Abstract: A gas turbine engine (10) and method of operation. The gas turbine engine (10) comprises a heating device configured to heat a rotor disc (32, 72) of the engine (10). A method of operation the heating device comprises detecting an engine acceleration or deceleration event, or determining that an engine acceleration or deceleration event is imminent or may be imminent. On detection of an engine acceleration or deceleration event, or in advance of the engine acceleration or deceleration event, increasing turbine rotor disc heat input to raise a temperature of the turbine rotor disc or reduce a cooling rate of the rotor disc.

Abstract: Rotatable discs combined with turbine blades in engines must be tested for critical life analysis. Thus, consideration must be made as to life expectancy for such components as a result of tensile circumferential hoops as generated by the weight of blades under rotation as well as compressive axial stress as a result of thermal gradients during initial warm up. Previous testing arrangements have considered tensile circumferential hoop stress but not compressive axial stress combinations such as “Von Mises” stress. By provision of bend structures 13, 223 a bending moment is created about a base 2, 22 formed in a test component 1, 21 such that a bending moment force 4, 24 creates a bending moment in the test component 1, 21. This bending moment results in a compressive axial stress reminiscent of that in a practical turbine engine disc as a result of initial thermal gradients. In such circumstances a more realistic testing of the component 1, 21 representative of a practical disc/blade combination is achieved.