Wide-range high-precision small aero-engine thrust measuring platform with magnetic levitation support

Abstract

The present application belongs to the field of aero-engine testing technology, and discloses a magnetic levitation supported wide-range high-precision small aero-engine thrust measuring bench. The movable frame module and the fixed frame module of the thrust measuring bench are both horizontally placed plate structures, the movable frame module is fixed with a small turbojet aero-engine test piece to be measured on the top, and the fixed frame module is fixed on the test bench base; the movable frame module and the fixed frame module are supported through four vertical support cylinders arranged at four corners; a pair of vertical floating magnetic steel assemblies and fixed magnetic steel assemblies are respectively arranged in each support cylinder; and a multi-gear range selection module and a multi-gear in-situ calibration module are further fixed on the upper surface of the fixed frame module. The thrust measuring bench has a wide thrust measuring range, a large range ratio, high measuring efficiency, high calibration accuracy, high calibration efficiency and good economy, and can meet the requirements of wide-range small turbojet aero-engine thrust measurement, and has engineering practical value.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engine test, and particularly relates to a magnetic levitation supported wide-range high-precision small aero-engine thrust measuring bench. BACKGROUND

[0002] When a turbojet aero-engine is working, the momentum change of internal flow circulation air exerts force on its support structure, and the sum of the axial forces acting on each support structure constitutes the engine thrust. The engine thrust is the most core evaluation index of the turbojet aero-engine, and the engine thrust size directly reflects the overall development level of the turbojet aero-engine. Generally, under the condition of the same aerodynamic characteristics, the greater the engine thrust, the more superior the performance. Therefore, accurate measurement of the engine thrust has decisive significance for the development and performance evaluation of high-performance aero-engines. Generally, the engine thrust is directly measured by a ground thrust measuring bench, therefore, the development and development of a high-precision thrust measuring bench is the basis for the innovative development of high-performance turbojet aero-engines, and has very important significance for improving the development level of turbojet aero-engines.

[0003] Small turbojet aero-engines are widely used in unmanned aerial vehicles, missiles, small aircraft and some special purpose aircraft, and the thrust range thereof is usually between 50 pounds (about 22.7 kg) and 3000 pounds (about 1362 kg). This puts higher requirements on the measurement accuracy of the thrust measuring bench under wide-range conditions, and the thrust measuring bench needs to have a large range ratio (the ratio of the maximum value to the minimum value that can be accurately measured).

[0004] The thrust measuring bench can be divided into a suspended bench and a supported bench according to the connection mode of the moving frame and the fixed frame. The suspended bench is commonly used in open-air thrust test benches, and the supported bench is commonly used in closed high-altitude simulation test cabins. For the supported bench, the support mode of the moving frame is the main factor affecting the measurement accuracy of the thrust measuring bench. At present, the moving frame mainly adopts spring sheet support, which has the advantages of simple structure, easy manufacturing and maintenance, convenient installation and relatively low cost, but has the following significant deficiencies:

[0005] Firstly, the spring sheet has a narrow linear range, insufficient transmission of small thrust, poor response, and insufficient measurement accuracy of small thrust in a wide-range thrust change range;

[0006] Secondly, the spring sheet is prone to fatigue failure after long-term use, resulting in variable measurement accuracy;

[0007] Thirdly, the non-linear characteristic of the spring sheet support stiffness leads to complex calibration work of the spring sheet, and frequent calibration is required.

[0008] In summary, the current thrust measurement bench is generally of a single range, and due to the narrow linearity range of the spring sheet, the range of high-precision thrust measurement is narrow, and the range ratio is small, so it is difficult to ensure the thrust measurement accuracy for small turbojet aircraft engines with a wide range of thrust variation. In order to improve the thrust measurement accuracy, it is necessary to frequently replace the thrust measurement bench with a suitable range, which is low in work efficiency. At the same time, the wide range of thrust variation of small turbojet aircraft engines also brings challenges to the calibration of the thrust measurement bench. The replacement of thrust measurement benches with different ranges requires frequent calibration, which is complicated to operate and easy to damage precision components, low in work efficiency and poor in economy.

