DE2410161C3 - Device for adjusting the gas outlet cross-section of a thrust nozzle, which is assigned to a beam deflection device consisting of rotatable pipe sections - Google Patents

Description

The invention relates to a device for adjusting the gas outlet cross-section of a thrust nozzle, those at the exit end of the furthest downstream

arranged pipe section one of at least two adjoining a stationary jet pipe, rotatably attached to each other mounted pipe sections existing beam deflector.

There are through the DT-AS 20 56 088 uad through the DT-OS 2109 205 and the US-PS 37 76 467 beam deflection devices known, which consists of at least two adjoining a stationary jet engine jet pipe, rotatably attached to each other are pipe sections to the exhaust jet of a jet engine for an airplane e.g. B. from a horizontal to a vertical outflow direction for optional horizontal or vertical flight of the aircraft or around spatially changeable outflow directions of the Exhaust jet ζ. B. for quickly executable, diverse To enable control maneuvers of the aircraft.

In the known beam deflection devices mentioned, the one should be furthest downstream arranged rotatable pipe section with an adjustable thrust nozzle for the purpose of adapting their gas ^ outlet cross-section equipped to the changing thermodynamic conditions when the afterburning is switched on being.

However, these known jet deflection devices do not have devices for adjusting the thrust nozzle removable.

The known cases mentioned at the beginning do not deal with the problem of a functional one To create thrust nozzle cross-section adjustment, from the stationary engine jet pipe via the rotatably mounted on one another, adjustable by the same or different angles of rotation away on the thrust nozzle, especially taking into account almost any spatial adjustment Beam deflection angle.

From US-PS 33 19 892 a beam deflector for aircraft is known, which also has a Device for adjusting the gas outlet cross-section is assigned to a thrust nozzle; the exhaust nozzle is in this known solution at the outlet end of an axis of rotation extending transversely to the gas flow arranged from a horizontal in a rearwardly downwardly inclined position pivotable pipe part.

The pivotable tubular part here engages around an end section that is slightly bulged in a spherical shape on the outlet side a stationary engine jet pipe.

A change in the gas outlet cross-section takes place in the present known solution by means of a movable parallel to the longitudinal axis of the pivotable pipe part and pivotable at the same time with this, on the adjustable body articulated on the nozzle flaps.

Based on a thrust nozzle adjustment that takes place here from the stationary engine jet pipe can the pipe part with the nozzle z. B. only be pivoted backwards after the nozzle flaps in the position of the pivotable pipe part that is decisive for horizontal flight have previously been moved to the gas outlet area, which is enlarged for the post-combustion case, while it is in in practice it is often desirable to switch the afterburner on only after the desired end position has been reached Switch on the beam deflector so that the gas outlet surface is only in the desired end position the beam deflector would have to be enlarged in view of the post-combustion case.

In addition, in the present known solution, the pipe part with the thrust nozzle is only in one Level can be pivoted at a relatively limited angle of inclination. A contribution to the solution the thrust nozzle cross-section adjustment problem for a beam deflection device formed from rotatable blanks according to the type mentioned above is not provided on the basis of the present known solution

The invention is based on the object of eliminating the known disadvantages and

ίο a device according to the type mentioned create the individual twisting and swiveling from the stationary engine jet pipe the pipe parts taking into account thrust nozzle cross-section adjustment

Furthermore, the thrust nozzle cross-section adjustment device should have a relatively low structural design Characterized by effort and relatively low weight; also due to the thrust nozzle cross-section adjustment device the installation volume required by the beam deflector, e.g. B. in the aircraft tail or within an engine nacelle, can be kept as low as possible.

To solve the problem, the invention is characterized by a stationary jet engine jet pipe arranged thrust nozzle adjustment motor for driving one on the outer periphery of the stationary Jet pipe and / or on the outer circumference of the first rotatable pipe section opposite these rotatably mounted first ring-shaped gear rim

} o carrier, which has two ring gears, one of which is intended for the engagement of a gear driven by the thruster variable displacement motor, while the other ring gear is intended for the engagement of a gear attached to the upstream end of a flexible shaft, one on the downstream end of the outer periphery of the first rotatable tube section rotatably mounted flexible shaft gearwheel engages in a second annular ring gear carrier rotatably mounted on the outer periphery of the inlet end of the second rotatable tube section, the rotational movement of which can be converted into an adjustment movement of the thrust nozzle flaps to increase or decrease the gas outlet cross-section of the thruster nozzle is.

