CN1234849A

CN1234849A - Axisymmetric vectoring nozzle actuating system having multiple power control circuits

Info

Publication number: CN1234849A
Application number: CN 96180470
Authority: CN
Inventors: R·M·奥斯登莫尔
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 1996-10-16
Filing date: 1996-10-16
Publication date: 1999-11-10
Anticipated expiration: 2016-10-16
Also published as: CN1080375C

Abstract

A failsafe nozzle actuating system for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle has a vectoring ring operably linked to a plurality of pivotal flaps which are circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle. The failsafe nozzle actuating system has at least two independently operable first and second vertoring actuating systems including first and second groups of actuators operably connected to the vectoring ring and first and second failsafe control means to control power to the first and second groups of actuators, respectively. The first group of vectoring actuators is interdigitated with the second group of second vectoring actuators around the nozzle. Either of the two groups of actuators are operable to actuate the nozzle when the other group is failsafed.

Description

Axisymmetric vectoring nozzle actuating system with multiple power control circuits

The present invention relates generally to the directed ejector exhaust pipe of combustion gas turbine axisymmetric, relates in particular to the actuating system of these motors of the many power loops with control verge ring.

Military aircraft Designer and engineers constantly make great efforts to improve aircraft with respect to the mobility of combat mission and complicated ground strike mission air to air.They have improved thrust orientation jet pipe, and these jet pipes rotate blast airs or make blast air and drive the thrust orientation of the combustion gas turbine of aircraft, to replace or to promote application such as the conventional aerodynamic force surface of hinged joint and aileron.A kind of new improved thrust orientation jet pipe be a kind of by Hauer at US4, disclosed axisymmetric vector ejector exhaust pipe is here quoted as a reference in 994,660.The directed ejector exhaust pipe of this axisymmetric is by some the expansion hinged joints with universal this jet pipe of rotation of asymmetric manner, in other words, radially and tangentially rotate these expansion hinged joints with respect to this not directed jet pipe center line, a kind of device in order to orientation axes symmetry contraction/distension jet pipe thrust is provided.These hinged joints rotate by a verge ring, and the latter can and be equipped with universal joint or cross a limited scope (making its attitude obtain levelling basically) around its level and vertical shaft string pendulum by axial displacement.

Directed ejector exhaust pipe of this axisymmetric and relatively more conventional combustion gas turbine ejector exhaust pipe be the same also to comprise major and minor exhaust hinged joint, and they are provided to limit a variable area and shrink one and expand ejector exhaust pipe.This ejector exhaust pipe generally is axisymmetric or ring, and this blast air is with main hinged joint or shrink the hinged joint sealing upward to this nozzle throat, then with secondary hinged joint or the sealing of expansion hinged joint.These expand hinged joint, for example, have one to limit the rear end that the front end of throat of minimum flow area and have the big flow area that limits an expanding nozzle that extends downstream from this throat.These expansion hinged joints are variable, this means that the space between these expansion hinged joints must increase when they move on in radial location from the small radii position.Therefore, the ejector exhaust pipe seal arrangement will suitably be fixed between the adjacent expansion hinged joint, with the sealing blast air, and prevents that blast air from leaking between the expansion hinged joint.

Orientation nozzle, especially axisymmetric directed ejector exhaust pipe in disclosed here provides orientable expansion hinged joint in the Hauer documents.These expansion hinged joints not only can be located symmetrically with respect to the vertical center line of this ejector exhaust pipe, and can asymmetricly locate, to reach pitching and the orientation of vacillating now to the left, now to the right.At US4, the directed ejector exhaust pipe of disclosed axisymmetric adopts three directed actuator moving and to swing a verge ring in 994,660 by Hauer, the latter again on some predetermined positions to this expansion hinged joint application of force.This verge ring pivot angle and swaying direction have been established the orientation angle and the orientation direction of this jet pipe respectively.Moving axially of verge ring is that a given throat area (often being called A8) has been stipulated discharge area (being commonly referred to A9).