[0009] At present, it is urgent to develop a wide-range high-precision small aircraft engine thrust measurement bench supported by magnetic suspension. SUMMARY

[0010] The technical problem to be solved by the present application is to provide a wide-range high-precision small aircraft engine thrust measurement bench supported by magnetic suspension.

[0011] The wide-range high-precision small aircraft engine thrust measurement bench supported by magnetic suspension of the present application comprises a movable frame module, a fixed frame module, a multi-gear range selection module, a multi-gear in-situ calibration module and a support cylinder.

[0012] The movable frame module and the fixed frame module are both horizontally placed flat plate structures, the movable frame module is above, and the fixed frame module is below, and the movable frame module and the fixed frame module are supported by four vertical support cylinders arranged at the four corners; the movable frame module is fixed above the small turbojet aircraft engine test piece to be measured, and the fixed frame module is fixed on the test bench base; the upper surface of the fixed frame module is also fixed with the multi-gear range selection module and the multi-gear in-situ calibration module;

[0013] A pair of vertical floating magnetic steel assemblies and fixed magnetic steel assemblies are arranged in each support cylinder, the upper end of the floating magnetic steel assembly is fixed to the lower surface of the movable frame module, and the lower end of the fixed magnetic steel assembly is fixed to the lower surface of the fixed frame module; a contact plane is arranged between the floating magnetic steel assembly and the fixed magnetic steel assembly;

[0014] During thrust measurement, the movable frame module and the fixed frame module are non-contact separated by electromagnetic force, the multi-gear range selection module selects the range, and the thrust measurement of the small turbojet aircraft engine test piece to be measured is carried out; in addition, in order to ensure the thrust measurement accuracy, the in-situ online calibration of the measurement bench is carried out by the multi-gear in-situ calibration module before the thrust measurement test.

[0015] Further, the moving frame module comprises horizontal thrust measurement support rods fixed on the floating magnetic steel assembly and L-shaped thrust calibration support rods fixed on the lower surface of the moving frame module; the multi-grade range selection module comprises a measurement grade selection assembly and a measurement sensor; the multi-grade in-situ calibration module comprises a calibration grade selection assembly, a calibration sensor and a calibration load loading assembly;

[0016] Different range measurement sensors are fixed along the circumference of the thrust measurement support rods, the measurement sensor with a range suitable for the small turbojet aircraft engine to be measured is selected through the measurement grade selection assembly, and the range ratio and the thrust measurement accuracy are improved by using the linearity range of each range measurement sensor.

[0017] Different grade calibration sensors are fixed along the circumference of the horizontal rods of the L-shaped thrust calibration support rods, the calibration sensor with a suitable grade is selected through the calibration grade selection assembly, and the in-situ online calibration of the calibration sensor of each grade is realized by loading through the calibration load loading assembly.

[0018] The magnetic floating support wide-range high-precision small aircraft engine thrust measurement bench of the application installs the small turbojet aircraft engine test piece to be measured on the thrust measurement bench by using the moving frame module to carry out engine thrust measurement experiments; the entire thrust measurement bench is fixed on the test bench base by using the fixed frame module, and the moving frame module and the fixed frame module are supported through four support cylinders; during the thrust measurement test, a pair of magnetic suspension floating magnetic steel assemblies and fixed magnetic steel assemblies arranged in a vertical direction in the four support cylinders are used to realize the non-contact separation of the moving frame module and the fixed frame module by means of electromagnetic force, which overcomes the shortcomings of the spring leaf supported thrust measurement bench, such as insufficient small thrust axial force transmission sensitivity caused by the spring leaf stiffness itself, and changes in engine thrust transmission and measurement accuracy caused by changes in spring leaf stiffness coefficient after long-term use. Compared with the suspension type bench, the magnetic floating support bench has a more compact structure; by using the multi-grade range selection module, the linearity range of each grade force sensor is fully utilized to improve the range ratio and realize high-precision measurement of the thrust of the small aircraft engine in a wide-range thrust change range, which overcomes the shortcomings of the single-range thrust measurement bench, such as narrow linearity range, low measurement accuracy and poor universality; in addition, through the multi-grade in-situ calibration module, the in-situ online calibration of each grade force sensor is realized, which not only improves the calibration accuracy, but also overcomes the shortcomings of different range force sensors, such as complex calibration operation, long calibration period and frequent disassembly and assembly causing damage to precision measurement components, etc., which can greatly improve the measurement efficiency and prolong the service life of the sensor and other precision components, and has good economic efficiency.

