FIELD: engines and pumps.
SUBSTANCE: claimed method comprises registration of signal from linear displacement transducer arranged in the engine housing to register the short-term housing oscillation caused by pulsed energy release at the crack formation and stepwise development at the engine maximum acceleration in the working cycle.
EFFECT: detection of crack formation and development and disc damage without the engine dismantling.
2 cl
| Title | Year | Author | Number |
|---|---|---|---|
| WAY OF AERO GAS-TURBINE ENGINE DISK DIAGNOSTIC EFFICIENCY UPGRADING | 2016 |
|
RU2623856C1 |
| METHOD OF DETERMINING MAXIMUM ALLOWABLE VALUES OF VIBRATORY SIGNALS OF GAS TURBINE ENGINE HOUSING WITH DISK WITH CRACK | 2017 |
|
RU2702951C2 |
| METHOD FOR RESTORING THE CYCLIC DURABILITY OF DISKS OF AIRCRAFT GAS TURBINE ENGINES | 2021 |
|
RU2760895C1 |
| METHOD OF OPERATING AN AIRCRAFT GAS TURBINE ENGINE BASED ON ITS TECHNICAL STATE | 2018 |
|
RU2696523C1 |
| METHOD TO DEFINE SAFE LIFE OF GAS TURBINE ENGINE PARTS | 2008 |
|
RU2373508C1 |
| METHOD FOR PREVENTION OF FATIGUE FAILURE BASED ON MAGNETOELASTICITY | 2007 |
|
RU2353909C2 |
| METHOD OF OPERATING AIRCRAFT GAS TURBINE ENGINE BASED ON TECHNICAL STATE THEREOF | 2020 |
|
RU2742321C1 |
| HEAT-RESISTANT DEFORMED ALLOY ON BASE OF NICKEL AND ITEM MADE OF THIS ALLOY | 2014 |
|
RU2571674C1 |
| METHOD TO PROVIDE SERVEABILITY OF BLADE OF GAS-TURBINE ENGINE | 2006 |
|
RU2317420C1 |
| METHOD FOR INSPECTION INTERVALS DETERMINATION FOR AERO-DERIVATIVE GAS TURBINE ENGINE PARTS IN CASE OF OPERATION ACCORDING TO ITS TECHNICAL CONDITION | 2014 |
|
RU2618145C2 |
