CN105865694A - Turboprop engine pull strength measurement device - Google Patents
Turboprop engine pull strength measurement device Download PDFInfo
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- CN105865694A CN105865694A CN201610484818.4A CN201610484818A CN105865694A CN 105865694 A CN105865694 A CN 105865694A CN 201610484818 A CN201610484818 A CN 201610484818A CN 105865694 A CN105865694 A CN 105865694A
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- 238000005259 measurement Methods 0.000 title abstract description 20
- 238000012360 testing method Methods 0.000 claims abstract description 23
- 230000003068 static effect Effects 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 208000027418 Wounds and injury Diseases 0.000 claims description 2
- 230000006378 damage Effects 0.000 claims description 2
- 208000014674 injury Diseases 0.000 claims description 2
- 230000007547 defect Effects 0.000 abstract description 3
- 230000004044 response Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 6
- 238000009434 installation Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003028 elevating effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention provides a turboprop engine pull strength measurement device. The turboprop engine pull strength measurement device comprises a fixed frame, a movable frame, leaf springs, a pull strength calibration system, a pull strength measurement system, an engine mounting frame, an ejection barrel, safety devices and the like. The fixed frame is supported on a rack, an engine is mounted in front of the engine mounting frame which is suspended below the movable frame, and the ejection barrel is arranged in the engine mounting frame and positioned behind a nozzle of the engine. The turboprop engine pull strength measurement device can be used for measurement of pull strength of the turboprop engine in ground test, and the defect that existing equipment fails to measure the pull strength is overcome. By the scheme that the fixed frame, the movable frame and the leaf springs are combined for mounting of pull strength sensors for measuring pull strength of the engine, the requirement of ground test of the engine is met, and the pull strength measurement system is quick in response and high in stability.
Description
Technical Field
The invention relates to ground test equipment for an aero-engine, in particular to a measuring device for measuring the tension of a turboprop engine. The technical field is non-standard equipment design and manufacture technology, and belongs to engine ground process trial run equipment.
Background
In the traditional ground test run of a turboprop engine, the engine is fixed on a rack through a mounting frame, and a dynamometer system in the engine is used for measuring parameters such as the power of the engine, but the traditional test run scheme does not provide a device for measuring the tensile force of the engine.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a turboprop tension measuring device to reduce or avoid the aforementioned problems.
In order to solve the technical problem, the invention provides a turboprop engine tension measuring device which is used for testing and measuring the engine tension of a turboprop series engine on the ground, wherein the measuring device comprises a static frame, a movable frame, a spring piece, a tension calibration system, a tension measuring system, an engine mounting frame, a guiding and ejecting cylinder, a safety device and the like. Wherein the stationary frame is supported on a gantry, the main body strength of which is about 1.25 times the maximum power of the engine. The engine is installed in the place ahead of engine mounting bracket, and the engine mounting bracket hangs the below of movable rack, the setting of guide cylinder is in the inside of engine mounting bracket is located the spout rear of engine.
Preferably, the fixed frame comprises a front frame and a rear frame, two ends of the front frame and the rear frame are respectively supported on four supporting points on the rack, the movable frame is suspended below the fixed frame through four spring pieces, and each fixed frame is respectively connected with two spring pieces.
Preferably, the tension measuring system comprises two groups of working sensors arranged on the static frame, two groups of ejector rods are arranged on the movable frame corresponding to the working sensors, the centers of the ejector rods are aligned with the centers of the working sensors, and the two groups of working sensors are arranged in parallel.
Preferably, the tension calibration system comprises a set of calibration sensors installed on the stationary frame, a set of push rods corresponding to the calibration sensors are installed on the movable frame, the centers of the push rods are aligned with the centers of the calibration sensors, and the calibration sensors are installed at the middle positions of the rear portion of the movable frame.
Preferably, the safety devices are used for preventing the movable frame from falling to hurt the engine and personnel when the front spring piece and the rear spring piece fail, wherein the safety devices at least comprise four safety devices, and each safety device comprises an auxiliary support frame fixed on the fixed frame and a limiting frame fixed on the movable frame. When the spring piece is in failure, the movable frame is stressed by the safety device.