Modern many missions aircraft adopts such as the GE110 motor, and it has the contraction/distension jet pipe to satisfy action need.Contraction/distension jet pipe flowing relation in order has a shrinking zone, a throat and an expansion regions.Its characteristics are that these jet pipes adopt the variable area device in its throat and outlet.This just provides a kind of device that keeps desirable outlet and throat opening area ratio, and this allows to control effectively the operation of jet pipe again.The purpose of operation jet pipe is to provide one with respect to engine design optimized nozzle exit/throat opening area (A9/A8) scope that circulates, and tackles low subsonic speed in theory and high supersonic speed situation provides effective control.This class jet pipe generally adopts pneumatic or hydraulic actuator provides variable operation.Usually, outlet and throat opening area are pressed the mutual mechanical engagement of this sample loading mode, to set up an area as nozzle throat area (A8) function than (A9/A8).Generally capable nozzle exit area and the throat opening area independently controlled of thrust orientation jet pipe, this allows motor can obtain higher performance standard in its broad operating range.

During engine running and aircraft flight, because such as unit failure that causes because of fight or damage, the hydraulic actuation system of jet pipe is malfunctioning in may the one or more operating modes in several operating modes.This fault may be mechanical failure or control system fault, and it is generally detected by flight-control computer and/or the targeted electronic controller that is used as the thrust orientation jet pipe.This jet pipe actuating system has been provided with the hydraulic failure protective position, and it utilizes the verge ring actuator to withdraw fully and under the situation of verge ring, jet pipe is set in a fixing not directed position, and like this, the thrust of motor is not directed.These directed actuator also are used to control A9.Yet resultant jet pipe geometrical shape has very big area than (A9/A8), has hindered unlatching A8, thereby has hindered the work of augmentor, therefore, is not best on aerodynamics.This fail safe system is bad in fight.This large size is than the exhaust plume in the jet pipe expansion regions is separated.Especially this blast air can cause a kind of directive force unintentionally to be interrupted to separate and regroup with respect to the asymmetric pattern of engine centerline.The enlarged portion of complete opening jet pipe causes very different jet pipe kinologys, and can badly damaged jet pipe than opening this nozzle throat with high like this area.Can not open nozzle throat, when under the ground feelings are changed a job condition and by the afterburner pattern, working, the proper functioning that has hindered motor, this can make the operation of aircraft depart from normal state.

These shortcomings are that the serial number by 29 applications September in 1994 is 08/314; 124 U.S. Patent application overcomes; it discloses the fail safe mechanism that jet pipe is shaped rapidly with secure mode of operation this patent application; like this; this fail safe system can be with the adverse effect work to the whole operation minimum of aircraft and motor thereof, especially during fighting.Yet this jet pipe no longer can make thrust orientation, and this is a significant disadvantages between the fight operational period.

The distinct disadvantage of an inherence of three actuator schemes is with respect to a given inner loop size, has big span between any two actuator.The deflection of beam theory engineering science regulation simply supported beam is directly proportional with the first power of load, is directly proportional with the cube of span, is inversely proportional to rigidity.In other words, for given load and rigidity, if span doubles, then the deflection meeting increases by 8 times (23).Three actuator schemes of orientation nozzle form the longest possible span between two actuator, therefore, need the rigidity of maximum possible, thereby cause heavy pair to make rotating ring, so that between with the directional pattern operational period, keep a given acceptable minimum deflection value.

The deflection of making rotating ring is undesirable, because it can make the augmentation system of orientation nozzle towards the unloading of nondirectional state, thereby reduces directional properties.Make the cross section maximization, and the load path of utilizing internal-rib control to disperse, as described in the PCTWO98/20245 of bulletin on May 14th, 1998, can reduce deflection.Another latent defect of three actuator schemes of orientation nozzle system is that the fault of actuating system can have a negative impact to aircraft flight.Three actuator are that minimum this inner loop of maintenance that needs is at a fixed position and pivot angle.If an actuator breaks down (for example, hydraulic fault), should the ring swing will be no longer restricted this moment, and a kind of uncontrolled exhaust location may occur.The appearance of this situation is extremely undesirable.

