Services:
Thermal Gradient Testing
The Issue
The flow path or outer flow annulus of a gas turbine engine experiences continuous temperature changes. This results from the work done during compression and from the energy added during combustion and expansion of gases through the turbine stages. These flow path temperatures determine the metal temperatures of each disk rim.
Simultaneously, the secondary flow systems tend to maintain disk bore temperatures at more constant levels to prevent excessive rim growth and lowering of the disk material properties.
Why It Matters
At the mid stages of the high compressor, rim temperatures become high enough relative to the bores to create significant radial thermal gradients. These gradients induce thermal hoop stresses that become a significant percentage of the overall disk stress.
In the extreme case, the thermal stresses induced in a high pressure turbine disk rim can override the hoop stresses caused by rotation. In the case of drum rotors, axial thermal gradients exist along with the radial gradients of the individual stages, which tends to add bending stresses at critical welded or bolted interfaces.
What You can Do
By conducting spin tests at a temperature that simulates the stress state a component would be exposed to under operating conditions, test data is more valid and useful than for spin tests conducted at ambient temperature.
For these reasons, spin testing of any hot section disk should include testing with the proper radial thermal profile applied, either as a constant gradient or synchronized with speed.
How Test Devices Can Help
NEW: Thermal Mechanical Fatigue Testing
Contact
For more information about Thermal Gradient Testing – including TMF – please contact Christine Murner (+1-978-562-4930) in our sales department.




