Aero-engine installation thrust testing device

Abstract

The utility model provides an aero-engine installation thrust testing device, which belongs to the field of aero-engine performance testing and comprises a static frame and a movable frame, the movable frame is arranged in the middle of the static frame, and a gap is reserved between the movable frame and the static frame. The static frame is of a hollow rectangular structure; the movable frame is connected with the static frame through a spring piece, and a thrust sensor is further arranged at the bottom of the movable frame. A first threaded hole connected with the first end of the spring piece is formed in the side wall of the movable frame, and a second threaded hole connected with the second end of the spring piece is formed in the inner side wall of the static frame. According to the utility model, the installation thrust of the aero-engine is measured by arranging the movable frame and the static frame.

Description

Technical Field

[0001] The utility model belongs to the field of aviation engine performance testing, in particular to an aviation engine installation thrust testing device. Background Art

[0002] Engine installed thrust directly impacts aircraft performance, including takeoff roll distance, takeoff weight, and range. Existing aircraft engine thrust testing equipment primarily performs bench thrust measurements in an unassembled state. This fails to accurately simulate bleed air, power extraction, internal and external flows, and requires conversion using empirical formulas. This results in low accuracy, fails to simulate actual engine flow field losses, and fails to accurately reflect installed engine performance. Furthermore, the equipment is complex to install and debug. For example, the SB101 high-altitude test bench engine thrust measurement system, due to the presence of unmeasured secondary flow and vacuum forces, requires a complex cold calibration method to determine their relationship with the aerodynamic parameters within the high-altitude cabin. The resulting engine bench performance requires a dimensionless conversion relationship for total thrust, combined with in-flight measurements of the engine's primary aerodynamic interfaces, to evaluate the actual total thrust level. This method is cumbersome and inaccurate. Direct installed thrust testing, on the other hand, can reflect the interaction between the engine and aircraft's actual flow field, assess the engine-aircraft match, and provide a true reflection of engine performance.

[0003] Therefore, there is a need for a thrust test device that can perform an installed state of an aircraft engine to solve the above problems. Utility Model Content

[0004] In response to the deficiencies of the existing technology, the utility model provides an aircraft engine installation thrust test device. The device makes the test simple and convenient through the cooperation of a static frame and a dynamic frame, and can measure the engine installation thrust in real time through sensor data.

[0005] To achieve the above purpose, the present invention discloses the following technical solutions:

[0006] An aircraft engine mounting thrust test device comprises a static frame and a dynamic frame, wherein the dynamic frame is arranged in the middle of the static frame, and a gap is formed between the dynamic frame and the static frame; the static frame is a hollow rectangular structure; the dynamic frame is connected to the static frame via a spring sheet, and a thrust sensor is provided at the bottom of the dynamic frame; a first threaded hole connected to the first end of the spring sheet is provided on the side wall of the dynamic frame, and a second threaded hole connected to the second end of the spring sheet is provided on the inner side wall of the static frame; an aircraft to be tested is fixed to the upper end surface of the dynamic frame, and the aircraft to be tested is fixed to the dynamic frame via multiple connecting members; an angle adjustment device is provided on the dynamic frame below the wheels of the aircraft to be tested.

[0007] Preferably, the angle adjustment device includes an adjustment plate and an adjustment assembly, the first end of the adjustment assembly is movably connected to the movable frame, the second end of the adjustment assembly is movably connected to the bottom of the adjustment plate, the adjustment assembly includes a telescopic rod and a universal hinge, and the two ends of the telescopic rod are respectively connected to two universal hinges.

[0008] Preferably, a connecting groove for installing the angle adjustment device is provided on the movable frame.

[0009] Preferably, a thrust sensor fine-tuning device is further provided on the static frame, and a transmission end of the thrust sensor fine-tuning device is connected to an operating end of the thrust sensor through a control member.

[0010] Preferably, there are three connecting members, and the connecting members are steel cables.

[0011] Preferably, a plurality of fixed connection points are provided on the movable frame, and the connecting members are connected to the fixed connection points.

[0012] Preferably, it further includes a remote control device, which is wirelessly connected to the thrust sensor fine-tuning device and the adjustment component and controls the movement of the thrust sensor fine-tuning device and the adjustment component.

[0013] Compared with the prior art, the present invention has the following beneficial effects:

[0014] 1. The utility model realizes the test of the aircraft to be tested by setting a static frame and a dynamic frame. A spring sheet and a thrust sensor are arranged between the static frame and the dynamic frame. The spring sheet can keep the dynamic frame arranged above the static frame and can be deformed when subjected to an external force, thereby driving the dynamic frame to change its position. After the external force disappears, the spring sheet can drive the dynamic frame to return to its original state. When the dynamic frame changes, the thrust sensor will measure that the dynamic frame can generate an installation thrust in the thrust test experiment. At the same time, the utility model is quick to install and easy to operate, and can quickly test the aircraft to be tested.

