liquid flow control device |
| EP0381361A1 (en) * | 1989-02-01 | 1990-08-08 | Woodward Governor Company | Multiplex control systems |
| EP0410811A3 (en) * | 1989-07-28 | 1991-05-29 | Woodward Governor Company | Hydraulic control system |
| EP0410811A2 (en) * | 1989-07-28 | 1991-01-30 | Woodward Governor Company | Hydraulic control system |
| US5048394A (en) * | 1989-07-28 | 1991-09-17 | Woodward Governor Company | Multiplexed hydraulic control system with oscillator for multiplexer drive |
| US5054369A (en) * | 1989-07-28 | 1991-10-08 | Woodward Governor Company | Multiplexed hydraulic control system with plural selector valves |
| EP0437111A2 (en) * | 1990-01-09 | 1991-07-17 | Woodward Governor Company | Multiplexed hydraulic control systems |
| EP0437111A3 (en) * | 1990-01-09 | 1991-08-21 | Woodward Governor Company | Multiplexed hydraulic control systems |
| US5081903A (en) * | 1990-01-09 | 1992-01-21 | Woodward Governor Company | Multiplexed hydraulic control system with multi-bit binary selector signal control |
| US5088383A (en) * | 1990-01-22 | 1992-02-18 | Woodward Governor Company | Multiplexed hydraulic control system with multiplexing valve having planar port array |
| EP0438925A3 (en) * | 1990-01-22 | 1991-08-14 | Woodward Governor Company | Multiplexed hydraulic control systems |
| EP0438925A2 (en) * | 1990-01-22 | 1991-07-31 | Woodward Governor Company | Multiplexed hydraulic control systems |
| GB2248887A (en) * | 1990-08-22 | 1992-04-22 | Gen Electric | Fluidic multtplexer. |
| US5353685A (en) * | 1990-08-22 | 1994-10-11 | General Electric Company | Redundant fluidic multiplexer |
| GB2248887B (en) * | 1990-08-22 | 1994-12-14 | Gen Electric | Fluidic multiplexer |
| FR2698919A1 (en) * | 1992-12-03 | 1994-06-10 | Le Gall Philippe | Control of hydraulic receivers e.g. in agricultural and construction equipment - using distributor having two slide valves, oil flow detector, oil switching unit and control buttons |
| US5570718A (en) * | 1993-09-18 | 1996-11-05 | Lucas Industries Public Limited Company | Multiplexing valve |
| EP0644336A1 (en) * | 1993-09-18 | 1995-03-22 | Lucas Industries Public Limited Company | Multiplexing valve |
| US6158208A (en) * | 1998-12-04 | 2000-12-12 | Woodward Governor Company | Multiplexed fluid control system with pressure transducer feedback |
| US5996464A (en) * | 1998-12-07 | 1999-12-07 | Woodward Governor Company | Fail safe valve and multiplexed fluid control systems incorporating the same |
| US6186045B1 (en) | 1998-12-07 | 2001-02-13 | Woodward Governor Company | Latching valve and a multiplexed hydraulic control system utilizing same |
| EP1688625A1 (en) * | 2005-02-04 | 2006-08-09 | Hispano-Suiza | Control system for a plurality of relief valves of a turbomachine |
| FR2881800A1 (en) * | 2005-02-04 | 2006-08-11 | Hispano Suiza Sa | SYSTEM FOR CONTROLLING A PLURALITY OF DISCHARGE VALVES OF A TURBOMACHINE |
| US7946310B2 (en) | 2005-02-04 | 2011-05-24 | Snecma | System for controlling a plurality of turbomachine discharge valves |
| US10094288B2 (en) | 2012-07-24 | 2018-10-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine volute attachment for a gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2174824B (en) | 1989-07-19 |
| GB8511597D0 (en) | 1985-06-12 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19920508 |