CN216594172U - Test jig and test apparatus - Google Patents
Test jig and test apparatus Download PDFInfo
- Publication number
- CN216594172U CN216594172U CN202220177153.3U CN202220177153U CN216594172U CN 216594172 U CN216594172 U CN 216594172U CN 202220177153 U CN202220177153 U CN 202220177153U CN 216594172 U CN216594172 U CN 216594172U
- Authority
- CN
- China
- Prior art keywords
- section
- test
- fixture
- clamp
- lobe
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a test fixture and test device for aeroengine fan blade bird hits the experiment, can reduce test cost, shortens test cycle. The test device comprises a test fixture, wherein the test fixture is used for clamping a test piece in a bird strike test of the fan blade of the aircraft engine, the test piece is a local section of the fan blade, the local section comprises a bird strike section, an upper clamping section and a lower clamping section, the upper clamping section and the lower clamping section are positioned at two ends of the bird strike section in the spanwise direction, the test fixture comprises an upper fixture and a lower fixture, the upper fixture is used for clamping the upper clamping section, and the mass of the upper fixture is enough to simulate the inertial constraint of a blade tip section of the fan blade on the local section; the lower clamp is configured to clamp the lower clamping section with a mass sufficient to simulate inertial constraints of a root section and a dovetail section of the fan blade on the local section.
Description
Technical Field
The utility model relates to an aeroengine tests technical field, concretely relates to test fixture and test device.
Background
The civil large bypass achieves the technical and commercial success recognized in the industry compared with the selection of composite material fan blades for aeroengines. The composite material has the advantages of high specific strength and specific stiffness, excellent corrosion resistance and fatigue resistance, strong designability and the like, and the whole weight reduction of the aircraft engine structure can be realized by selecting the composite material fan blade, so that the fuel efficiency of the aircraft engine is greatly improved, and the economy and market competitiveness of the aircraft engine are improved. Bird strike design of fan blades made of composite materials meets the requirement of civil aircraft engines on airworthiness and evidence obtaining. Statistically, about 1 million bird-to-aircraft accidents occur worldwide each year, and the damage caused by bird-to-aircraft, especially aircraft engines, is catastrophic.
The bird strike test of the composite fan blade is an indispensable technical means for designing the bird strike resistance of the composite fan blade. The common test method comprises a single-blade part-level bird impact test, a whole-level fan part-level bird impact test, a whole-machine bird swallowing test and the like, wherein compared with the part-level test and the whole-machine test, the part-level test has the advantages of low test cost, low risk and low requirement on test conditions, so the part-level test becomes an important means in designing and evaluating the bird impact resistance of the aircraft engine. However, due to the fact that the three-dimensional modeling of the composite material fan blade is extremely complex, even in a single-blade part level bird strike test, the problems of high manufacturing cost and long manufacturing period of the test blade still exist, and the test efficiency and the design iteration speed are affected.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a test fixture can reduce aeroengine fan blade bird and hit experimental test cost, shortens test cycle.
The test fixture comprises an upper fixture and a lower fixture, wherein the upper fixture is used for clamping the upper clamping section, and the mass of the upper fixture is enough to simulate the inertial constraint of a blade tip section of the fan blade on the local section; the lower clamp is configured to clamp the lower clamping section with a mass sufficient to simulate inertial constraints of a root section and a dovetail section of the fan blade on the local section.
In one or more embodiments of the test fixture, the upper fixture is attached to the leaf back side and the leaf basin side of the upper clamping section, and the lower fixture is attached to the leaf back side and the leaf basin side of the lower clamping section.
In one or more embodiments of the test fixture, the upper fixture includes an upper leaf back flap and an upper leaf basin flap, the upper leaf back flap is used for being attached to a leaf back side of the upper clamping section, the upper leaf basin flap is used for being attached to a leaf basin side of the upper clamping section, and the upper leaf back flap and the upper leaf basin flap are detachably connected.
In one or more embodiments of the test fixture, the lower fixture includes a lower back lobe and a lower basin lobe, the lower back lobe is configured to engage with a back side of the lower clamping section, the lower basin lobe is configured to engage with a basin side of the lower clamping section, and the lower back lobe and the lower basin lobe are detachably connected.
The clamp simulates the inertia constraint of the full-size blade of the specification corresponding to the local section by utilizing the dead weights of the upper clamp and the lower clamp, can accurately simulate the boundary constraint of a bird impact test of a test piece, and ensures the accuracy of a test result, so that the local section can be adopted to replace the full-size blade to be used as the test piece for carrying out the bird impact test, the manufacturing cost of the test piece is reduced, the test period is shortened, and the rapid iteration of the design is realized.