Increase preventive measure, verge ring actuating system rate of breakdown can be reduced to the level of a practicality, be included in the parts that repeat are installed in the structure, like this, any one unit failure can not cause the malfunctioning of whole actuating system.These preventive measure have increased the cost of this system, complexity and weight.The another kind of method that prevents verge ring actuating system fault is to adopt the reaction measure to come the generation of control fault, and it can comprise that increasing parts comes detection failure, then on one's own initiative with this loop mapping to one fail safe position.All these schemes all make this system increase cost.Complexity and weight, they are all felt relieved the swing of inner loop on the neutral position, eliminate all capacity of orientation of directed ejector exhaust pipe system whereby.If aircraft system wants to utilize thrust orientation to take off or land as short distance, as the runway or the operation of aircraft airplane carrier that damage because of fight or may need under the fight state like that, eliminating this capacity of orientation so is to be harmful to especially.Therefore, the utmost point wishes to have the directed ejector exhaust pipe of a kind of axisymmetric, and it has a hydraulic failure protective system, makes the load minimum that is added on the verge ring, provides control to the nozzle outlet/throat opening area that is in the fail safe pattern than (A9/A8).And in one embodiment, when in this actuating system, certain fault occurring, can make this jet pipe, and can not cause the malfunctioning of whole actuating system thrust orientation.

The invention provides the fail safe jet pipe actuating system of the directed ejector exhaust pipe of a kind of aircraft combustion gas turbine axisymmetric; this jet pipe has a verge ring, operationally is connected in somely to be configured in around the jet pipe center line and to define the rotation hinged joint of grate flow channel in the jet pipe along circumference.This fail safe jet pipe actuating system has the first fail safe control gear of being defeated by first group of actuator power with the first directed actuating system of first group of actuator that operationally is connected in this verge ring and control.Operationally be connected in the actuator second directed actuating system of verge ring and the second fail safe control gear that second group of actuator power is defeated by in control with second group in addition.First group of actuator becomes interlaced arrangement with jet pipe second group of actuator on every side.

This preferential embodiment provides two groups of actuator and two corresponding directed actuating systems, and one group of three fail safe actuator respectively arranged.Yet, the present invention includes and adopt two or more actuator, and have two or more corresponding directed actuating systems.The preferential embodiment of this fail safe jet pipe actuating system is hydraulically powered.

One more specifically embodiment single hydraulic power supply is provided, get the oil hydraulic pump form that motor is installed and drive, can become hydraulic power supply to be communicated with operation with each group and the corresponding fail safe control gear in first and second groups of actuator.Perhaps adopt two oil hydraulic pumps of being installed and being driven by motor, as first and second hydraulic power supplies, they only become corresponding hydraulic power supply to be communicated with respectively with one of first and second groups of actuator and corresponding fail safe control gear separately.One in this two pump also can be an aircraft hydraulic pumps, and it also is used to provide power to plane hydraulic system.Perhaps, can be with aircraft two oil hydraulic pumps as first and second hydraulic power supplies, they only become corresponding hydraulic power supply to be communicated with respectively with one of first and second groups of actuator and corresponding abating protection device separately.

Another embodiment of the present invention provides two groups of actuator and two groups of corresponding directed actuating systems, and one group of two fail safe actuator respectively arranged.Yet this embodiment does not provide thrust orientation to jet pipe in the fail safe pattern, and provides nozzle exit/throat opening area to control than (A9/A8).

A more special embodiment provides the control system of a kind of monitoring hydraulic pressure signal of each parts in comprising the actuating system of this control system; and comprise a fail safe pattern actuator; when this control system when these parts detect a dropout (a significant predetermined hydraulic pressure is fallen), carry out the fail safe pattern.Signal occurrence device can be one or more in following: flight-control computer, targeted electronic controller and hydraulic control switch.

The invention provides advantage with respect to previous nozzle structure; its means are to provide the ability of the thrust orientation jet pipe being taken to the fail safe pattern according to the trouble or failure signal in the jet pipe hydraulic actuation system that does not completely lose the thrust orientation ability; under the fight state; this is a particular importance, and makes the load that is added on the verge ring reduce to minimum.The present invention also provides the nozzle exit/throat opening area when the thrust orientation jet pipe places the fail safe pattern to control than (A9/A8).

