CN212423529U - Two-stage turbine and coupling decomposition tool of airplane auxiliary power device - Google Patents

Abstract

The utility model discloses an aircraft auxiliary power unit's second grade turbine and decomposition frock of shaft coupling, including the puller axle, two arcs draw the piece, the holding ring, a force application section of thick bamboo, nut and base, one end at the puller axle is equipped with the external screw thread, the middle part of puller axle is equipped with conical boss, two arcs draw the both sides that the piece is located conical boss relatively, draw the piece at the arc and be equipped with the flange with the great one end corresponding of the diameter of conical boss, the holding ring is used for the cover on two arcs draw the piece, the one end of a force application section of thick bamboo is equipped with the end plate, middle part at the end plate is equipped with the perforation, the tip that is equipped with the external screw thread of puller axle is worn out outside the force application section of thick bamboo from the perforation, the other end of a force application section of thick bamboo is used for leaning on the. The utility model provides high work efficiency.

Description

Two-stage turbine and coupling decomposition tool of airplane auxiliary power device

Technical Field

The utility model relates to a second grade turbine of aircraft auxiliary power device and decomposition frock of shaft coupling.

Background

The Auxiliary Power device is a Power device on the airplane except for a main engine, is called Auxiliary Power Unit (APU for short) in English, is used for independently providing a Power supply and an air supply for the airplane, and is also used for providing additional thrust.

Boeing 737 series aircraft and air passenger a320 series aircraft are each equipped with an auxiliary power unit of the type 131-9. Through years of work, the coupler of the 131-9 series auxiliary power device connected with the secondary turbine is very easy to be seized by metal oxides and colloidal hydrocarbons generated under the catalysis of high temperature and oxygen due to thermal stress of long-term operation, and further the metal oxides and the colloidal hydrocarbons are seized by key teeth of the secondary turbine, so that the decomposition between the secondary turbine and the coupler is influenced. And because a sealing ring is arranged between the secondary turbine and the coupling, the sealing ring is also easily clamped by metal oxide and colloid hydrocarbon, and the decomposition is further influenced.

As shown in fig. 6, which is a schematic structural diagram of the secondary turbine 101 and the coupling 102, the secondary turbine 101 and the coupling 102 both have a central hole, a convex ring that extends and shrinks radially is disposed at an outer end of the central hole of the coupling 102, and a sealing ring 104 is disposed between the secondary turbine and the coupling.

Aiming at the problem of difficult decomposition between a secondary turbine and a coupler, a manual does not mention corresponding measures, APU manufacturers propose to use an alkaline rust remover to dissolve internal metal oxides and hydrolyze grease through analysis and then decompose the grease, but through multiple attempts, the effect is not obvious, and parts can be corroded to a certain extent by soaking the parts for a long time, the balance of a subsequent rotor assembly is influenced, even if the balance is smooth, if the size deviation of the air seal of the coupler is caused, the gas circuit fault of a core machine in the operation process of the APU can be finally caused, the output power of the turbine is influenced, the performance of the APU is further deteriorated, and the performance degradation of the APU is accelerated. If the corrosion causes damage to the key teeth or the turbine, the key teeth are not regular curved surfaces, and the turbine disc and the blades are of an integrated structure, so that the damage to the key teeth and the blades can cause the whole part to be scrapped, thereby causing serious economic loss and increasing the repair cost. In addition, the long-term soaking does not damage the parts, the working time is greatly prolonged, and manpower and material resources are lost.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that a second grade turbine of aircraft auxiliary power device and decomposition frock of shaft coupling is provided, it has improved work efficiency.

