| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor comprising an acoustic liner capable of preventing shortening of its service life by heat stress and largely adjusting its aperture ratio. SOLUTION: A cooling groove extending obliquely to a line of intersection of a central axis and a wall of a heat chamber, is formed inside of the wall of the heat chamber in the acoustic liner. Thus uniform cooling can be performed even when a diameter of an acoustic hole is large. Inside of the acoustic liner, a cooling fin is mounted on an outer wall of the heat chamber to improve cooling efficiency. Several kinds of materials different in coefficients of thermal expansion are used in the acoustic liner. The material of high coefficient of thermal expansion is used at a part far from the heat chamber 2 and decreased in its temperature during operation, to reduce the difference in thermal expansion with respect to a part of high temperature. A housing of the acoustic liner is mounted on the heat chamber in a state of being incorporated by a bolt or inserted by a guide. Thus the thermal expansion is further relieved by the play of a mounting part. The housing is covered by a thermal shield to prevent the release of heat, thus the temperature difference from a wall surface of the heat chamber is reduced, and heat stress can be reduced. COPYRIGHT: (C)2006,JPO&NCIPI
|