It is believed that it is that the features of novelty of feature of the present invention is limited in claims.Together with accompanying drawing, illustrate in greater detail the present invention and other purpose and advantage, wherein:

Fig. 1 is the perspective view that has the directed ejector exhaust pipe of axisymmetric of a fail safe jet pipe actuating system according to one embodiment of the present of invention;

Fig. 2 is the actuator of fail safe jet pipe actuating system in the depiction 1 and the perspective illustration of verge ring position;

Fig. 3 is the schematic representation according to the actuating system of one embodiment of the invention;

Fig. 4 is the schematic representation according to the actuating system of another embodiment of the present invention;

Fig. 5 has a motor and has sectional elevation by the aircraft of the orientation nozzle of the fail safe actuating system of one embodiment of the present of invention.

In the one embodiment of the present of invention shown in Fig. 1 are maintenance jet pipe actuating systems that lost efficacy of the axisymmetric thrust orientation jet pipe 14 in aircraft gas turbine engine (the not whole expression) exhaust component 10, totally by 2 expressions.Exhaust component 10 is included in scorching hot blast air 4 in the grate flow channel, it roughly along circumference be configured in engine centerline 8 around, and flowing relation comprises a fixed-area conduit or engine housing 11 in order, the latter comprises the variable area catchment 13 of contraction/distension profile shaft symmetry thrust orientation jet pipe 14 of an after-burning lining 12, and this thrust orientation jet pipe 14 is analogous to the sort of in the Hauer patent of quoting previously.With reference to Fig. 1, jet pipe 14 flowing relation in order comprises a shrinking zone 34, one throats 40 and expansion regions 48.Shrinking zone 34 comprises some contractions or main hinged joint 50, be configured in engine centerline 8 along circumference around, overlapping with the main sealing device 51 that is configured in therebetween, the latter becomes sealing engagement with radially inner surface at the contiguous main hinged joint 50 of circumferencial direction.Each main hinged joint 50 usefulness, first pivot connector or shackle link 52 are fixed in housing 11 with its front end by the swing mode.Each is expanded hinged joint 54 usefulness, one common two degrees of freedom (2 DOF) joint 56 and is connected in the main hinged joint rear end 53 that is close to main hinged joint 50 downstreams with its front end 53 by rotation mode, and joint 56 roughly is on the axial position of jet pipe 14, overlaps with throat 40.Expansion is around hinged joint 54 roughly is configured in engine centerline 8 along circumference, and is overlapping with the auxiliary or expansion seal arrangement 55 that is configured in therebetween, the latter and contiguous in a circumferential direction expansion hinged joint 54 radially to internal surface or sealing engagement.Work as nozzle exit pressure, hinged joint and seal arrangement radially to internal pressure usually greater than the jet pipe external pressure, when promptly general ambient atmosphere pressure or nozzle entry pressure, at the jet pipe duration of work, expansion seal arrangement 55 is used for sealing expansion hinged joint 54.There is a throat area in throat 40, uses the A8 mark usually, and nozzle exit 44 is in the end of expansion hinged joint 54 usually, and a discharge area is arranged, and uses the A9 mark usually.

Some cam bawls 62 are configured in the main ring 66, and main ring is moved forward and backward by some first jet pipe actuator 70 again, in this preferential embodiment, 4 actuator are arranged.Variable throat area A 8 is controlled by the action of the cam bawl 62 on the camming surface 60, and camming surface 60 forms on the back side of main hinged joint 50.During operation, the exhaust high pressure in the jet pipe forces main hinged joint 50 and expansion hinged joint 54 radially outwards, thereby makes one in camming surface 60 and the cam bawl 62 to keep in touch.One conical ring executor support 76 is installed on the engine housing 11 with its narrow front end, and the first jet pipe actuator 70 is rotatably connected to the wide rear end of executor support 76 by a spherical joint 74.The first jet pipe actuator 70 has an actuator bar 73, and the latter is connected in main ring 66 through spherical joint 68 again.

