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 film cooling characteristics of turboshaft engine vanes were studied under one engine
inoperative (OEI) conditions. Variations in the operating conditions caused tremendous …

High-pressure turbine (HPT) rotor blades work in a harsh environment with high temperature
and rotational speed. Affected by blade row interaction and inlet non-uniformities, the rotor …

In modern lean-burn aero-engine combustors, highly swirling flow structures are adopted to
control the fuel-air mixing and to provide the correct flame stabilization mechanisms …

Modern lean-burn combustors generate aggressive swirling flow at the entrance of high-
pressure turbine nozzle guide vane (NGV), and lead to cooling performance deterioration of …

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 …

In this paper, cooling characteristics of a novel film hole are experimentally evaluated over a
linear turbine endwall for enhancing the endwall film cooling. The novel hole features a …

At the large scale turbine rig (LSTR) at Technische Universität Darmstadt, Darmstadt,
Germany, the aerothermal interaction of combustor exit flow conditions on the subsequent …