Aero-engine mounting rack suitable for two-dimensional overturning movement

Abstract

The invention provides an aero-engine mounting rack suitable for two-dimensional overturning movement. The aero-engine mounting rack comprises an upper flying attachment case supporting frame and a lower flying attachment case supporting frame. The air inlet channel support is fixedly connected with the main frame; the main frame is fixedly connected with a fixed rack of the open-air test bed, and an engine auxiliary support is arranged in the main frame; the engine main support is installed on the main frame and comprises a sleeve, a main pin shaft, a cover plate, an outer sleeve nut, a tensioning pull rod, an adjusting pull rod and a connecting bolt, the sleeve is fixed to a cross beam on the lower side of the main frame, the main pin shaft is inserted into the sleeve, and the cover plate is arranged on the left side of the sleeve and fixedly connected with the cross beam of the main frame through the connecting bolt; the outer sleeve nut is matched with an outer thread at the end of the main pin shaft, the tensioning screw is arranged in the main pin shaft and connected with the engine, the adjusting connecting rod is arranged in the main pin shaft and connected with the tensioning screw, the tensioning screw can rotate synchronously by rotating the adjusting connecting rod, and then the engine is tensioned and fixed.

Description

Technical Field

[0001] The present application belongs to the field of aero-engine testing, and in particular relates to an aero-engine mounting stand that is adaptable to two-dimensional flipping motion. Background Art

[0002] Aircraft engines need to be tested outdoors. Before installing the aircraft engine on an open-air test bench, the engine needs to be installed on a mounting bench in the factory, and then the mounting bench and the engine need to be transported to the open-air test bench together, and the mounting bench and the fixed bench of the open-air test bench need to be fixedly connected. The function of the mounting bench is to fix the engine and be able to connect to the fixed bench. Some open-air test benches need to perform multi-dimensional flipping movements - for example, the attitude test bench needs to achieve flipping movements in two dimensions, roll and pitch. Therefore, a mounting bench is required to meet the requirements of engine installation and fixation, and to adapt to multi-dimensional flipping motion test conditions.

[0003] The existing engine mounting rig and engine mounting structure, as well as the connection structure between the mounting rig and the fixed rig, cannot adapt to the rollover motion. In particular, the existing fixed rig cannot meet the requirements for attitude tests that require roll and pitch rollover motions. Summary of the invention

[0004] The purpose of the present application is to provide an aircraft engine mounting stand that can adapt to two-dimensional flipping motion, so as to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: an aircraft engine mounting stand adapted to two-dimensional flipping motion, comprising:

[0006] An upper attachment receiver support frame and a lower attachment receiver support frame respectively adapted to the installation forms of an upper attachment receiver and a lower attachment receiver, one of the upper attachment receiver support frame and the lower attachment receiver support frame being fixedly connected to the main frame;

[0007] An air intake bracket used to support the air intake when the air intake is installed, wherein the air intake bracket is fixedly connected to the main frame;

[0008] A main frame fixedly connected to a fixed frame of an open-air test bench, wherein an engine auxiliary support is provided inside the main frame to assist in fixing the engine;

[0009] An engine main support installed on the main frame for connecting to the engine, the engine main support includes a sleeve, a kingpin shaft, a cover plate, an outer sleeve nut, a tensioning rod, an adjustment rod and a connecting bolt. The sleeve is fixed to the crossbeam on the lower side of the main frame, and the kingpin shaft is inserted into the sleeve. The cover plate is arranged on the side of the sleeve away from the engine and is fixedly connected to the crossbeam of the main frame by connecting bolts. The outer sleeve nut cooperates with the external thread at the end of the kingpin shaft to connect the kingpin shaft, the cover plate and the crossbeam of the main frame into one body. A step hole is provided at the center of the axis of the kingpin shaft, the tensioning screw is arranged in the step hole on one side of the kingpin shaft and is connected to the engine structure, the adjustment connecting rod is arranged in the step hole on the other side of the kingpin shaft, and the adjustment connecting rod is connected to the tensioning screw. The tensioning screw can be rotated synchronously by rotating the adjusting connecting rod, and then the engine is tightened and fixed by the tensioning screw.

[0010] In an optional embodiment of the present application, the main frame is a semicircular frame structure as a whole, rollers are provided at the bottom of the main frame and a plurality of lifting ears are distributed on the main frame, so as to realize overall movement under the condition that the engine, air inlet and flight accessory casing are fully installed.