First group the first directed actuator 90A has 3 actuator 90A in this preferential embodiment, along the circumference equal angles be configured in around the shell 11, and be installed on the executor support 76 through spherical joint 94 in the mode identical with the first jet pipe actuator 70.Second group the second directed actuator 90B, three actuator 90B are arranged in this preferential embodiment, along the circumference equal angles be configured in around the shell 11, staggered with first group the first directed actuator 90A, be installed on the executor support 76 through spherical joint 94 in the mode identical with the first jet pipe actuator 70.First and second groups of directed

actuator

90A and 90B stagger the angle A of being separated by respectively each other between all first and second adjacent directed actuator 90A and 90B.In the exemplary embodiment of the present invention shown in these figure, three first directed actuator 90A and three second directed actuator 90B are arranged, angle A is 60 °.Verge ring 86 is connected in first and second directed actuator 90A and the 90B through a spherical joint 96 respectively with the rear end of the directed operating bar 93 of each directed actuator.This moves axially and around the rotation of center line 8, so that control its attitude and moving axially along engine centerline 8 thereof for verge ring 86 provides.The location and the rotation of verge ring 86 control expansion hinged joints 54.Expansion hinged joint 54 usefulness two degrees of freedom ordinary couplings devices 56 are connected in main hinged joint 50 rotationally, and control rotationally in multivariant mode by some corresponding Y shape framework 59, Y shape framework has

control arm

58a and 58b, and they operationally are connected in expansion hinged joint 54 with verge ring 86.Other hinged joint 64 is supported by Y shape framework 59 at least in part, and along the fairshaped smooth aerodynamic appearance of the outside formation of jet pipe.

Control arm

58a and 58b are connected in verge ring 86 with three degree of freedom spherical joint 82, and are connected in the rear end of expansion hinged joint 54 with a spherical joint 84.This connection the attitude change transitions of verge ring 86 can be become the multi-freedom degree of expansion hinged joint 54 to rotate variation and track moves, and whereby, each expands hinged joint can turn over different angles.The employing that connects the spherical joint 82 of

control arm

58a and 58b provides the rotation of the shackle link type of Y shape framework 59, prevents that simultaneously any torsional load that may pass to control

arm

58a and 58b from transferring back to positioning ring 86.Backbone 92 serves as that diffusion hinged joint 54 provides pillar with its two ends, and provides supporting for

joint

84 and 56.

Thrust orientation jet pipe utilization expansion hinged joint 54 and seal arrangement 55 be with respect to center line 8 axisymmetric location, thus make expansion hinged joint and seal arrangement radially locate directional thrust with location about and attitude axisymmetric.Verge ring 86 is moved by three first directed actuator 90A and three second directed actuator 90B and around the 8 universal rotations of jet pipe center line, these actuator concerted actions are with directed this thrust and move this verge ring and regulate and/or control variable discharge area A9, and set discharge area and throat opening area compares A9/A8.This variable-throat area A 8 can be come mobile main ring 66 and independent the setting by first actuator 70, and then sets discharge area and compare A9/A8 with throat opening area.

Perhaps, mix to adopt actuator group and ring to organize to set discharge area and compare A9/A8 with throat opening area.In case of emergency; when start system 2 is set at the fail safe pattern; first group of first directed actuator 90A or second group of second directed actuator 90b can be operated and other be subjected to fail safe the time, arbitrary group by moving it or it can be used to driving ring 86 around center line 8 universal rotations along center line 8.This actuating system 2 comprises an electronic controller, and it can be the part of an independent assembly or targeted electronic controller VEC.The invention provides fail safe jet pipe actuating system 2, have 2 first and second directed

actuating system

2A and 2B of control separately respectively.The first directed actuating system 2A only controls first group of first directed actuator 90A, and the second directed actuating system 2B only controls second group of second directed actuator 90B.

Shown in Fig. 2 is the distribution of the first directed actuator 90A; be staggered around jet pipe with second group of second directed actuator 90B; represent that each group can both be operated; this another group is subjected to fail safe simultaneously, by moving it along center line 8 or it drives this ring 86 around center line 8 universal rotations.Also expression is followed the advantage that provides between the tie point P of verge ring than short circumferential span S along ring 86 at the first directed actuator 90A and second group of second directed actuator 90B.This can make ring 86 thinner, and weight is lighter.The size ratio of six actuator is needed little when adopting three, therefore, makes the whole weight of orientation nozzle system keep minimum.The system of six actuator is not only the part of fail safe system, and its gross weight even can be lower than the system of three actuator, and this just allows in fight if one group of three actuator breaks down, to the small part thrust orientation.

