The figure shows in a comparison diagram, that the part-load consumption is definitely higher than traditional reciprocating engines. A significant improvement of the efficiency is possible by increasing the turbine inlet temperature. The continuous thermal load limit for metallic materials, however, lies at a temperature of approx. 1,300 K. As a result, unburned secondary air has to be mixed into the combustion gases (bypass) for cooling. If cooling is to be withdrawn in order to optimize consumption, ceramic materials, which are stable up to gas temperatures of approx. 1,600 K, have to be used in the combustion chamber, inlet cone, turbine blade ring, and turbine blade wheel. The use of ceramic materials, in addition allows for a considerably smaller operating gap between turbine cover ring and blades as a result of lower thermal dilatation. Since losses due to leakage decrease in doing so, a further additional improvement in efficiency can be achieved. In the entire operating area, these measures signify a fuel consumption reduction of 20-30 %. The emission behavior of gas turbines is better than the one of comparable reciprocating engines. Due to the high air flow rate, catalytic after-treatment is not possible.