Structural Analysis

Structural analysis of the dovetail attachments of the blades is very challenging due to non-linearity (contact). Due to nature of contact mechanism (i.e. edge type contact), high tensile stresses can occur and may cause crack initiation and disk failures. For this reason, the interaction between the mating parts has to be understood very well, in order to optimize the interface geometry to reduce the risk of possible failures.

 Explicit Analysis

It is desired that liberated blade as a result of fatigue or FOD (Foreign Object Damage) must be contained inside the casing. Otherwise, this liberation may result in catastrophic failures. Therefore, the whole process must be simulated in computer environment and tested before the final design is frozen to assure that the casing is capable of containing the failed blade. For this purpose, implicit-explicit sequential analysis must be performed.

 Thermal Analysis

Outer surfaces of IGV's (Inlet Guide Vanes) must remain above a certain minimum temperature under all flight conditions to prevent ice formation on the vane surfaces. To overcome this difficulty, hollow type blades are designed and hot air is circulated through vanes. Additionally, trailing edge is provided with some through holes, to increase the temperature in this region.

 Modal Analysis

Exhaust Nozzle has very flexible structure due to its geometry and mounting. This brings about the vibration problems under some flight conditions. To prevent the same, the design must be checked against various vibratory excitations, and if required, the design must be modified.

 Transonic Compressors

The simulation of the flow field in a rotating or a stationary blade row is a descriptive example of CFD in turbomachinery applications. In this study, different blade rows of the compressor are investigated and the pressure and temperature distributions on the blade surfaces are obtained in CFD calculations and the calculated data is used for the structural analysis.

In-house developed design codes are used to create airfoil geometries.

 Combustion

Combustion phenomenon includes both physics and chemistry. Therefore, combustor design is such a complex task that it is often referred to as a 'Black Art'.

Research activities and studies related to combustion for gas turbine engines are being continued. Cold and hot flow CFD analyses are performed for different geometries of gas turbine combustion chambers.

 Turbine Aerodynamics

In-house developed codes are being used in the design of turbine airfoils.

CFD calculations are performed to check if flow field variables satisfy design requirements.