In this way, after the desired jet exit direction has been reached, the thrust nozzle can be adjusted to the desired gas exit cross-section.
In order to prevent the thrust nozzle adjustment motor from always rotating when the jet deflecting device is adjusted, a releasable coupling should be connected according to the invention to the drive connection of the thrust nozzle adjustment motor with the first ring-shaped ring gear carrier.

Starting from a beam deflection device, in which the first and the second rotatable pipe section of the Beam deflection device each via a drive motor and located on the stationary engine jet pipe Gear drives can be adjusted independently of one another by the same or different angles of rotation, is further proposed according to the invention that for the purpose of one of the respective tube adjustment an electronic control device is provided for undisturbed thrust nozzle cross-section adjustment,

(15 which the respective speed setpoint of the thrust nozzle adjustment motor from the superposition of the respective speeds and directions of rotation of the rotatable Pipe sections determined.

5 6

Taking into account the already known F i g. 5 the interaction of the adjustment assembly

th beam deflection device according to DT-OS 21 09 205 according to FIG. 4 explanatory details with the exhaust nozzle

or the US-PS 37 76 467 proposed drive on the second rotatable pipe section, the better

and transmission elements for pipe adjustment must be within the understanding of the nozzle flap adjusting system partially

Frame of an expedient embodiment according to FIG. 5 is shown cut along the longitudinal center axis

the invention is the drive power of the thrust nozzle,

Servomotor together with that of the second Fig. 6 the side view of a beam deflection device

Drive motor initially a common planning according to FIG. 1 and 2 with a thrust nozzle cross

ten wheel gears are supplied, which one of the cutting adjustment drive in a second embodiment

the respective pipe wrapping unaffected form,

Distribution of power for the thrust nozzle cross-section adjustment Fig. 7 shows the side view of a beam deflection device on the one hand and for the rotation of the second device according to FIGS. 1, 2 and 6 with a thrust nozzle transverse pipe section on the other hand worried, with the cutting adjustment drive in a third embodiment, Thrust nozzle adjustment motor-driven power train F i g. 8 is a side view of a beam deflection device Planetary gear with the thrust nozzle device according to FIG. 7, but with a thrust nozzle cross-section adjustment provided first ring-shaped sectional adjustment drive is engaged in a fourth embodiment, the ring gear carrier, while the form,

second drive motor driven power train F i g. 9 compared to FIG. 2 enlarged and more detailed

of the planetary gear with the first ring gear shown details of the transmission device

of the ring-shaped ring gear carrier of the differential counter 20 for the thrust nozzle cross-section adjustment and the

drive is engaged. Rotation of the second rotatable pipe section of

In this way, at any time, including during the beam deflection device and

the tube adjustment and from this completely Fig. 10 compared to Fig. 2 enlarged and practical

unaffected, the thrust nozzle on the desired details shown on the right here on the side

Gas outlet cross-section can be adjusted. 25 fixed jet pipe arranged planetary

A more compact gear arrangement results in gear drives with the direct assignment of the

the last-mentioned embodiment according to the invention drive and gear elements for rotating the

further in that the first annular first rotatable pipe section of the beam deflection

Toothed ring carrier for the thrust nozzle cross-sectional direction.

