CN112276539B - Device and method for screwing nut of aircraft engine - Google Patents
Device and method for screwing nut of aircraft engine Download PDFInfo
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- CN112276539B CN112276539B CN201910675805.9A CN201910675805A CN112276539B CN 112276539 B CN112276539 B CN 112276539B CN 201910675805 A CN201910675805 A CN 201910675805A CN 112276539 B CN112276539 B CN 112276539B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/04—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
- B23P19/06—Screw or nut setting or loosening machines
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Abstract
The invention relates to a device and a method for screwing nuts of an aircraft engine, wherein the device comprises: the screwing component (1) comprises a screwing head (11), a second clamping part (111) is arranged on the outer side wall of the end part of the screwing head (11), and the second clamping part (111) is matched with the first clamping part (51) so as to be screwed after the screwing head (11) extends into an inner hole of the nut (50); a support member (3) fixed to a casing of an engine; the anti-torsion component (2) is fixed with the rotating shaft assembly, and the anti-torsion component (2) is fixed with the supporting component (3); the rotary driving part (5) is used for driving the screwing part (1) to rotate; and the linear driving part (7) is used for driving the screwing part (1) and the rotating driving part (5) to integrally move along the axial direction so as to enable the screwing head (11) to extend into or be separated from the inner hole of the nut (50). The device is suitable for screwing the nut of the aircraft engine and can improve the assembly efficiency of the nut.
Description
Technical Field
The invention relates to the technical field of assembly of aero-engines, in particular to a nut screwing device and method for an aero-engine.
Background
A locking nut needs to be installed in the assembly process of an aircraft engine fan unit body and used for locking the fan unit body, the nut is large in diameter and large in requirement on tightening torque and is located in a deep cavity of an engine, a special tool needs to be designed for tightening, and meanwhile the nut needs to ensure that the spline phase of an inner ring of the nut is the same as that of a locking sleeve after the torque requirement is met, so that the locking sleeve can be inserted into the nut for locking, and whether the locking sleeve rebounds in place needs to be measured. Based on above-mentioned demand, need design an aeroengine nut and screw up device.
Disclosure of Invention
The embodiment of the invention provides a device and a method for screwing an aero-engine nut, which can improve the assembly efficiency of the aero-engine nut.
In order to achieve the above object, an embodiment of the present invention provides an aircraft engine nut tightening device, in which a nut is mounted on a rotating shaft assembly of an engine, an inner hole of the nut is provided with a first engaging portion, and an axial direction of the nut in a mounted state coincides with an axial direction of the engine, the tightening device including:
the screwing component comprises a screwing head, the outer side wall of the end part of the screwing head is provided with a second clamping part, and the second clamping part is matched with the first clamping part so as to be convenient for screwing after the screwing head extends into the inner hole of the nut;
a support member fixed to a casing of an engine;
the anti-torsion component is fixed with the rotating shaft assembly and the supporting component so as to fix the rotating shaft assembly relative to the casing;
the rotation driving part is used for driving the screwing part to rotate; and
and the linear driving part is used for driving the screwing part and the rotating driving part to integrally move along the axial direction so as to enable the screwing head to extend into or be separated from the inner hole of the nut.
In some embodiments, the nut is locked by a locking sleeve arranged in the rotating shaft assembly in a screwed state, and one end of the locking sleeve is provided with a fifth clamping part;
when the nut is screwed in place, one end of the locking sleeve extends into the inner hole of the nut under the action of the first return spring, and the fifth clamping part is matched with the first clamping part for circumferential limiting;
when the nut needs to be screwed, the screwing part is used for extending into an inner hole of the nut from one end of the nut, which is far away from the locking sleeve, and ejecting the locking sleeve.
In some embodiments, the screwing head, the torsion resistant member, the support member and the rotation driving member are arranged in order in the axial direction;
the screw member further includes a dowel having a first end connected to the screw head and a second end connected to the output shaft of the rotary drive member through the torsion member and the support member, the screw member being rotatable relative to the torsion member and the support member.
In some embodiments, the torque resistant component comprises:
the free end of the sleeve part is provided with a third clamping part, the inner hole wall of the rotating shaft assembly is provided with a fourth clamping part, and the third clamping part and the fourth clamping part are matched to circumferentially limit the rotating shaft assembly; and
the thrust portion is connected in the sleeve portion one end that is close to the supporting component, and thrust portion is equipped with a plurality of buckles along circumference towards the terminal surface of sleeve portion, and the buckle is used for carrying out axial spacing to the countershaft subassembly.
In some embodiments, the device further comprises a mounting seat, the rotary driving part is fixed on the mounting seat, the first end of the linear driving part is fixed on the torsion resisting part, and the second end of the linear driving part penetrates through the supporting part to drive the mounting seat to move along the axial direction.
In some embodiments, the linear driving device further comprises a guide sleeve, the screw member axially penetrates through the guide sleeve and is rotatable relative to the guide sleeve, one end of the guide sleeve is fixed at one end of the mounting seat facing the support member, the other end of the guide sleeve sequentially penetrates through the support member and the torsion-resistant member, the guide sleeve is axially movable relative to the support member and the torsion-resistant member, and the second end of the linear driving member penetrates through the support member and is connected with the guide sleeve.
