Gas turbine engine efficiency and reliability is generally improved through better
understanding and improvements to the design of individual components. The life limiting …

The high pressure (HP) turbine is subject to inlet flow nonuniformities resulting from the
combustor. A lean-burn combustor tends to combine temperature variations with strong swirl …

Unsteady component interaction represents a crucial topic in turbomachinery design and
analysis. Combustor/turbine interaction is one of the most widely studied topics both using …

Recently developed lean-burn combustors offer reduced NO x emissions for gas turbines.
The flow at exit of lean-burn combustors is dominated by hot streaks and residual swirl …

The flow at the combustor turbine interface of power generation gas turbines with can
combustors is characterized by high and nonuniform turbulence levels, lengthscales, and …

Conjugate heat transfer (CHT) analyses were conducted on the film-cooled first stage vane
of GE-E 3 engine to reveal the influences of inlet swirl and hot streak (HS) on vane film …

The mutual interference between the combustor and turbine of modern aero-engines has
gradually increased with recent advancements, and turbine cooling design considering the …

A high-pressure vane (HPV) equipped with a realistic film-cooling configuration has been
studied. The vane is characterized by the presence of multiple rows of fan-shaped holes …

A design of linear matrix inequality (LMI)-based fractional-order surface for sliding-mode
controller of a class of uncertain fractional-order nonlinear systems (FO-NSs) is proposed in …

In new generation aero-engines, lean-burn combustors are equipped with swirl injectors in
order to reduce pollutant emissions. At the exit of these combustors, the flow is dominated by …