Solve above-mentioned technical problem, the utility model discloses a technical scheme as follows:

the utility model provides a decomposition frock of aircraft auxiliary power device's second grade turbine and shaft coupling which characterized in that: the device comprises a puller shaft, two arc-shaped pulling blocks, a positioning ring, a force application cylinder, a nut and a base, wherein an external thread is arranged at one end of the puller shaft, a conical boss concentric with the puller shaft is arranged in the middle of the puller shaft, the end with the smaller diameter of the conical boss is close to the end part with the external thread of the puller shaft, the two arc-shaped pulling blocks are oppositely arranged at two sides of the conical boss, the inner side surface of each arc-shaped pulling block is a curved surface attached to the side surface of the conical boss, a blocking edge used for abutting against the inner side surface of a convex ring at the outer end of a central hole of a coupler is arranged at the end part, corresponding to the end with the larger diameter of the conical boss, of each arc-shaped pulling block, the positioning ring is sleeved on the two arc-shaped pulling blocks, an end plate is arranged at one end of the force application cylinder, a through hole is arranged in the middle of, the nut is connected on the tip that is equipped with the external screw thread of tool shaft, and the connection can be dismantled at the other end of tool shaft to the base.

Furthermore, a fixed beam for fixing on the vice is arranged on the lower surface of the base.

Furthermore, the puller shaft is in threaded connection with the base.

Furthermore, the outer side surface of the arc-shaped pulling block is an arc surface with the circle center coinciding with the axis of the puller shaft.

Further, the diameter of the middle hole of the positioning ring is larger than that of the middle hole of the convex ring of the coupler.

Compared with the prior art, the utility model discloses following beneficial effect has:

1. the utility model discloses a shaft coupling is held to the flange that the arc draws the piece, produces pressure to a force application section of thick bamboo through rotating the nut to apply to the second grade turbine on, thereby realize directly to the separation of second grade turbine and shaft coupling, need not to carry out any preliminary treatment, improved work efficiency, and the workman carries out the application of force through rotating the nut, and is more laborsaving. The utility model discloses not only having practiced thrift time and human cost greatly, can protecting parts again, scrap the whole of second grade turbine and shaft coupling, the cost of ten thousand yuan can be practiced thrift in the protectiveness decomposition.

2. The utility model discloses a curved surface of holding ring and the cooperation of conical boss produce radial bulging force for the holding ring fully expands in the shaft coupling, makes the inside atress of shaft coupling distribute evenly along circumference, and then will reduce the damage to the shaft coupling to the minimum.

Drawings

Fig. 1 is a schematic front view of the present invention;

fig. 2 is an exploded schematic view of the present invention;

FIG. 3 is a schematic structural view of the present invention after the force application cylinder is hidden;

FIG. 4 is a schematic view of the present invention in exploded view of the two-stage turbine and the coupling;

FIG. 5 is a schematic cross-sectional view taken along line B-B of FIG. 4;

fig. 6 is a schematic structural view of a conventional two-stage turbine and coupling.

The reference numerals in the drawings mean:

1-a nut; 2-a gasket; 3-a force application cylinder; 3.1-perforating; 3.2-end plate; 4-a positioning ring; 5, arc-shaped pulling blocks; 5.1-inner side surface of the arc-shaped pulling block; 5.2-flange; 6-pulling the tool shaft; 6.1-conical boss; 6.2-external thread; 7-a base; 7.1-fixed beam; 101-a two-stage turbine; 102-a coupling; 103-convex ring; 104-sealing ring.

Detailed Description

The present invention will be further described with reference to the following examples.

The disassembly tool for the second-stage turbine and the coupling of the auxiliary power device of the airplane as shown in fig. 1 to 3 comprises a puller shaft 6, two arc-shaped pull blocks 5, a positioning ring 4, a force application cylinder 3, a nut 1 and a base 7.