Position on the outer circumference of the ring-shaped ring gear 30 from F i g. 1 is the broken end of one to one carrier of the differential gear is mounted. Turbines for not shown in the drawing a particularly useful type of jet pipe 1 belonging to the thrust nozzle jet engine Senquiertelsverstellung sees the invention further apparent, at which two against each other Connect twistable pipe sections 2, 3 to the outer circumference of the second rotatable pipe. the Cut at least one bevel gear with which the 35 second pipe section 3 carries a at the outlet end Rotational movement of the second to the thrust nozzle cross adjustment thrust nozzle 4. The first pipe section 2 is over Sectional adjustment provided annular tooth - a perpendicular to the extended engine center axis 5 wreath support on flexible shafts on several rotating pivot bearings 6 at the outlet end of the Reduction gear is transmitted, each having an engine jet pipe 1 rotatably arranged. the Ball screw and thus an associated recirculating ball 40 pipe sections 2, 3 are opposite to the Drive nut, the respective ball screw extended engine center axis 5 inclined rotary nuts to an axially displaceable nozzle adjustment shirt bearing 7 connected to each other. Coaxial to extend which is one to one by means of rollers along the curved engine center axis 5 ger guide cams of the nozzle flaps in the sense of an aircraft fuselage tail belonging engine cowling 8 Enlargement or reduction of the nozzle outlet 45 is arranged, which is correspondingly tapered cross-section can be moved in a further, but separate from this one

On the basis of the drawing, embodiments of the cladding section 9 are continued, which via holding

the invention explained below; It shows elements 9 'with the second pipe section 3

F i g. FIG. 1 shows the side view of a beam deflection device connected in FIG. 1 with solid lines

device in two different end positions, with 50 positions of the second pipe section 3 and the

further beam deflection angles schematically indicated thrust nozzle 4, that is to say in the most frequently used end position

are, of cruise or high-speed flight, thus forms

F i g. 2 shows the side view of the beam deflecting device, the cladding section 9 is a flow-favorable one

according to Fig. 1, but shown enlarged, with continuation of the engine cowling 8. Is exemplary

Assignment to the pipe and exhaust nozzle cross-section references, the second pipe section 3 with the exhaust nozzle 4 in

position of provided drive devices and ver the end position shown in dashed lines reaches a

Actuating gear, outlet direction of the gases inclined downwards to the rear

Fig. 3 enlarged details - to be generated here, then the one with the second

Angular gear and flexible shafts - cladding section firmly connected to the second pipe section 3

rotatable pipe section for transmission of the engine 60 9 moved forward from the top of the engine cowling 8,

drive torque on the thrust nozzle, but at the bottom in the free space between the

FIG. 4 further enlarged details of the inner wall of the engine cowling 8 on the one hand,

for transmitting the engine drive torque to and also the jet pipe 1 and the first pipe section 2

the thrust nozzle, here one on the second rotatable on the other hand, moved. The one shown in dashed lines

Pipe section arranged, with the devices according to position 65 of the second pipe section 3 and the F i g. 3 non-positively connected adjustment assembly thrust nozzle 4 further identifies the largest possible

(Reduction gear, spindle, ball nut) additional beam deflection angle between the extended drive

ternd, plant center axis 5 and the longitudinal center axis 10 of the

second pipe section 3 and the nozzle 4. Positions 11, 12 and 13 (Fig. 1) give more possible angles of inclination between the extended engine center axis 5 and the common longitudinal center axis 10 of the second pipe section 3 and the thrust nozzle 4 digestion.

The angle of inclination <x, tx ' and ß, ß' of the longitudinal center axis 10 sketched out by way of example can be assumed to be located in the plane of the drawing and can thus be achieved by simultaneously rotating the pipe sections 2, 3 in opposite directions by the same angle of rotation, whereby at the same time the second pipe section 3 with the thrust nozzle 4 and thus from which the gas jet exiting from this would be pivotable in a vertical plane passing through the extended engine center axis 5.

The maximum achievable beam deflection angle tx or α ', which the extended engine center axis 5 includes with the common longitudinal center axis 10 of the second pipe section 3 and the thrust nozzle 4, depends, among other things, on the selected angle of inclination γ, which the inclined plane 14 of the pivot bearing 7 with a through the center 15 of the pivot bearing 7 and the extended engine axis 5 through vertical transverse plane 16 includes, so that the value of the angle

) '= y.

