CN1158454C - Hollow nozzle-actuating ring - Google Patents

Abstract

The present invention relates to a hollow actuating ring (86) and a device, wherein the hollow actuating ring actuates and/or positions adjusting sheets (50) of a jet pipe (14) of an aircraft gas turbin by transferring the actuating load to a large quantity of rotation and expansion adjusting sheet components of the jet pipe (14) from a small quantity of actuators (90); the actuating ring (86) is provided with an approximate annular hollow component which comprises the front wall (110) and the rear wall (114) of coaxial lines axially separated, connecting supporters (118) for connecting the front wall (110) and the rear wall (114) in structures, and an actuating ring reinforcement device (124), wherein the connecting supporters (118) extend between the front wall (110) and the rear wall (114) along the axial direction; the device can reduce the effective bending and twisting length (L) of at least one actuating ring of the actuating rings in the front wall (110) and the rear wall (114) among the connecting supporters (118); the reinforcement structure (124) can disperse a load transferred to one of the front wall (110) and the rear wall (114) from the connecting supports (118) by a structure supporting bar (132) which extends along the diagonal among the connecting supports (118) and one of the front wall (110) and the rear wall (114).

Description

Hollow nozzle-actuating ring

The background of invention

According to the F33657-91-D-2084 contract that US Air army headquaters sign, U.S. government enjoys the right of this invention.

Invention field

The present invention relates generally to the rotating ring of doing of the variable jet pipe of axisymmetric, more specifically is about a kind of hollow rotating ring and device done, and it is used to make the cut-out governing sheet to rotate so that jet pipe blast air and thrust orientation.

Description of Related Art

Military aircraft needs to improve mobility in the application facet of air battle and attack complicated ground target.The aircraft designer is exploring the use that substitutes or strengthen common pneumatic (as hinged joint and aileron) with orientable jet pipe, and this jet pipe can change the blast air of the combustion gas turbine that drives aircraft and the direction of thrust, or with its orientation.Hauer is in the U.S. 4,994, disclosed a kind of axisymmetric variable directed ejector exhaust pipe in No. 660 patents (be used for reference to) herein, provide a kind of its method of device that makes the thrust orientation of axisymmetric contraction/distension type jet pipe be with asymmetric mode can universal ground rotable nozzle the expansion adjustment sheet, in other words, radially and tangentially rotate the expansion adjustment sheet with respect to unoriented jet pipe center line.This adjustment sheet to be to be that pivot rotates as rotating ring, do that rotating ring can move axially or around its level and vertical axis do universal, rotate or swing a limited scope (main) in order to regulate its attitude.In the past, what two-dimensional nozzle used was the directional thrust device, adopted more smooth adjustment sheet to control the pitching of motor power or the direction of vacillating now to the left, now to the right.

Oriented thrust produces tangential and radial load, is called the side load, the side load is to be returned through the actuating ring transmission by various load paths from adjustment sheet, is delivered to engine hood through actuator again.The load that these are huge particularly is applied to bending moment on the actuator shaft by thrust orientation, needs heavy actuator to absorb.Once studied various designs a kind of device is provided, it reduces as far as possible or eliminates the bending moment that is delivered to the side load of actuator and actuator is born owing to radial load from jet pipe.5,174, No. 502 patents of people's such as Lippmeier the U.S. (herein be used for reference to) have disclosed such design, but picture other design, actuating ring still must bear big radial and axial load and bending moment.Actuating ring must have rigidity in case locking system is out of shape under the orientation load, that can cause thrust coefficient loss, orientation angle decreased performance and potential unstability.The flexibility of actuating ring makes it can deflection and distortion under the directed load of jet pipe, thereby has reduced the orientation that can reach with respect to a rigid motion system.This problem owing to be used for makes the actuator quantity of jet pipe orientation few and seem serious more, have three actuators just suitable.This distortion finally causes the reduction of total directional properties.

Attempting to increase the antitorque and problem that the Designer faced flexural rigidity is, actuating ring can with the space generally all be subjected to the restriction of aircraft, engine interior flow channel, nozzle structure and contraction actuating system.When reequiping existing aircraft combustion gas turbine ejector exhaust pipe system with the AVEN jet pipe, this problem bothers especially, because in nondirectional original design, is not provided with or considers actuating ring.Can often only allow a kind of comparatively flexible actuating ring for the actuating ring occupation space.