In some embodiments, the support member comprises:
the fixing part is used for fixing with the casing;
the guide part is arranged at one end of the fixing part close to the torsion-resistant part and used for providing guidance for the movement of the guide sleeve; and
and a connecting rod connected between the fixing part and the guide part.
In some embodiments, the fixing portion comprises:
a mounting ring through which the guide sleeve passes; and
and the fixing plates are arranged on the periphery of the mounting ring at intervals along the circumferential direction, and each fixing plate is used for fixing with the casing.
In some embodiments, further comprising:
the protective bracket is arranged at one end of the mounting seat far away from the supporting part, and the rotation driving part is at least partially arranged in the protective bracket;
wherein, the one end of protective bracket far away from the mount pad is equipped with a plurality of rings along circumference for make the nut of screwing up under the state that the device suspends in midair.
In some embodiments, the rotational drive component comprises:
the electric tightening gun is used for outputting tightening torque; and
and the angle detection part is used for detecting the rotation angle of the output shaft of the electric tightening gun so as to control the rotation angle of the screwing part.
In some embodiments, the screw element further includes a dowel, a first end of the dowel is connected to the screw head, a receiving hole is formed at a bottom of the screw head, and the screw element further includes:
the first end of the movable sleeve is inserted into the accommodating hole, the second end of the movable sleeve is closed, and the movable sleeve is axially movably arranged relative to the screw head; and
the distance detection part is arranged in the movable sleeve, and a detection head of the distance detection part is propped against the inner bottom of the movable sleeve and is used for detecting the distance between the screwing head and the locking sleeve.
In some embodiments, the inner hole of the locking sleeve is a stepped hole, a plurality of bosses are circumferentially arranged on the outer side wall of the second end of the movable sleeve, the bosses are in contact with a stepped surface of the stepped hole in a state that the locking sleeve is completely ejected out by the screw head, and a detection value of the distance detection part is cleared.
In some embodiments, the tightening device further comprises:
the controller is used for resetting the detection value of the distance detection part when the screwing head completely ejects the locking sleeve, retreating the screwing part by a preset distance after the screwing head screws the nut until the preset screwing torque is reached, finely adjusting the rotation angle of the screwing head when the detection value of the distance detection part is not kept in a reset state, and continuously retreating the screwing head to separate from the nut until the detection value of the distance detection part is cleared; wherein the preset distance is smaller than the depth of the inner hole of the nut.
In some embodiments, the outer side wall of the screwing head is provided with a plurality of recesses which are through along the axial direction, and the screwing part further comprises an imaging part which is arranged on the dowel bar and is used for observing whether the locking sleeve rebounds to the position or not through the recesses.
In some embodiments, the screw member further comprises:
and the conductive slip ring is arranged at one end of the torsion-resistant part far away from the supporting part and is used for leading out signal wires of the distance detection part and the imaging part.
To achieve the above object, an embodiment of the present invention provides an aircraft engine nut tightening method, including:
extending a screwing head into an inner hole of the nut from one end of the nut, which is far away from the locking sleeve, and completely ejecting out the locking sleeve;
clearing the detection value of the distance detection part;
starting the rotary driving part, and screwing the nut until a preset screwing torque is reached;
enabling the screwing component to retreat for a preset distance, wherein the preset distance is smaller than the depth of an inner hole of the nut;
judging whether the detection value of the distance detection part is kept in a zero clearing state or not, if so, starting the linear driving part, and enabling the screwing part to continuously retreat to be separated from the nut; otherwise, the rotation angle of the rotating screwing head is finely adjusted until the detection value of the distance detection part is cleared.
In some embodiments, after the screwing member is further retreated to disengage the nut, the method further comprises:
and observing whether the locking sleeve rebounds in place through an imaging part arranged on the dowel bar, if so, completing the screwing of the nut and removing the screwing device, and otherwise, removing the screwing device and manually checking.
In some embodiments, the tightening method further comprises:
connecting the torsion-resistant part with the rotating shaft assembly;
the support member is fixed to the casing.
In some embodiments, a nut is used to lock the fan unit body, and the nut tightening method further includes:
placing the engine in an axially vertical direction;
and hoisting the tightening device to the position above the engine through the hoisting ring.
Based on the technical scheme, the aero-engine nut tightening device provided by the embodiment of the invention has the advantages that the tightening head can extend into the deep cavity of the engine to tighten the nut, the operation is convenient, the tightening torque can be stably and accurately applied to the nut with the larger diameter through the rotary driving device, the feeding and the withdrawing of the tightening head from the inner hole of the nut can be realized through the linear driving device, the aero-engine nut tightening device is suitable for tightening the nut of an aero-engine, and the nut assembling efficiency can be improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic structural view of one embodiment of an aircraft engine nut tightening device of the present invention;
FIG. 2 is a schematic view of the rotary drive unit of FIG. 1;
FIG. 3 is a schematic structural view of the support member and the torsion member of FIG. 1;
FIG. 4 is an enlarged view of the torsion resistant member of FIG. 3;
FIG. 5 is a schematic view of the screw member of FIG. 1;
FIG. 6 is a cross-sectional view of the twist head of FIG. 1;
FIG. 7 is a schematic view of a nut to be tightened in cooperation with a locking sleeve;
fig. 8 is a schematic flow chart of an embodiment of a nut tightening method of the present invention.