The vertical setting of puller axle 6, be equipped with external screw thread 6.2 in the upper end of puller axle 6, the middle part of puller axle 6 is equipped with and pulls out concentric conical boss 6.1 of utensil axle, the less one end of diameter of conical boss 6.1 is up, the great one end of diameter is down, two arcs draw piece 5 to be located conical boss 6.1's both sides relatively, the medial surface 5.1 of arc draw piece 5 is the curved surface of laminating mutually with conical boss 6.1's side, arc draw piece 5 can slide from top to bottom along conical boss 6.1's side, the lateral surface of arc draw piece 5 is the arc surface that the centre of a circle coincides mutually with the axle center of puller axle 6, be equipped with the flange 5.2 that is used for leaning on the medial surface of the bulge loop 103 of the mesopore of shaft coupling at the lower extreme of arc draw piece 5. When the two arc-shaped pulling blocks 5 are mutually folded to a certain distance, the whole diameter formed by the two arc-shaped pulling blocks 5 is smaller than the diameter of the middle hole of the convex ring 103 of the coupler, the whole formed by the two arc-shaped pulling blocks 5 can penetrate through the middle hole of the convex ring 103, and when the two arc-shaped pulling blocks 5 are spread by a certain distance through the conical boss 6.1, the outer side surfaces of the two arc-shaped pulling blocks 5 can be tightly attached to the hole wall of the middle hole of the convex ring 103. The positioning ring 4 is used for being sleeved on the two arc-shaped pulling blocks 5, the diameter of the middle hole of the positioning ring 4 is slightly larger than that of the middle hole of the convex ring 103 of the coupler, and the positions of the two arc-shaped pulling blocks 5 can be limited when the positioning ring is used, so that the parts, located outside the coupler 102, of the two arc-shaped pulling blocks 5 cannot be opened towards the side edge. The upper end of the force application cylinder 3 is provided with an end plate 3.2, the middle of the end plate 3.2 is provided with a through hole 3.1, the upper end part of the puller shaft 6 provided with the external thread 6.2 penetrates out of the through hole 3.1 to the outside of the force application cylinder 3, the lower end of the force application cylinder 3 is used for being abutted against the second-stage turbine 101, the nut 1 is connected on the end part of the puller shaft 6 provided with the external thread, the nut 1 is positioned on the force application cylinder 3, and the base 7 can be detachably connected at the lower end of the puller shaft 6.

The concrete mounting structure of base 7 does: a threaded hole is formed in the middle of the upper surface of the base 7, and the lower end of the puller shaft is connected into the threaded hole in a threaded mode. The lower surface of the base 7 is provided with a fixed beam 7.1 for fixing to a vise.

In this embodiment, a washer 2 is further provided between the nut 1 and the urging cylinder 3.

As shown in fig. 4 and 5, which are schematic diagrams for disassembling the second-stage turbine and the coupling (fig. 6 shows the structure of the second-stage turbine and the coupling in more detail, fig. 4 and 5 show the second-stage turbine and the coupling only by simple square boxes), when disassembling, the coupling 102 is located above the second-stage turbine 101, the puller shaft 6 is passed through the central holes of the coupling 102 and the second-stage turbine 101 from top to bottom, two arc-shaped pulling blocks 5 are placed from top to bottom, and the flanges 5.2 of the arc-shaped pulling blocks 5 are located in the coupling 102, then the puller shaft 6 is pulled up, the two arc-shaped pulling blocks 5 are spread to the side edge by the conical boss 6.1, the side surfaces of the two arc-shaped pulling blocks 5 are attached to the hole wall of the central hole of the convex ring 103 of the coupling 102, the flanges 5.2 of the arc-shaped pulling blocks 5 are abutted to the inner surface (i.e. the lower surface) of the convex ring 103 of the coupling, and, the locating ring 4 is located above the shaft coupling 102, then, the force application barrel 3 is sleeved, the upper end, provided with the external thread, of the puller shaft 6 penetrates out of the upper surface of the force application barrel 6, the lower end of the force application barrel 6 abuts against the secondary turbine 101, then, the gasket 2 and the nut 1 are installed, the base 7 is fixed on a vice, the lower end of the puller shaft 6 is in threaded connection with the base 7, the nut 1 is rotated after preparation is completed, the nut 1 moves downwards, pressure is generated on the force application barrel 3, downward pressure is applied to the secondary turbine 101 through the force application barrel 3, the shaft coupling 102 is pulled by the flange 5.2 of the arc-shaped pull block 5, upward pulling force is generated, and finally, the secondary turbine 101 is separated from the shaft coupling 102.