Two key parameters that influence actuating ring rigidity in existing design are the distance (having cubic effect) between the actuator and the section character of actuating ring.If take three actuators and restricted actuating ring shell and transverse section, the thickness that then increases the actuating ring material can improve the rigidity of actuating ring, but weight has also just increased.

Summary of the invention

In brief, according to one aspect of the present invention, a hollow actuating ring and device are provided, it activates by the rotation expansion adjustment sheet member that will activate load from several (preferably 3) actuator and be delivered to larger amt and/or the adjustment sheet of directed aircraft combustion gas turbine jet pipe, and these rotate expansion adjustment sheet members and can operate directional thrust and change the nozzle exit area.

Actuating ring is substantially hollow loop configuration, the front and back walls that comprises axially spaced coaxial line, the support of between antetheca and rear wall, axially extending and they structurally being coupled together, and actuating ring strengthens structure, and it is effectively crooked and reverse length that this structure can reduce in the front and back walls between supporting the actuating ring of at least one.One embodiment of the present of invention provide an intensifier, and it can scatter the load that is delivered to one of front and back walls from support.Another embodiment provides an intensifier, is supporting and is forming A shape frame at least between one of front and back walls, or have a structure stay that extends along diagonal at least between one of each support and front and back walls.A shape frame can have filleted corner.Some more detailed embodiments of the present invention provide adjustment sheet to activate linkage, and the back ring circumference that they are arranged in this structure structurally is connected on every side and with it, and actuator coupling device also is provided, and they structurally are connected with support.This adjustment sheet activates linkage and actuator coupling device preferably includes some globular hinge elements.

Another more specifically embodiment the part of the incision of constitute to strengthen supporting is provided, these are supported between the front and back walls and axially extend, and further front and back walls are structurally coupled together.Shaped outer cover plate and inner cover plate preferably strengthen structure with antetheca and rear wall, support, actuating ring and strengthen support etc. and form individual construction.Another kind of scheme is that one of annular cover plate can separately form and be connected in this individual construction.One embodiment of the present of invention comprise a jet pipe, and it has some actuating rod, the tapered channel that each actuating rod cuts out in all being passed in and strengthening supporting.Another embodiment comprises some globular hinge heads, in the half-cylindrical breach that each articulated joint is drawn out in all being installed in and strengthening supporting.

In following drawing, described a preferential embodiment; Yet, under the situation that does not deviate from true spirit of the present invention and scope, also can make various other modification and alternative structure.

Advantage

One of advantage of actuating ring and jet pipe actuator is a relatively rigidity of actuating ring among the present invention, and it can will activate from the actuator of minority to load and be delivered to a fairly large number of rotation expanding adjustment sheet member, can not gain in weight the former design and do not resemble.The present invention can also design actuating ring less and be flexible, can be contained in the restricted shell and does not resemble and can gain in weight the former design.Actuating ring of the present invention can design to such an extent that have smaller profile, comprises less radial height, thereby can make whole jet pipe actuating system and jet pipe itself more compact.

Another object of the present invention provides the hollow actuating ring of a rigidity, is used for the rotable nozzle adjustment sheet with the orientation nozzle blast air.Another purpose provides the actuating ring of a rigidity, and it can be contained in the restricted shell.A further object of the invention provides a hollow actuating ring, and its weight ratio is previously used light, and this helps the size of lance system and weight are reduced to minimum.

These purposes and other characteristics and advantage in the narration below the reading and after referring to appended accompanying drawing, just become obvious extraordinarily.

The accompanying drawing summary

Following narration has been explained above-mentioned aspect of the present invention and other characteristics together with accompanying drawing, wherein:

Fig. 1 has the perspective view that the part of the directed ejector exhaust pipe of combustion gas turbine axisymmetric of actuating ring of the preferred embodiment of the invention and device is cut;

Fig. 2 is the enlarged portion cut-away, perspective view of the part of the actuating ring among Fig. 1, shows the embodiment of an intensifier of the present invention;

Fig. 2 A is the amplification partial cut perspective view of the part of the actuating ring among Fig. 1, shows a preferential embodiment's of the present invention single-piece actuating ring intensifier;

Fig. 3 be actuating ring shown in Figure 1 from the forward-looking front view in back;

Fig. 4 is the respectant front view of the past of actuating ring shown in Figure 3;

Fig. 5 is another amplification partial cut perspective view of the part of the actuating ring among Fig. 1.