[0011] In an optional embodiment of the present application, a fixed bench mounting plate is provided on the front end surface of the lower cross beam of the main frame, and the main frame is connected to the fixed bench of the open-air test bench through the fixed bench mounting plate and bears the engine thrust.

[0012] In an optional implementation manner of the present application, an auxiliary mounting plate is provided on the rear side of the main frame to ensure the support stability of the mounting stand.

[0013] In an optional embodiment of the present application, the auxiliary support is a bidirectionally adjustable pull rod mechanism, and the engine is tightened by adjusting the length of the pull rod.

[0014] In an optional embodiment of the present application, a groove is provided on the side of the sleeve away from the engine, and a guide protrusion is provided on the kingpin shaft at a position adapted to the groove, and the correct angular position of the kingpin shaft and the sleeve is ensured to be installed through the cooperation between the groove and the guide protrusion.

[0015] In an optional implementation manner of the present application, an adjustment plate is provided between the cross beam of the main frame and the cover plate for adjusting the extension distance of the kingpin shaft.

[0016] In an optional embodiment of the present application, one end of the tightening screw is provided with an inner hexagonal structure, and the other end is provided with a threaded structure connected to the engine structure;

[0017] The extending end of the adjusting connecting rod is provided with a hexagonal head structure, and the hexagonal head structure of the adjusting connecting rod cooperates with the inner hexagonal structure of the tightening screw.

[0018] This application improves the main support structure of the mounting bench and the mounting structure of the fixed bench on the test bench, so that the engine mounting bench can meet the test requirements of flipping motion in two dimensions of roll and pitch. At the same time, the structure is more compact and more adaptable to the installation of the engine on the closed structure fixed bench. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0020] Figure 1 It is a schematic diagram of the engine mounting stand structure (upper flight attachment casing support frame) of the present application.

[0021] Figure 2 This is a top view of the engine mounting stand structure of the present application.

[0022] Figure 3 It is a schematic diagram of the engine mounting stand structure (lower attached casing support frame) of the present application.

[0023] Figure 4 Based on Figure 1 AA view in .

[0024] Figure 5 Based on Figure 1 BB view in the figure.

[0025] Figure 6 Based on Figure 1 CC view in .

[0026] Figure 7 Based on Figure 1 DD view in.

[0027] Figure 8 Based on Figure 3 EE view in the diagram.

[0028] Fig. 9 This is a schematic diagram of the main support structure of the engine of this application.

[0029] Fig.10 Based on Fig. 9 FF view in the figure.

[0030] Fig.11 Based on Fig. 9 GG view in the figure.

[0031] Fig.12 This is a P-direction schematic diagram of the main support structure of the engine of this application.

[0032] Reference numerals:

[0033] 1- Upper flight attachment receiver support frame;

[0034] 2-Intake duct support frame

[0035] 3-Engine main support

[0036] 31-Sleeve

[0037] 32-Kingpin shaft

[0038] 33-Cover

[0039] 34-Adjustment plate

[0040] 35-jacket nut

[0041] 36-Tension screw

[0042] 37-Adjust the connecting rod

[0043] 38-Connecting bolt

[0044] 4- Main frame

[0045] 41-Roller

[0046] 42-Legs

[0047] 43-Engine auxiliary support

[0048] 44-Fixed stand mounting plate

[0049] 45-Auxiliary mounting plate

[0050] 5-Measurement and control equipment box

[0051] 6-Lower flying receiver support frame DETAILED DESCRIPTION

[0052] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0053] The present application makes structural improvements to the main support structure of the existing mounting stand and the mounting structure connected to the fixed stand, so that it can meet the test requirements of flipping motion in two dimensions of roll and pitch.

[0054] like Figures 1 to 8 As shown, the aviation engine mounting stand adapted to two-dimensional flipping motion provided by the present application mainly includes: an upper flight attachment casing support frame 1, a lower flight attachment casing support frame 6, an air inlet support frame 2, an engine main support 3 and a main frame 4.

[0055] The upper attachment casing support frame 1 and the lower attachment casing support frame 6 are respectively adapted to the installation forms of the upper attachment casing and the lower attachment casing, and both are fixed on the main frame 4 and the air inlet bracket 2, and are not installed at the same time.