Preferably, the static frame is in the form of airplane wings, and the direction of the static frame facing the airflow is designed into a sharp arc shape, so that the pneumatic flow field in a test room is ensured to be in the same direction and has no turbulent flow.
Preferably, the guiding barrel is position-adjustably disposed inside the engine mount.
Preferably, the guiding barrel can move back and forth along the engine mounting frame in a gear rack mode to adjust the position.
Preferably, the tension measuring system further comprises a sensor mounting seat and an ejector rod mounting seat, the working sensor is mounted right behind the two groups of spring pieces at the front part and is collinear with the connecting line of the front spring piece and the rear spring piece, and the tension value causing the deformation of the spring pieces is accurately measured.
Preferably, the measuring device further comprises at least one lifting platform disposed below the engine mount for mounting an engine below the stationary frame.
The turboprop engine tension measuring device can be used for measuring the tension of an engine during ground test of the turboprop engine, overcomes the defect that the existing equipment cannot measure the tension, adopts the scheme of combining the movable frame, the static frame and the spring piece and installing the tension sensor to measure the tension of the engine, meets the ground test requirement of the engine, and has quick response and good stability of a tension measuring system. Calibrating a working sensor by using a calibration sensor, wherein the working sensor measures the tension; the calibration sensor is used for precision transmission, and normal work of the test bed is not influenced when the calibration sensor is used for calibration. The measuring method has high measuring precision, reaches the national standard of a test bed, and has good repeatability; the calibration is simple and convenient.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 is a schematic side cross-sectional view of a turboprop engine tension measurement apparatus according to an embodiment of the present invention;
FIG. 2 shows a schematic view of another embodiment of the present invention from the left side of FIG. 1;
FIG. 3 is a schematic top view of the structure of FIG. 2;
FIG. 4 shows an enlarged side view of the tension calibration system and the tension measurement system;
FIG. 5 is an enlarged schematic view of FIG. 1 at A;
FIG. 6 is an enlarged schematic view of the section B in FIG. 1;
FIG. 7 is a schematic left side sectional view of FIG. 5;
fig. 8 is an enlarged cross-sectional view of the stationary frame shown in fig. 1.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
As described in the background art, the prior art has no mature measuring device for measuring the tension of the turboprop engine, so the invention provides a completely new designed measuring device for measuring the tension of the turboprop engine, which is used for testing the turboprop engine on the ground to measure the tension of the engine.
Fig. 1 is a schematic side sectional view showing a turboprop engine tension measuring apparatus according to an embodiment of the present invention, and as shown in the drawing, the turboprop engine tension measuring apparatus of the present invention is composed of a stationary frame 1, a movable frame 2, a spring plate 3, a tension calibration system 4, a tension measurement system 5, an engine mounting frame 6, a guiding cylinder 7, a safety device 8, and the like. The engine 20 is installed in front of the engine installation frame 6, the engine installation frame 6 is hung below the movable frame 2, and the injection cylinder 7 is arranged inside the engine installation frame 6 and behind a nozzle of the engine 20.
In one embodiment, the fixed frame 1 comprises a front frame and a rear frame, the movable frame 2 is suspended below the fixed frame 1 by four spring strips 3, and each fixed frame 1 is connected with two spring strips 3 (only two spring strips are visible in the figure due to the view angle).
Fig. 2 is a schematic view showing another embodiment of the present invention as seen from the left side of fig. 1, and it can be seen that this embodiment is different from fig. 1 in that the stationary frame 1 of fig. 2 is supported on a frame 10, both ends of which are supported on four fulcrums of the frame 10, respectively, and the frame 10 has a body strength of about 1.25 times the maximum power of the engine, providing a sufficient load margin and improving the reliability of the apparatus. In the figure, a static frame 1 is fixed on four brackets of a rack 10, an engine 20 is fixed in front of an engine mounting frame 6, the engine mounting frame 6 is connected with a movable frame 2, an injection cylinder 7 is fixed in the engine mounting frame, and the movable frame 2 is connected with the static frame 1 through four spring pieces 3. When the engine 20 generates a tensile force, the spring piece 3 deforms, the movable frame 2 moves forwards, and the force generated by the displacement is measured through the tensile force measuring system 5, so that the magnitude of the tensile force is measured. The range of the propeller trajectory is indicated by the dashed circle in fig. 2.
