CN1174934A - Thrust reverster synchronization shaft lock - Google Patents
Thrust reverster synchronization shaft lock Download PDFInfo
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- CN1174934A CN1174934A CN 96111535 CN96111535A CN1174934A CN 1174934 A CN1174934 A CN 1174934A CN 96111535 CN96111535 CN 96111535 CN 96111535 A CN96111535 A CN 96111535A CN 1174934 A CN1174934 A CN 1174934A
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Abstract
A thrust reverser synthronization shaft lock system that includes a sync lock control valve and two hydraulically controlled sync locks attached to the synchronization shafts of a jet engine thrust reverser system, is disclosed. The thrust reverser system further comprises an isolation valve, a directional control valve, a plurality of actuators, and synchronization shafts. The sync locks a capble via the synchronization shafts of preventing the actuators from deploying the thrust reversers of the jet engines. The sync locks remain in a locked state until an independent control signal sent from the flight deck positively instructs the sync lock control vavle to unlock the sync locks.
Description
The present invention relates to a kind of aircraft THR REV, more particularly, relate to a kind of air breathing engine THR REV and lock mechanism.
Jet airplane is used for high-speed flight.This causes when landing speed also higher relatively, and when wanting dead halt after the aircraft landing or unsuccessful taking off the time, such speed can cause serious difficulty.Aircraft landing gear braking device and wing Pneumatic actuator are the critical pieces that is used for reducing air speed.What these parts were helped out is THR REV, it by engine exhaust or the break-in of motor fan airflow for not being to after-blow, thereby further reduce air speed.Usually, behind the aircraft contact the runway, start THR REV work by the pilot immediately.
Different along with engine shop, engine structure and Push Technology, the design of THR REV is also just various.The THR REV that is used for turbofan engine is realized thrust reversing with three kinds of methods usually.The cascade type THR REV is positioned on the motor intermediate cross-section, and it makes to pass and is positioned at motor circumferentially and the air-flow of cascade blade change direction.The cascade type THR REV is generally used for the motor of high by-pass ratio.The baffle plate type THR REV also is the clam shell type THR REV sometimes, utilizes two doors to stop whole Jet Stream.This is positioned at the rear portion of motor, and forms the rear portion of engine nacelle.The baffle plate type THR REV is generally used for the motor of low by-pass ratio.The pivot door THR REV is not except having cascade blade, and is similar with the cascade type THR REV.In addition, four doors on the engine nacelle are petal-shaped and outwards launch to change airflow direction.
Can realize from following narration, the present invention is a kind of locking framework, more particularly, is a kind of thrust reverster synchronization shaft lock, and it most desirably is applicable to the cascade type THR REV of hydraulic control.When being ideally suited for the cascade type THR REV, it is also understood that: the present invention is through revising still applicable to other anti-pushing system, if this system be hydraulic control and have a synchronous mechanism to constitute a constituent element of its THR REV.
The working method of cascade type THR REV THR REV sleeve as described below (being called mobile cowling sometimes) is positioned at the peripheral of motor and covers cascade blade (just positive in the face of flow outlet).Cascade blade is between THR REV sleeve and fan airstream passage.A string gate that mechanically is connected with the sleeve of THR REV is arranged in the fan airstream passage.At its expanded position, these gates are across in air-flow path.When THR REV started, the THR REV sleeve slided backward, and made cascade blade expose to the open air out, and made gate move to their expanded position.And then fan airflow-reversing diversion blade.Is the fan airstream break-in effect of forwards hanging down air speed to landing.
The sleeve of THR REV is operated by the one or more actuators on each motor, and actuator is positioned on the housing of engine blower and by the lazy-tongs as flexible shaft and so on and interconnects.Lazy-tongs guarantee that actuator moves with same speed.
THR REV is controlled by a hydraulic type THR REV control system.The signal that sends to control system from the aircraft operating console is determined the state of required THR REV.Actuating system comprises the element of received signal and regulates pressure in the various undergrounds with them.Hydrodynamic pressure is being controlled the position of THR REV sleeve, guides them between its deployed condition and purse up state.Other underground of hydraulic fluid circuit and aircraft can be separate on hydraulic pressure, and perhaps, the hydraulic fluid that it utilized is the part of a bigger plane hydraulic system.So the latter's structure depends on the fluid supply and the return line of whole plane hydraulic system, this is just opposite in the former, and the former must comprise the parts that form internal flow supply and return line.Under each situation, the fluid supplies road is designed to be in higher pressure than fluid return line.
Usually, THR REV (hydraulic type or other forms) utilizes locking framework to guarantee that THR REV only starts in the correct time.Most of locking frameworks reach this point by not allowing actuator launch the THR REV sleeve up to sending to launch to order.In other words, these locking frameworks are only receiving when launching order just release THR REV.
Other locking device role only is that inside and outside the try hard to recommend moving sleeve of interception on THR REV enters its deployed condition.U.S. Patent No. 4,586,329 locking devices of being introduced that example is Carlin.This patent has been introduced the anti-rotary device of a kind of mechanical type, and it is accidental expansion of THR REV that is used for preventing that the aerodynamic loading owing to engine interior aerodynamic loading and external engine from causing.This anti-rotary device be one be fixed on the interconnective synchronizing shaft of mechanical screw jack on mechanical locking.
Characteristics of existing locking framework are that actual locking member often comprises a pin that makes gear remain on state of rest, above-mentioned Carlin patent is an exemplary of this device, wherein, the engaging force of locking member is concentrated and to be pressed the single of a single bearing and lock.
