An aircraft engine accessory installation method and inspection tool

Abstract

The present invention discloses a method for installing aircraft engine accessories and an inspection tool. The installation method includes steps carried out using the inspection tool for installing aircraft engine accessories. When assembling the coupling mandrel with the aircraft accessory casing, by using the inspection tool for installing aircraft engine accessories, the axial elongation of the coupling mandrel after assembly is ensured, and the included angle between the axis of the coupling mandrel and the installation hole axis of the aircraft accessory casing is ensured, thereby improving the low installation efficiency and solving the problem that it is impossible to ensure that the coupling mandrel can maintain a suitable included angle and a suitable elongation during operation after installation.

Description

Technical Field

[0001] The present invention relates to a method for installing aircraft engine accessories and an inspection tool, belonging to the technical field of aero-engine assembly. Background Art

[0002] At present, an aircraft engine and an aircraft accessory casing are connected by a flexible coupling to transfer the shaft power of the engine output shaft to the aircraft accessory casing. However, factors such as the angle between the axis of the mandrel of the flexible coupling and the engine output shaft during installation and the axial elongation of the coupling will affect the service life, power transmission efficiency and other performances of the coupling. Therefore, after the mandrel of the flexible coupling is installed on the aircraft accessory casing, it is necessary to check to ensure that the mandrel of the coupling maintains a suitable angle and a suitable elongation.

[0003] Although, for the installation of the shaft, an existing auxiliary installation device (a kind of automotive parts detection and positioning device with the Chinese Patent Publication No. CN212779890U) can be used to install and detect and position the mandrel of the coupling in an operating environment with a large installation space. However, when the aircraft accessory casing is installed on the aircraft, due to the limitations of the aircraft power cabin space and maintenance openings, the installation workers cannot enter the interior to use the auxiliary installation device for inspection. Currently, when the installation workers install the aircraft accessory casing, the docking end face position between the aircraft accessory casing and the mandrel of the coupling entirely depends on the naked eye observation and feeling of the workers, resulting in the problem that it is impossible to ensure that the mandrel of the coupling maintains a suitable angle and a suitable elongation after installation, and the installation efficiency is low. Summary of the Invention

[0004] To solve the above technical problems, the present invention provides a method for installing aircraft engine accessories and an inspection tool.

[0005] The present invention is achieved through the following technical solutions.

[0006] A method for installing aircraft engine accessories provided by the present invention includes steps performed using an inspection tool for installing aircraft engine accessories.

[0007] The steps performed using the inspection tool for installing aircraft engine accessories are specifically as follows:

[0008] Step 1: One end of a bracket is fixed to the engine, and the end face at the other end of the bracket is axially flush with the end face of the coupling installation end;

[0009] Step 2: A screw corresponds to a threaded through hole of the bracket. At this time, the screw is not screwed to the bottom and a certain length is reserved;

[0010] Step 3: An open circlip is snapped into the outer diameter of the coupling mandrel through the bayonet, and the hook of the mounting plate is hung on the screw already installed on the bracket;

[0011] Step 4: Then screw the other two screws into the other two threaded through-holes of the bracket from the mounting plate, and rotate and screw the three screws to the bottom so that the end face of the bracket is in full contact with the mounting surface iiiii of the mounting plate;

[0012] Step 5: By checking that the flanging completely sleeves the coupling mounting end installed on the flying accessory housing, the axial elongation of the coupling mandrel after assembly is ensured. By measuring multiple depth values obtained by inserting a depth gauge into the detection through-holes, the angle between the axis of the coupling mandrel and the mounting hole of the flying accessory housing is calculated and verified;

[0013] The inspection tool for installing aircraft engine accessories includes:

[0014] A mounting plate and an open snap ring fixed to the mounting plate;

[0015] A through-hole is provided in the middle of the open snap ring;

[0016] A bayonet with a width i is provided on the open snap ring;

[0017] The open snap ring axially extends with an inspection flanging. The inspection flanging is located at an axial depth of the open snap ring equal to the axial width of the coupling mounting end. The inner diameter iii of the inspection flanging is equal to the inner diameter of the coupling mounting end plus the tolerance amount for clearance fitting;

[0018] A plurality of detection through-holes are circumferentially and arrayed at intervals on the open snap ring.

[0019] A hook is fixed to the side of the mounting plate.

[0020] Mounting through-holes are provided on the mounting plate away from the hook.

[0021] The mounting through-holes are two spaced apart, and the two mounting through-holes and the groove opening of the hook form a triangular distribution.

[0022] It also includes three screws and a bracket.