Detailed Description
The present invention is described in detail below. In the following paragraphs, different aspects of the embodiments are defined in more detail. Aspects so defined may be combined with any other aspect or aspects unless clearly indicated to the contrary. In particular, any feature considered to be preferred or advantageous may be combined with one or more other features considered to be preferred or advantageous.
The terms "first", "second", and the like in the present invention are merely for convenience of description to distinguish different constituent elements having the same name, and do not denote a sequential or primary-secondary relationship.
In the description of the present invention, the directions or positional relationships indicated by "upper", "lower", "top", "bottom", "front", "rear", "inner" and "outer" and the like are used based on the directions or positional relationships shown in the drawings, and are only for convenience of describing the present invention, and do not indicate or imply that the device referred to must have a specific direction, be constructed in a specific direction and be operated, and thus, should not be construed as limiting the scope of the present invention.
For clarity of explanation of the aero-engine nut tightening device (simply referred to as "tightening device") of the present invention, tightening of nuts for tightening an aero-engine fan unit body during assembly is described below as an example, but may also be applied to tightening of other nuts in an aero-engine.
As shown in fig. 1, a fan unit body in an engine is sleeved on a fan rotating shaft 10 and fixed, and the fan rotating shaft 10 and a low-pressure turbine rotating shaft 30 are coaxially connected into a whole through a connecting piece 20 to form a rotating shaft assembly. When the fan unit body is operated, a force is generated in an axially outward direction (upward direction in fig. 1), and thus, in order to prevent the fan unit body from coming off, locking is performed by the nut 50, and the nut 50 is mounted on the rotational shaft assembly of the engine. Specifically, the nut 50 is screwed with the connector 20 through an external thread, and one end of the nut 50 close to the fan rotating shaft 10 is provided with a clamping boss 52 for clamping on a boss at an end of the fan rotating shaft 10.
In order to prevent the nut 50 from loosening during the operation of the engine, a locking sleeve 60 is provided in the inner bore of the low-pressure turbine rotary shaft 30, and the nut 50 is locked by the locking sleeve 60 in a tightened state. The inner hole of the nut 50 is provided with a first engaging portion 51, for example, the first engaging portion 51 may be an internal spline, and the axial direction of the nut 50 in the mounted state coincides with the engine axial direction. One end of the locking sleeve 60 is provided with a fifth engaging portion, for example, the fifth engaging portion is an external spline. A first return spring is arranged between the locking sleeve 60 and the low-pressure turbine rotating shaft 30, when the nut 50 is screwed in place, one end of the locking sleeve 60 extends into an inner hole of the nut 50 under the action of the first return spring 40, and the fifth clamping portion is matched with the first clamping portion 51 for circumferential limiting.
Furthermore, the locking sleeve 60 is movably disposed in the inner bore of the low pressure turbine shaft 30, a first guide groove 62 is axially disposed on a side wall of the locking sleeve 60, a fastening member 70, such as a pin, is disposed on a side wall of the low pressure turbine shaft 30, and the fastening member 70 is inserted into the first guide groove 62 to guide the movement of the locking sleeve 60.
As shown in fig. 2 to 7, the present invention provides an aircraft engine nut tightening device, which in some embodiments comprises: a screw member 1, a support member 3, a torsion member 2, a rotary drive member 5 and a linear drive member 7.
As shown in fig. 6, the screwing component 1 includes a screwing head 11, and an outer side wall of an end portion of the screwing head 11 is provided with a second engaging portion 111, for example, the second engaging portion 111 may be an external spline, and the second engaging portion 111 cooperates with the first engaging portion 51 so as to screw after the screwing head 11 extends into an inner hole of the nut 50.
The support component 3 is fixed on a casing of an engine and used for realizing the integral positioning and installation of the tightening device, so that the tightening device can be stably fixed during working, and the tightening precision is improved.
The torque resisting member 2 is adapted to be fixed to the shaft assembly, specifically, to the fan shaft 10, and the torque resisting member 2 is fixed to the support member 3. Since the nut 50 is fixed to the rotary shaft unit, the whole rotary shaft unit is rotated when the nut 50 is tightened, and the rotary shaft unit needs to be fixed to facilitate application of tightening force, and the torque receiving member 2 can fix the rotary shaft unit to the casing.
The rotation driving member 5 is used to drive the screwing member 1 to rotate, for example, the rotation driving member 5 may include: an electric torque gun for outputting a tightening torque; and an angle detecting part for detecting a rotation angle of an output shaft of the electric tightening gun to control the rotation angle of the screwing part 1 so as to accurately control the applied tightening torque.
The linear driving member 7 is used to drive the screwing member 1 and the rotary driving member 5 to move integrally in the axial direction so that the screwing head 11 is inserted into or removed from the inner hole of the nut 50. For example, the linear drive member 7 may be an electric push rod, a combination of a motor and a lead screw nut transmission mechanism, or the like.
When it is desired to tighten the nut 50, the screw member 1 is used to extend from the end of the nut 50 remote from the locking sleeve 60 into the internal bore of the nut 50 along arrow K and eject the locking sleeve 60, as shown in fig. 1. Therefore, the tightening head can extend into a deep cavity of the engine to tighten the nut, the operation is convenient, the tightening torque can be stably and accurately applied to the nut with a larger diameter through the rotary driving device, the feeding and the withdrawing of the tightening head from the inner hole of the nut can be realized through the linear driving device, the nut is suitable for the tightening of the nut of an aircraft engine, and the nut assembling efficiency can be improved.
