Blade cutting device and containment testing device for aero-engine fan case

Abstract

The invention belongs to the field of aero-engine fan case containment testing, and particularly relates to a blade cutting device and a containment testing device for an aero-engine fan case. The blade cutting device comprises a charging hole, a cutting cable, plastic steel mud, a detonator fixing bolt and a detonating switch, wherein the charging hole is formed in a to-be-cut blade tenon, and the two ends of the charging hole are provided with internal threads; the cutting cable is laid in the charging hole; the plastic steel mud is arranged in the gap between the cutting cable and the charging hole; the detonator fixing bolt is installed at the bottom of one end of the charging hole through a thread and internally provided with a detonator, and two detonator leads of the detonator stretch out of the top of the detonator fixing bolt through a lead passing hole; and the detonating switch is connected with the detonator leads through two detonating power lines so that the detonator canbe ignited. According to the blade cutting device and the containment testing device, a blade can be cut off at the specific rotation speed, so that the testing result is real and effective, in addition, large stress concentration can be avoided, the detonator and the cutting cable can be installed finally, the operation safety of testing piece assembling and lead working is ensured, and it can be ensured that a detonating system operates safely and reliably.

Description

technical field [0001] The application belongs to the field of containment test of aero-engine fan case, and in particular relates to a blade cutting device and a containment test device for aero-engine fan case. Background technique [0002] In the case of gas turbine engines, the high-energy debris generated when rotating parts fail puts the engine itself, the aircraft, control surfaces, fuel tanks and pilots at risk. Once the engine is not contained, the aircraft will be damaged, ranging from the loss of flight function to the loss of flight function, and the crash of the aircraft. Therefore, military and civilian gas turbine engine specifications worldwide all have inclusive relevant requirements without exception. The content is basically the same. At least 80% of a single blade must be damaged and contained, and the resulting engine damage must not have any dangerous effect on the aircraft. Generally, engine specifications require verification of fan blade containmen...

AI Technical Summary

Problems solved by technology

[0006] Due to the influence of material dispersion, processing error and notch sensitivity, the prefabricated notch method has low control accuracy of the fly-off speed. In practical applications, conservative prefabricated notches are usually used, resulting in the need to go up and down the test many times, and the success rate of the test is difficult. ensure

[0007] The method of combining prefabricated gaps and local rapid heating is only suitable for metal materials whose tensile strength is sensitive to temperature rise. In addition, it also faces the problem of difficult wiring when applied in component level and complete machine containment tests.

[0008] Using contact blasting to break the blade, because the detonation pressure has no directionality, it will increase the extra kinetic energy of the blade flying outward, thus affecting the test results; the energy-concentrating cutter is external, and it is at the tenon fracture position required by the actual engine containment test There is not enough layout space, and it cannot be directly applied to the engine component level and the complete machine containment test

[0009] 2. Cost

[0012] The existing fly-off speed control technology has large errors, and repeated tests are required, which affects efficiency

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