Aero-engine fan rotor locking blade stopping device and assembling method

Abstract

The invention discloses an aero-engine fan rotor locking blade stopping device and an assembling method. The stopping device comprises a base, a cushion block, a screw rod, a pin, a nut and a knurled high-head screw. The base comprises an axial support arm parallel to the axial direction of the aero-engine fan rotor and a radial support arm parallel to the radial direction of the aero-engine fan rotor, and a notch is formed in the axial support arm to divide the axial support arm into an upper support arm and a lower support arm. The nut and the screw rod are assembled on the axial support arm, and the cushion block is detachably connected to the base. When the stop pin is assembled, the base is firstly placed between the two adjacent stages of wheel discs, then the cushion block is placed between the two adjacent stages of wheel discs, the two adjacent stages of wheel discs abut against the opposite end faces of the two stages of wheel discs respectively, then the nut is screwed, the stop pin is jacked up through the lower supporting arm, and then flaring operation is conducted. Single-person assembly is achieved, the one-time assembly qualification rate of the stop pin is increased, and the machining time is shortened.

Description

Technical Field

[0001] The invention belongs to the field of aero-engine manufacturing, and in particular relates to a special device for fixing and locking a stop pin after assembling blades of a fan rotor balancing assembly, a core rotating component of an aero-engine, and a stop pin assembly method. Background Art

[0002] like Figure 1 and Figure 2 As shown, the fan rotor balancing assembly is implemented in the following manner when assembling the blades: first, install the blades into the tenon grooves of the wheel disc, then use a retaining ring to insert the retaining ring into the groove at the bottom of the blade along the circumferential direction to fix the blades, and finally use a stop pin to tighten the front and rear ends of the retaining ring. It is necessary to use a punch to punch open the stop pin and then lock the retaining ring to clamp the blades to prevent the blades from axial movement.

[0003] The current method of locking the fan rotor blade stop pin is: a pad is placed under the stop pin, one operator puts a crowbar on the pad and lifts the stop pin, and the other operator uses 30°, 60°, and 90° punches to punch open the stop pin until the stop pin fits into the inner surface of the pin hole on the wheel (such as Figure 2 Obviously, currently, locking the stop pin requires two people simultaneously, making it impossible for a worker to complete the task independently. Furthermore, the force applied by the crowbar to lift the stop pin is difficult to control. Excessive force can easily damage the pin head, resulting in the part being scrapped. Too little force can prevent the stop pin from locking properly during the punching process. Furthermore, with current existing technology, locking a fan rotor typically takes over 0.6 hours, which is not only time-consuming but also requires significant labor costs.

[0004] Based on the above situation, in order to achieve high-efficiency, high-quality and low-cost assembly of the fan rotor balancing assembly of the core rotating component of the aircraft engine, it is urgently necessary to propose a special device and assembly method for fixing and locking the stop pin after assembling the blades of the fan rotor balancing assembly of the core rotating component of the aircraft engine. Summary of the Invention

[0005] The present invention aims to provide an aircraft engine fan rotor locking blade stop device and assembly method, so that assemblers can independently complete the assembly process, effectively improve the one-time assembly pass rate of the stop pin, reduce manpower consumption, shorten processing time, and accelerate the flow efficiency within the fan rotor assembly unit.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] An aircraft engine fan rotor locking blade stopping device, comprising:

[0008] The base is L-shaped and includes an axial support arm parallel to the axial direction of the aircraft engine fan rotor and a radial support arm parallel to the radial direction of the aircraft engine fan rotor, wherein a notch is formed on the axial support arm to divide the axial support arm into an upper support arm and a lower support arm, and the end of the lower support arm forms a position for supporting a stop pin. The axial support arm also has a through hole, and the through hole passes through the upper support arm, the notch, and the lower support arm. The thickness of the upper support arm along the axis of the through hole is greater than the thickness of the lower support arm along the axis of the through hole.

[0009] A screw, comprising a head and a shaft, wherein the outer diameter of the head is larger than the inner diameter of the opening of the through hole corresponding to the upper hole of the lower arm, and at least a portion of the surface of the shaft is provided with an external thread. The screw is inserted into the through hole and the head is located on the side of the lower arm away from the upper arm;

[0010] A nut is connected to the external thread of the rod portion of the screw rod through a through hole corresponding to one side of the upper support arm.