Preferential embodiment describes

The present invention totally is illustrated among Fig. 1, and comprises an actuating ring 86, and it is as the verge ring of the axisymmetric orientation nozzle 14 in the aircraft combustion gas turbine exhaust section 10.Exhaust section 10 comprises by flowing relation in succession and the pipeline or the engine hood 11 of a fixed-area comprises afterbunring chamber lining 12.With the variable area tract 13 of shrinkage expansion profile shaft symmetry orientation nozzle 14, can be with reference to the patent of aforementioned Hauer.With reference to Fig. 1, jet pipe 14 comprises a contraction section 34, a trunnion 40 and an extending section 48 by flowing relation in succession.Contraction section 34 comprises a plurality of contraction adjustment sheets or homophony nodal plate 50.They along circumference around engine centerline 8, overlapping primary seal 51 be arranged between the inner radial surface of homophony nodal plate 50 adjacent around the circumference and with they sealing engagement.The front end of homophony nodal plate 50 is articulated in engine hood 11 by first articulated joint or U-joint 52.The front end 53 of expansion adjustment sheet or secondary adjustment sheet 54 is articulated in the rear end of homophony nodal plate 50 by two degrees of freedom universal joint 56, and universal joint 56 is in an axial position in the jet pipe 14 that overlaps with trunnion 40 usually.Secondary adjustment sheet 54 is arranged in around the circumference of engine centerline 8, overlapping expansion Sealing or secondary Sealing 55 be arranged between the inner radial surface of secondary adjustment sheet 54 adjacent around the circumference and with they sealing engagement.The throat area of trunnion 40 represents with A8 that generally nozzle exit 44 is usually in the end of secondary adjustment sheet 54, and the trunnion discharge area is generally represented with A9.

A plurality of cam rollers 62 are arranged in the main ring 66, and main ring is moved forward and backward by a plurality of main actuators 70 again, in preferential embodiment four so main actuators are arranged.Variable throat area A 8 is by the action control of the cam roller on the cam face 60 that forms on the back side of homophony nodal plate 50.During operation, the high pressure of exhaust forces homophony nodal plate 50 and secondary adjustment sheet 54 radially outside in the jet pipe, thereby cam face 60 and one of cam roller 62 are kept in touch.The narrow front end of a taper actuator support 76 is installed on the engine hood 11, and main actuator 70 is articulated in the wide rear end of actuator support 76 by a universal spherical joint 74.Main actuator 70 has an actuating rod 73, and actuating rod is connected in main ring 66 by a spherical joint again.

A plurality of guiding actuators 90 (having three in preferential embodiment) are arranged in to equal angles around the circumference of engine hood 11, and to be installed on the actuator support 76 by univesal sphere joint 94 with the same mode of actuator 70.Actuating ring 86 is connected in the rear end of the directed actuating rod 93 of guiding actuator 90 by spherical joint 96.This makes actuating ring 86 move axially and to swing to control its attitude around center line 8.The location or the swing of the secondary adjustment sheet 54 of actuating ring 86 controls.Secondary adjustment sheet 54 is articulated in homophony nodal plate 50 by two degrees of freedom universal joint 56, and carry out pivot by a plurality of corresponding Y shape framves 59 in multivariant mode and control, Y shape frame 59 has operating handle 58a and 58b, secondary actuating ring 86 can be connected in secondary adjustment sheet 54 by operation.Outer adjustment sheet 64 is supported by Y shape frame 59 at least in part and makes to become along the outside of jet pipe and all claims and smooth streamline-shaped.