The diameter of the upper end of the puller shaft 6 of the present embodiment cannot be too small, otherwise it will have insufficient strength and will be easily broken due to excessive stress during the decomposition process. Secondly, the inclination angle of the conical boss 6.1 of the puller shaft 6 needs to be as large as possible, otherwise, the component force of the supporting force perpendicular to the conical surface along the axial direction is too small, and the puller effect is influenced. Finally, the diameter of the lower end of the puller shaft 6 is to be as large as possible on the premise of being able to be inserted into the secondary turbine, since this part is the supporting part, if the diameter is too small, the lower end of the puller shaft will bend during operation, and even the thread screwed into the base part will break. In addition, the flange 5.2 of the arc-shaped pulling block 5 cannot be too thin, and the arc-shaped pulling block is easy to damage when being too thin. The contact surface of the force application cylinder 3, which is in contact with the secondary turbine, is also a main stress surface, the wall thickness of the force application cylinder 3 cannot be too thin, if the wall thickness is too thin, the contact area is too small, and then too large pressure is generated, and the surface of the secondary turbine is damaged.

The above embodiments of the present invention are not right the utility model discloses the limited protection scope, the utility model discloses an embodiment is not limited to this, all kinds of basis according to the above-mentioned of the utility model discloses an under the above-mentioned basic technical thought prerequisite of the utility model, right according to ordinary technical knowledge and the conventional means in this field the modification, replacement or the change of other multiple forms that above-mentioned structure made all should fall within the protection scope of the utility model.

Claims (5)

1. The utility model provides a decomposition frock of aircraft auxiliary power device's second grade turbine and shaft coupling which characterized in that: the clamping device comprises a puller shaft, two arc-shaped pulling blocks, a positioning ring, a force application cylinder, a nut and a base, wherein an external thread is arranged at one end of the puller shaft, a conical boss concentric with the puller shaft is arranged in the middle of the puller shaft, the end with the smaller diameter of the conical boss is close to the end part with the external thread of the puller shaft, the two arc-shaped pulling blocks are relatively positioned at two sides of the conical boss, the inner side surface of each arc-shaped pulling block is a curved surface attached to the side surface of the conical boss, a blocking edge used for abutting against the inner side surface of a convex ring at the outer end of a middle hole of a coupler is arranged at the end part of each arc-shaped pulling block corresponding to the end with the larger diameter of the conical boss, the positioning ring is sleeved on the two arc-shaped pulling blocks, an end plate is arranged at one end of the force application cylinder, a through hole is arranged in the middle of the end plate, the end part with the, the other end of the force application cylinder is used for abutting against the second-stage turbine, the nut is connected to the end portion, provided with the external thread, of the puller shaft, and the base is detachably connected to the other end of the puller shaft.

2. The disassembly tool for the secondary turbine and the coupling of the auxiliary power device of the aircraft as claimed in claim 1, wherein: and a fixed beam for fixing on the vice is arranged on the lower surface of the base.

3. The disassembly tool for the secondary turbine and the coupling of the auxiliary power device of the aircraft as claimed in claim 2, wherein: the puller shaft is in threaded connection with the base.

4. The disassembly tool for the secondary turbine and the coupling of the auxiliary power device of the aircraft as claimed in claim 1, wherein: the outer side surface of the arc-shaped pulling block is an arc surface with the circle center coinciding with the axis of the puller shaft.

5. The disassembly tool for the secondary turbine and the coupling of the auxiliary power device of the aircraft as claimed in claim 1, wherein: the diameter of the middle hole of the positioning ring is larger than that of the middle hole of the convex ring of the coupler.

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