| 摘要 |
A gas turbine (10) comprises an annular combustion chamber (15, 25) which is outwardly limited by an outer shell (23) that can be divided in a parting plane, and surrounded by a plenum (14), said combustion chamber releasing at its output end a hot gas flow (26) to a subsequent turbine (13) the rotor (12) of which is enclosed by a turbine support (47) carrying guide vanes. The combustion chamber (15, 25) is mechanically connected to the turbine support (47) via sealing segments (35, 35') that form a ring and that are movably received on the outer shell (23) on their inner edges via a base portion (44) and on the turbine support (47) on their outer edges via a top portion (38). The service life of the welded combustion chamber shells of such a gas turbine is prolonged in that the sealing segments (35, 35') are received in such a manner that the combustion chamber (15, 25) or the outer shell (23) can move independently of each other relative to the turbine support (47) in the axial direction (B) and in the radial direction (C). |