[0019] In summary, the magnetically levitated, wide-range, high-precision thrust measurement rig for small aero-engines of this invention has a wide thrust measurement range, a large range ratio, high measurement efficiency, high calibration accuracy, high calibration efficiency, and good economic efficiency. It can meet the thrust measurement requirements of wide-range small turbojet aero-engines and has practical engineering value. Attached Figure Description

[0020] Fig. 1 This is a schematic diagram of the structure of the magnetic levitation support wide-range high-precision small aero-engine thrust measurement rig of the present invention.

[0021] Fig. 2 This is a schematic diagram of the multi-range selection module and the multi-range in-situ calibration module range selector in the magnetic levitation support wide-range high-precision small aero-engine thrust measurement bench of the present invention.

[0022] In the diagram, 1. Moving frame module, 2. Fixed frame module, 3. Multi-range selection module, 4. Multi-range in-situ calibration module, 5. Support cylinder;

[0023] 1.1. Thrust measurement support rod; 1.2. Thrust calibration support rod;

[0024] 3.1. Measurement range selection component; 3.2. Measurement sensor;

[0025] 4.1. Calibration gear selection component; 4.2. Calibration sensor; 4.3. Calibration load loading component;

[0026] 5.1. Floating magnet assembly; 5.2. Fixed magnet assembly. Detailed Implementation

[0027] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] Example: Figs. 1-2 As shown, the magnetic levitation support wide-range high-precision small aero-engine thrust measurement rig of this embodiment includes a moving frame module 1, a fixed frame module 2, a multi-range selection module 3, a multi-range in-situ calibration module 4, and a support cylinder 5.

[0029] Both the moving frame module 1 and the fixed frame module 2 are horizontally placed flat plate structures, with the moving frame module 1 on top and the fixed frame module 2 on the bottom. The moving frame module 1 and the fixed frame module 2 are supported by four vertical support cylinders 5 set at the four corners. The small turbojet aero-engine test piece to be tested is fixed on the top of the moving frame module 1, and the fixed frame module 2 is fixed on the test bench base. The upper surface of the fixed frame module 2 is also fixed with a multi-range selection module 3 and a multi-range in-situ calibration module 4.

[0030] A pair of vertical floating magnetic steel assemblies 5.1 and fixed magnetic steel assemblies 5.2 are arranged in each support cylinder 5, the upper end of the floating magnetic steel assembly 5.1 is fixed to the lower surface of the moving frame module 1, and the lower end of the fixed magnetic steel assembly 5.2 is fixed to the lower surface of the fixed frame module 2; a contact plane is arranged between the floating magnetic steel assembly 5.1 and the fixed magnetic steel assembly 5.2;

[0031] During thrust measurement, the moving frame module 1 and the fixed frame module 2 are non-contact separated by electromagnetic force, the multi-gear range selection module 3 selects the range, and the thrust measurement of the small turbojet aircraft engine test piece to be measured is carried out; in addition, in order to ensure the accuracy of the thrust measurement, before the thrust measurement test, the in-situ online calibration of the measurement bench is carried out by the multi-gear in-situ calibration module 4.

[0032] Further, the moving frame module 1 includes a horizontal thrust measurement support rod 1.1 fixed on the floating magnetic steel assembly 5.1, and an L-shaped thrust calibration support rod 1.2 fixed on the lower surface of the moving frame module 1; the multi-gear range selection module 3 includes a measurement gear selection assembly 3.1 and a measurement sensor 3.2; the multi-gear in-situ calibration module 4 includes a calibration gear selection assembly 4.1, a calibration sensor 4.2 and a calibration load loading assembly 4.3;

[0033] The measurement sensors 3.2 of different ranges are fixed along the circumference of the thrust measurement support rod 1.1, the measurement sensor 3.2 suitable for the range of the small turbojet aircraft engine to be measured is selected by the measurement gear selection assembly 3.1, and the linearity range of each range of the measurement sensor 3.2 is used to improve the range ratio and the thrust measurement accuracy;

[0034] The calibration sensors 4.2 of different gears are fixed along the circumference of the horizontal rod of the L-shaped thrust calibration support rod 1.2, the calibration sensor 4.2 of the appropriate gear is selected by the calibration gear selection assembly 4.1, and the in-situ online calibration of the calibration sensor 4.2 of each gear is realized by the calibration load loading assembly 4.3.