[0011] Furthermore, the aircraft engine fan rotor locking blade stopping device also includes a pad, which is detachably connected to one side of the radial support arm on the base through a connecting piece and fits with the surface of the radial support arm.

[0012] Furthermore, the aircraft engine fan rotor locking blade stopping device further comprises:

[0013] A notch is provided on the head of the screw;

[0014] The pin is assembled on the lower support arm, and a part of the pin is inserted into the notch.

[0015] As an option, the cross-sectional shape of the notch of the axial support arm is a combination of a rectangle and a circle, wherein the circular cross-sectional shape is located at one end of the rectangular cross-sectional shape in the length direction.

[0016] As an option, the end of the upper arm further includes an avoidance groove, below which is the end of the lower arm supporting the stop pin.

[0017] A method for assembling locking blades of an aircraft engine fan rotor employs the aforementioned stopper without a pad and comprises the following steps:

[0018] Step 1: Place the base between two adjacent wheel discs, ensuring that the two end faces of the axial support arms are pressed tightly against the two opposite surfaces of the two wheel discs;

[0019] Step 2: Rotate the nut to drive the screw to move so that the lower arm moves closer to the upper arm and the end of the lower arm pushes up the stop pin;

[0020] Step 3: Use punches of different sizes to expand the stop pin. After expanding, use a file to flatten the part of the stop pin that protrudes from the surface of the wheel.

[0021] A method for assembling locking blades of an aircraft engine fan rotor employs the aforementioned stopper with a spacer and comprises the following steps:

[0022] Step 1: First, place the base between the two adjacent wheel discs, ensuring that one end face of the axial support arm is pressed tightly against one of the two opposite surfaces of the two wheel discs. Then, insert the spacer between the base and the other wheel disc surface, ensuring that the spacer is pressed tightly against the wheel disc surface, and then connect the spacer to the base.

[0023] Step 2: Rotate the nut to drive the screw to move so that the lower arm moves closer to the upper arm and the end of the lower arm pushes up the stop pin;

[0024] Step 3: Use punches of different sizes to expand the stop pin. After expanding, use a file to flatten the part of the stop pin that protrudes from the surface of the wheel.

[0025] The above two methods for assembling the locking blades of the fan rotor of an aircraft engine also include step four, removing the stop device, placing the stop device between two other adjacent two-stage wheels, and repeating steps one to three until all the stop pins are assembled.

[0026] The existing stop pin locking assembly method requires two people to work together at the same time. One person puts a crowbar on the pad to lift the stop pin, and the other person uses a punch to expand the lock mouth of the stop pin. The force of using the crowbar to lift the stop pin each time is difficult to control. If the force is too small, the expansion is not in place and the locking requirements cannot be met. If the force is too large, the stop pin is easily damaged. As a result, the current assembly method is time-consuming and labor-intensive, inefficient, and easily damages parts.

[0027] Compared with the existing assembly method, the use of the stop assembly device of the present invention for stop pin assembly not only solves the current problem that the stop pin cannot be assembled independently by one person, but also ensures that the force of lifting the stop pin is the same each time (the force depends on the material of the base and the size of the slot), thereby preventing damage to parts, effectively improving the stop pin assembly efficiency and the one-time assembly pass rate, and realizing high-efficiency, high-quality and low-cost assembly of the fan rotor balance assembly, the core rotating component of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a partial schematic diagram of the assembly of the locking blade stop pin of the fan rotor of the aircraft engine in the present invention;

[0029] Figure 2 This is a schematic diagram of the assembly principle of the locking blade stop pin of the aircraft engine fan rotor in the present invention;

[0030] Figure 3 It is a schematic diagram of the locking blade stopping device of the fan rotor of an aircraft engine in the present invention;

[0031] Figure 4 Figure 1 is a schematic view of the base in the locking blade stop device of the fan rotor of an aero-engine in the present application;

[0032] Figure 1 is a schematic view of the base in the locking blade stop device of the fan rotor of an aero-engine in the present application; DETAILED DESCRIPTION

[0033] The present application will be further described in conjunction with specific embodiments, but should not be construed as limiting the scope of the subject matter described herein to the following embodiments. Any modifications, substitutions and variations made according to ordinary technical knowledge and common practices in the art without departing from the technical ideas of the present application are included in the scope of the present application.