As shown in fig. 2, the screw head 11, the torque resisting member 2, the support member 3, and the rotation driving member 5 are arranged in this order in the axial direction; the screw member 1 further comprises a force transfer rod 12, the force transfer rod 12 may be an elongated rod-like structure having a first end connected to the screw head 11 and a second end connected to the output shaft of the rotary drive member 5 through the torsion member 2 and the support member 3, the screw member 1 being rotatable relative to the torsion member 2 and the support member 3.
The parts of the tightening device are arranged in sequence in the axial direction to form a slender structure, so that the nut can be conveniently stretched into a deep cavity of an engine to be tightened, the space is saved, in operation, the support part 3 is reliably fixed with the casing, the screwing head 11 is inserted into an inner hole of the nut 50, the torsion-resisting part 2 is inserted into an inner hole of the fan rotating shaft 10, the space in the engine is fully utilized, and the tightening force can be stably applied to the nut 50 by reliably fixing the tightening device.
As shown in fig. 4 and 5, the torsion member 2 includes: the free end of the sleeve part 21 is provided with a third clamping part 24, such as an external spline, the inner hole wall of the fan rotating shaft 10 in the rotating shaft assembly is provided with a fourth clamping part, such as an internal spline, and the third clamping part 24 is matched with the fourth clamping part to circumferentially limit the rotating shaft assembly; and the thrust part 22 can adopt a disc structure and is connected to one end of the sleeve part 21 close to the support component 3, a plurality of buckles 23 are arranged on the end face, facing the sleeve part 21, of the thrust part 22 at intervals along the circumferential direction, and the buckles 23 are used for axially limiting the rotating shaft assembly.
The sleeve portion 21 and the thrust portion 22 limit circumferential and axial degrees of freedom of the rotation shaft assembly with respect to the torsion member 2, respectively, while the torsion member 2 is fixedly connected to the support member 3, so that it is possible to secure the rotation shaft assembly against rotation when the nut is tightened, provide a fulcrum for tightening the nut, and effectively apply tightening force.
Further, as shown in fig. 4, the tightening device of the present invention may further include a mounting seat 6, the rotary driving member 5 is fixed to one end of the mounting seat 6, which is away from the support member 3, a plurality of linear driving members 7 may be provided at intervals along a circumferential direction of the mounting seat 6, a first end of the linear driving member 7 is fixed to the thrust portion 22 of the torsion resisting member 2, and a second end of the linear driving member 7 passes through the support member 3 to drive the mounting seat 6 to move in the axial direction. During the process of screwing the nut, the linear driving part 7 can drive the screwing part 1, the mounting seat 6 and the rotary driving part 5 to move integrally along the axial direction so as to flexibly drive the screwing head 11 to enter or leave the inner hole of the nut 50.
In some embodiments, as shown in fig. 5, the tightening device of the present invention may further include a guide sleeve 9, the dowel 12 of the screw member 1 axially passes through the guide sleeve 9 and is rotatable with respect to the guide sleeve 9, one end of the guide sleeve 9 is fixed to one end of the mounting seat 6 facing the support member 3, the other end sequentially passes through the support member 3 and the torsion resistant member 2, the guide sleeve 9 is axially movable with respect to the support member 3 and the torsion resistant member 2, and the second end of the linear driving member 7 passes through the support member 3 and is connected to the guide sleeve 9.
By arranging the guide sleeve 9, the resistance of the dowel bar 12 during rotation can be reduced, and meanwhile, a guide effect can be provided for the movement of the whole screwing component 1, the mounting seat 6 and the rotation driving component 5 relative to the supporting component 3 along the axial direction, so that the friction resistance is reduced, and the friction loss of the screwing device during working is reduced.
As shown in fig. 3, the support member 3 includes: the fixing part can adopt a plate-shaped structure and is used for fixing with the casing; a guide portion 34, which may be a guide sleeve, provided at an end of the fixing portion adjacent to the torsion member 2 for guiding movement of the guide sleeve 9; and a connecting rod 35 connected between the fixing portion and the guide portion 34. The center of the fixed part is provided with a hole 33 along the axis, and the diameter of the first hole 33 is larger than the outer diameter of the guide sleeve 9 and is used for the guide sleeve 9 to pass through; the inner bore of the guide sleeve is adapted to the outer diameter of the guide sleeve 9 for guiding the axial movement of the guide sleeve 9.
Specifically, the fixing portion includes: a mounting ring 31, wherein a hole 33 is arranged on the mounting ring 31 for the guide sleeve 9 to pass through; and a plurality of fixing plates 32 arranged at intervals along the circumferential direction on the outer periphery of the mounting ring 31 to form a radial structure, for example, four fixing plates 32 are arranged at intervals along the outer periphery of the mounting ring 31, and each fixing plate 32 is provided with a mounting hole for fixing with the casing. The fixing portion can reduce the weight of the tightening device, prevent the support member 3 from being deformed by a large stress when a large machining precision error exists on the mounting surface of the casing, and improve the guiding precision of the guide sleeve 9.
