| 摘要 |
PROBLEM TO BE SOLVED: To maintain clearance between tips of a turbine blade to reduce overshoot of exhaust gas temperature and specific fuel consumption. SOLUTION: The method includes the circumferential mount of a plurality of case segments 38 together so as to form a casing and at least one turbine shroud assembly around a plurality of blades. Each of the case segments contains at least two mounting flanges 54, 55, 56 and passages 52, 53 sectioned between them. The method includes the adhesion of thermal isolation coating to inside surface 60 of the passage and at least one portion of each the mounting flanges in cruise action in order to prompt to maintain a clearance 48 of rotary tips of axial symmetry between a plurality of the blades and at least one turbine shroud assembly. The thermal isolation coating also prompts to control clearance of rotary tips of axial symmetry in launching operation so as to lower exhaust gas temperature and specific fuel consumption. COPYRIGHT: (C)2006,JPO&NCIPI |