[0015] 2. The utility model is provided with an angle adjustment device on the movable frame. The angle of the adjustment plate in the angle adjustment device can be adjusted by adjusting the different extension and contraction amounts of the multi-directional telescopic rod to adjust the inclination angle of the adjustment plate, and finally simulate the environment required for the actual test. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the overall structure of the thrust test device installed on the aircraft engine of the utility model;

[0017] Figure 2 This is the second schematic diagram of the overall structure of the thrust test device installed on the aircraft engine of the utility model;

[0018] Figure 3A side view of the thrust test device installed on an aero-engine according to the utility model;

[0019] Figure 4 A schematic diagram of the installation of a spring sheet and a thrust sensor fine-tuning device for an aero-engine according to the utility model;

[0020] Figure 5 The utility model is a schematic diagram of the overall structure of the angle adjustment device for installing the thrust test device of the aircraft engine.

[0021] Some of the accompanying drawings are described as follows:

[0022] 1. Static frame; 2. Dynamic frame; 3. First threaded hole; 4. Spring leaf; 5. Second threaded hole; 6. First connecting piece; 7. Second connecting piece; 8. Third connecting piece; 9. First fixed connection point; 10. Second fixed connection point; 11. Third fixed connection point; 12. Thrust sensor; 13. Thrust sensor fine-tuning device; 14. Aircraft to be tested; 15. Adjustment plate; 16. Telescopic rod. DETAILED DESCRIPTION

[0023] The following will describe in detail exemplary embodiments, features, and aspects of the present invention with reference to the accompanying drawings. The same reference numerals in the accompanying drawings represent elements with the same or similar functions. Although various aspects of the embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless otherwise indicated.

[0024] The utility model provides an aircraft engine installation thrust test device, such as Figure 1-Figure 5 As shown, it includes a static frame 1, a dynamic frame 2 and a remote control device. The dynamic frame 2 is arranged in the middle of the static frame 1, and there is a gap between the dynamic frame 2 and the static frame 1, so that the dynamic frame 2 will not be affected by the static frame 1 when it moves; the static frame 1 is a hollow rectangular structure; the dynamic frame 2 is connected to the static frame 1 through a spring sheet 4, and a thrust sensor 12 is also provided at the bottom of the dynamic frame 2; a first threaded hole 3 connected to the first end of the spring sheet 4 is provided on the side wall of the dynamic frame 2, and a second threaded hole 5 connected to the second end of the spring sheet 4 is provided on the inner side wall of the static frame 1; the aircraft to be tested 14 is fixed to the upper end surface of the dynamic frame 2, and the aircraft to be tested 14 is fixed to the dynamic frame 2 through multiple connecting parts; an angle adjustment device is provided on the dynamic frame 2 below the wheel of the aircraft to be tested 14.

[0025] The angle adjustment device includes an adjustment plate 15 and an adjustment component. The first end of the adjustment component is movably connected to the movable frame 2, and the second end of the adjustment component is movably connected to the bottom of the adjustment plate 15. The adjustment component includes a telescopic rod 16 and a universal hinge. The two ends of the telescopic rod 16 are respectively connected to two universal hinges.

[0026] A connecting groove for installing the angle adjustment device is provided on the movable frame 2 so that the highest height of the adjustment plate 15 is kept level with the highest height of the movable frame 2 .

[0027] The thrust sensor 12 is always kept in the open state, and is reset to zero after the data is measured.

[0028] A thrust sensor fine-tuning device 13 is also provided on the static frame 1. The transmission end of the thrust sensor fine-tuning device 13 is connected to the operating end of the thrust sensor 12 through a control member, so that the thrust sensor 12 is controlled to return to zero through the thrust sensor fine-tuning device 13. By rotating the top rod knob of the thrust sensor fine-tuning device 13, the control member is rotated, and finally the thrust sensor 12 is returned to zero.

[0029] The multiple connecting members are a first connecting member 6 , a second connecting member 7 and a third connecting member 8 ; the connecting members are steel cables.

[0030] The movable frame 2 is provided with a plurality of fixed connection points, which are not provided on the adjustment plate 15 . The connecting parts are connected to the fixed connection points. The plurality of fixed connection points include a first fixed connection point 9 , a second fixed connection point 10 and a third fixed connection point 11 .

[0031] The remote control device is wirelessly connected to the thrust sensor fine-tuning device 13, the adjustment assembly, and the aircraft under test 14, and controls the movement of the thrust sensor fine-tuning device 13 and the adjustment assembly. The remote control device can control the extension and retraction of multiple telescopic rods 16 through any known control method, thereby adjusting the inclination angle of the adjustment plate 15 above the telescopic rods 16 to meet the angle required for the experiment.