With an assumed angle of inclination of γ = 15 °, the angle α can be assumed to have a value of 30 ° and with an assumed angle of inclination of γ = 45 °, the angle tx can be assumed to be 90 °, for which purpose the extended cruising position of the device ( Fig. 1) starting, the pipe sections 2, 3 would each have to be rotated by 90 ° against each other at the same time.

Furthermore, the requirement of a gas jet that can be spatially pivoted in any direction is to be met can be, if necessary, with a planned arrangement in the aircraft fuselage tail to replace existing elevator and rudder units in the conventional manner in aircraft. This one Requirement goes hand in hand with the condition that the gas jet conveyed by the engine not only in the To pivot drawing plane (F i g. 1), but also in addition z. B. to the side of this drawing plane or To pivot away from the extended engine axis 5 obliquely backwards, downwards or upwards, it is provided, the pipe sections 2, 3 with different angles of rotation and adjustment speeds to rotate against each other and to provide a drive device for the pipe sections 2, 3 (Fig. 2), which rotations or angles of rotation of the separate from one another with relatively simple means Pipe sections 2.3 allows

For this purpose, a first and a second drive motor 17 and 18 are located on the outside of the jet pipe 1 attached These can be air motors, hydraulic motors, or electric motors. the The first drive motor 17 drives the first pipe section 2 via a gear 19, namely by engaging a Gear 20 in one on the outer circumference of the first pipe section 2 in the area of its inlet side End arranged ring gear 21. The second drive motor 18 drives with the interposition of a in its effect later explained in more detail planetary gear P and a differential gear 22 and a transmission device coupled to this and guided over the pivot bearing 7

23 to the second pipe section 3.

This transmission device 23 is

here around a flexible shaft with a first shaft end guided parallel to the engine center axis 5

24 and one of the plane 14 (FIG. 1) of the pivot bearing 77 associated second shaft end 25. For mounting and storage of the flexible shaft are shaft holders attached to the outside of the first pipe section 2

ίο 27, 27 'provided. The ring gear 31 of a first annular ring gear carrier 30 of differential gear 22 is for meshing one with the second Drive motor 18 via the planetary gear coupled gear 33 is provided. The ring gear 32 is for the engagement of a with the first shaft end 24 of the transmission device 23 connected Gear 34 is provided. The gears 33, 34 on the one hand and the ring gears 31, 32 on the other hand can expediently each have the same diameter and

To be assigned to the number of teeth or the transmission ratios of gear 33 to gear rim 31 or gear 34 to gear rim 32 can be selected to be the same. The transmission ratio between the gear 28 located on the second shaft end 25 and the ring gear 29 located at the inlet end of the second pipe section 3 can be selected to correspond to that of the gears 33, 34 to the ring gears 31, 32. To achieve a circular pivot bearing 7 in the case of FIG. 1, the angles of inclination γ of the plane 14 of this pivot bearing 7 described by way of example, the cross-sections of the pipe sections 2, 3 are slightly elliptical, at least in this bearing area.

Through the in F i g. 2 described arrangement and structure of the differential gear 22 and the transmission device 23, the pipe sections 2, 3 are at the same time common to the same or different Adjustable angle of rotation. Furthermore, the pipe sections 2, 3 are completely independent of one another adjustable, namely with only the desired rotation of the second pipe section 3 and stationary first pipe section 2 caused no forced movement of the first drive motor 17, as well as is the case with the second pipe section 3 at a standstill and only the desired twisting of the first Pipe section 2 no forced movement of the second drive motor 18 is caused.

In order to illustrate the additional drive for adjusting the cross section of the thrust nozzle 4, the for this purpose required drive or gear elements in Figure 2 for the sake of simplicity in the plane of the drawing projected shown.

For simultaneous pipe and thrust nozzle cross-section adjustment, the drive power of the thrust nozzle adjusting motor 35, together with that of the second drive motor 18, is first fed to the common planetary gear P , which is intended to enable a power distribution unaffected by the respective pipe adjustment for the thrust nozzle cross-section adjustment on the one hand and for the rotation of the second pipe section 3.