Fig. 3 is a schematic top view of fig. 2, in which the structural layout of the tension calibration system 4 and the tension measurement system 5 of the present invention can be seen, fig. 4 is an enlarged side view of the tension calibration system 4 and the tension measurement system 5, and fig. 3-4 show that, in an embodiment of the present invention, the tension measurement system 5 includes two sets of working sensors 51 mounted on the stationary frame 1, two sets of push rods 52 are mounted on the movable frame 2 corresponding to the working sensors 51, the centers of the push rods 52 are aligned with the centers of the working sensors 51, and the two sets of working sensors 51 are arranged in parallel.
The tension calibration system 4 comprises a set of calibration sensors 41 arranged on the static frame 1, a set of mandrils 42 are arranged on the movable frame 2 corresponding to the calibration sensors 41, the centers of the mandrils 42 are aligned with the centers of the calibration sensors 41, and the calibration sensors 41 are arranged at the middle positions of the rear part of the movable frame 2.
The tension measurement is completed by two groups of working sensors and a group of calibration sensors, and the calibration sensors calibrate the working sensors. The tension measuring system 5 is composed of a sensor mounting seat, a working sensor 51, a mandril 52, a mandril mounting seat and the like, wherein the working sensor 51 is arranged right behind the front two groups of spring pieces 3 and is collinear with the connecting lines of the front spring pieces 3 and the rear spring pieces 3, and the tension measuring system accurately measures the tension value causing the deformation of the spring pieces 3. The tension calibration system 4 is composed of a hydraulic loader (1 set of hydraulic system including an oil cylinder), a hydraulic loader mounting seat, a calibration sensor 41, an ejector rod 42 and the like. The movable frame is provided with a working tension measuring mounting seat, two ejector rods and a calibration oil cylinder, and the fixed frame is provided with working sensors and a calibration sensor. The range of the tension measurement calibration sensor (one) is 10T, and the precision is 0.03% FS. The range of the working sensor is 10T (two), and the precision is 0.03% FS.
The tension calibration method comprises the following steps: during calibration, the hydraulic loader moves the piston rod of the calibration oil cylinder, the piston rod props against the calibration sensor to obtain a measurement value (F1) of the calibration sensor, meanwhile, the movable frame moves, the ejector rod props against the working sensor to obtain a measurement value (F1 ') of the working sensor, and the F1 value and the F1' value are compared, so that the working sensor is calibrated. The measurement precision of the whole set of thrust measurement system is not more than 0.5% FS.
And (3) tension measurement: when the engine is in process test, the engine sends forward pulling force, the movable frame moves forward, the ejector rod props against the working sensor, and the working sensor deforms, so that the pulling force F value is measured. And correcting the tension value according to the calibrated difference, and determining the tension value as the tension of the engine.
Before the working sensor and the calibration sensor are installed, all three sensors are calibrated and installed after being qualified.
Purpose of setting up working sensor and calibration sensor: the sensors are calibrated every half or one year as specified. After the working sensor is installed, the working sensor is not detached and is sent to a calibration department, only the calibration sensor is periodically sent to a qualification detection department for calibration, and the working sensor is calibrated after the calibration is qualified.
