Fastening tool for turboprop engine rotor fastener

Abstract

The utility model provides a fastening tool for a turboprop engine rotor fastener. The fastening tool comprises a fastening sleeve, a pressing seat and a pressing block. Convex teeth are arranged at the bottom end of the fastening sleeve, and a square through hole is formed in a sleeve opening in the top end of the fastening sleeve. The pressing base comprises a flange plate and an outer sleeve, a bolt through hole is formed in the flange plate, the fastening sleeve is inserted into the outer sleeve in a sleeved mode, and internal threads are arranged on the top of the outer sleeve. An external thread is arranged on the outer surface of the pressing block, the pressing block is inserted into the top sleeve opening of the outer sleeve to form threaded connection, an axial through straight hole is formed in the pressing block, the bottom end face of the pressing block is pressed on the top end face of the fastening sleeve, and a screwing part is arranged on the top of the pressing block. The pressing seat and the pressing block provide stable axial downward pressing force all the time, and personnel injury or product and tool damage caused by sudden slippage of the fastening sleeve and the fastening tool is prevented. Operators do not need to press downwards with force any more, more manpower is saved, and locking or loosening with larger torque can be completed.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aero-engine assembly tool, especially to a fastening tool for a turboprop engine rotor fastener. BACKGROUND

[0002] The rotor assembly of an aero-engine generates very large vibration and axial force during rotation, so the locking requirement of the fastener thereon is very high, and once the fastener is loosened during the rotation of the engine, the safety of the engine and even the aircraft will be seriously threatened, so during the assembly of the aero-engine, the fastener on the rotor often needs to be locked according to a specific fastening torque.

[0003] Since the fastener on the rotor is often a non-standard part, a special fastening tool is required to pre-tighten it. The commonly used fastening tool is usually designed in a cylindrical shape, one end of which is designed according to the shape of the fastener, and the other end face is left with a square through hole for installing a torque wrench. This fastening tool is simple in structure, but during use, the fastening tool itself does not provide axial pressing force, and the operator needs to press the fastening tool axially during use to ensure that the fastening tool is tightly fitted with the fastener and prevent the fastening tool from slipping off the fastener.

[0004] Therefore, the current fastening tool has the following two disadvantages:

[0005] (1) If the pre-tightening force of the fastener is large, the fastening tool may suddenly come off the fastener during pre-tightening, causing damage to the product and the fastening tool, and even causing injury to the operator;

[0006] (2) The operator needs to press the fastening tool during operation, and needs to maintain the vertical angle of the torsional force relative to the fastening tool, which is difficult to operate and requires a high strength of the operator. INVENTION CONTENTS

[0007] The utility model aims at providing a fastening tool for a turboprop engine rotor fastener.

[0008] To solve the above technical problems, the utility model provides the technical scheme:

[0009] A fastening tool for a turboprop engine rotor fastener, comprising a fastening sleeve, a pressing seat and a pressing block;

[0010] The fastening sleeve is cylindrical, and the bottom end of the fastening sleeve is provided with a protruding tooth for inserting into the tooth groove on the rotor fastener and forming meshing connection with the tooth groove, and the top end of the fastening sleeve is provided with a square through hole for inserting the screw rod of a torque wrench;

[0011] The pressing seat comprises a flange plate and an outer sleeve, the flange plate is provided with bolt through holes for inserting bolts to bolt-connect and fix the flange plate on the stator workpiece, the fastening sleeve is inserted into the outer sleeve, and the top inner surface of the outer sleeve is provided with internal threads;

[0012] The lateral outer surface of the pressing block is provided with external threads, the pressing block is inserted into the top sleeve port of the outer sleeve, the external threads on the pressing block are in threaded connection with the internal threads of the top of the outer sleeve, an axial through straight hole for inserting the rotating rod of the torque wrench is arranged in the pressing block, the bottom end surface of the pressing block is pressed against the top end surface of the fastening sleeve, the axial through straight hole on the pressing block is in straight-line communication with the inner diameter cavity of the fastening sleeve, and the exposed top of the pressing block is provided with a square-shaped rotating part for the wrench rotation.

[0013] Preferably, the flange plate is a rectangular flange plate.

[0014] Preferably, the rotating rod of the torque wrench is a round rod.

[0015] Preferably, the cross section of the rotating part is square-shaped.

[0016] Preferably, the fastening sleeve, the pressing seat and the pressing block are all made of stainless steel.