[0034] In the present embodiment, the assembly problem of the stop pin is solved in the following manner:

[0035] First, the design of the stop device.

[0036] First, as shown in Figs. 1 and 2, the stop device mainly consists of a base 1, a spacer 2, a screw 3, a pin 4, a nut 5 and a knurled head screw 6. The base 1 is L-shaped, with an axial arm parallel to the axial direction of the fan rotor of the aero-engine, which enables it to be tightly fitted between the axial end faces of the two-stage disks with the spacer 2, and a radial arm parallel to the radial direction of the fan rotor of the aero-engine, which enables it to correspond to the assembly position of the stop pin. Since the space between the two-stage disks after the fan assembly is limited, interference structures exist, causing the entire base 1 to be unable to be placed therein at one time. Therefore, a split design is adopted, i.e., one part of the base 1 is split into the spacer 2, and the base 1 and the spacer 2 are placed in turn to avoid the interference structures. The base 1 and the spacer 2 are connected and fixed by the knurled head screw 6. Figure 3 As shown in Fig. 3, a notch is processed in the middle of the upper and lower arms of the base 1, and a through hole is processed near the right end part of the upper and lower arms, with the inner diameter of the through hole of the upper arm being greater than the outer diameter of the nut 5, leaving a gap for the rotation of the nut 5. The right end of the lower arm contacts the head (horizontal part) of the stop pin. When the nut 5 is rotated, the lower arm deforms and approaches the upper arm due to the fact that the thickness dimension of the upper arm along the axis of the through hole is greater than that of the lower arm along the axis of the through hole (so that the rigidity of the lower arm is less than that of the upper arm, and the lower arm deforms before the upper arm or deforms more than the upper arm under the action of external force), and the notch between the upper and lower arms gradually narrows, so that the end of the lower arm lifts up the stop pin. Figure 4 Figure 3 In the above scheme, the height of the notch can be 1.5 mm to 2.5 mm.

[0037] In the above scheme, the height of the notch can be 1.5 mm to 2.5 mm.

[0038] ​In the above scheme, in order to prevent the screw 3 from rotating, a notch is opened at the head of the screw 3, and a pin 4 is installed on the lower arm, and the pin 4 is inserted into the notch, so that the screw 3 only moves linearly under the drive of the nut 5 and does not rotate.

[0039] In the above scheme, if Figure 4 As shown, for the "T"-shaped stop pin, the right end of the upper arm of the base 1 has a circular avoidance groove for avoiding the vertical part (rod) of the stop pin, and below the avoidance groove is the end of the lower arm for supporting the horizontal part (head) of the stop pin.

[0040] Second, the assembly method of the aircraft engine fan rotor locking blades:

[0041] Step 1: For adjacent primary and secondary disks, first place the base 1 against the top end surface of the secondary disk;

[0042] Step 2: Place the spacer 2 between the base 1 and the first-stage plate, and press against the bottom end face of the first-stage plate. Use the knurled high-head screw 6 to connect and fix the spacer 2 and the base 1. At this time, the lower arm of the base 1 contacts the head (horizontal part) of the "T"-shaped stop pin.

[0043] Step 3: Tighten the nut 5 to drive the screw 3 upward, thereby driving the lower arm closer to the upper arm, so that the end of the lower arm pushes the stop pin upward, and tighten the nut 5 until the stop pin can no longer move upward. At this time, the assembler uses punches with angles of α1, α2, α3, α4, and α5 to expand the stop pin in this state. After expanding, use a file to flatten the part of the stop pin that protrudes above the surface of the fan wheel disc until the final state required by the design is achieved. Figure 2 shown.

[0044] In the above solution, the angles α1, α2, α3, α4 and α5 are 30°, 45°, 60°, 75° and 90° respectively.

[0045] Step 4: Similarly, the locking assembly method of the stop pins corresponding to the third-stage disk and the fourth-stage disk is the same as that of the second-stage disk, and finally the stop pins are fixed and locked after the blades of the fan rotor balance assembly, the core rotating component of the aircraft engine, are assembled.