According to the present invention, a hydraulic type THR REV synchronization shaft lock fixed system is provided, it is allowing to need a reliable unlock command before the THR REV expansion.When the pilot gives an order when launching THR REV, hydraulic fluid pressure acts on actuator by separating valve and position control valve.Actuator generally includes a connecting rod-piston structure, and the THR REV sleeve and the stationary part of motor are coupled together.When hydraulic fluid pressure acted in the suitable chamber of actuator, connecting rod just was forced to stretch or shrink.The sleeve that the stretching, extension of connecting rod or contraction cause joining moves (promptly launching) backward or moves forward (being purse up).Between the actuator is to finish by a flexible synchronizing shaft that is placed in the conduit synchronously.Direct and the actuator connection of flexible shaft, when actuator linkage moved, flexible shaft will rotate.By this method, make all actuators synchronously shrink simultaneously or stretch by same speed.Synchronization shaft lock fixed system of the present invention comprises two genlocing devices and a genlocing device control valve.Each genlocing device all is connected with a synchronizing shaft conduit and and flexible shaft connection.Normal state genlocing device is locked, rotates to prevent flexible shaft, thereby stops THR REV to launch.The genlocing device is to be opened by an independent control signal that sends to genlocing device control valve from aircraft operating console or other control place.When genlocing device control valve received a control signal, valve was opened, and utilized hydraulic fluid pressure to open the genlocing device, allowed flexible shaft to rotate simultaneously.In this way, actuator can freely mobile THR REV sleeve.Genlocing device and genlocing device control valve are formed among the THR REV start-up system, thereby, no matter the start-up system internal pressure is how, unless open by genlocing device control valve instruction genlocing device, it can not unblanked.
According to another aspect of the invention, genlocing device control valve comprises a standard electromagnetism hydraulic control valve.Preferably, genlocing device control valve is positioned at the position away from the genlocing device.
According to other aspects of the invention, each genlocing device comprises: one is rotated jaw; A slip jaw; A snap; A plurality of seal rings; The bolt mechanism of unblanking; A plurality of internal hydraulic pressures chamber and passage, and a plurality of hydraulic fluid interface.An end that rotates jaw and flexible shaft is connected, acts on pressure on the piston that is connecting the slip jaw promote to slide jaw and rotate jaw and form and mesh by a snap.Genlocing device control valve acts on the side away from snap of piston to hydraulic fluid pressure, breaks away from thereby make the slip jaw and rotate jaw.
One the aspect again according to the present invention is rotated jaw and is being supported by bearing.
According to a further aspect in the invention, maintenance for convenience, each genlocing device comprises the structure of manually unblanking, and it allows the genlocing device manually to unblank.
In another aspect of the invention, the genlocing device comprises an indicating device, is used on the spot or remotely warning aircrew's genlocing device and is in the lock state or unlocking condition.
Can realize from the introduction of front, being connected of genlocing device and flexible shaft means that each motor only needs two genlocing devices (for the motor of a pair of mobile cowling is arranged), and standard electromagnetism hydraulic control valve of needs guides the genlocing device on two mobile cowlings of fluid opened by pressure in genlocing device control valve.Standard electromagnetism hydraulic control valve has used for many years, and it is representing the maturation design that has an important standby valve shaft.Genlocing device control valve can be positioned at So Far Away, and this is an advantage, and it means that only the less engine nacelle of needs contains area, and in general the space of machine nacelle is limited.The genlocing device is connected with synchronizing shaft one end means that the genlocing device is easy to install, and is easy to approachingly during maintenance, is easy to an existing group of planes is retrofited.
In conjunction with the accompanying drawings, with reference to following detailed description, the many advantages that can understand each side of the present invention better and be brought just.These accompanying drawings comprise:
Fig. 1 is the isometric drawing of a typical THR REV in retracted position, is wherein connecting a genlocing device on the synchronizing shaft according to the present invention;
Fig. 2 is the sketch of a typical hydraulic type THR REV actuating and control system.They have formed synchronization shaft lock fixed system of the present invention;
Fig. 3 be among the present invention at present preferred genlocing device embodiment at the sectional view of lock state;
Fig. 4 be among the present invention at present preferred genlocing device embodiment at the sectional view of unlocking condition;
Fig. 5 is the side view of Fig. 3 and genlocing device shown in Figure 4, and an end of itself and synchronizing shaft conduit is connected.
At first with reference to figure 1, it is the isometric drawing of a kind of typical cascade type THR REV in retracted position.This THR REV comprises: two THR REV outer sleeves 11; A core cover 8; An annular pass 15; Cascade blade (not showing among the figure); A plurality of Rotary grates 9; A plurality of actuators 19 and two synchronizing shafts 5.Sleeve 11 is along the outside that circumferentially is centered around motor, and forms annular passage 15 together with core cover 8, and the air-flow of engine blower promptly flows through this passage.Sleeve 11 is to lead before and after two guide rails parallel to each other 17, and guide rail 17 is to be fixed on the upper and lower vertical wall of core cover 8.In the interior week of sleeve 11,15 li in the annular pass, cascade blade forward is installed on THR REV supporting structure 21.The inside of cascade blade is gate 9, they are connected with sleeve 11, and it does not have great interference to the air-flow through annular pass 15 at its purse up state, in this preferred embodiment, each THR REV sleeve 11 is all driven by one or more actuators 19, and what show among Fig. 1 is that each THR REV sleeve 11 has three actuators 19.Actuator 19 is positioned on the fixed structure of THR REV front.Synchro system 5 is connected with each other these actuators.
Each actuator 19 all is a typical hydraulic type connecting rod and packed-piston type actuator.Actuator linkage 20 is positioned at the aerodynamic surface the inside of sleeve 11, and is connected with sleeve 11 by a ball-joint (not showing among the figure).The wallboard that dismounting is connected with sleeve 11 outer surfaces by double-screw bolt (not showing among the figure) just can be near ball-joint.Preferably each actuator 19 all is connected with the structure torsion box by a universal joint seat, and the side direction that this universal joint makes actuator can adapt to the sleeve motion changes.Actuator piston (not showing among the figure) links to each other with actuator linkage 20.In the inside of actuator 19 and the relative both sides of actuator piston, be a development chamber (not showing among the figure) and a purse up chamber (not showing among the figure).Each chamber can both the acceptable solution hydraulic fluid pressure, and moves according to relative pressure official post actuator linkage and the piston on each piston face in two chambers.Actuator 19 also comprises the element (figure does not show) that is used for connecting actuator linkage 20 and flexible shaft described below 7.Also will further introduce actuator below according to the function of actuator 19 in the THR REV control system.