[0017] The application has the following beneficial technical effects:

[0018] Under the premise of ensuring the normal use of the fastening sleeve, the pressing seat and the pressing block can always provide stable axial downward pressing force in the use process, preventing the sudden slipping out of the fastening sleeve and the fastening tool from causing personnel injury or product and tool damage.

[0019] The pressing seat and the pressing block can provide stable axial downward pressing force, and the operator no longer needs to keep pressing downward during the operation process, thus saving manpower, and under the condition that other conditions remain unchanged, the operator can complete the locking or loosening of a larger torque. BRIEF DESCRIPTION OF DRAWINGS

[0020] Fig. 1 A perspective structural schematic view of a fastening tool for a turboprop engine rotor fastener is provided for the embodiment of the application;

[0021] Fig. 2 A perspective structural schematic view of a fastening tool for a turboprop engine rotor fastener in a use state is provided for the embodiment of the application;

[0022] Fig. 3A cross-sectional structure schematic diagram of an axial center plane section of a fastening tool for a turboprop engine rotor fastener is provided for an embodiment of the present application;

[0023] In the figure: 1 fastening sleeve, 101 protruding teeth, 2 pressing seat, 201 flange, 202 outer sleeve, 3 pressing block, 301 axial straight hole, 302 screwing part;

[0024] 4 torque wrench screwing rod, 5 rotor fastener. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0026] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "center", "axial", "radial", "longitudinal", "transverse", "length", "width", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "high", "low", "clockwise", "counterclockwise", "inboard", "outboard", "horizontal", "vertical" and the like are based on the orientations or positional relationships in the actual use process, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0027] Referring to Figs. 1-3 , in the figure: fastening sleeve 1, protruding teeth 101, pressing seat 2, flange 201, outer sleeve 202, pressing block 3, axial straight hole 301, screwing part 302; torque wrench screwing rod 4, rotor fastener 5.

[0028] The present application provides a fastening tool for a turboprop engine rotor fastener, comprising a fastening sleeve 1, a pressing seat 2 and a pressing block 3;

[0029] The fastening sleeve 1 is cylindrical, and the bottom end of the fastening sleeve 1 is provided with protruding teeth 101 for inserting into a tooth groove on the fastener 5 of the rotor and forming meshing connection with the tooth groove, and the top end of the fastening sleeve 1 is provided with a square (square) through hole for inserting the torque wrench screwing rod 4;

[0030] The compression seat 2 comprises a flange plate 201 and an outer sleeve 202, the flange plate 201 is provided with bolt through holes for inserting bolts to bolt and fix the flange plate 201 and the compression seat 2 on the static workpiece near the rotor, the fastening sleeve 1 is inserted into the outer sleeve 202, and the top inner surface of the outer sleeve 202 is provided with internal threads;

[0031] The lateral outer surface of the compression block 3 is provided with external threads, the compression block 3 is inserted into the top sleeve opening of the outer sleeve 202, the external threads on the compression block 3 are in threaded connection with the internal threads of the top of the outer sleeve 202, the axial through straight hole 301 in the compression block 3 is used for inserting the rotating rod 4 of the torque wrench, the bottom end surface of the compression block 3 is compressed on the top end surface of the fastening sleeve 1, the axial through straight hole 301 on the compression block 3 is in straight-line communication with the inner diameter cavity of the fastening sleeve 1, and the exposed top of the compression block 3 is provided with a rotating part 302 for wrench rotation.

[0032] In one embodiment of the present application, the flange plate 201 is a rectangular flange plate.

[0033] In one embodiment of the present application, the rotating rod 4 of the torque wrench is a round rod.

[0034] In one embodiment of the present application, the cross section of the rotating part 302 is square (square).

[0035] In one embodiment of the present application, the fastening sleeve 1, the compression seat 2 and the compression block 3 are all made of stainless steel.

[0036] The structure of the fastening tool for the fastener 5 of the turboprop engine rotor of the present application is as follows:

[0037] The fastening tool of the present application adds two parts, the compression seat 2 and the compression block 3, to the fastening sleeve 1, and the installation and cooperation relationship between the parts is as follows Figs. 1-3 ;

[0038] The main structure of the compression seat 2 is the flange plate 201 below and the outer sleeve 202 above, the flange plate 201 can be designed according to the working scene of the fastening tool, the flange plate 201 finds a suitable fixing hole or fixing stud in the working scene, and the corresponding flange plate 201 structure is designed to ensure the stable installation of the compression seat 2 itself, and the outer sleeve 202 above is used for installing the compression block 3, the compression block 3 is screwed into the outer sleeve 202 until it is tightly pressed against and presses the fastening sleeve 1;