Operating handle 58a and 58b are connected in actuating ring 86 by three degree of freedom spherical joint 82, and are connected in the rear end of secondary adjustment sheet 54 by spherical joint 84.Operating this linkage can change multivariant rotation change or the orbiting that is converted into secondary adjustment sheet with the attitude of actuating ring 86, thereby each secondary adjustment sheet can be put different angles.Connect the U-shaped swing that operating handle 58a and 58b provide Y shape frame 59 with spherical joint 82, prevent that simultaneously any torsional load transmission that may put on operating handle 58a or 58b from getting back to actuating ring 86.Framework 92 provides a bearing for secondary adjustment sheet 54, and the two ends of framework 92 provide support for joint 84 and 56.

Actuating ring 86 is preferably supported by three axial adjustable actuating ring holder devices 100, is arranged in around the circumference of engine hood 11 to their equal angles, makes actuating ring 86 to be moved axially and universal rotation by directed actuator 90.Axially movable A shape frame 210 usefulness three degree of freedom spherical joints 206 supporting actuating rings 86.Form with spherical joint is articulated in slide block 220 to A shape frame 210 in operating handle 211a and 211b end by U-shaped hinge means 208.Use the spherical joint of operating handle 211a and 211b end to provide the U-shaped rotation, and avoided to put on the transmission of the torsional load of operating handle as A shape frame 210.Slide block 220 can slide along hollow slide bar 226, and slide bar 226 is connected in engine hood 11 by front rack 230 and tail-bracket 236.Actuating ring supporting member 100 allows actuating ring 86 axially to move and swing to change its attitude forward and backward.The more detailed description of actuating ring supporting member 100 can find in 5,174, No. 502 patents of the U.S. that is entitled as " support of mobile jet pipe verge ring " of people such as Lippmeier, and here quoting is for reference.

See Fig. 2 now again, hollow actuating ring 86 is hollow ringwise substantially structures, and the coaxial line antetheca 110 and the rear wall 114 of axially spaced-apart arranged respectively.Connect and support 118 extensions between antetheca 110 and rear wall 114, and they are structurally coupled together.Actuating rod 93 is connected in actuating ring 86 at pedestal 120 places that support 118 by spherical joint 96.Actuating ring intensifier totally by 124 expressions is used for reducing the effective bending of actuating ring of the rear wall 114 between the adjacent supports 118 and reversing length L (also seeing Fig. 3).This is by finishing from supporting 118 load dispersing that are delivered to rear wall 114.Between each support 118 and rear wall 114, form an A shape frame 130.A shape frame 130 provides a structure stay 132 that extends along diagonal between each support 118 and rear wall 114.A shape frame preferably has filleted corner 134.Noting, is through revising from pedestal 120 nearest filleted corners 134, and that is by adding a spacer 138 with acute angle 136 in forming effectively, and it has two fillets 140 in Qi Zijiao 144.

Annular inner cover plate 150 and outer cover plate 152 structurally are connected to the radial inner end 154 and the outer end 156 of corresponding front and rear wall, thereby finish the external structure of hollow actuating ring 86.Annular inner cover plate 150 and outer cover plate 152 structurally also are connected to actuating ring intensifier 124.In preferential embodiment, be made for an individual construction basically with casting or other method with inner cover plate 150 and outer cover plate 152, structure stay 132, support 118, antetheca 110 and rear wall 114 etc. are whole, shown in Fig. 2 A.Can use dewax known in the industry or investment casting.Another method is, inside and outside cover board 150 and one of 152, structure stay 132, support 118, antetheca 110 and rear wall 11 etc., can make one with casting or other method, in the inside and outside cover board 150 and 152 another then made separately, is connected in these component with welding, soldering, diffusion bonding or other connecting means then.Spherical joint 96 usefulness hinge brackets 164 are connected in actuating rod 93 and support 118 base 120, and hinge bracket 164 has two flanges 166 that separate on around, and they are connected in the base of support by two screws 168 that separate on around.

As shown in Figure 1, operating handle 58a and 58b are connected in the spherical joint 82 of actuating ring 86,, provide an adjustment sheet to activate linkage by the pairing 174 of lug frame 176, this is illustrated among Fig. 3 in more detail, and wherein each lug frame has parallel lug to this place's extension certainly.Lug frame 176 is arranged in around the circumference of rear wall 114, and structurally is connected with it, and their all lugs 178 are parallel to a radius R that extends from center line 8, and divide a central angle A between lug frame 176 equally, and the initial point of central angle A is in centerline.Each pairing of lug frame 176 is connected in actuating ring 86 with one of corresponding operating handle 58a and 58b.