As shown in fig. 3, the tightening device of the present invention may further include: and the protective bracket 4 is arranged at one end of the mounting seat 6 far away from the supporting part 3, and the rotary driving part 5 is at least partially arranged in the protective bracket 4, so that the rotary driving part 5 is prevented from being damaged due to collision in the process of mounting the tightening device. Specifically, the protection bracket 4 may include a first plate and a second plate that are axially spaced apart, the first plate being fixed to the mounting seat 6, the first plate and the second plate being connected by a plurality of rods therebetween to form a protection space between the first plate, the second plate, and the plurality of rods.
Wherein, a plurality of rings 41 are arranged along the circumferential direction at one end of the protection bracket 4 far away from the mounting seat 6, and are used for enabling the tightening device to tighten the nut 50 in a suspended state. When the engine is in a vertical state and the position where the fan unit body is mounted is placed upward, each of the suspension rings 41 can be hooked by a crane or the like, so that the tightening device completes the fixation with the support member 3 and the torsion resistant member 2 in a suspended state. The installation mode can reduce the burden of an operator and improve the mechanization and automation degree of engine assembly.
As shown in fig. 6 and 7, the screw element 1 further includes a dowel 12, a first end of the dowel 12 is connected to the screw head 11, a receiving hole 113 is formed at the bottom of the screw head 11, and the screw element 1 further includes: a movable sleeve 13, a first end of the movable sleeve 13 is inserted into the receiving hole 113, a second end of the movable sleeve 13 is closed, the movable sleeve 13 is axially movably arranged relative to the screwing head 11, and the outer diameter of the movable sleeve 13 is smaller than that of the screwing head 11, so that when the screwing head 11 extends into the inner hole of the nut 50, the movable sleeve 13 can extend into the inner hole of the locking sleeve 60; and a distance detection part 15 which is arranged in the movable sleeve 13, and a detection head of the distance detection part 15 is propped against the inner bottom of the movable sleeve 13 and is used for detecting the distance between the screwing head 11 and the locking sleeve 60. For example, the distance detection part 15 may be a laser sensor, an infrared sensor, a photoelectric sensor, or the like.
Further, the nut 50 is locked by a locking sleeve 60 provided in the rotation shaft assembly in a tightened state, and the tightening apparatus further includes: the controller can be integrated on the supporting part 3 and is used for clearing the detection value of the distance detection part 15 when the screwing head 11 completely ejects the locking sleeve 60 out to serve as a detection zero position, enabling the screwing part 1 to retreat for a preset distance through the linear driving part 7 after the screwing head 11 screws the nut 50 until a preset screwing torque is reached, and finely adjusting the rotating angle of the screwing head 11 when the detection value of the distance detection part 15 is not kept in a cleared state until the screwing head 11 continuously retreats to be separated from the nut 50 when the detection value of the distance detection part 15 is cleared; wherein the predetermined distance is less than the depth of the inner bore of the nut 50.
In this embodiment, the purpose of retracting the screw member 1 by the predetermined distance is to make the phases of the internal splines of the nut 50 and the external splines of the locking sleeve 60 coincide by finely adjusting the rotation angle of the nut 50, so that the locking sleeve 60 can be smoothly returned into the inner bore of the nut by the first return spring 40 after the nut is tightened to lock the nut 50. If the detection value of the distance detection part 15 is continuously kept zero in the process of the back-off of the screwing head 11 by the preset distance, the locking sleeve 60 can be successfully reset along with the movable sleeve 13, and if the detection value is not kept zero, the locking sleeve 60 is not reset along with the movable sleeve 13, and the angle position of the nut 50 needs to be adjusted.
Specifically, as shown in fig. 1 and 6, the inner hole of the locking sleeve 60 is a stepped hole, the outer side wall of the second end of the movable sleeve 13 is circumferentially provided with a plurality of bosses 131, when the locking sleeve 60 is completely ejected by the screw head 11, the bosses 131 contact the stepped surface 61 of the stepped hole, the detection value of the distance detection component 15 is cleared, and this position is used as a detection zero position.
Further, as shown in fig. 7, a second return spring, not shown, is provided between the movable sleeve 13 and the screwing head 11 or the dowel 12, so that the movable sleeve 13 can be in a state of extending out of the screwing head 11, and the bottom of the movable sleeve 13 can be adapted to the position of the step surface 61 by deformation of the second return spring, so that the bottom of the movable sleeve 13 can be reliably contacted with the step surface 61.
In order to move the movable sleeve 13 along the screwing head 11, the side wall of the movable sleeve 13 is provided with a second guide groove 132 along the axial direction, and the screwing head 11 is provided with a second clamping part, such as a pin shaft, which is embedded in the second guide groove 132 to provide guidance.
As shown in fig. 6, the outer side wall of the screw head 11 is provided with a plurality of recesses 112 penetrating along the axial direction, for example, circular arc-shaped recesses, and the screw member 1 further includes an imaging member 14 provided on the dowel bar 12, for example, a camera, a bore finder or an endoscope, for determining whether the locking sleeve 60 is rebounded to the proper position through the space formed by the recesses 112. Specifically, a bracket 13 may be provided at an end of the screw head 11 remote from the movable sleeve 13 to mount the imaging part 14. The dowel bar 12 has a diameter smaller than that of the sleeve portion 21 so as to leave a space for mounting the imaging part 14.