It can also be the case with the thrust nozzle adjustment motor 35 be an air, hydraulic or electric motor. To adjust the thrust nozzle 4, the thrust nozzle drives

6s senverstellmotor 35 via a shaft 36 to a gear 37 located on this. The gear wheel 37 engages in the toothing of a further ball bearing mounted on an inner shaft 38 of the planetary gear transmission P.

Gear 39, which is also designed as a carrier of planet gears 40 (pinions). The pinions 40 engage on the one hand in the internal toothing of an outer planetary gear 41, which has a shaft extension 42 is connected to a gear 43, which is in the first ring gear 44 of a first, for thrust nozzle cross-section adjustment provided annular ring gear carrier 45 engages.

On the other hand, the pinions 40 mesh with the teeth of a sun gear 46, which is connected to the inner shaft 38 connected is.

Another gear 47, which is seated further forward on the inner shaft 38, meshes with one on the Output shaft 48 of the second drive motor 18 seated gear 49, wherein on this output shaft 48 also the gear 33 is seated, which is in the first ring gear 31 of the first ring-shaped ring gear carrier 30 of the differential gear 22 engages.

To adjust the cross section of the thrust nozzle 4, there is further on the outer circumference of the first pipe section 2 a flexible transmission device 50, here in the form of a flexible shaft 51, via bearing body 52, 53 arranged so as to be rotatable in the circumferential direction.

A gear 54 located on the upstream shaft end of the flexible shaft 51 meshes with the second Toothed ring 55 of the first ring-shaped toothed ring carrier 45 for the thrust nozzle cross-section adjustment.

Furthermore, the torque generated by the thrust nozzle adjustment motor 35 is then passed on via the flexible shaft 51 to the second ring-shaped ring gear carrier 56, which is rotatable in the circumferential direction on the outer circumference of the second pipe section 3, by inserting a gear 57 located on the downstream end of the shaft of the flexible shaft 51 into the first ring gear 58 of the second, provided for the thrust nozzle cross-section adjustment ring-shaped ring gear carrier 56 engages.

A gear 60 engaging in the second ring gear 59 of the second ring-shaped ring gear carrier 56 leads to an angular gear 61 (FIG Gear axis rotations in the same direction (arrow F) running essentially transversely to the longitudinal axis 10 of the second pipe section 3 are converted and transmitted to a plurality of flexible shafts 62.

The flexible shafts 62 are arranged in plural on the outer periphery of the second pipe section 3 Nozzle adjustment assemblies 63 in connection (Fig. 4).

The nozzle adjustment assemblies 63 each contain - from left to right - a reduction gear 64 driven by the flexible shafts 62, which drives a ball screw 65 and thus adjusts a recirculating ball nut 66 mounted on it , which is attached to the nozzle adjustment shirt via a pull or push rod 67 68 articulated attacks

The elements 64, 65, 66, 67 are each suspended elastically between lateral support rods 69, 70 which are flanged downstream at the end of the second pipe section 3 and upstream in turn are also elastically suspended from holders 71,72 (FIG. 3) which the latter are attached to a sleeve 73 , which envelops the gear mechanism located in the area of the pivot bearing 7 ( FIG. 2) or on the outer circumference of the inlet end of the second pipe section 3 in a dust-tight manner.

A similar cuff 73 '(FIG. 9) can also be used also provided to cover the gear mechanism located on the outer circumference of the first pipe section 2 being.

FIG. 5 then shows the example of a nozzle flap 80 which is pivoted into the exhaust gas flow as far as possible End position for the smallest nozzle outlet cross-section.

The distance χ then characterizes the greatest possible adjustment path of the nozzle adjustment shirt 68 in order to be able to move all nozzle flaps 80 from the end position of the thrust nozzle 4 selected for the smallest gas outlet cross section into the end position selected for the largest gas outlet cross section - or vice versa.

To adjust the nozzle flaps 80 of the thrust nozzle 4, the nozzle adjustment shirt 68 is further supported by rollers 81 can be moved along curved guide cams 82 of nozzle flaps 80. As a result of the within the Second pipe section 3 of the prevailing gas pressure, the nozzle flaps 80 with the guide cams 82 pressed against the rollers 81.

