| 摘要 |
A method of manufacturing an annular wall (46) of a gas turbine combustion chamber comprises depositing layers of a metal powder sequentially one upon the other to form the wall (45) of the combustion chamber. Each layer of metal is deposited in a spiral pathway, so as to achieve a wall (45) of spiral form at first. The spiral wall (45) is then further processed for example by rolling it up to an annular combustion chamber of typical form, thereby joining together the former spiral ends (E1, E2). Alternatively the resulting spiral wall (45) is cut into different combustion chamber segments which then can be joined together. Air passage apertures such as dilution, impingement or effusion holes are directly manufactured during the typical methods of additive manufacturing used. Alternatively, double layered walls can be manufactured in one step with the method. |