This embodiment determines whether the locking sleeve 60 has sprung back into place by the imaging assembly 14 provided on the dowel 12 and if so completes the tightening of the nut 50 and removes the tightening device, otherwise removes the tightening device and checks the cause manually. Moreover, through double judgment of the imaging part 14 and the distance detection part 15, whether the locking sleeve 60 rebounds in place can be judged more accurately, the locking reliability after the nut 50 is screwed up is improved, and the problem that the nut installation process of the aircraft engine cannot be directly observed is solved.
Further, as shown in fig. 5, the tightening apparatus of the present invention may further include a conductive slip ring 8 provided at an end of the torque preventing member 2 remote from the supporting member 3, the conductive slip ring 8 serving to lead out signal lines from the distance detecting member 15 and the imaging member 14.
Specifically, the specific method for assembling the nut by using the tightening device of the invention comprises the following steps: firstly, vertically placing an engine, hoisting the device above the engine, installing a supporting part 3 on a casing of the engine, installing a torsion-resistant part 2 on a rotor assembly, inserting a screwing head 11 into an internal spline of a nut 50 until the locking sleeve 60 is completely ejected, clearing the reading of a contact-type distance detection part 15, starting an electric screwing gun, screwing the nut 50 to a required torque value, starting a linear driving part 7, retreating the screwing part 1 by a preset distance, slowly screwing the nut 5, judging whether the reading of the distance detection part 15 keeps zero or not, if not, continuing to slowly screw the nut 5, if returning zero, starting the linear driving part 7, retreating the screwing part 1, judging whether the locking sleeve 60 rebounds in place or not by using an imaging part, if not, dismantling the whole set of tool, checking the reason, if rebounds in place, the operation is completed.
The tightening device can be used for tightening the nut with high automation and high precision, monitoring and controlling the installation phase of the nut, detecting the axial rebound distance of the locking sleeve, ensuring the reliable locking of the nut and improving the quality and the efficiency of the nut device.
Secondly, the invention also provides a nut tightening method based on the nut tightening device of the aircraft engine in the embodiment, as shown in the flow diagram of fig. 8, the method comprises the following steps:
step 110, extending the screwing head 11 into an inner hole of the nut 50 from one end of the nut 50 far away from the locking sleeve 60, and completely ejecting out the locking sleeve 60;
140, enabling the screwing component 1 to retreat for a preset distance, wherein the preset distance is smaller than the depth of an inner hole of the nut 50;
and step 170, fine-tuning the rotation angle of the screwing head 11 until the detection value of the distance detection part 15 is cleared.
The steps are sequentially executed, the tightening head can extend into a deep cavity of the engine to tighten the nut, the operation is convenient, the tightening torque can be stably and accurately applied to the nut with the larger diameter through the rotary driving device, the feeding and the withdrawing of the tightening head from the inner hole of the nut can be realized through the linear driving device, the nut is suitable for tightening the nut of the aero-engine, and the nut assembling efficiency can be improved.
In some embodiments, still referring to fig. 8, after the step 160 of withdrawing the screw member 1 from the nut 50, the method further includes:
190, completing the screwing of the nut 50 and disassembling the screwing device;
and 200, dismantling the tightening device and manually checking.
In this embodiment, the imaging component 14 and the distance detection component 15 perform double determination, so that whether the locking sleeve 60 rebounds in place can be determined more accurately, and the reliability of locking after the nut 50 is tightened is improved.
In some embodiments, still referring to fig. 8, prior to step 110, such a tightening method further comprises:
103, connecting the torsion-resistant part 2 with the rotating shaft assembly;
Considering that the support member 3 is located outside the torsion member 2, step 103 is performed before step 104 for ease of installation. This embodiment can make the tightening device install steadily when screwing up the nut, prevents to take place to rock, improves the moment precision that the nut required when screwing up, but also can guarantee that the pivot subassembly does not take place to rotate, provides the fulcrum for screwing up the nut, exerts the tightening force effectively.
In some embodiments, the nut 50 is used for locking the fan unit body, and before step 103, the nut tightening method further comprises:
101, placing an engine in an axial vertical direction;
and 102, hoisting the tightening device to the position above the engine through the hoisting ring 41.
The engine is vertically arranged for installation, axial centering of the screwing device and the nut can be guaranteed, eccentric load can be prevented from being increased under the action of gravity, the nut is placed to be subjected to unbalanced force after being screwed, and the locking sleeve 60 can be smoothly embedded into the inner hole of the nut 50. Moreover, the device can be hung and screwed by a crane used in the process of assembling the engine, so that the supporting component 3 is fixed on the casing, the torsion-resistant component 2 is connected with the rotating shaft component, and the device can be consistent with the placing posture in the process of assembling the engine.
