Non destructive Testing Gas Turbines Destructive testing

1. Civil Aviation Technology College
IRAN

5. Examination of component surfaces, using special equipment
such as Borescopes, and magnifying glasses.

6. The application of a coloured or fluorescent
dye to detect surface breaking defects on
non-porous materials.

7. Detection of flaws on or just underneath the surface of
ferromagnetic materials, using fluorescent, black, or dry
magnetic particles.
Prods
DC or
AC
Electro-
magnet
(yolk) DC or
AC
Crack
like
indicati
on
Crack
like
indicati
on

8. This method uses the transmission of high-frequency
sound waves through a material to detect internal
defects. The pulse-echo method is the most commonly
used ultrasonic testing technique. Automated and
advanced ultrasonic testing methods, such as phased
array and time of flight diffraction, are also used.

9. This technique generates eddy currents up to a few millimeters below the
surface of a conductive material through an induced alternating magnetic
field.
Material defects will disturb the flow of eddy currents and generate a
traceable signal.

11. Replication is used to evaluate microstructures and
other surface features.

12. Radiography uses an x-ray device or radioactive isotope as a source of
radiation which passes through the material and is captured on film or digital
device.
After processing the film an image of varying density is obtained. Possible
imperfections are identified through density changes.

13. One of many advantages of cast steel for complex designed structures such as
turbine components is, that defects can be repaired by welding .

15. A large variety of NDT methods are available for the condition
assessment of gas turbine components.
Selecting the most appropriate one depends upon:
 The type of component
 The type of defect
 The specific situation, such as the accessibility or cleanliness of the part

17. Images for surfaces of gas turbine blades made of the ŻS6-K alloy, ordered
according to the criterion of the increasing degree of the material overheating

18. General Electric MS7001FA

19. Impact damage on the leading edge S-5
stator vane
White deposits on all of the effusion plates

20. mid-span sidewall cracking on first stage
nozzle 1, segment 24.
trailing edge of the first stage nozzles and
the leading edge of the first stage buckets.

22. Manual Ultrasonic Inspection

23. UT for discs

24. UT for Shafts

26. www.Rolls-royce.com
www.Mtu.de
www.Saarschmiede.com
SDF)(fahr.com-www.Samedeutz
www.Bohler-forging.com
www.FAA.gov
Józef BŁACHNIO : EXAMINATION OF CHANGES IN MICROSTRUCTURE OF TURBINE
VANES WITH THE USE OF NON-DESTRUCTIVE METHODS