The invention provides a fail safe jet pipe actuating system 2, have two first and second directed

actuating system

2A and 2B of control separately, detailed being shown among Fig. 3.The first directed actuating system 2A utilizes the start of a cover first actuator servo valve control one first directed actuator 90A1, second directed actuator 90A2 and one the 3rd directed actuator 90A3, this overlaps first start body clothes valve and comprises one first actuator servo valve 16A1, one second actuator servo valve 16A2 and one the 3rd actuator servo valve 16A3, they only control among the directed actuator 90A1-90A3 corresponding one separately.Therewith roughly the same, the second directed actuating system 2B utilizes a cover second actuator servo valve to control the start of second group the 4th, the 5th and the 6th directed actuator 90B1-90B3 respectively, this overlaps the second actuator servo valve and comprises one the 4th actuator servo valve 16B1, one the 5th actuator servo valve 16B2 and one the 6th actuator servo valve 16B3, they only control among the the 4th, the 5th and the 6th directed actuator 90B1-90B3 corresponding one separately.In every group and every group in 3 servo valves each can independently be controlled.Best, the servo valve in two systems is loaded in the control valve 3, makes the component number of increase minimum.Perhaps, every group 3 valves to be obeyed can be loaded in the independent control valve, or are integrated in their corresponding actuator.

The first and second directed

actuating system

2A and 2B have and operationally are configured in first and second in the first and second transfer line 19A and the 19B respectively and carry separating

valve

18A and 18B, and their self-hydraulic power source H pass to first and second transfer line top 20A and the 20B respectively.The first and second directed

actuating system

2A and 2B have and operationally are configured in first and second in the first and second return line 23A and the 23B respectively and return separating

valve

22A and 22B, and they pass to hydraulic power supply H to the direction of leaving the first and second return line top 24A and 24B.Leak or inefficacy if detect in the fail safe system, this allows fail safe jet pipe actuating system 2 that exercisable directed

actuating system

2A or 2B are isolated with the remaining part of this system.Between the first transfer line top 20A and the first return line head 24A, operationally dispose one first recycle valve 26A, thereby a device that allows hydraulic fluid directly to flow between the chamber, top 28 of fail safe actuator group and bar chamber 30 is provided.

This first directed actuating system 2A of fail safe is finished by fail safe jet pipe actuating system 2, and it is closed first and carries blocked valve 18A and first to return separating valve 22A.The first directed actuating system 2A is set in some positions so respectively with first cover, 3 servo valve 16A1-16A3; they allow hydraulic fluid to flow to epicoele 28 from the first transfer line top 20A through first group of upper pipeline 102H; and flow to the bar chamber of the one 3 directed start 90A1-90A3 respectively through rod tube line 102R in the middle of the first return line top 24A, thereby provide a device that allows hydraulic fluid between the epicoele 28 of the fail safe group of actuator and bar chamber 30, directly to flow.The first directed actuating system 2A opens the first recycle valve 26A, flows between the first transfer line top 20A and the first return line top 24A to allow hydraulic fluid.

Therewith roughly the same, if the 23 directed actuator 90B1-B3 replaces and is subjected to fail safe, then this fail safe jet pipe actuator system 2 is closed the second conveying separating valve 18B and second and is returned separating valve 22B.This second directed actuating system 2A is set in some positions like this with second cover, 3 servo valve 16B1-16B3, and they allow hydraulic fluid flowing between the second feed pipeline 20B and each epicoele 28 and between each bar chamber 30 of the second return line top 24B and the 23 directed actuator 90B1-90B3 respectively.The second directed actuating system 28 is also opened second and is followed valve 28 again, flows between the second transfer line top 20B and the second return line top 24B to allow hydraulic fluid.