The device and the method for screwing the nut of the aircraft engine provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to aid in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (17)
1. The utility model provides an aeroengine nut tightening device, its characterized in that, nut (50) are installed on the pivot subassembly of engine, the hole of nut (50) is equipped with first block portion (51), nut (50) are unanimous with the engine axial at the axial of mounted state, and tightening device includes:
the screwing component (1) comprises a screwing head (11), a second clamping part (111) is arranged on the outer side wall of the end part of the screwing head (11), and the second clamping part (111) is matched with the first clamping part (51) so as to be screwed after the screwing head (11) extends into the inner hole of the nut (50);
a support member (3) fixed to a casing of the engine;
a torsion-resistant part (2) for fixing with the rotating shaft assembly, and the torsion-resistant part (2) is fixed with the supporting part (3) to fix the rotating shaft assembly relative to the casing;
the rotary driving part (5) is used for driving the screwing part (1) to rotate;
the linear driving component (7) is used for driving the screwing component (1) and the rotating driving component (5) to integrally move along the axial direction so as to enable the screwing head (11) to extend into or be out of the inner hole of the nut (50);
the rotary driving part (5) is fixed on the mounting seat (6), the first end of the linear driving part (7) is fixed on the anti-torsion part (2), and the second end of the linear driving part penetrates through the supporting part (3) to drive the mounting seat (6) to move along the axial direction; and
a guide sleeve (9), the screw member (1) axially passes through the guide sleeve (9) and is rotatable relative to the guide sleeve (9), one end of the guide sleeve (9) is fixed at one end of the mounting seat (6) facing the support member (3), the other end sequentially passes through the support member (3) and the torsion-resistant member (2), the guide sleeve (9) is axially movable relative to the support member (3) and the torsion-resistant member (2), and the second end of the linear driving member (7) passes through the support member (3) and is connected with the guide sleeve (9).
2. The aircraft engine nut tightening device according to claim 1, characterized in that the nut (50) is locked in a tightened state by a locking sleeve (60) provided in the spindle assembly, one end of the locking sleeve (60) being provided with a fifth engaging portion;
when the nut (50) is screwed up to a proper position, one end of the locking sleeve (60) extends into the inner hole of the nut (50) under the action of a first return spring (40), and the fifth clamping part is matched with the first clamping part (51) to carry out circumferential limiting;
when the nut (50) needs to be screwed, the screwing part (1) is used for extending into an inner hole of the nut (50) from one end, far away from the locking sleeve (60), of the nut (50) and ejecting out the locking sleeve (60).
3. Aeroengine nut tightening device according to claim 1, characterized in that the screwing head (11), the anti-torque member (2), the support member (3) and the rotary drive member (5) are arranged in the axial direction in succession;
the screwing element (1) further comprises a dowel (12), a first end of the dowel (12) is connected with the screwing head (11), a second end of the dowel passes through the torsion resistant part (2) and the supporting part (3) to be connected with an output shaft of the rotating driving part (5), and the screwing element (1) can rotate relative to the torsion resistant part (2) and the supporting part (3).
4. Aeroengine nut screwing device according to claim 1, wherein said torsion member (2) comprises:
the free end of the sleeve part (21) is provided with a third clamping part (24), the inner hole wall of the rotating shaft assembly is provided with a fourth clamping part, and the third clamping part (24) is matched with the fourth clamping part to circumferentially limit the rotating shaft assembly; and
the thrust part (22) is connected to one end, close to the supporting component (3), of the sleeve part (21), the thrust part (22) is provided with a plurality of buckles (23) towards the end face of the sleeve part (21) along the circumferential direction, and the buckles (23) are used for axially limiting the rotating shaft assembly.
5. An aircraft engine nut tightening device according to claim 1, characterized in that the support member (3) comprises:
the fixing part is used for fixing the casing;
a guide portion (34) provided at an end of the fixing portion adjacent to the torsion member (2) for guiding movement of the guide sleeve (9); and
a connecting rod (35) connected between the fixing portion and the guide portion (34).
6. The aircraft engine nut tightening device according to claim 5, wherein the fixing portion includes:
a mounting ring (31) through which the guide sleeve (9) passes; and
and a plurality of fixing plates (32) which are arranged on the periphery of the mounting ring (31) at intervals along the circumferential direction, wherein each fixing plate (32) is used for being fixed with the casing.
7. The aircraft engine nut tightening apparatus according to claim 1, further comprising:
the protective bracket (4) is arranged at one end, far away from the supporting part (3), of the mounting seat (6), and the rotary driving part (5) is at least partially arranged in the protective bracket (4);
wherein, a plurality of rings (41) are arranged on one end of the protective bracket (4) far away from the mounting seat (6) along the circumferential direction, and are used for enabling the tightening device to tighten the nut (50) in a suspended state.
8. An aircraft engine nut tightening device according to claim 1, characterized in that the rotary drive member (5) comprises:
the electric tightening gun is used for outputting tightening torque; and
and the angle detection component is used for detecting the rotation angle of the output shaft of the electric tightening gun so as to control the rotation angle of the screwing component (1).
9. Aeroengine nut tightening device according to claim 2, characterized in that screw element (1) further comprises a dowel (12), a first end of dowel (12) is connected with screw head (11), a receiving hole (113) is provided at the bottom of screw head (11), and screw element (1) further comprises:
a movable sleeve (13), a first end of the movable sleeve (13) is inserted into the receiving hole (113), a second end of the movable sleeve is closed, and the movable sleeve (13) is axially movably arranged relative to the screwing head (11); and
the distance detection part (15) is arranged in the movable sleeve (13), and the detection head of the distance detection part (15) abuts against the inner bottom of the movable sleeve (13) and is used for detecting the distance between the screwing head (11) and the locking sleeve (60).
