GUIDE BLADE FIXTURE IN A FLOW CHANNEL OF AN AIRCRAFT GAS TURBINE

摘要

Disclosed is an arrangement for detachably fixing a guide blade segment (16) of an aircraft gas turbine (10) comprising a high and low pressure turbine, said guide blade segment (16) forming a transition channel. The aircraft gas turbine (10) is provided with a groove-hook-type connection (40, 44) in the front area of the outer platform (30) of the guide blade segment (16) for radially fixing said guide blade segment (16) and at least one pin (46) penetrating the groove-hook-type connection in order to make the guide blade segment torsion-proof.