| 摘要 |
<p>The invention relates to a thermal engine, especially a gas turbine, which comprises an annular combustion chamber that is outwardly limited by an outer shell and an inner shell, the outer shell and the inner shell being subdivided into an upper half (23a) and a lower half (23b) in a parting plane (29), said halves being welded to each other in the parting plane (29). An additional mechanical form-locking connection (30) is provided on the parting planes (29) to receive any tensile and shearing forces acting upon the parting planes (29), thereby increasing the mechanical stability and the service life of the combustion chamber.</p> |