[0023] Three threaded through-holes are provided on the bracket in a triangular distribution.

[0024] The three threaded through-holes correspond to the two mounting through-holes and the groove opening of the hook for triangular stable installation corresponding to the three screws.

[0025] The beneficial effect of the present invention is that when assembling the coupling mandrel and the flying accessory housing, by using the inspection tool for installing aircraft engine accessories, the axial elongation of the coupling mandrel after assembly is ensured, and the angle between the axis of the coupling mandrel and the mounting hole of the flying accessory housing is ensured, thereby improving the low installation efficiency and solving the problem that it is impossible to ensure that the mandrel of the coupling can maintain a suitable angle and a suitable elongation during operation after installation. Description of the Drawings

[0026] Figure 1 It is a schematic structural diagram composed of the split retaining ring and the mounting plate of the present invention;

[0027] Figure 2 It is a top view schematic diagram composed of the split retaining ring and the mounting plate of the present invention;

[0028] Figure 3 It is a schematic structural diagram of a screw of the present invention mounted on a bracket;

[0029] Figure 4 It is a schematic structural diagram after the hook of the present invention is snapped into the coupling mandrel;

[0030] Figure 5 It is a schematic structural diagram of the hook and a screw installation of the present invention;

[0031] Figure 6 It is a schematic structural diagram of the hook and three screws installation of the present invention;

[0032] Figure 7 It is a schematic structural diagram of the inspection of the flanging and the installation of the coupling installation end of the present invention;

[0033] Figure 8 It is a schematic structural diagram when the depth gauge and the detection through hole are being detected of the present invention;

[0034] In the figure: 1 - mounting plate; 2 - split retaining ring; 3 - mounting through hole; 4 - hook; 5 - detection through hole; 6 - inspection flanging; 7 - bracket; 8 - threaded through hole; 9 - coupling mandrel; 10 - coupling installation end; 11 - screw; 14 - attached engine case; 15 - depth gauge. Detailed implementation manners

[0035] The technical solution of the present invention will be further described below, but the scope of protection claimed is not limited thereto.

[0036] See Figures 1 to 8 as shown.

[0037] An inspection tool for installing aircraft engine accessories of the present application includes:

[0038] A mounting plate 1 and a split retaining ring 2 made of rigid materials such as stainless steel or rigid plastic, and the mounting plate 1 and the split retaining ring 2 are integrally and fixedly formed;

[0039] A through hole with a diameter greater than or equal to the inside and outside of the coupling installation end 10 is provided in the middle of the split retaining ring 2;

[0040] A bayonet with a width i greater than the outer diameter of the coupling mandrel 9 is provided on the split retaining ring 2, which facilitates the split retaining ring 2 to be radially snapped into or pulled away from the outer diameter of the coupling mandrel 9, so that the split retaining ring 2 can be used in a working environment with a small installation space;

[0041] On one axial side of the split snap ring 2, an inspection flange 6 is integrally formed and fixed. The inspection flange 6 is located at an axial depth of the split snap ring 2 equal to the axial width of the coupling mounting end 10. The inner diameter iii of the inspection flange 6 is equal to the inner diameter of the coupling mounting end 10 plus a tolerance amount that can be sleeved with a clearance, so that the inspection flange 6 can be sleeved with the coupling mounting end 10 with a clearance;

[0042] On the split snap ring 2, a plurality of detection through holes 5 are circumferentially and arrayed at intervals. The number of the detection through holes 5 is seven. A depth gauge 15 is used to respectively penetrate into the plurality of detection through holes 5 to detect the depth value from the axial end face of the split snap ring 2 at the position of the detection through holes 5 to the coupling mandrel 9. The included angle between the axis of the coupling mandrel 9 and the axis of the mounting hole of the flywheel housing 14 is calculated through each depth value.

[0043] A hook 4 is integrally formed and fixed on one side of the mounting plate 1; on the mounting plate 1 far from the hook 4, two mounting through holes 3 are provided. The two mounting through holes 3 are distributed at intervals, and the two mounting through holes 3 and the groove opening of the hook 4 form a triangular distribution.

[0044] It further includes three screws 11 and a bracket 7 fixed on the engine during use. The bracket 7 is provided with three threaded through holes 8 distributed in a triangle. The three threaded through holes 8 correspond to the two mounting through holes 3 and the groove opening of the hook 4, so as to be stably mounted in a triangle corresponding to the three screws 11.