[0056] The air intake duct bracket 2 is fixedly connected to the main frame 4, and an air intake duct supporting device is installed on the air intake duct bracket 2 to support the air intake duct when the air intake duct is installed.

[0057] The main frame 4 is a semicircular frame structure as a whole, with rollers 41 arranged at the bottom and multiple lifting ears 42 distributed on the frame, so that the main frame 4 has the functions of moving and lifting, and realizes the overall movement under the condition that the engine, air intake duct, and flight accessory casing are fully installed, which is convenient for installation. A fixed stand mounting plate 44 is arranged on the front end surface of the lower crossbeam of the main frame 4, which is used to connect with the fixed stand (not shown) of the open-air test bench and bear the engine thrust. An auxiliary mounting plate 45 is arranged on the rear side of the main frame 4 to ensure the support and stability of the mounting stand.

[0058] In addition, measurement and control equipment boxes 5 are installed on both sides of the main frame 4, and an engine auxiliary support 43 is provided on the inner side of the rear end of the main frame 4, which can assist in fixing the engine. In some embodiments of the present application, the auxiliary support 43 is a bidirectional adjustable pull rod mechanism, and the engine is tightened by adjusting the length of the pull rod.

[0059] In some embodiments of the present application, the above-mentioned upper attachment casing support frame 1, the lower attachment casing support frame 6, the air inlet bracket 2 and the main frame 4 are all frame structures composed of square tubes.

[0060] The engine main support 3 passes through the cross beam on the lower side of the main frame 4 and is installed on the main frame 4 for connecting with the engine to support the engine.

[0061] like Figures 9 to 12 As shown, the engine main support 3 includes: a sleeve 31, a kingpin shaft 32, a cover plate 33, an adjustment plate 34, a sleeve nut 35, a tension rod 36, an adjustment rod 37 and a connecting bolt 38.

[0062] The sleeve 31 is welded and fixed on the crossbeam at the lower side of the main frame 4, and the main pin shaft 32 is inserted into the sleeve 31. The sleeve 31 is away from the engine side ( Fig. 9 A groove is provided on the left side of the center, and a guide protrusion is provided on the main pin shaft 32 at a position adapted to the groove. The two cooperate to ensure that the angular position of the main pin shaft 32 and the sleeve 31 is correctly installed.

[0063] The inner side (the side close to the engine) of the kingpin shaft 32 has a conical structure, the outer side (the side away from the engine) has an external thread, the middle outer surface has a straight structure, and the center of the axis of the kingpin shaft 32 has a stepped hole structure.

[0064] The cover plate 33 is arranged on the outside of the sleeve 31, and is fixedly connected to the crossbeam of the main frame 4 by connecting bolts 38, and the main pin shaft 32, the cover plate 33 and the crossbeam of the main frame 4 are connected into one by a sleeve nut 35 that cooperates with the external thread on the outside of the main pin shaft 32.

[0065] In some embodiments of the present application, an adjustment plate 34 may be provided between the crossbeam of the main frame 4 and the cover plate 33 to adjust the extension distance of the main pin shaft 32. Furthermore, a top screw hole may be provided on the cover plate 33 to facilitate the removal of the main pin shaft 32.

[0066] The tensioning screw 36 is set in the small hole on the right side of the step hole of the main pin shaft 32. Its outer head is a hexagonal structure and its inner part is a threaded structure, which can be connected to the engine structure. The adjustment connecting rod 37 is set in the large hole on the left side of the step hole of the main pin shaft 32. Its inserted end is a hexagonal head structure. The hexagonal head structure of the adjustment connecting rod 37 cooperates with the hexagonal structure of the tensioning screw 36. By rotating the adjustment connecting rod 37, the tensioning screw 36 can be rotated synchronously, and the thread at the other end of the tensioning screw 37 is used to tighten and fix the engine (one side of the two main supports of the engine is tightened, and the other side is free laterally).

[0067] It should be noted that the engine main support 3 can be adapted to different engines by adjusting the size of the kingpin shaft 32 .

[0068] This application improves the main support structure of the mounting bench and the mounting structure of the fixed bench on the test bench, so that the engine mounting bench can meet the test requirements of flipping motion in two dimensions of roll and pitch. At the same time, the structure is more compact and more adaptable to the installation of the engine on the closed structure fixed bench.

