Modern gas turbines work under demanding high temperatures

high pressures

and high rotational speeds. In order to ensure durable and reliable operation

effective cooling measures must be applied to the high-temperature rotating components

including turbine blades and turbine disks. Cooling technology

however

is one of the most challenging problems in this field. The present work reviews the current state of cooling technology research

at both the fundamental science and engineering implementation levels

including modeling and simulation

experiments and diagnostics

and cooling technologies for blades and disks. In numerical simulation

the RANS approach remains the most commonly used technique for flow-dynamics and heat-transfer simulations. Much attention has been given to the development of improved turbulence modeling for flows under rotation. For measurement and diagnostics

advanced instrumentation and rotating-flow test facilities have been developed and valuable experimental data obtained. Detailed velocity and temperature distributions in rotating boundary layers have been obtained at scales sufficient to resolve various underlying mechanisms. Both isothermal and non-isothermal conditions have been considered

and the effects of Coriolis and buoyancy forces on flow evolution and heat transfer quantitatively identified. Cooling technologies have been improved by optimizing cooling passage designs

especially for curved configurations under rotation. Novel methods such as lamellar cooling and micro-scale cooling were proposed

and their effectiveness evaluated. For disk/cavity cooling

efforts were mainly focused on rotor-stator systems

with special attention given to the position of air injection into disks.