10. The aircraft engine nut tightening device according to claim 9, characterized in that the inner hole of the locking sleeve (60) is a stepped hole, a plurality of bosses (131) are circumferentially provided on the outer side wall of the second end of the movable sleeve (13), the bosses (131) contact with a stepped surface (61) of the stepped hole in a state where the locking sleeve (60) is completely ejected by the screwing head (11), and the detection value of the distance detection member (15) is cleared.
11. The aircraft engine nut tightening apparatus according to claim 9, further comprising:
the controller is used for clearing the detection value of the distance detection part (15) when the screwing head (11) completely ejects the locking sleeve (60), retreating the screwing part (1) by a preset distance after the screwing head (11) screws the nut (50) until a preset screwing torque is reached, finely adjusting the rotation angle of the screwing head (11) when the detection value of the distance detection part (15) is not kept in a cleared state, and continuously retreating the screwing head (11) to separate from the nut (50) until the detection value of the distance detection part (15) is cleared; wherein the predetermined distance is less than the depth of the inner bore of the nut (50).
12. Aeroengine nut tightening device according to claim 9, characterized in that the outer side wall of the screwing head (11) is provided with a plurality of axially through recesses (112), the screwing part (1) further comprising an imaging part (14) provided on the dowel (12) for observing whether the locking sleeve (60) rebounds into place through the recesses (112).
13. Aeroengine nut screwing device according to claim 12, wherein said screwing component (1) further comprises:
and the conductive slip ring (8) is arranged at one end of the torsion-resistant part (2) far away from the supporting part (3), and the conductive slip ring (8) is used for leading out signal wires of the distance detection part (15) and the imaging part (14).
14. A nut tightening method based on the aircraft engine nut tightening device as defined in any one of claims 1 to 13, characterized by comprising:
the screwing head (11) extends into an inner hole of the nut (50) from one end, far away from the locking sleeve (60), of the nut (50), and completely ejects out the locking sleeve (60);
zero clearing the detection value of the distance detection part (15);
opening the rotary driving part (5) and screwing the nut (50) until a preset screwing torque is reached;
retreating the screwing part (1) by a preset distance, wherein the preset distance is smaller than the inner hole depth of the nut (50);
judging whether the detection value of the distance detection part (15) is kept in a zero clearing state or not, if so, starting the linear driving part (7) to enable the screwing part (1) to continuously retreat to be separated from the nut (50); otherwise, the rotation angle of the screwing head (11) is finely adjusted until the detection value of the distance detection part (15) is cleared.
15. The nut tightening method according to claim 14, further comprising, after continuing to retreat the screw member (1) away from the nut (50):
observing whether the locking sleeve (60) rebounds in place through an imaging part (14) arranged on the dowel bar (12), if so, completing the screwing of the nut (50) and removing the screwing device, otherwise, removing the screwing device and manually checking.
16. The nut tightening method according to claim 14, further comprising:
connecting the torsion resistant member (2) with the spindle assembly;
fixing the support part (3) on the casing.
17. The nut tightening method according to claim 14, wherein the nut (50) is used for locking a fan unit body, the nut tightening method further comprising:
placing the engine in an axially vertical orientation;
and hoisting the tightening device to the position above the engine through a hoisting ring (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910675805.9A CN112276539B (en) | 2019-07-25 | 2019-07-25 | Device and method for screwing nut of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910675805.9A CN112276539B (en) | 2019-07-25 | 2019-07-25 | Device and method for screwing nut of aircraft engine |
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| Publication Number | Publication Date |
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| CN112276539A CN112276539A (en) | 2021-01-29 |
| CN112276539B true CN112276539B (en) | 2022-05-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910675805.9A Active CN112276539B (en) | 2019-07-25 | 2019-07-25 | Device and method for screwing nut of aircraft engine |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114952712B (en) * | 2021-02-25 | 2023-07-07 | 中国航发商用航空发动机有限责任公司 | Air duct assembly screwing tool |
| CN112975797B (en) * | 2021-02-26 | 2022-08-30 | 西安航天发动机有限公司 | Assembly tool and assembly method for shaft end nut of turbopump of liquid rocket engine |
| CN113858105B (en) * | 2021-09-24 | 2023-10-03 | 中国航发南方工业有限公司 | Aeroengine guiding assembly mechanism and assembly method |
| CN114535994B (en) * | 2022-03-17 | 2022-12-20 | 中国航发沈阳发动机研究所 | Device is screwed up to axle intracavity pipeline bearing structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9281663B2 (en) * | 2013-04-26 | 2016-03-08 | Howard Johnson | General aviation igniter cable assembly |
| CN103949878B (en) * | 2014-05-13 | 2017-10-20 | 苏州博众精工科技有限公司 | A kind of suction screw locking device |
| CN106541363B (en) * | 2015-09-18 | 2018-07-10 | 中国航发商用航空发动机有限责任公司 | Locking nut tighten and back off tool |
| CN206029250U (en) * | 2016-08-30 | 2017-03-22 | 中航锂电（洛阳）有限公司 | Power module bolt tightening mechanism |
| CN108098687B (en) * | 2017-12-11 | 2020-02-18 | 中国航发沈阳黎明航空发动机有限责任公司 | Aeroengine internal force limiting nut assembling device and using method |
| CN109968012B (en) * | 2019-04-16 | 2020-06-30 | 西安航天动力研究所 | Helium turbine shafting tightening method and axial loading type tightening tool |
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