[0039] The pressing block 3 is a hollow cylinder with external threads, the external threads are matched with the internal threads of the outer sleeve 202, and the length of the threads should be designed according to the actual stroke requirement, the inner diameter of the axial through straight hole 301 needs to be larger than the outer diameter of the rotating rod 4 of the torque wrench, therefore, the rotating rod 4 of the torque wrench can pass through the axial through straight hole 301 of the pressing block 3 and be smoothly inserted into the square through hole of the fastening sleeve 1, the upper part of the pressing block 3 is designed as a square boss structure rotating part 302, so as to facilitate the use of another wrench to tighten or loosen the pressing block 3.

[0040] The working principle of a fastening tool for a turboprop engine rotor fastener according to the present application is as follows:

[0041] 1) Installation of the tool

[0042] After the fastening sleeve 1 is installed, the pressing seat 2 is fixed on the working site, and the pressing block 3 is screwed into the outer sleeve 202 of the pressing seat 2 until the bottom end surface of the pressing block 3 contacts the top end surface of the fastening sleeve 1, and the tightness is appropriately adjusted to maintain a small pressing force;

[0043] 2) Use of the tool

[0044] The rotating rod 4 of the torque wrench is inserted into the square through hole of the fastening sleeve 1 through the axial through straight hole 301 of the pressing block 3, and the fastening sleeve 1 is rotated by using the torque wrench, since the force of the operator twisting the fastening sleeve 1 is not completely perpendicular to the axis of the fastening tool, the fastening sleeve 1 will have a tendency to come out of the fastener 5, and at this time, the pressing block 3 tightly presses the fastening sleeve 1 and provides a stable axial pressing force, which can prevent the fastening sleeve 1 from coming out of the fastener 5; after the fastening sleeve 1 rotates by a certain angle, it will also have a slight displacement in the axial direction, which will cause the pressing force between the fastening sleeve 1 and the pressing block 3 to increase or decrease, at this time, the pressing block 3 should be rotated by using a wrench, so as to maintain the pressing force between the pressing block 3 and the fastening sleeve 1 within a suitable range.

[0045] The methods and devices not described in detail in the present application are all prior art, and will not be described again.

[0046] The principles and implementation modes of the present application are described by using specific examples in this paper, and the above examples are only used to help understand the method and core idea of the present application. It should be pointed out that, for ordinary skilled persons in the technical field, without departing from the principles of the present application, the present application can be improved and modified in many ways, and these improvements and modifications also fall within the protection scope of the claims of the present application.

Claims

1. A fastening tool for fasteners of a turboprop engine rotor, characterized in that, The fastening sleeve, the pressing seat and the pressing block are included. The fastening sleeve is cylindrical, and a convex tooth is arranged at the bottom end of the fastening sleeve for engaging with a tooth groove on the fastener of the rotor; a square through hole is arranged at the top opening of the fastening sleeve for inserting the rotating rod of the torque wrench. The pressing seat includes a flange plate and an outer sleeve, the flange plate is provided with bolt through holes for inserting bolts to bolt-connect and fix the flange plate on the stator workpiece, the fastening sleeve is inserted into the outer sleeve, and the top inner surface of the outer sleeve is provided with internal threads; The outer surface of the pressing block is provided with external threads, the pressing block is inserted into the top opening of the outer sleeve, the external threads on the pressing block are in threaded connection with the internal threads of the top of the outer sleeve, an axial through straight hole is arranged in the pressing block for inserting the rotating rod of the torque wrench, the bottom end surface of the pressing block is pressed against the top end surface of the fastening sleeve, the axial through straight hole of the pressing block is in straight-line communication with the internal diameter cavity of the fastening sleeve, and the exposed top of the pressing block is provided with a rotating part for the wrench.

2. A fastening tool for fasteners of a turboprop engine rotor according to claim 1, characterized in that, The flange plate is a rectangular flange plate.

3. A fastening tool for fasteners of a turboprop engine rotor according to claim 1, characterized in that, The rotating rod of the torque wrench is a round rod.

4. A fastening tool for fasteners of a turboprop engine rotor according to claim 1, characterized in that, The cross section of the rotating part is square.

5. A fastening tool for fasteners of a turboprop engine rotor according to claim 1, characterized in that, The fastening sleeve, the pressing seat and the pressing block are all made of stainless steel.

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