Vibration Test of Blade Disc of High Pressure Turbine in High Rotating Speed

Abstract

In the high-speed rotating state, the experimental study on the vibration characteristics of high-pressure turbine rotor blade and the vibration reduction effect of flange damping device is beneficial to the later design iteration and obtain the real blade vibration situation.With high pressure turbine rotor simulator as an object, simulating the turbine blade periodic pneumatic excitation by non-contact atomizing oil excitation, the vibration characteristics test system of high rotational speed high pressure turbine rotor blades is designed and created. The component level test is between the fixed blade test and the direct test of the core turbine aero-engine system. The test system excites the rotor blades under operation status, obtains data of blade vibration characteristics successfully, and verifies the vibration reduction level of the platform damper. Research shows under 10 000~19 000 r/min operating rotating speed at the normal temperature, the platform damper device can reduce the vibration of rotor blades by about 40%, and frequency of the rotor blade with higher damping mass is higher.

Keywords

• high pressure
• turbine
• rotor blade
• vibration
• damper
• vibration reducing