[0032] like Figure 1-Figure 3 The novel aircraft engine installation thrust test equipment shown in the figure includes a static frame 1 and a dynamic frame 2. The static frame 1 is provided with a thrust sensor fine-tuning device 13. The static frame 1 is connected to the dynamic frame 2 through four spring leaves 4. The dynamic frame 2 is provided with connecting parts, which include a first connecting part 6, a second connecting part 7 and a third connecting part 8. One end of the first connecting part 6 is connected to the left rear landing gear of the aircraft to be tested, and the other end of the first connecting part 6 is connected to the first fixed connection point 9 of the dynamic frame 2. The first fixed connection point is located at the left rear of the aircraft to be tested 14. The second connecting part 7 is connected to the left rear of the aircraft to be tested 14. One end is connected to the right rear landing gear of the aircraft to be tested, the other end of the second connecting member 7 is connected to the second fixed connection point 10, the second fixed connection point 10 is located at the right rear of the aircraft to be tested, and the second fixed connection point 10 and the first fixed connection point 9 are respectively arranged symmetrically along the central axis of the aircraft to be tested. One end of the third connecting member 8 is connected to the front landing gear of the aircraft to be tested, and the other end of the third connecting member 8 is connected to the third fixed connection point 11 of the dynamic frame 2, the third fixed connection point 11 is located behind the front landing gear of the aircraft to be tested and arranged along the central axis of the aircraft to be tested.

[0033] Among them, the first connecting member 6, the second connecting member 7 and the third connecting member 8 are all steel cables and the lengths of the first connecting member 6 and the second connecting member 7 are equal. A thrust sensor 12 is installed under the movable frame 2, and the thrust sensor 12 is in contact with the thrust sensor fine-tuning device 13.

[0034] In this embodiment, the first, second, and third connectors 6, 7, and 8 meet the strength and rigidity requirements for the test run. During testing, the first, second, and third connectors 6, 7, and 8 are kept in a taut state, preventing relative displacement between the aircraft and the gantry 2. Force analysis can be performed on the aircraft and gantry 2 as a single entity, a crucial prerequisite for accurate measurement in this utility model. During the test run, the combined force conditions of the aircraft and gantry 2 are analyzed, and combined with data from the thrust sensor 12 and known information, the installed engine thrust can be quickly determined.

[0035] The operation of this device includes the following steps:

[0036] Step 1: Install the aircraft engine to be tested on the aircraft.

[0037] Step 2: Install the aircraft on the dynamic frame 2 of the thrust test equipment.

[0038] Step 3: Adjust the angle adjustment device to the position to be measured.

[0039] Step 4: Use the thrust sensor fine-tuning device 13 to calibrate the thrust sensor 12.

[0040] Step 5: Start the test run and record the data measured by the thrust test equipment.

[0041] Step 6. Calculate the installed thrust of the aircraft engine under different operating conditions.

[0042] The embodiments described above are merely descriptions of preferred implementations of the present invention and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should fall within the scope of protection determined by the claims of the present invention.

Claims

1. An aircraft engine installation thrust test device, characterized by: It includes a static frame and a dynamic frame, wherein the dynamic frame is arranged in the middle of the static frame, and there is a gap between the dynamic frame and the static frame; The static frame is a hollow rectangular structure; The movable frame is connected to the static frame via a spring sheet, and a thrust sensor is also provided at the bottom of the movable frame; A first threaded hole connected to the first end of the spring sheet is provided on the side wall of the movable frame, and a second threaded hole connected to the second end of the spring sheet is provided on the inner side wall of the static frame; The aircraft to be tested is fixed on the upper end surface of the movable frame, and the aircraft to be tested is fixed on the movable frame through a plurality of connecting members; An angle adjustment device is provided on the moving frame below the wheels of the aircraft to be tested.

2. The aircraft engine installation thrust test device according to claim 1, characterized in that: The angle adjustment device includes an adjustment plate and an adjustment assembly, the first end of the adjustment assembly is movably connected to the movable frame, the second end of the adjustment assembly is movably connected to the bottom of the adjustment plate, the adjustment assembly includes a telescopic rod and a universal hinge, and the two ends of the telescopic rod are respectively connected to two universal hinges.

3. The aircraft engine installation thrust test device according to claim 1, characterized in that: The movable frame is provided with a connecting groove for installing the angle adjustment device.

4. The aircraft engine installation thrust test device according to claim 2, characterized in that: The static frame is also provided with a thrust sensor fine-tuning device, and a transmission end of the thrust sensor fine-tuning device is connected to the operating end of the thrust sensor through a control member.

5. The aircraft engine installation thrust test device according to claim 1, characterized in that: There are three connecting pieces, and the connecting pieces are steel cables.

6. The aircraft engine installation thrust test device according to claim 1, characterized in that: The movable frame is provided with a plurality of fixed connection points, and the connecting pieces are connected to the fixed connection points.

7. The aircraft engine installation thrust test device according to claim 4, characterized in that: It also includes a remote control device, which is wirelessly connected to the thrust sensor fine-tuning device and the adjustment component and controls the movement of the thrust sensor fine-tuning device and the adjustment component.

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