Synchro system 5 is to be used for guaranteeing that actuator linkage 20 can be simultaneously with same speed contraction and stretching, extension sleeve 11, in order to avoid be restricted when actuator linkage 20 moves forward and backward sleeve 11.Each synchro system 5 comprises a static outer conduit 6 and an inner rotation flexible shaft 7 (as shown in Figure 2).Hydraulic fluid from THR REV control system (also will introduce below as shown in Figure 2) flows into outer conduit 6 and surrounds flexible shaft 7.Preferably, flexible shaft 7 is to link to each other with each actuator 19 by worm and worm wheel mechanism, conduit 6 is to be rigidly connected with actuator 19 by rotary connector (not showing among the figure), when arbitrary actuator linkage 20 is moved, the gear connecting structure of flexible shaft 7 drives flexible shaft 7 and rotates, thereby drives all actuator linkage 20 same moved further.If can not be synchronized with the movement because of an actuator is damaged these actuator linkage 20, flexible shaft just can not rotate.So flexible shaft is being controlled actuator and is being synchronized with the movement.Flexible shaft is not supplied with power to actuator.As following more complete introduction, hydraulic fluid pressure is supplied with power to actuator.
Synchronization shaft lock fixed system of the present invention comprises a genlocing device control valve 50 (as shown in Figure 2) and two genlocing devices 60 (as illustrated in fig. 1 and 2).Genlocing device control valve 50 is connected with genlocing device 60.This point will be understood from following introduction preferably, each genlocing device 60 comprises: a shell block 65, slip jaw 81 and rotation jaw 75 (as shown in Figure 3 and Figure 4), shell block 65 is rigidly connected to an end of outer conduit 6 (as shown in Figure 1), and an end that rotates jaw 75 and flexible shaft 7 links to each other.Because each motor all has two separate synchro systems 5, each motor will have respectively one of two each flexible shaft 7 of synchronizing shaft locking device 60-at least.When a genlocing device was locked, it just prevented that flexible shaft 7 from rotating, thus also just stoped actuator linkage 20 and sleeve 11 to move, and then prevent that THR REV from launching.Fig. 3 and 4 schematically shows genlocing device 60 of the present invention, also will introduce in detail below.Fig. 2 is a system schematic, and it has shown synchronizing shaft locking device and it are how to be connected with whole hydraulic type THR REV actuating system.Before introducing these figure, introduce earlier the operation of THR REV shown in Figure 1 briefly.
In the time will launching THR REV, as what below will more intactly introduce, at first, a signal is sent to the synchronization shaft lock fixed system, and it makes genlocing device control valve 50 open genlocing device 60.Then, a plurality of signals are sent to the THR REV actuator system, and are final, and it makes hydraulic fluid pressure stretch actuator linkage 20.The stretching, extension of actuator linkage 20 make sleeve 11 backward (as indicated by arrow 13) be moved, become deployed condition (the figure not show) from purse up state (as shown in Figure 1).In this process, cascade blade exposes to the open air out.The motion backward of sleeve 11 makes gate 9 that pivoting action take place, and also becomes deployed condition from the purse up state.When deployed condition, the gate 9 that the annular pass is 15 li is transverse on the normal air flow path, thereby cloudy only air communication is crossed annular pass 15 and moved backward.Like this, the engine blower air-flow moves through cascade blade backward and becomes outside motion.Blade turns forward.So when THR REV is worked, cross blade commutation for forward, thereby help aircraft brake from the air communication of motor.
When wanting the purse up THR REV, a signal is sent to the THR REV actuating system, it makes that activating connecting rod 19 shrinks, thereby cause sleeve 11 to move forward, progressively cover cascade blade, equally, gate 9 turns back to the position of their purse ups, and fan airstream flows along normal path backward by annular pass 15.Another signal is sent to the synchronization shaft lock fixed system, and the pressure that it discharges in the genlocing devices 60 synchronizing shaft locking device control valve 50 allows the genlocing device get back to oneself locked position, so just finished counter push off to.
Fig. 2 is the schematic representation of a typical hydraulic type THR REV actuating and control system, and it has adopted the synchronization shaft lock fixed system among the present invention.This actuating system comprises: 45, one position control valves 47 of a separating valve, 37, one of 35, one hydraulic fluid return lines of 5, one hydraulic fluid supply lines of 19, two synchro systems of a plurality of actuators launch pressure line 39 and a purse up pressure line 41.The synchronization shaft lock fixed system comprises: 50, two genlocing devices 60 of a genlocing device control valve and genlocing device circuit 43 of unblanking.
Separating valve 45 is connected with fluid return line 37 with fluid supplies road 35, and when will mobile THR REV, separating valve 45 be accepted from the control signal on the flight controlling platform.In general, this control signal is from certain electronic engine management system.With regard to purpose of the present invention, this signal can be from any one signal source, as long as it is effective control signal.
In case the control signal of receiving, separating valve 45 just begin to work, allow to be delivered to the THR REV actuating system from the hydraulic fluid pressure on fluid supplies road 35, specifically be position control valve 47.The structure of separating valve 45 can guarantee fluid return line 37 always with THR REV actuating system hydraulic pressure UNICOM, no matter and whether separating valve starts.Such connection has guaranteed to obtain suitable continuous release from the hydraulic fluid pressure of THR REV actuating system, rises to prevent any undesirable pressure.