In addition, in order to prevent the movable frame 2 from falling and causing injury to the engine 20 and personnel, the invention further provides a safety device 8 (shown in fig. 1), for clarity, fig. 5 is an enlarged schematic view of a position a in fig. 1, and fig. 6 is an enlarged schematic view of a position B in fig. 1, wherein the shapes of the safety device 8 at the position a and the safety device at the position B are not exactly the same, but the structural principle is the same, or the safety devices 8 at the two positions can adopt exactly the same shapes and structures as will be understood by those skilled in the art. As can be seen from fig. 1, 5-6, the safety device 8 of the present invention can be used for preventing the movable frame 2 from falling when the movable frame 2 is supported by the safety device 8 after the front and rear four spring leaves 3 fail, wherein the safety device 8 comprises at least four safety devices, and each safety device 8 comprises an auxiliary support frame 81 fixed on the fixed frame 1 and a limiting frame 82 fixed on the movable frame 2. When the auxiliary supporting frame 81 and the limiting frame 82 are not in contact during normal operation, that is, as shown in fig. 7, which is a schematic left sectional view of fig. 5, a long hole 822 is formed on a protruding web 821 of the limiting frame 82, the narrowest position of the auxiliary supporting frame 81 can move back and forth in the long hole 822 without being in contact with the long hole 822, when the spring plate 3 fails, the movable frame 2 moves downwards, and the web 821 of the limiting frame 82 is limited by a nut 812 at the lower part of the long hole 822 of the auxiliary supporting frame 81 and cannot fall further, so that a safety structure for preventing the movable frame 2 from falling is formed. In addition, the auxiliary support frame 81 can move back and forth along the long hole 822, and has a guiding function, so that the movable frame can be adjusted to move on a straight line.
In another embodiment, shown in fig. 8, which shows an enlarged cross-sectional view of the static frame of fig. 1, wherein the direction of the arrow is the incoming flow direction, the static frame 1 is in the form of an airplane wing, and the direction of the incoming flow is designed to be sharp arc, so that the pneumatic flow field of the test room is ensured to be the same direction and free of turbulence.
Further, in another preferred embodiment, the ejector sleeve 7 is arranged inside the engine mounting frame 6 in a position-adjustable manner. Specifically, the ejector sleeve 7 can move back and forth along the engine mounting frame 6 in a rack and pinion (not shown) manner to adjust the position. The movable installation of the injection cylinder has the advantages that the injection cylinder can move back and forth so as to be compatible with the ground test run requirements of tail nozzles with different lengths, and the adjustment is convenient. The requirement that engines with tail nozzles of different lengths share one test bed to carry out ground process test running can be met.
In addition, as shown in fig. 1-2, the measuring device of the present invention further includes at least one elevating platform 30 disposed below the engine mount 6 for assisting in mounting the engine below the stationary frame.
In conclusion, the turboprop engine tension measuring device can be used for measuring the tension of an engine during ground test of the turboprop engine, the defect that the existing equipment cannot measure the tension is overcome, the scheme that the movable frame, the static frame and the spring piece are combined, and the tension sensor is installed to measure the tension of the engine is adopted, so that the ground test requirement of the engine is met, and the tension measuring system is quick in response and good in stability. Calibrating a working sensor by using a calibration sensor, wherein the working sensor measures the tension; the calibration sensor is used for precision transmission, and normal work of the test bed is not influenced when the calibration sensor is used for calibration. The measuring method has high measuring precision, reaches the national standard of a test bed, and has good repeatability; the calibration is simple and convenient.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (10)
1. A turboprop engine tension measuring device is used for testing and measuring engine tension on the ground for turboprop series engines and is characterized by comprising a static frame (1), a movable frame (2), a spring piece (3), a tension calibration system (4), a tension measuring system (5), an engine mounting frame (6), an injection cylinder (7), a safety device (8) and the like. Wherein the stationary frame (1) is supported on a gantry (10), the main body strength of the gantry (10) being calculated about 1.25 times the maximum power of the engine. The engine (20) is installed in the front of the engine mounting frame (6), the engine mounting frame (6) is hung below the movable frame (2), and the guiding barrel (7) is arranged inside the engine mounting frame (6) and located behind a nozzle of the engine (20).
2. The measuring device according to claim 1, characterized in that the stationary frame (1) comprises a front frame and a rear frame, two ends of the front frame and the rear frame are respectively supported on four supporting points on the table frame (10), the movable frame (2) is suspended below the stationary frame (1) through four spring strips (3), and two spring strips (3) are respectively connected to each stationary frame (1).