Expression has the another embodiment of the present invention of 4 actuator altogether among Fig. 4, and it provides a fail safe jet pipe actuating system 2, and two difference, first and second directed actuating system 2A and the 2B of control are separately only arranged, and respectively carries only two directed actuator.The first directed actuating system 2A utilizes the first cover actuator servo valve to control the action of one first directed actuator 90A1 and one second directed actuator 90A2, this cover servo valve comprises one first actuator servo valve 16A1 and one second actuator servo valve 16A2, and they only control among directed actuator 90A1 and the 90A2 corresponding one separately.Therewith roughly the same, the second directed actuating system 2B utilizes the second cover actuator servo valve that comprises the third and fourth actuator servo valve 16B1 and 16B2 to control the action of the third and fourth directed actuator 90B1 and 90B2 respectively, and they only control among the third and fourth directed actuator 90B1 and the 90B2 corresponding one separately.In every cover and the every cover in 2 servo valves each is independently controlled.Best, the servo valve in two systems is assembled into a control valve 3, so that the component number that increases reduces to minimum.Perhaps every cover two servo valves can be assembled into independent control valve or be integrated in their corresponding actuator.Though this embodiment does not provide the jet pipe thrust orientation by the fail safe pattern; yet it allows to control nozzle exit/throat opening area than (A9/A8) with the fail safe pattern really, and it is applicable to the light-duty fail safe jet pipe actuating system of axisymmetric thrust orientation jet pipe 14.

The various layouts and the position of expression oil hydraulic pump among Fig. 5, oil hydraulic pump provides hydraulic power to the first and second directed

actuating system

2A and 2B respectively by the first and second

transfer line top

20A and 20B and the first and second return line top 24A and 24B.Motor 130 has exhaust component 10 and the orientation nozzle 14 that is installed in the military version aircraft 132.First and second directed actuator 90A and the 90B have also been represented in the accompanying drawings, to help explain through diagrams exhaust component 10 and orientation nozzle 14.The line shaft 134 that is driven by engine rotor 138 extends downwardly into engine mission 140 from this rotor, and gearbox has a right angle gear, drives a power index axle 142 (PTO), and the latter extends to motor 130 front ends.Being installed under the motor 130 is respectively the first and second motor mounting type oil

hydraulic pumps

146 and 148, and it extends back from motor gearbox 140, and driven by gearbox.These motor mounting type first and second oil

hydraulic pumps

146 and 148 are used to provide hydraulic power to motor and annex thereof.Axle 134 extends forward, drives an auxiliary drive gearbox 150, and gearbox has suitable gear again to drive each annex of aircraft 132.Auxiliary drive gearbox 150 is installed on the aircraft 132 by suitable frame fitting seat 152, and misaligns ABAP Adapter 154 by one and be connected on the power traction axle.

Fig. 5 shows each the hydraulic power supply H together that is applicable to the first and second directed

actuating system

2A and 2B as crossing the threshold.One embodiment of the present of invention adopt the first and second motor mounting type oil

hydraulic pumps

146 and 148 to come to provide hydraulic power supply H respectively to the first and second directed actuating system 2A and 2B.Perhaps, in this motor mounting type hydraulic-pressure pump only one can be used as hydraulic power supply H, it makes the first and

second transfer line

19A and 19B be integrated into the pipeline that certain between separating

valve

18A and 18B a bit passes to hydraulic power H among an oil hydraulic pump and Fig. 3.Therewith roughly the same, the first and second aircraft mounting type oil

hydraulic pumps

156 and 158 any among both, they are installed on the auxiliary drive gearbox 150 and are driven by it, and can be used to drive first and second directed actuating system 2A and the 2B.Perhaps, only of can be used to separately drive among this orientation actuating system 2A and the 2B in the motor mounting type oil hydraulic pump and the aircraft mounting type oil hydraulic pump.The benefit of the staggered layout of the hydraulic power of these drivings and this orientation nozzle of start is fairly obvious.The damage that suffers in an aircraft part can damage in these pumps, thereby allows the pump in aircraft another part to keep running, to drive orientation nozzle.