[0046] Any matters not described in detail in the present specification are prior art known to those skilled in the art. Although the above description of the present invention is based on illustrative embodiments to facilitate understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the specific embodiments. As long as various modifications are within the spirit and scope of the present invention as defined and determined by the appended claims, such modifications will be obvious to those skilled in the art, and all inventions and creations utilizing the concepts of the present invention are protected.

Claims

1. An aircraft engine fan rotor locking blade stop device, characterized in that: include: A base (1) is L-shaped and includes an axial support arm parallel to the axial direction of the aircraft engine fan rotor and a radial support arm parallel to the radial direction of the aircraft engine fan rotor, wherein a notch is provided on the axial support arm to divide the axial support arm into an upper support arm and a lower support arm, and the end of the lower support arm forms a position for supporting a stop pin, and a through hole is also provided on the axial support arm, and the through hole passes through the upper support arm, the notch and the lower support arm, and the thickness dimension of the upper support arm along the axis direction of the through hole is greater than the thickness dimension of the lower support arm along the axis direction of the through hole; A screw rod (3), the screw rod (3) comprising a head and a rod, the outer diameter of the head being larger than the inner diameter of the hole corresponding to the upper opening of the lower support arm, at least a portion of the surface of the rod having an external thread, the screw rod (3) being inserted into the through hole and the head of the screw rod being located on a side of the lower support arm away from the upper support arm; A nut (5) is connected to the external thread of the rod portion of the screw rod (3) via a through hole corresponding to one side of the upper support arm.

2. The aircraft engine fan rotor locking blade stopping device according to claim 1, characterized in that: It also includes a pad (2), which is detachably connected to one side of the radial support arm on the base (1) through a connecting piece and fits the surface of the radial support arm.

3. The aircraft engine fan rotor locking blade stopping device according to claim 1, characterized in that: Also includes: a notch, the notch being provided at the head of the screw (3); A pin (4) is assembled on the lower support arm, and a part of the pin (4) is inserted into the notch.

4. The aircraft engine fan rotor locking blade stopping device according to claim 1, characterized in that: The cross-sectional shape of the notch of the axial support arm is a combination of a rectangle and a circle, wherein the circle cross-sectional shape is located at one end of the length direction of the rectangle cross-sectional shape.

5. The aircraft engine fan rotor locking blade stopping device according to claim 1, characterized in that: The end of the upper support arm also includes an avoidance groove, and below the avoidance groove is the end of the lower support arm supporting the stop pin.

6. A method for assembling locking blades of an aircraft engine fan rotor, characterized in that: The stopping device according to claim 1 is used, and includes the following steps: Step 1: Place the base (1) between two adjacent wheel discs, ensuring that the two end faces of the axial support arms are pressed against two opposite surfaces of the two wheel discs; Step 2: Rotate the nut (5) to drive the screw (3) to move so that the lower arm moves closer to the upper arm and the end of the lower arm lifts the stop pin; Step 3: Use punches of different sizes to expand the stop pin. After expanding, use a file to flatten the part of the stop pin that protrudes from the surface of the wheel.

7. A method for assembling locking blades of an aircraft engine fan rotor, characterized in that: The stopping device according to claim 2 is used, and includes the following steps: Step 1: First, place the base (1) between two adjacent wheel discs, ensuring that one end face of the axial support arm is pressed against one of the two opposite surfaces of the two wheel discs, then insert the pad (2) between the base (1) and the other wheel disc surface, ensuring that the pad (2) is pressed against the wheel disc surface, and then connect the pad (2) to the base (1); Step 2: Rotate the nut (5) to drive the screw (3) to move so that the lower arm moves closer to the upper arm and the end of the lower arm lifts the stop pin; Step 3: Use punches of different sizes to expand the stop pin. After expanding, use a file to flatten the part of the stop pin that protrudes from the surface of the wheel.

8. The method for assembling locking blades of an aircraft engine fan rotor according to claim 6 or 7, characterized in that: The method further includes step 4, disassembling the stopper, placing the stopper between two other adjacent two-stage wheel discs, and repeating steps 1 to 3 until all the stopper pins are assembled.

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