3. A measuring device as claimed in claim 2, characterized in that said tension measuring system (5) comprises two sets of working sensors (51) mounted on the stationary frame (1), two sets of jack rods (52) mounted on said movable frame (2) in correspondence of said working sensors (51), the centers of the jack rods (52) being aligned with the centers of the working sensors (51), the two sets of working sensors (51) being arranged in parallel.
4. The measuring device according to claim 2, characterized in that said tension calibration system (4) comprises a set of calibration sensors (41) mounted on the stationary frame (1), a set of jack rods (42) mounted on the movable frame (2) in correspondence of said calibration sensors (41), the centers of the jack rods (42) being aligned with the centers of the calibration sensors (41), the calibration sensors (41) being mounted in rear intermediate positions of the movable frame (2).
5. A measuring device as claimed in claims 2 to 4, characterized in that said safety means (8) are adapted to prevent the fall of the mobile frame (2) and the injury to the engine and personnel when the four front and rear leaf springs (3) fail, wherein said safety means (8) comprise at least four, each safety means (8) comprising an auxiliary support (81) fixed to the stationary frame (1) and a limiting frame (82) fixed to the mobile frame (2). When the spring piece (3) fails, the movable frame (2) is supported by the safety device (8).
6. A measuring device as claimed in claims 1-5, characterized in that the static frame (1) is in the form of an airplane wing, and the direction of the incoming airflow is designed to be sharp arc, so as to ensure that the pneumatic flow field in the test room is in the same direction and has no turbulence.
7. Measuring device according to one of claims 1 to 6, characterized in that the guiding cylinder (7) is arranged position-adjustably inside the engine mount (6).
8. A measuring device as claimed in claim 7, characterised in that the guiding cylinder (7) is displaceable back and forth along the engine mount (6) in a rack and pinion manner to adjust the position.
9. A measuring device as claimed in claim 3, wherein said tension measuring system (5) further comprises a sensor mount and a ram mount, and said operation sensor (51) is mounted directly behind the front set of spring strips, in line with the front and rear spring strips, for accurately measuring the magnitude of the tension causing the deformation of the spring strips.
10. A measuring device as claimed in claim 4, characterized in that the measuring device further comprises at least one lifting platform (30) arranged below the engine mounting frame (6) for mounting an engine below a stationary frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610484818.4A CN105865694A (en) | 2016-06-28 | 2016-06-28 | Turboprop engine pull strength measurement device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610484818.4A CN105865694A (en) | 2016-06-28 | 2016-06-28 | Turboprop engine pull strength measurement device |
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| CN105865694A true CN105865694A (en) | 2016-08-17 |
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| CN201610484818.4A Pending CN105865694A (en) | 2016-06-28 | 2016-06-28 | Turboprop engine pull strength measurement device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107238457A (en) * | 2017-06-28 | 2017-10-10 | 北京航空航天大学 | A kind of low thrust measurement apparatus |
| CN107478366A (en) * | 2017-07-03 | 2017-12-15 | 河北汉光重工有限责任公司 | A kind of underwater metal fuel motor power test device |
| CN109029808A (en) * | 2018-07-05 | 2018-12-18 | 陈俊胤 | A kind of airborne propeller dynamic tension measuring device |
| CN115436065A (en) * | 2022-11-08 | 2022-12-06 | 中国航发四川燃气涡轮研究院 | Multifunctional rack for aircraft engine test bed |
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| CN107478366A (en) * | 2017-07-03 | 2017-12-15 | 河北汉光重工有限责任公司 | A kind of underwater metal fuel motor power test device |
| CN107478366B (en) * | 2017-07-03 | 2019-09-10 | 河北汉光重工有限责任公司 | A kind of underwater metal fuel motor power test device |
| CN109029808A (en) * | 2018-07-05 | 2018-12-18 | 陈俊胤 | A kind of airborne propeller dynamic tension measuring device |
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Application publication date: 20160817 |