Another object of the utility model is to provide a test device can reduce aeroengine fan blade bird and hit experimental test cost, shortens test cycle.
The test device for achieving the purpose is used for a bird strike test of the fan blade of the aircraft engine and comprises the test fixture.
In one or more embodiments of the testing device, the testing device further comprises a testing stand, and the upper clamp and the lower clamp are respectively connected with the testing stand in a hanging manner.
The test device can accurately simulate the boundary constraint of the bird strike test of the test piece by adopting the clamp, and the accuracy of the test result is ensured, so that the local section can be adopted to replace a full-size blade to be used as the test piece for carrying out the bird strike test, the manufacturing cost of the test piece is reduced, the test period is shortened, and the rapid iteration of the design is realized.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
fig. 1 and 2 are schematic views of a test fixture holding a test piece from different perspectives.
FIG. 3 is a schematic view of a full size blade.
Fig. 4 is a front view schematically showing the upper jig.
Fig. 5 is a schematic top view of the upper clamp.
FIG. 6 is a schematic view of an upper lobe back lobe.
Fig. 7 is a schematic view of an upper lobe basin valve.
Fig. 8 is a front view schematically showing the lower jig.
Fig. 9 is a schematic top view of the lower clamp.
Fig. 10 is a schematic view of the lower leaflet dorsal flap.
FIG. 11 is a schematic view of a lower lobe basin valve.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present invention. It is to be noted that the drawings are designed solely as examples and are not to scale, and should not be construed as limiting the scope of the invention as it is actually claimed. Furthermore, some of the features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
The test device according to one embodiment of the invention is used for bird strike test of an aircraft engine fan blade, and comprises a test stand (not shown), a test fixture 1 and a test piece 2, which are shown in fig. 1 and 2.
The test piece 2 employs a spanwise local section 20 of a full-size fan blade to reduce the manufacturing cost of the test piece 2, shorten the test period, and achieve rapid iteration of the design.
Referring to fig. 3, the full-size blade 3 corresponding to the test piece 2 includes an airfoil section 31 and a dovetail section 32, and the airfoil section 31 includes a tip section 311, a root section 312, and the partial section 20. The partial section 20 is located between the tip section 311 and the root section 312, and includes the bird strike section 200, the upper clamp section 201, and the lower clamp section 202. The bird strike section 200 is a range of the fan blade bearing bird strike according to the airworthiness evidence requirement, the upper clamping section 201 and the lower clamping section 202 are respectively located at two ends of the bird strike section 200 in the spanwise direction, the upper clamping section 201 is adjacent to the blade tip section 311, and the lower clamping section 202 is adjacent to the blade root section 312.
The test fixture 1 comprises an upper fixture 11 and a lower fixture 12 for clamping the upper clamping section 201 and the lower clamping section 202, respectively, and simulating the boundary constraint of the bird strike test of the test piece 2.
The boundary constraint of the bird strike test of the test piece 2 is different from simple fixed support or simple support, but is an inertia constrained spring support, in order to accurately simulate the boundary constraint of the bird strike test of the test piece 2, the upper clamp 11 and the lower clamp 12 are respectively and freely suspended on a test bed of the test device through different suspension ropes, and the mass of the upper clamp 11 and the mass of the lower clamp 12 are respectively designed according to the following method:
1) the upper clamp 11 is used for simulating the part of the tip section 311 pair of the full-size blade 3 with the specification corresponding to the test piece 2Inertial constraint of the section 20, upper clamp mass m, since the tip is the free end in the bird strike test of the full-size blade 3On the upper part＝m1，m1The mass of the tip section 311 of the full size blade 3;
2) the lower fixture 12 is used for simulating the inertial constraint of the blade root section 312 and the tenon section 32 of the full-size blade 3 with the specification corresponding to the test piece 2 on the local section 20, and the mass m of the upper fixture is because the tenon section 32 is fixed in the bird strike test of the full-size blade 3Lower part＝k×m2，m2For the mass of the root section 312 and the dovetail section 32 of the full-size blade 3, the factor k is set as a function of the configuration of the partial section 20, the recommended value k being 1.5.
Therefore, the clamp 1 utilizes the self weights of the upper clamp 11 and the lower clamp 12 to simulate the inertia constraint of the full-size blade 3 with the specification corresponding to the local section 20, can accurately simulate the boundary constraint of the bird strike test of the test piece 2, and ensures the accuracy of the test result, so that the local section 20 can be adopted to replace the full-size blade 3 to be used as the test piece 2 to carry out the bird strike test, the manufacturing cost of the test piece 2 is reduced, the test period is shortened, and the rapid design iteration is realized.