[0045] An installation method for aircraft engine accessories in this application uses an inspection tool for installing aircraft engine accessories, and includes the following steps:

[0046] Step 1: One end of the bracket 7 is fixed on the engine, and the end face of the other end of the bracket 7 is axially flush with the end face of the coupling mounting end 10; Figure 3 .

[0047] Step 2: One screw 11 corresponds to one threaded through hole 8 of the bracket 7. At this time, the screw 11 is not screwed to the bottom and a certain length is reserved; Figure 3 .

[0048] Step 3: The split snap ring 2 is snapped onto the outer diameter of the coupling mandrel 9 through the bayonet, and the hook 4 of the mounting plate 1 is hung on the screw 11 already installed on the bracket 7; Figures 4 to 5 .

[0049] Step 4: Then the other two screws 11 are screwed into the other two threaded through holes 8 of the bracket 7 from the mounting plate 1, and the three screws 11 are rotated and screwed to the bottom, so that the end face of the bracket 7 is in full contact with the mounting surface iiiii of the mounting plate 1; Figures 6 to 7 .

[0050] Step 5: By checking that the flanging 6 completely encloses the coupling installation end 10 installed on the flying accessory housing 14, the axial elongation of the coupling mandrel 9 after assembly is ensured. Through the multiple depth values measured by inserting the depth gauge 15 into the detection through-hole 5, the angle between the axis of the coupling mandrel 9 and the installation hole of the flying accessory housing 14 is calculated and verified. For example, Figure 8 .

[0051] When assembling the coupling mandrel 9 and the flying accessory housing, by using the inspection tool for the installation of aircraft engine accessories, the axial elongation of the coupling mandrel 9 after assembly is ensured, and the angle between the axis of the coupling mandrel 9 and the installation hole of the flying accessory housing 14 is ensured. In this way, the installation efficiency is improved, and the problem that the mandrel of the coupling cannot be maintained at a suitable angle and a suitable elongation during operation after installation is solved.

Claims

1. A method for installing aircraft engine accessories, characterized in that, Including: Steps carried out using an inspection tool for the installation of aircraft engine accessories; The inspection tool for the installation of aircraft engine accessories includes: A mounting plate (1) and an open snap ring (2) fixed to the mounting plate (1); A through hole is provided in the middle of the open snap ring (2); A bayonet with a width of i is provided on the open snap ring (2); An inspection flange (6) axially extends from the open snap ring (2). The inspection flange (6) is located at an axial depth of the open snap ring (2) equal to the axial width of the coupling mounting end (10), and the inner diameter iii of the inspection flange (6) is equal to the inner diameter of the coupling mounting end (10) plus a tolerance amount that can be sleeved with a clearance; A plurality of detection through holes (5) are circumferentially and arrayed at intervals on the open snap ring (2); A hook (4) is fixed to the side of the mounting plate (1); Mounting through holes (3) are provided on the mounting plate (1) away from the hook (4); The two mounting through holes (3) are spaced apart. The two mounting through holes (3) and the groove opening of the hook (4) form a triangular distribution; It also includes three screws (11) and a bracket (7); Three threaded through holes (8) distributed in a triangle are provided on the bracket (7); The steps are specifically as follows: Step 1: One end of the bracket (7) is fixed to the engine, and the end face of the other end of the bracket (7) is axially flush with the end face of the coupling mounting end (10); Step 2: One screw (11) corresponds to one threaded through hole (8) of the bracket (7). At this time, the screw (11) is not screwed to the bottom and a certain length is reserved; Step 3: The open snap ring (2) is snapped onto the outer diameter of the coupling mandrel (9) through the bayonet, and the hook (4) of the mounting plate (1) is hung on the screw (11) already installed on the bracket (7); Step 4: Then the other two screws (11) are screwed into the other two threaded through holes (8) of the bracket (7) from the mounting plate (1), and the three screws (11) are rotated and screwed to the bottom so that the end face of the bracket (7) is in complete contact with the mounting surface iiiii of the mounting plate (1); Step 5: The coupling mounting end (10) mounted on the aircraft accessory housing (14) is completely sleeved by the inspection flange (6), ensuring the axial elongation of the coupling mandrel (9) after assembly. By measuring multiple depth values obtained by inserting a depth gauge (15) into the detection through holes (5), the angle between the axis of the coupling mandrel (9) and the mounting hole of the aircraft accessory housing (14) is calculated and verified.

2. The method for installing an aircraft engine accessory according to claim 1, wherein The three threaded through holes (8) correspond to the two mounting through holes (3) and the groove opening of the hook (4) for convenient triangular and stable installation corresponding to the three screws (11).

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