When allowing hydraulic fluid pressure be delivered to actuating system when starting separating valve 45, it is to be used to launch THR REV that the determining positions of position control valve 47 hydraulic fluid pressure, or the purse up THR REV, the position of position control valve 47 is determined by the independent control signal from the flight controlling platform.Position control valve 47 passes to actuator 19 to hydraulic fluid pressure by launching pressure line 39 and purse up pressure line 41, and makes the both sides of each actuator piston produce pressure difference.As can be seen from Figure 2, expansion pressure line 39 is divided into many branch roads and is connected with each actuator 19 respectively by synchronizing shaft 5, and purse up pressure line 41 is connected with each actuator 19 respectively.
In a kind of preferred embodiment, the motion that the finish actuator piston is come in two basic operation positions of position control valve 47 usefulness.In first position, position control valve 47 is connected to fluid supplies road 35 and launches on the pressure line 39 fluid return line 37 to be connected on the purse up pressure line.Because launching the development chamber of pressure line and actuator 19 is connected, when this position, the hydraulic fluid pressure on fluid supplies road rises at the pressure of the expansion side of piston, so cause THR REV sleeve 11 to stretch, second position, position control valve 47 is connected to fluid supplies road 35 on the purse up pressure line 39, fluid return line 37 is connected to launches on the pressure line 41.Because the purse up chamber of purse up pressure line and actuator 19 is connected.When this position, the hydraulic fluid pressure on fluid supplies road rises at the pressure of purse up pressure line one side of piston, so cause 11 withdrawals of THR REV sleeve.
Certainly, separating valve 45, position control valve 47 and the hydraulic fluid pressure mode that puts on actuator can also have other form.For example, can improve the efficient of THR REV control system, thereby in hydraulic fluid supply circuit, need less pressure with a circulatory system.This system can not influence enforcement of the present invention or aim.The critical function of separating valve and position control valve is to produce pressure difference in the piston both sides, thereby piston is moved on a direction or another direction.
As mentioned above, synchronization shaft lock fixed system of the present invention comprises genlocing device control valve 50 and two genlocing devices 60, genlocing device control valve 50 is connecting fluid supplies road 35, the unlock pressure circuit 43 of fluid return line 37 and genlocing device.Then, 43 fens two-way of the unlock pressure circuit of genlocing device are connected with genlocing device 60 respectively.The function of genlocing device control valve 50 is the hydrodynamic pressures in the unlock pressure circuit 43 of regulation and control genlocing device.Genlocing device control valve 50 also has two basic operating positions.In first position, genlocing device control valve 50 is connected to fluid on the circuit 35 with the genlocing device circuit 43 of unblanking.In genlocing device control valve 50, comprise and be used for receiving, and be used to start the structure of an independent control signal of genlocing device control valve 50 from the aircraft operating console.After genlocing device control valve 50 began to start, the hydraulic fluid pressure in the fluid supplies road 35 made genlocing device 60 open by the mode of introducing below.
When genlocing device control valve 50 was not activated, it was in an off position, at this moment, it is connected to the genlocing device circuit 43 of unblanking on the fluid return line 37, like this, make genlocing device 60 get back to their normal locked positions, below this point will be described.Genlocing device control valve 50 is the electromagnetic hydraulic pressure control valve of a standard preferably, and it can control fluid supplies road 35 and fluid return line 37 and the genlocing device UNICOM between the hydraulic fluid in the circuit 43 of unblanking individually.The position of genlocing device control valve 50 can be located near the of genlocing device 60 or from its place far away.
As mentioned above, as shown in Figure 2, synchronizing shaft system 5 comprise an inner flexible axle 7 and one around outer conduit 6.The hydraulic fluid that self-deploys in the pressure line 39 charges in the conduit 6.Synchronously conduit 6 is connected with each actuator 20 respectively, like this, pressure launch in the circuit 39 fluid pressure with regard to and actuator 19 link.As mentioned above, flexible shaft 7 is connected with actuator linkage 20, makes connecting rod keep synchronously when stretching and shrink.When genlocing device 60 was locked, its stoped flexible shaft 7 to rotate, so also just stop actuator linkage 20 and sleeve 11 to move, did not allow THR REV launch.Will introduce in detail below the operating in of genlocing device 60.
On the whole, THR REV control system sequential in operation is as follows.From normal purse up state, the order of the startup THR REV that the aircraft operating console sends produces first control signal, it is sent in the genlocing device control valve 50, so genlocing device control valve 50 moves on to its enable position, fluid supplies road 35 is connected to the genlocing device unblanks on the circuit 43, the hydraulic fluid pressure that the genlocing device is unblanked in the circuit 43 makes genlocing device 60 open by following mode.Then, second control signal makes position control valve 47 set, makes to flow into hydraulic fluids from fluid supplies road 35 and flow to and launch the pressure line 39, in the hydraulic fluid incoming fluid return line 37 that flows out from purse up pressure line 41.The 3rd control signal starts separating valve 45, and allows to be delivered to position control valve 47 from the hydraulic fluid pressure on fluid supplies road 35; Then, position control valve 47 then passes to hydraulic fluid pressure again and launches in the pressure line 39.
The hydraulic fluid pressure that launches in the pressure line 39 is delivered in the development chamber of each actuator 19 by synchronous conduit 6.So actuator 19 launches their connecting rod backward.As mentioned above.Actuator linkage 20 is connected with the flexible shaft 7 of synchronizing shaft 5, so the straight line of each actuator linkage 20 moves the rotation that all causes flexible shaft 7.By this method, make all actuator linkage 20 simultaneously with same speed motion.The motion of actuator piston enters in the purse up pressure line 41 hydraulic fluid pressure in the purse up chamber, and then passes in the return line 37.As mentioned above, moving backward of actuator linkage 20 moved THR REV sleeve 11 backward, thereby produces counter pushing away.
