GAS TURBINE ENGINE AND TURBINE ENGINE ROTOR

摘要

PROBLEM TO BE SOLVED: To improve reduction of flow passage cross sectional area to improve efficiency of a turbine part. SOLUTION: A rotor stack 32 is provided with blade discs 34A to 34C for supporting blade steps 36A to 36C. Vane steps 38A to 38C are alternately arranged with the blade steps along a core flow passage 500. Bores 52A to 52C surround a central opening part of the disc, and a part 33 of a low speed shaft 29 passes through it. Spacers 62A, 62B recessed on an outer side have an end part connecting an adjacent pair of discs 34A to 34C and coming into contact and engaging with an adjacent part of the disc. Engagement and contact with a peripheral fringe part 54 of the adjacent disc cause engaging force in the longitudinal direction which is increased with speed by centrifugal force for making cross section of the spacer flat. Joints 70A, 70B are positioned between the discs 34A to 34C and are provided with a first tubular structure part 74 extending backward from the front disc and a second tubular structure part 76 extending forward from the rear disc. COPYRIGHT: (C)2006,JPO&NCIPI