According to the test device, by adopting the clamp 1, boundary constraint of a bird strike test of the test piece 2 can be accurately simulated, and the accuracy of a test result is ensured, so that a local section 20 can be adopted to replace a full-size blade 3 to be used as the test piece 2 for carrying out the bird strike test, the manufacturing cost of the test piece 2 is reduced, the test period is shortened, and the design fast iteration is realized.
Referring to fig. 1 to 11, test piece 2 includes a back side 203 and a bowl side 204, upper fixture 11 includes upper back lobe 111 and upper bowl lobe 112, upper back lobe 111 includes a first profile 1111, upper bowl lobe 112 includes a second profile 1121, first profile 1111 is adapted to be fitted to all or most of a surface of back side 203 of upper clamping section 201, and second profile 1121 is adapted to be fitted to all or most of a surface of bowl side 204 of upper clamping section 201.
The lower clamp 12 comprises a lower dorsal lobe 121 and a lower pelvic lobe 122, the lower dorsal lobe 121 comprising a third profile 1211, the lower pelvic lobe 122 comprising a fourth profile 1221, the third profile 1211 for engaging all or most of the surface of the dorsal side 203 of the lower clamping section 202, the fourth profile 1221 for engaging all or most of the surface of the pelvic side 204 of the lower clamping section 202.
Therefore, the upper clamp 11 and the lower clamp 12 are attached to the blade back side 203 and the blade basin side 204 of the test piece 2 and clamp the test piece 2, so that the test piece 2 with a complex three-dimensional structure shape can be reliably clamped, the test piece 2 can be smoothly installed and compacted at large bending, large distortion and rapid structural spanwise change positions of the test piece 2, the upper clamp 11, the lower clamp 12 and the test piece 2 can be automatically fixed in the spanwise direction by using the spanwise change of the blade shape, and the upper clamp 11 and the lower clamp 12 cannot fall off in the bird impact test process.
The upper lobe back lobe 111 is detachably connected to the upper lobe basin lobe 112 to facilitate mounting of the upper clamp 11. For example, the lengths of the upper back leaflet 111 and the upper pot leaflet 112 are longer than the chord length of the test piece 2, fastener mounting holes 13 are respectively formed in both sides of the upper back leaflet 111 and the upper pot leaflet 112 in the length direction, and the upper back leaflet 111 and the upper pot leaflet 112 are detachably connected and clamped by a fastener 14 penetrating through the fastener mounting holes 13. Similarly, the lower dorsal leaflet 121 and the lower pelvic leaflet 122 are removably attached and clamped by fasteners 14 to facilitate installation of the lower clamp 12.
In other embodiments, the upper dorsal leaflet 111 is hinged to the upper pot leaflet 112 on one chordal or spanwise side of the test piece 2 and is connected and clamped by fasteners on the other side, and similarly, the lower dorsal leaflet 121 is hinged to the lower pot leaflet 122 on one chordal or spanwise side of the test piece 2 and is connected and clamped by fasteners on the other side to facilitate mounting of the upper clamp 11 and the lower clamp 12.
The method of mounting and using the test fixture 1 is described below in connection with one embodiment:
1. vertically placing a test piece 2 on a workbench, attaching a lower lobe back 121 and a lower lobe basin 122 to a lobe back side 203 and a lobe basin side 204 of the test piece 2, installing and screwing a fastener 14, enabling a lower clamp 12 to clamp and compact the test piece 2, attaching an upper clamp 11 to the lobe back side 203 and the lobe basin side 204 of the test piece 2, installing and screwing the fastener 14, and enabling the upper clamp 11 to clamp and compact the test piece 2;
2. adopt different suspension ropes to twine the fastener 14 department at last anchor clamps 11 and 12 both sides down respectively, hoist test piece 2 to the experimental position, make the exhibition of test piece 2 to along vertical direction, make upper clamp 11 and lower anchor clamps 12 be located the upper and lower both ends of test piece 2 respectively, guarantee the stability of test piece 2 to make the gravity of test piece 2 mainly lean on the suspension rope atress of anchor clamps 12 to come the equilibrium.
In another embodiment, the upper clamp 11 is attached and clamps the test piece 2 by way of a lifting installation.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.