When the aircraft control panel sends the purse up axial force and changes the order of taking out device, a control signal at first makes position control valve 47 set, so that the hydraulic fluid pressure that flows into from fluid supplies road 35 is delivered to purse up pressure line 41, and the outflow hydraulic fluid pressure is discharged in the return line 37 from launch pressure line 39.Hydraulic fluid pressure in purse up pressure line 41 acts on the purse up chamber of each actuator 19.Actuator 19 its connecting rod 20 of withdrawing forward.As noted earlier, the contraction of actuator linkage is to reach synchronous by the connection that synchronizing shaft 5 provides.The motion of actuator piston makes the hydraulic fluid pressure in the development chamber of actuator 19 pass to synchronous conduit 6 and launch and enters return line 37 then in the pressure line 39.Moving forward of actuator linkage 20 travels forward THR REV sleeve 11, thereby finishes aforesaid counter pushing away.
Then, independent control signal makes genlocing device control valve connect genlocing device unblank circuit 43 and return line 37, so hydraulic fluid is discharged from the genlocing device is unblanked line ball road 43 and made genlocing device 60 get back to its locked position, this point below will be introduced.At last, the another one control signal makes separating valve 45 inoperative, prevents that hydraulic fluid pressure imports in control system and the position control valve 47 in the fluid supplies road 35.
Fig. 3 and Fig. 4 are the sectional views of the genlocing device 60 of the preferred embodiment of the present invention.The synchrolock that Fig. 3 shows is installed and put 60 is in its locked position, and Fig. 4 demonstration is its enable possition.Genlocing device 60 comprises: shell block 65; One is rotated jaw 75; A slip jaw 81; A snap 87; One is launched pressure interface 91; A cracking pressure interface 89; Open mortise lock 106 for one; 97, one manual unlocking mechanisms 99 of a plurality of seal rings and a plurality of chamber and passage.The material of genlocing device 60 all constituents all is the material that the Machine Design personnel are familiar with.The overall dimensions of genlocing device 60 is unfixing, and it depends on the many factors in the hydraulic transmission technology, for example, puts on the size of the hydrodynamic pressure on the latch fitting.
The shell block 65 of genlocing 60 devices is normally columnar, the chamber that will introduce below wherein comprising.Connector is rigidly connected to an end 60 of the shell block 65 of genlocing device 60 on the outer conduit 6 of synchro system 5, sees Fig. 5.Novel part of the present invention does not also lie in this connection, and selected any connection can guarantee in pressure process that at least the shell block 65 of genlocing device is connected on the conduit 6 securely, and the energy bottom line reduces the leakage of hydraulic fluid.Some typical connectors are bolt and nut linkage structures, screw connection structure and clamping dop structure, the preferential Connecting format that adopts of the present invention as shown in Figure 5, it comprises the linkage structure of being made up of 5 bolts 74, wherein, each bolt 70 injects radially along the axis of synchronous interlocking device 60 abreast, is positioned among the flange 71 of shell block 65 1 ends 66.Bolt 70 is connected to genlocing device 60 on the flange 72 rigidly, flange 72 or be the part of conduit 6, or be rigidly attached to an end of conduit 6.
The connecting end 66 that is positioned at shell block 65 has a passage that extends to 65 li of shell blocks, and it has formed first order driving channel 67.The hydraulic fluid that self-deploys pressure line 39 enters among the genlocing device shell block 65 by this first driving channel.First driving channel ends at 93 places, jaw chamber, and jaw chamber 93 is connected by an end 94 of second driving channel 68 and piston chamber 95 again.93 second driving channels 68 in jaw chamber and piston chamber 95 all are made in the shell block 65.In this preferred embodiment, piston chamber 95 processes inwards from an other end 64 of shell block 65, and end cap 103 closes the opening of piston chamber 95, and end cap 103 can be shaped on and be threaded into, so just can be from 65 dismountings of seat shell.In the time of on being connected to shell 65, end cap must can be born the pressure in the piston chamber 95 and be securely fixed on the shell block 65.
Rotating jaw 75 is made up of a rotor 76 and an axle 77.Rotor 76 is a gear or shallow cylinder, has rotor tooth 78 on one of its annular surface.Axle 77 1 direct sum rotors 76 connect, and a plane is arranged on the opposite flank of the rotor surface with rotor tooth 78, and axle 77 promptly extends along the Normal direction on this plane.Rotate jaw 75 and be positioned within the shell block 65, rotor 76 is arranged in jaw chamber 93, and axle 77 stretches out by first driving channel 67.Usually the longitudinal axis that rotates jaw 75 is parallel with the longitudinal axis of first driving channel 67.In the preferred embodiment of the present invention, rotate jaw 75 and can only rotate.Rotating the other end of jaw axle 77 and the flexible shaft 7 of synchronizing shaft system 5 is connected.The preferential Connecting format that adopts (not showing among the figure) is such: rotating jaw axle 77 is square drive mechanisms, and it can be connected in the square hole that flexible shaft 7 one ends are processed into by broaching.
In first driving channel, around and back shaft 77 be one or more bearings 69.These bearings axle 77, and allow axle 77 to rotate around its longitudinal axis.Bearing 69 is common, and it can comprise some typical bearing elements, just, and ring in; An outer shroud and a ball support.Bearing 69 can allow hydraulic fluid flow into jaw chamber 93 through them from this driving channel.
A snap 87, it is whole to be arranged in piston chamber 95, and is between disconnected of piston 84 and the end cap 103.Snap 87 always is in compressive state in piston chamber 95, movable jaw 81 is pushed rotate to jaw 75 always.