Using the same reference symbols for essentially compared to FIGS. 1 to 5 unchanged 6, 7 and 8 illustrate further possible modifications for the thrust nozzle adjustment drive.

It would also be assumed here that the in F i g. 2 explained adjustment drive for the pipe sections 2, 3 is not binding, just as the assignment of the planetary gear set P contained in FIG. 2 is not mandatory.

So if one assumes that in the embodiments according to FIGS. 6, 7 and 8, an adjustment drive system for the pipe sections 2, 3 according to FIG. 2 or according to the German Auslegeschrift 20 56 088 is based - however without using a planetary gear transmission P (Fig. 2) or an electronic control device mentioned at the beginning - the thrust nozzle 4 can then always be actuated by means of the thrust nozzle adjusting motor 35 after the desired beam exit direction has been set beforehand.

In order to prevent the in the F i g. 7 and 8 on the drive side directly via the shaft 74 and the Gear 43 with the first annular gear carrier provided for adjusting the thrust nozzle cross-section 45 coupled thrust nozzle adjustment motor 35 is rotated when adjusting the pipe sections 2, 3, can - according to FIG. 6 - a clutch 75 can be connected in the shaft 74, which is only used for thrust nozzle cross-section control a non-positive connection of the thrust nozzle adjustment motor 35 with the associated Adjusting drives brings about.

The first annular ring gear carrier 45 provided for adjusting the thrust nozzle cross-section can furthermore be arranged directly on the outer circumference of the inlet-side end of the first pipe section 2 (FIG. 6) or directly on the outer circumference of the outlet-side end of the engine jet pipe 1 (FIG. 7) or on the rotary bearing 6 - between the outlet opening of the jet pipe 1 and the inlet opening of the first pipe section 2 (Fig. 8).

Different from the thrust nozzle adjustment drive system according to Fig. 2 and 6, the transmission device for the motor drive torque of the first, 45, onto the second annular ring gear carrier 56 provided for adjusting the thrust nozzle cross-section

11 12

two pen, each coupled via a spherical socket joint 76, on the second pipe section 3, a different device

Shaft parts 77,78 are formed (Fi g. 7 and 8). device can be provided to the rotational movement of the

The second ring-shaped gear carrier is provided with the second for the thrust nozzle cross-section adjustment.

56 from can then in the exemplary embodiments according to the annular ring gear carrier in a pressure

6, 7 and 8 the remaining thrust nozzle cross-section adjustment or pulling movement for the nozzle cross-section adjustment

position in the to F i g. 3, 4 and 5 already explained to convert.

respectively. For example, it would be conceivable to use the angular gear on

Instead of the second rotatable pipe section, which can be pivoted about transverse axes, via lever rods

The nozzle flaps of the nozzle 4 could, for. B. to couple the same with the nozzle flaps or cias from

mig at the outlet end of the second Rohrah- io second ring-shaped ring gear carrier 56 for the

Section 3 distributed torque generated to reduce the thrust nozzle cross-section adjustment

Gas outlet cross-section along a cone jacket to suitable hydraulic or pneumatic components

downstream in the gas jet movable or displaceable adjusting members, which the thrust nozzle

re nozzle flaps be provided. cross-section adjustment required adjustment

Furthermore, instead of 15, torque can then be generated in the present case.
from the Fi g. 4 and 5 adjustable assembly

See S sheet drawings

Claims (7)