[0069] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An aircraft engine mounting stand adapted to two-dimensional flipping motion, characterized in that: include: An upper attached casing support frame (1) and a lower attached casing support frame (6) respectively adapted for installation of an upper attached casing and a lower attached casing, one of the upper attached casing support frame (1) and the lower attached casing support frame (6) being fixedly connected to the main frame (4); An air intake duct support (2) used for supporting the air intake duct when the air intake duct is installed, wherein the air intake duct support (2) is fixedly connected to the main frame (4); A main frame (4) fixedly connected to a fixed frame of an open-air test bench, wherein an engine auxiliary support (43) is provided inside the main frame (4) for assisting in fixing the engine; An engine main support (3) mounted on a main frame (4) for connecting to an engine, the engine main support (3) comprising a sleeve (31), a kingpin shaft (32), a cover plate (33), a sleeve nut (35), a tension rod (36), an adjustment rod (37) and a connecting bolt (38), the sleeve (31) being fixed on a crossbeam at the lower side of the main frame (4), the kingpin shaft (32) being inserted into the sleeve (31), the cover plate (33) being arranged on a side of the sleeve (31) away from the engine, and being fixedly connected to the crossbeam of the main frame (4) via a connecting bolt (38), the sleeve nut (35) being connected to the kingpin shaft The external thread at the end of the main pin (32) cooperates to connect the main pin shaft (32), the cover plate (33) and the cross beam of the main frame (4) into one body. The center of the axis of the main pin shaft (32) is provided with a step hole. The tensioning screw (36) is arranged in the step hole on one side of the main pin shaft (32) and is connected to the engine structure. The adjusting connecting rod (37) is arranged in the step hole on the other side of the main pin shaft (32), and the adjusting connecting rod (37) is connected to the tensioning screw (36). By rotating the adjusting connecting rod (37), the tensioning screw (36) can be rotated synchronously, and then the tensioning screw (37) is used to tighten and fix the engine.

2. The aircraft engine mounting stand adapted to two-dimensional flipping motion according to claim 1, characterized in that: The main frame (4) is a semicircular frame structure as a whole. A roller (41) is arranged at the bottom of the main frame (4) and a plurality of lifting ears (42) are distributed on the main frame, so as to realize overall movement under the condition that the engine, air intake duct and flight accessory casing are fully installed.

3. The aircraft engine mounting stand adapted to two-dimensional flipping motion as claimed in claim 2, characterized in that: A fixed bench mounting plate (44) is provided on the front end surface of the lower cross beam of the main frame (4), and the main frame (4) is connected to the fixed bench of the open-air test bench through the fixed bench mounting plate (44) and bears the engine thrust.

4. The aircraft engine mounting stand adapted to two-dimensional flipping motion as claimed in claim 3, characterized in that: An auxiliary mounting plate (45) is arranged on the rear side of the main frame (4) to ensure the support stability of the mounting stand.

5. The aircraft engine mounting stand adapted to two-dimensional flipping motion as claimed in claim 1, characterized in that: The auxiliary support (43) is a bidirectionally adjustable pull rod mechanism, and the engine can be tightened by adjusting the length of the pull rod.

6. The aircraft engine mounting stand adapted to two-dimensional flipping motion as claimed in claim 1, characterized in that: The sleeve (31) is provided with a groove on a side away from the engine, and a guide protrusion is provided on the kingpin shaft (32) at a position adapted to the groove, and the kingpin shaft (32) and the sleeve (31) are correctly installed in angular position through the cooperation between the groove and the guide protrusion.

7. The aircraft engine mounting stand adapted to two-dimensional flipping motion as claimed in claim 1, characterized in that: An adjustment plate (34) is provided between the cross beam of the main frame (4) and the cover plate (33) for adjusting the extension distance of the main pin shaft (32).

8. The aircraft engine mounting stand adapted to two-dimensional flipping motion as claimed in claim 1, characterized in that: The tightening screw (36) has a hexagonal structure at one end and a threaded structure connected to the engine structure at the other end; The extending end of the adjusting connecting rod (37) is provided with a hexagonal head structure, and the hexagonal head structure of the adjusting connecting rod (37) cooperates with the inner hexagonal structure of the tightening screw rod (36).

Images