Fig. 5 is illustrated in the actuating ring 86 position of the shape that the quilt that forms cuts out, and illustrates tapered channel 180 and semi-cylindrical shaped breach 182.Tapered channel 180 provides leeway (being shown in Fig. 1) for the actuating rod 73 of main actuator 70, and it is illustrated among Fig. 5 in more detail.Half-cylindrical breach 182 provides a zone for spherical joint 206 is installed, and spherical joint 206 is connected in actuating ring 86 with A shape frame 210, and the latter is illustrated among Fig. 2 in more detail.Strengthen supporting 300 axially extends between the front and rear wall 110 and 114 at the location about place of these shapes that cut out respectively.Shape that is cut out such as tapered channel 180 and half-cylindrical breach 182 are preferably in strengthens supporting 300 middle formation own.Usually can reduce the place of the intensity of actuating ring 86 at these bodies that cut out, strengthen supporting 300 and help structurally to strengthen it, make the diameter of jet pipe can design lessly.The profile of actuating ring and radial height can design lessly, thereby allow whole jet pipe actuating system and jet pipe itself more compact.Reinforcement support 300 the most handy castings or other method are made with inner cover plate 150, structure stay 132, support 118 and front and rear wall 110 and 114 etc. and are made an integral body.

Though preferential embodiment of the present invention has been done sufficient description, thereby has explained its principle, yet should be understood that, can make various modifications or replacement to preferential embodiment as long as within the invention scope defined in the claim of appendix.

Claims (9)

1. hollow actuating ring (86) that is used for rotating synchronously aircraft combustion gas turbine jet pipe (14), this actuating ring (86) comprising:

A general toroidal hollow unit, it has axially spaced antetheca (110) and rear wall (114);

Between above-mentioned front and rear wall (110 and 114), axially extend and be connected support (118), it is characterized in that what they structurally coupled together:

An actuating ring intensifier (124), be used for reducing supporting in the actuating ring front and rear wall (110 and 114) between (118) the effective bending of at least one and reversing length L in described connection, described intensifier (124) comprises that one is used for being delivered to the device of the load dispersing of one of front and rear wall (110 and 114) from connection support (118).

2. a kind of hollow actuating ring (86) described in claim 1 is characterized in that described intensifier (124) is included in connection and supports the A shape frame that forms between at least one in (118) and the front and rear wall (110 and 114).

3. a kind of hollow actuating ring (86) described in claim 1, it is characterized in that described intensifier (124) comprises at least one structure stay (132), it connects to support between one of (118) and front and rear wall (110 and 114) at each extends along diagonal.

4. a kind of hollow actuating ring (86) described in claim 2 is characterized in that described A shape frame has filleted corner (136).

5. a kind of hollow actuating ring (86) described in claim 2, it is characterized in that also comprising annular inner cover plate (150) and outer cover plate (152), they with inside and outside wall (110 and 114) separately radially in outer end (154 and 156), be connected support (118) and actuating ring intensifier (124) structurally couples together.

6. a kind of hollow actuating ring (86) described in claim 5 is characterized in that described annular inside and outside cover board (150 and 152) and front and rear wall (110 and 114), is connected support (118) and actuating ring intensifier (124) forms an integrated member.

7. a kind of hollow actuating ring (86) described in claim 6, it is characterized in that also comprising the adjustment sheet connection set, they are arranged in around the circumference of rear wall (114) of described member, and structurally couple together with it, and comprise actuator coupling device, it be connected support (118) and structurally couple together.

8. a kind of hollow actuating ring (86) described in claim 7, it is characterized in that also being included in and strengthen supporting the shape that cuts out (180) that forms in (300), strengthen being supported between the front and rear wall (110 and 114) axially extension and they are structurally coupled together.

9. a kind of hollow actuating ring (86) described in claim 8 is characterized in that it is arranged in the jet pipe (14) with some actuating rod (93), and each actuating rod is passed incision and strengthened supporting (300) interior tapered channel (180).

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