Get back to Fig. 1, verge ring 86 by 3 axles adjustable be configured in verge ring bearing device 100 supportings around the housing 11 along the circumference equal angles, it allows to encircle surely 86 and moves axially and by directed actuator 90A and the universal rotation of 90B.An axially movable A-bracket 210 is by a 3DOF spherical joint 206 supporting verge rings 86.The fork shaped head hinge means 208 of this A-bracket 210 usefulness one joint form spherical in shape is connected in a slide block 220 rotationally in the end of arm 211a and 211b.The A-bracket 210 that is applied as in

arm

211a and 211b end ball joint provides the forked type hair style to rotate, and has also got rid of the transmission that may pass to the torsional load on these arms.Slide block 220 can slide along hollow slide block bar 226, and the slide block bar is connected in motor body 11 by fore poppet 236 and back poppet 230.Verge ring bearing device 100 allows verge ring 86 axially to move forward and backward, and can swing, thereby changes its attitude.Can find verge ring bearing device 100 more detailed descriptions in people's such as Lippmeier the US that is entitled as " a kind of bearing device of mobile jet pipe verge ring " 5,174,502, here quoting is for reference.

Though in order to explain that principle of the present invention has proved absolutely preferential embodiment of the present invention, yet should be appreciated that under the situation that does not break away from the scope of the present invention of defined in appended claims and can make all improvement and change.

Claims

1. jet pipe fail safe actuating system (2) that is used for the directed ejector exhaust pipe of aircraft combustion gas turbine axisymmetric (14); has a verge ring (86) that operationally is connected in some rotation hinged joints (50); these hinged joints along circumference be configured in jet pipe center line (8) around; and define grate flow channel in the jet pipe (14), the fail safe actuating system (2) of described jet pipe comprises:

One first directed actuating system (2A) has first group of actuator (90A), operationally is connected in verge ring (86); With one first fail safe control gear, to control to described first group of actuator transmitting power;

One second directed actuating system (2B) has second group of actuator (90B), operationally is connected in verge ring (86); With one second fail safe control gear, to control to described second group of actuator transmitting power;

Described first group actuator and described second group actuator are along jet pipe (14) circumference interlaced arrangement.

2. by the described jet pipe fail safe of claim 1 actuating system (2), it is characterized in that jet pipe fail safe actuating system (2) is that fluid power drives.

3. by the described jet pipe fail safe of claim 2 actuating system (2), it is characterized in that also comprising single hydraulic power supply (H), become hydraulic power supply to be communicated with described each first and second fail safe control gear.

4. by the described jet pipe fail safe of claim 2 actuating system (2), it is characterized in that also comprising first and second hydraulic power supplies (H), they become corresponding hydraulic power supply to be communicated with each of the described first and second fail safe control gear respectively.

5. by the described jet pipe fail safe of claim 4 actuating system (2); it is characterized in that also comprising the first and second fail safe control gear; can fail safe in first and second groups of actuator corresponding one group (90A), be expanded to corresponding to by not any position of setting of another group of fail safe and all places of attitude in first and second groups of actuator (90A and 90B) to allow actuator group by fail safe.

6. by the described jet pipe fail safe of claim 5 actuating system (2), it is characterized in that having only two groups of actuator, (90A3) (90B1,90B2 90B3) have only 3 actuator to described first and second groups of actuator separately for 90A1,90A2.

7. lost efficacy to protect by the described jet pipe of claim 5 and expand actuating system (2), and it is characterized in that having only two groups of actuator, (90A1,90A2) (90B1 90B2) has only 2 actuator to described first and second groups of actuator separately.

8. by the described jet pipe fail safe of claim 5 actuating system (2), it is characterized in that

The described first and second fail safe control gear respectively comprise one operationally be configured on the described operator recycle valve between the control (28) and bar chamber (30) (26A, 26B);

Described first and second fail safe control gear and described recycle valve can be operated; allowing hydraulic fluid when be subjected to fail safe for one in the described actuator group, directly mobile between the epicoele (28) of the actuator group that is subjected to fail safe and bar chamber (30).

9. by the described jet pipe fail safe of claim 8 actuating system (2); it is characterized in that first and second hydraulic power supplies (H) are two oil hydraulic pumps that are loaded on motor and are driven by it (146; 148), wherein each pump can be operated only one and the corresponding fail safe control gear that come in the described actuator group hydraulic power is provided.

10. by the described jet pipe fail safe of claim 8 actuating system (2); it is characterized in that described first and second hydraulic power supplies (H) are two oil hydraulic pumps, at least one in the described pump is the aircraft hydraulic pumps (156) that also is used to drive plane hydraulic system.