To prevent an excessive stress from occurring in a composite material liner in a tightening unit even if a difference in thermal expansion from a base member is produced in the tightening portion by providing, in the tightening unit, means for absorbing the difference in thermal expansion in an excellent structure for tightening the composite material liner for use in a combustion device such as a gas turbine.
A composite material liner 1 for use in a combustion device in a gas turbine is tightened at one end thereof in a state held between a metallic swirler 2 and a tightening metal fitting 21. A spring member 4 is inserted into a tightening unit J. The spring member 4 comprises a first spring 41 adapted to absorb forcible displacement in a radial direction due to a difference in thermal expansion to be exerted on the composite material liner 1 and disposed in a space 5 inside the tightening unit in such a manner as to abut against the inner circumference or outer periphery of the composite material liner 1, and a second spring 42 adapted to absorb forcible displacement in a radial direction due to a difference in thermal, expansion to be exerted on the composite material liner 1, and disposed in the space 5 inside the tightening unit in such a manner as to abut against the end face of the composite material liner 1.
| JP7335038 | gas turbine combustor structure |
KUYAMA TOSHIYUKI
TAKE KOJI
NISHIO KOJI
ARAI MASASHI