Fig. 3 also further shows, launches pressure interface 91 and by a hydraulic channel 52 (as shown in Figure 2) piston chamber 95 is connected on the expansion pressure line 39.In a preferred embodiment of the invention, hydraulic channel 52 will launch pressure interface 91 and be connected on the outer conduit 6 of synchronizing shaft system 5, and this outer conduit itself is connected with expansion pressure line 39, as mentioned above.So hydraulic fluid pressure is delivered in first driving channel 67 of genlocing device by launching pressure line 39 by synchronous conduit 6, and pass in the part of the piston chamber 95 that comprises snap 87 by launching pressure interface 91.
The unlock pressure circuit 43 (as shown in Figure 2) of unlock pressure interface 89 and genlocing device is connected.The interface 89 of unblanking provides passage for hydraulic fluid pressure from the circuit 43 of unblanking passes on the piston 84 part away from the piston chamber 95 of snap 87 1 sides.
Fig. 3 has also shown the latch 106 of unblanking, and it is used for 81 lockings of slip jaw at lockset position of coupler.In a preferred embodiment, the latch 106 of unblanking is simple spring loaded pins 109, and it is arranged in pin-and-hole 107 and perpendicular to the longitudinal axis of piston 84, pin-and-hole 107 extends radially outwardly from piston chamber 95 with respect to the longitudinal axis of piston 84.Pin-and-hole 108 is connected with expansion pressure interface 89 by a conduit 110.Be enclosed within pin 108 little spring 107 on every side and be configured in the pin-and-hole 108, and little spring 107 is constantly pushed away pin 109 to the direction away from piston chamber 95.When piston 84 was in unlocking condition, the cotter way 111 on the piston 84 can pin-receiving 109.There is certain relativeness the position of pin 109 and cotter way 111, that is, when pin pushed cotter way 111, slip jaw 81 was thrown off rotation jaw 75.
In a preferred embodiment, slip jaw 81 comprises many seal rings 97, and they lay respectively on the diverse location of slip jaw 81 side faces and (have only shown one around slip kinematic link 83 among the figure), is used to prevent hydraulic fluid pressure exchange between the different chamber.
Manually unlocking mechanism 99 can make slip jaw 81 mechanically enter its lockset position of coupler.Manually unlocking mechanism 99 is useful when safeguarding THR REV, because it allows the machinist needn't use the THR REV control system to the release of synchronous interlocking device.Unlocking mechanism 99 is arranged in shell block 65 pistons, 95 places and near on the position of piston 84, it comprises a turning gear 100.An external lever 102 (as shown in Figure 5) that is arranged on shell block 65 outsides is installed on the same axle of turning gear 100, thereby can make machinist's turning gear 100.Piston 84 has a sliding-groove 101 on its side face, its size can be accepted turning gear 100.The installation position of turning gear is wanted and can be guaranteed: when rotating external lever, turning gear 100 forces sliding-groove 101, piston 84 and slip jaw 81 towards sliding away from the direction of rotating jaw 75.Like this, rotating jaw 75 and slip jaw 81 has just separated.The reversing motion of external lever makes slip jaw 81 slide towards rotating jaw 75, connects and form jaw.The shell block outside also is provided with the position that sign (as shown in Figure 5) shows rotation slot 100.As shown in Figure 5, except lever both sides externally are provided with simple pass/close the sign, this sign also can comprise some more perfect things, for example, delivers to the electrical signal of aircraft operating console display system.
This locking device is operated as follows: from normal purse up state, the aircraft operating console sends an order that starts deboost, at first a control signal is delivered to genlocing device control valve 50, genlocing device control valve 50 is just reacted, fluid supplies road 35 is connected on the genlocing device release pressure line 43, and the pressure of the hydraulic fluid in the genlocing device release circuit 43 is delivered in the shell block 65 by unlock pressure interface 89.Among hydraulic fluid pressure entered piston chamber 95 from the joint of piston 84 and slip drive link 83, piston 84 promoted facing to snap 87.Hydraulic fluid pressure overcomes the pressure of little spring 107 rapidly by passage 110, enters piston chamber 95 along pin-and-hole 108 pushing pins 109, and heads on piston 84.The pressure of setting up on the piston 84 accumulates gradually until overcoming the pressure that snap 87 acts on piston 84 opposite sides.In case reach enough values at the piston face upward pressure, slip jaw 81 is forced to move backward, further compresses snap 87, and pin 109 is moved in the cotter way 111.In this way, slip jaw 81 usefulness latches break away from the slip jaw and rotate jaw 75, and the genlocing device just is unlocking condition shown in Figure 4.Because slip jaw 81 no longer connects with rotation jaw 75, the rotation jaw is just free to rotate, so flexible shaft 7 also just can freely rotate.Above-mentioned introduction promptly be all the other operating process of THR REV.
As mentioned above, in the THR REV expansion process, the THR REV control system makes the hydraulic fluid pressure from fluid supplies road 35 be delivered to expansion pressure line 39, finally, this pressure enters and launches pressure interface 91 and piston chamber 95, and reaches on the piston 84 among the part that piston chamber 95 includes snap 87.Acting on hydraulic fluid pressure on the piston 84 in the piston chamber 95 has offset by the genlocing device circuit 43 of unblanking and has acted on the hydraulic fluid pressure of piston opposite side.As a result, the shear pin 109 across piston 84 can not produce the extremely high pressure difference.
When the aircraft operating console sent the order of a purse up THR REV, THR REV will be as mentioned above and purse up.One is in retracted position, and genlocing device control valve 50 circuit 43 of just the genlocing device being unblanked is connected on the return line 37.Discharge the interface 89 of unblanking at first end 94 of piston chamber 95 and the hydraulic fluid in the passage 110, and enter return line 37 by the genlocing device circuit 43 of unblanking.The reducing of pressure just makes little spring 107 will sell 109 and releases from cotter way 111, and it is up along pin-and-hole 108 to make it leave piston 84.Because THR REV will launch pressure line 39 and return line 37 couples together, so just do not have pressure difference in piston 84 both sides.When the pin 106 of unblanking was inoperative, snap 87 made slip jaw 81 lean rotation jaw 75, and the genlocing device is just got back to its normal locked position 60 this moments, rotates and prevent to rotate jaw 75.