[0035] The length, width and height dimensions of the measurement bench of the embodiment are 1200mm, 600mm and 420mm respectively, and the size is compact. The multi-gear range selection module 3 and the multi-gear in-situ calibration module 4 of the embodiment are both 3 gears, and the 3 gears have ranges of (0.1~1.25)kN, (1.25~7.5)kN and (7.5~15)kN respectively, and the accuracy levels are 0.02%, 0.02% and 0.03% respectively. The total range of the thrust measurement of the measurement bench of the embodiment is (0.1~15)kN, the range ratio is 150, and the measurement accuracy is not less than 0.03%.

[0036] While embodiments of the application have been disclosed in connection with the above specification, it will be apparent to those skilled in the art that numerous modifications and variations can be made without departing from the principles of the application. For example, although the application has been described in the context of a particular method, it will be apparent that the application can be implemented in any appropriate type of computer system, or in a computer program product suitable for use in an information handling or processing system. The application is not to be limited to the specific details and examples described above, but is to be controlled by the claims and their equivalents.

Claims

1. A magnetically levitated, wide-range, high-precision thrust measurement rig for small aero-engines, characterized in that, The measuring stand includes a moving frame module (1), a fixed frame module (2), a multi-range selection module (3), a multi-range in-situ calibration module (4), and a support cylinder (5); Both the moving frame module (1) and the fixed frame module (2) are horizontally placed flat plate structures, with the moving frame module (1) on top and the fixed frame module (2) on the bottom. The moving frame module (1) and the fixed frame module (2) are supported by four vertical support cylinders (5) set at the four corners. The small turbojet aero-engine test piece to be tested is fixed on the top of the moving frame module (1), and the fixed frame module (2) is fixed on the test bench base. The upper surface of the fixed frame module (2) is also fixed with a multi-range selection module (3) and a multi-range in-situ calibration module (4). Each support cylinder (5) is equipped with a pair of vertical floating magnet components (5.1) and fixed magnet components (5.2). The upper end of the floating magnet component (5.1) is fixed to the lower surface of the moving frame module (1), and the lower end of the fixed magnet component (5.2) is fixed to the upper surface of the fixed frame module (2). A contact plane is provided between the floating magnet component (5.1) and the fixed magnet component (5.2). During thrust measurement, the moving frame module (1) and the fixed frame module (2) are disconnected from each other without contact by electromagnetic force. The multi-range selection module (3) selects the range and performs thrust measurement on the small turbojet aero-engine test piece. In addition, to ensure the accuracy of thrust measurement, the in-situ online calibration of the measuring platform is performed by the multi-range in-situ calibration module (4) before the thrust measurement test. The moving frame module (1) includes a horizontal thrust measurement support rod (1.1) fixed on the floating magnet assembly (5.1) and an L-shaped thrust calibration support rod (1.2) fixed on the lower surface of the moving frame module (1); the multi-range selection module (3) includes a measurement range selection component (3.1) and a measurement sensor (3.2); the multi-range in-situ calibration module (4) includes a calibration range selection component (4.1), a calibration sensor (4.2) and a calibration load loading component (4.3); Measurement sensors (3.2) with different ranges are fixed along the circumference of the thrust measurement support rod (1.1). The measurement sensor (3.2) with the appropriate range for the small turbojet aero-engine to be measured is selected by the measurement range selection component (3.1). The range ratio and thrust measurement accuracy are improved by utilizing the linearity range of the measurement sensors (3.2) with different ranges. Calibration sensors (4.2) at different gears are fixed circumferentially along the horizontal bar of the L-shaped thrust calibration support rod (1.2). The appropriate gear calibration sensor (4.2) is selected by the calibration gear selection component (4.1), and the calibration load is loaded by the calibration load loading component (4.3) to achieve in-situ online calibration of the calibration sensor (4.2) at each gear.

Images