Turbo machine e.g. gas turbine engine, components` determining method for aircraft, involves determining operational geometry of gap from nominal geometry and total displacement vector of gap

摘要

The method involves defining a nominal geometry of a gap (10) formed between two components (11, 12) of a turbo machine. A displacement vector of the gap is found to determine displacement vectors for inner and outer stresses and tolerance of the gap. The vectors of stresses and tolerance are superimposed to find a total displacement vector. The gap`s operational geometry is found from the nominal geometry and the total vector of gap.