From the introduction of front, can realize, according to the present invention, even when accidental pressure taking place in the purse up chamber of actuator 19 descending, the synchronization shaft lock fixed system still can remain on locked position, because the genlocing device proper is not connecting or is being associated with pressure in the purse up chamber of actuator 19.Equally, according to the present invention, when even the accidental pressure of generation increases in the development chamber of actuator 19, synchronizing shaft locking device still remains on locked position, can be presented in slip jaw both sides (promptly because launch any pressure increase of hydraulic fluid in the pressure line 39, disconnected part at stator 82 parts and piston 84), so to the not influence of slip jaw.
So far, the preferred embodiment of the present invention is introduced.It must be understood that: the various variations in the appending claims scope, all do not deviate from spirit of the present invention and category.
Claims (15)
1, a THR REV synchronization shaft lock fixed system that is used for air breathing engine hydraulic type THR REV synchronizing shaft comprises:
(a) genlocing device control valve that can pass through SC sigmal control, it has two input interfaces and a signal output interface, one of them input interface is suitable for being connected with a fluid supply line road, and another input interface is suitable for being connected with a return line;
(b) output interface with genlocing device control valve be connected and and the genlocing device that is used for preventing the synchronizing shaft rotation that is connected of a synchronizing shaft of the THR REV of an air breathing engine, this genlocing device comprises:
(i) one is rotated jaw, and it comprises: a cylindrical rotor has tooth on one of this rotor ring surface; With an axle that outwards stretches from another barrel surface, it is connected with synchronizing shaft;
(ii) slip jaw, it comprises a stator, has at the one end that tooth is used for and the tooth that rotates on the jaw is meshed, and the slip jaw also comprises a slip kinematic link and a piston, slip kinematic link one end is connected with stator, and its other end is connected with piston;
(iii) snap, it applies a power to piston, and the tooth that promotes the tooth of slip jaw and rotate jaw forms engagement; And
(iv) conduit, it is used for genlocing device control valve output interface is connected with piston, thereby makes the hydrodynamic pressure in the conduit produce a power, impels the tooth of slip jaw to break away from the tooth that rotates jaw.
2, THR REV synchronization shaft lock fixed system as claimed in claim 1, wherein, genlocing device control valve is positioned at the position away from the genlocing device.
3, THR REV synchronization shaft lock fixed system as claimed in claim 1, wherein, genlocing device control valve is single electromagnetic hydraulic pressure control valve.
4, THR REV synchronization shaft lock fixed system as claimed in claim 1, wherein, the genlocing device also comprises:
(a) shell block of drum type normally, it comprises one first driving channel, a jaw chamber, one second driving channel and a piston chamber; Rotating jaw and be located in the shell block, is to be positioned at first driving channel and partly to extend into the jaw chamber and make axle, and rotor is to be positioned at the jaw chamber; The slip jaw is located in the shell block, is in the jaw chamber and make stator, and the slip kinematic link enters piston chamber by second driving channel from the jaw chamber, and piston is to be in the piston chamber;
(b) connector that shell block is linked to each other with air breathing engine hydraulic type THR REV synchronizing shaft; And
(c) mortise lock of unblanking, when the hydraulic fluid pressure from genlocing device control valve output interface entered piston chamber and further compresses snap, the latch of unblanking was used for the genlocing device is remained on lockset position of coupler.
5, THR REV synchronization shaft lock fixed system as claimed in claim 4, wherein the genlocing device comprises that also being positioned at first Transmission Room is used to support the bearing that rotates jaw around axle.
6, THR REV synchronization shaft lock fixed system as claimed in claim 4 also comprises a plurality of seal rings that are provided with around slip jaw circumference on select location.
7, THR REV synchronization shaft lock fixed system as claimed in claim 4 also comprises a manual unlocking mechanism, and it is used for manual mobile piston and overcomes the power of snap and compress snap and make rotor tooth break away from stator tooth.
8, THR REV synchronization shaft lock fixed system as claimed in claim 4 also comprises an indicator, and it is used for indicating the genlocing device is in locked position or at lockset position of coupler.
9, THR REV synchronization shaft lock fixed system as claimed in claim 4, wherein the connector of genlocing device comprises a nut bolt formula structure, is used for synchronizing shaft is connected with shell block.
10, genlocing device that is used for air breathing engine hydraulic pressure THR REV synchronization shaft lock fixed system, it comprises:
(a) shell block of drum type normally, it comprises one first driving channel; A jaw chamber; One second driving channel and a piston chamber;
(b) connector is used for shell block is connected with air breathing engine hydraulic type THR REV;
(c) one is rotated jaw, and it comprises a cylindrical rotor and an axle, and rotor has rotor tooth on one of its annular surface; Axle is fixed on the rotor, and extends perpendicular to the opposite direction of rotor to the annular surface that has tooth; Rotate jaw and be located in the shell block, and axle is also partly extended in the jaw chamber in first Transmission Room, and rotor is in the jaw chamber;
(d) slip jaw, it comprises a cylindrical stator, a slip kinematic link and a piston; Stator has stator tooth on one of its annular surface, be suitable for being meshed with rotor tooth, one end of slip kinematic link is fixed on the stator and perpendicular to stator and extends to the annular surface opposite direction that has stator tooth, one end of the other end of slip kinematic link and piston is connected, the slip jaw is located at shell block inside, and make stator in the jaw chamber, and the slip kinematic link extends to the piston chamber from the jaw chamber through second driving channel, and piston is in piston chamber;
(e) compression snap, it is placed in a side of piston in the piston chamber, is used for the power that produces towards the direction pushing slip jaw that rotates jaw;
(f) unlock pressure interface, it extends in the piston chamber a side relative with snap at piston by shell block, the unlock pressure interface allows hydraulic fluid pressure to import in the piston chamber, makes the slip jaw further compress snap, thereby rotor tooth and stator tooth are broken away from;
(g) open latch for one, when the hydraulic fluid pressure from the unlock pressure interface was delivered to piston chamber and further spring is locked in compression, it was used to guarantee that the genlocing device is in the enable possition.
