| 摘要 |
An annular combustion chamber of a gas turbine engine comprises a front burner device 6 located in the inlet cross section of the combustion chamber and a flame tube 8, the combustion chamber being dividable in the longitudinal direction in a plane coinciding with the longitudinal dividing plane of the engine. The flame tube 8 is formed by two concentrically arranged shells with curvilinear surfaces, that is, an outer shell 9 and an inner shell 10. Each one of the shells 9, 10 is split longitudinally into sections 11 and 12, respectively, the places of the split being sealed with sealing members. According to the invention, the combustion chamber is provided with at least two ring-shaped longitudinally- dividable supporting members 15-18 for each one of the shells 9 and 10, respectively. One ring-shaped supporting member 15, 17, located in the zone of the combustion chamber 1 inlet section, is capable of longitudinal and radial movements while the other supporting member 16, 18, located in the zone of the combustion chamber 1 outlet section, is capable of only radial movement. Each shell section 11 and 12, respectively, is coupled with a respective ring-shaped supporting member 15-18, such that the central portion of the section is rigidly attached to the ring-shaped member while its ends are connected to the ring-shaped member with the provision for movement in the circumferential direction. <IMAGE> |