Patent claims: 1. Device for adjusting the gas outlet cross-section an exhaust nozzle located at the exit end of the most downstream Pipe section one of at least two adjoining a stationary engine jet pipe, rotatably attached to each other mounted pipe sections existing beam deflector, characterized by a thrust nozzle adjustment motor arranged on the stationary jet pipe (1) (35) for driving one on the outer circumference of the stationary jet pipe (1) and or or on the outer circumference of the first rotatable Rohrabscbnitts (2) with respect to this rotatable mounted first annular ring gear carrier (45), which has two ring gears (44, 55) of those of the one (44) for the engagement of a gear driven by the thrust nozzle adjustment motor (43) is provided, while the other ring gear (55) for the engagement of one on the upstream End of a flexible shaft (51) attached gear (54) is provided, wherein a on downstream end of the rotatable on the outer circumference of the first rotatable pipe section (2) Bearing flexible shaft attached gear (57) in one on the outer circumference of the inlet side End of the second rotatable pipe section (3) rotatably mounted, second ring-shaped gear carrier (56) engages, the rotational movement of which is converted into an adjusting movement of the Thrust nozzle flaps to enlarge or reduce the gas outlet cross-section of the thrust nozzle (4) is convertible. 2. Apparatus according to claim 1, characterized in that in the drive connection of the Schubdüsenverstellniotors (35) with the first annular ring gear carrier (45) a detachable Clutch (75) is switched. 3. Apparatus according to claim 1, woüei the first and the second rotatable tube section of the beam deflector independently of one another via a drive motor and gear transmission arranged on the stationary jet pipe the same or different angles of rotation are adjustable, characterized in that for Purpose of a thrust nozzle cross-section adjustment unaffected by the respective pipe adjustment an electronic control device is provided, which the respective speed setpoint of the Thrust nozzle adjustment motor from the superposition of the respective speeds and directions of rotation rotatable pipe sections (2,3) determined. 4. The device according to claim 1, wherein two drive motors are provided on the stationary jet engine jet pipe, of which the first directly drives the first pipe section rotatably mounted on the fixed jet pipe via a gear drive, while the second drive motor via at least one differential gear unaffected by the rotary movement of the first pipe section and drives a second rotatable pipe section fts connected to the first pipe section via a transmission device coupled to this, the transmission device being guided over the pivot bearing between the first and second pipe section, and further the differential gear consisting of a first, coaxial to the longitudinal axis of the stationary jet pipe on the outer circumference of the first pipe section rotatably mounted, ring-shaped ring gear carrier, which has two ring gears, one of which is provided for engagement in a gear coupled to the second drive motor, while the other is provided for engagement with a gear which is attached to the upstream end of a rotatably mounted on the outer circumference of the second rotatable pipe section shaft of the transmission device, which with a gear attached to its downstream end in one on the circumference of the inlet end of the second rotatable pipe section engages, characterized in that the drive power of the thrust nozzle adjustment motor (35) together with that of the second drive motor (18) is initially fed to a common planetary gear (P) , which has a power distribution unaffected by the respective pipe adjustment for the thrust nozzle cross-section adjustment on the one hand and for the rotation of the second pipe section (3) on the other hand, and that in this case the power train of the planetary gear driven by the thrust nozzle adjustment motor with the first r ring-shaped ring gear carrier (45) is in engagement, while the power train of the planetary gear drive driven by the second drive motor (18) is in engagement with the first ring gear (31) of the ring-shaped ring gear carrier (30) of the differential gear (22). 5. Apparatus according to claim 4, characterized in that the first annular ring gear carrier (45) for adjusting the thrust nozzle cross-section on the outer circumference of the ring-shaped ring gear carrier (30) of the differential gear (22) is mounted. 6. Device according to one or more of the preceding claims, characterized in that that on the outer circumference of the second rotatable pipe section (3) at least one bevel gear (61) is arranged, with which the rotary movement of the second intended for thrust nozzle cross-section adjustment annular ring gear carrier (56) via flexible shafts (62) to several reduction gears (64) is transmitted, each having a ball screw (65) and thus an associated one Drive the recirculating ball nut (66), whereby the respective recirculating ball nut is connected to an axially displaceable Attack nozzle adjustment shirt (68), which by means of rollers (81) along curved guide cams (82) of the nozzle flaps (80) in the sense of an enlargement or reduction of the nozzle outlet cross-section is movable. 7. Apparatus according to claim 1, characterized in that the flexible shaft of the transmission device of the thrust nozzle adjustment system has two shaft parts (77, 78), which by a Ball socket joint (76) are coupled to one another.