11, genlocing device as claimed in claim 10, wherein, the genlocing device comprises that also being arranged in first Transmission Room is used for supporting the bearing that rotates jaw around axle.
12, genlocing device as claimed in claim 10 also comprises a plurality of seal rings that are arranged on the select location place around the slip jaw.
13, genlocing device as claimed in claim 10 also comprises a manual unlocking mechanism, and it is used for manual mobile piston and overcomes the power of snap and compress snap, makes rotor tooth break away from stator tooth.
14, genlocing device as claimed in claim 10 also comprises an indicator, and it is used for indicating the genlocing device is in locked position or at lockset position of coupler.
15, genlocing device as claimed in claim 10, wherein, connector comprises a nut double-screw bolt formula structure, is used for synchronizing shaft is connected with shell block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96111535A CN1077217C (en) | 1996-08-22 | 1996-08-22 | Thrust reverster synchronization shaft lock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN96111535A CN1077217C (en) | 1996-08-22 | 1996-08-22 | Thrust reverster synchronization shaft lock |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1174934A true CN1174934A (en) | 1998-03-04 |
| CN1077217C CN1077217C (en) | 2002-01-02 |
Family
ID=5121147
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN96111535A Expired - Lifetime CN1077217C (en) | 1996-08-22 | 1996-08-22 | Thrust reverster synchronization shaft lock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1077217C (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100424334C (en) * | 2003-10-06 | 2008-10-08 | 埃尔塞乐公司 | Thrust reverser lock comprising locking device |
| CN104603441A (en) * | 2012-04-23 | 2015-05-06 | 萨热姆防务安全公司 | Actuating device for moving a thrust reverser |
| CN104960669A (en) * | 2015-06-23 | 2015-10-07 | 中国航空工业集团公司西安飞机设计研究所 | Engine reverse-thrust control system |
| CN108884784A (en) * | 2016-02-09 | 2018-11-23 | 伍德沃德有限公司 | Trhrust-reversal device actuating |
| CN110466796A (en) * | 2019-07-30 | 2019-11-19 | 中国航发沈阳发动机研究所 | Retracting device is unfolded in a kind of thrust reverser manually |
| CN110466797A (en) * | 2019-07-30 | 2019-11-19 | 中国航发沈阳发动机研究所 | Retracting device is unfolded in a kind of thrust reverser manually |
| CN112824665A (en) * | 2019-11-21 | 2021-05-21 | 中国航发商用航空发动机有限责任公司 | Culvert spray pipe driving device, culvert spray pipe assembly and airflow output area adjusting method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2846377B1 (en) * | 2002-10-25 | 2006-06-30 | Hispano Suiza Sa | ELECTROMECHANICAL THRUST INVERTER FOR PERMANENTLY POSITION CONTROLLED TURBOREACTOR |
| FR2890644B1 (en) * | 2005-09-15 | 2007-11-02 | Aircelle Sa | DYNAMIC SELF-JOINTING HANGING DEVICE |
| EP2870349B1 (en) * | 2012-07-05 | 2016-05-04 | Aircelle | Clutching and declutching mechanism for an embarqued nacelle of a turbofan engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1994007018A1 (en) * | 1992-09-21 | 1994-03-31 | The Boeing Company | Mechanical lock for jet engine thrust reverser |
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1996
- 1996-08-22 CN CN96111535A patent/CN1077217C/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100424334C (en) * | 2003-10-06 | 2008-10-08 | 埃尔塞乐公司 | Thrust reverser lock comprising locking device |
| CN104603441A (en) * | 2012-04-23 | 2015-05-06 | 萨热姆防务安全公司 | Actuating device for moving a thrust reverser |
| CN104603441B (en) * | 2012-04-23 | 2016-02-10 | 萨热姆防务安全公司 | For the actuator of mobile thrust reverser |
| CN104960669A (en) * | 2015-06-23 | 2015-10-07 | 中国航空工业集团公司西安飞机设计研究所 | Engine reverse-thrust control system |
| CN108884784A (en) * | 2016-02-09 | 2018-11-23 | 伍德沃德有限公司 | Trhrust-reversal device actuating |
| CN108884784B (en) * | 2016-02-09 | 2020-12-08 | 伍德沃德有限公司 | Thrust reverser actuation |
| CN110466796A (en) * | 2019-07-30 | 2019-11-19 | 中国航发沈阳发动机研究所 | Retracting device is unfolded in a kind of thrust reverser manually |
| CN110466797A (en) * | 2019-07-30 | 2019-11-19 | 中国航发沈阳发动机研究所 | Retracting device is unfolded in a kind of thrust reverser manually |
| CN112824665A (en) * | 2019-11-21 | 2021-05-21 | 中国航发商用航空发动机有限责任公司 | Culvert spray pipe driving device, culvert spray pipe assembly and airflow output area adjusting method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1077217C (en) | 2002-01-02 |
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Co-applicant after: Hydraulic Institutions Co., Ltd. |
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Inventor after: Mark J. Guckor Inventor after: Mark H. Smith Inventor after: John Jackson Inventor after: Michael E Lunzeerman Inventor after: Joseph Kopercik Inventor after: Henry.Fang Inventor before: Mark J. Guckor Inventor before: Mark H. Smith Inventor before: John Jackson |
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