Claims (6)
1. The test fixture is used for clamping a test piece in a bird strike test of a fan blade of an aircraft engine, and is characterized in that the test piece is a local section of the fan blade, the local section comprises a bird strike section, an upper clamping section and a lower clamping section, the upper clamping section and the lower clamping section are positioned at two ends of the bird strike section in the spanwise direction, and the test fixture comprises:
an upper clamp for clamping the upper clamping section, the mass of the upper clamp being sufficient to simulate inertial constraints of the blade tip section of the fan blade on the local section; and
a lower clamp for clamping the lower clamping section, the mass of the lower clamp being sufficient to simulate inertial constraints of a root section and a tenon section of the fan blade on the local section.
2. The test fixture of claim 1, wherein the upper fixture is configured to engage a leaf back side and a leaf basin side of the upper clamping section, and the lower fixture is configured to engage a leaf back side and a leaf basin side of the lower clamping section.
3. The trial clamp of claim 2, wherein the upper clamp includes an upper dorsal lobe for engaging a dorsal side of the upper clamping section and an upper pot lobe for engaging a pot side of the upper clamping section, the upper dorsal lobe and the upper pot lobe being removably connected.
4. The trial clamp of claim 2, wherein the lower clamp includes a lower dorsal lobe for engaging a dorsal side of the lower clamping section and a lower pelvic lobe for engaging a pelvic side of the lower clamping section, the lower dorsal lobe and the lower pelvic lobe being removably connected.
5. Test device for bird strike testing of aircraft engine fan blades, characterized in that it comprises a test fixture according to any one of claims 1 to 4.
6. The testing device of claim 5, further comprising a test stand, wherein the upper fixture and the lower fixture are each in suspended connection with the test stand.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220177153.3U CN216594172U (en) | 2022-01-21 | 2022-01-21 | Test jig and test apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220177153.3U CN216594172U (en) | 2022-01-21 | 2022-01-21 | Test jig and test apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216594172U true CN216594172U (en) | 2022-05-24 |
Family
ID=81634658
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220177153.3U Active CN216594172U (en) | 2022-01-21 | 2022-01-21 | Test jig and test apparatus |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216594172U (en) |
-
2022
- 2022-01-21 CN CN202220177153.3U patent/CN216594172U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107084844B (en) | A kind of test method of blade construction simulating piece | |
| CN104568351B (en) | Damping-structure-optimized blade testing experiment table and experimental method thereof | |
| ES2690651T3 (en) | Apparatus and method of sample loading | |
| CN105004504B (en) | The starting of oscillation wind speed appraisal procedure and selection method of composite insulator | |
| CN109490113B (en) | Test piece and test method for fatigue test of hanging thrust pin of aircraft engine | |
| CN216594172U (en) | Test jig and test apparatus | |
| CN112525737A (en) | Test device and test method for measuring flapping rigidity of helicopter blade | |
| CN112113731B (en) | Rotor blade high-frequency vibration fatigue test fixture and design method thereof | |
| CN106840630A (en) | Damping test device with listrium damper structure turbo blade | |
| CN107679347B (en) | Crankshaft stress analysis method based on finite element | |
| Jafari et al. | A numerical simulation method in time domain to study wind-induced excitation of traffic signal structures and its mitigation | |
| CN206339319U (en) | A kind of ejection guns device for testing tensile force | |
| CN102798509A (en) | Test method for high-speed railway contact network wind-induced response wind tunnel | |
| JP4326453B2 (en) | Two-dimensional wind tunnel and wind resistance stability evaluation method | |
| Grasse et al. | Structural health monitoring of wind turbine blades by strain measurement and vibration analysis | |
| CN201258875Y (en) | Single blade blowing test device for tube-axial fan of turbine generator | |
| Paturu et al. | Numerical analysis of flow over naca0012 at fixed mach number, using computational fluid dynamics | |
| Cieren et al. | On the validation and use of a simplified model of aeolian vibration of overhead lines for parametric studies | |
| CN201075058Y (en) | Hanger tester | |
| US1367478A (en) | Standardized connecting-rod and process for standardizing the same | |
| Lee et al. | Damping mechanism model for fatigue testing of a full-scale composite wind turbine blade, Part 2: Application of fairing | |
| CN219625218U (en) | Test device for measuring flapping rigidity of large-size main blade of helicopter | |
| CN221377027U (en) | Static loading test device for stabilizing device | |
| CN109018428A (en) | A kind of engine installation structure load-carrying properties test device | |
| DANSBERRY | Dynamic characteristics of a Benchmark models program supercritical wing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |