Abstract: This invention relates to a gas turbine having a combustion chamber arrangement and a turbine chamber connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers formed by input areas and transition areas converging in an annular gap leading to the turbine chamber and wherein the longitudinal axes of the individual combustion chambers are placed at an angle relative to an engine axis that is defined by the axial extension of the turbine chamber. In order to improve said gas turbine by visibly reducing the thermal and mechanical loads of the individual combustion chambers in the transition area so that cooling requirements can be lowered in said area, the transition area of at least one individual combustion chamber into the turbine chamber is deflected in the direction of the engine axis and substantially in the input area of the turbine chamber.

Abstract: The invention relates to a method for producing a monocrystalline component, having a complex moulded structure with different structure parts, from a molten metal. According to the method, said molten metal is located in a negative mould, corresponding to the moulding structure and said negative mould moves with the formation of a solidification front on a temperature drop, which is adapted to the crystallization speed of the molten metal and which includes the melting point. Said method is characterized in that at least one of the structure parts of the moulded structure experiences an individual temperature drop. If the solidification front has to grow through a structure part, which is inappropriately oriented in relation to the solidification front, said structure part or zone can experience an individual temperature drop. This enables monocrystalline components, having a complex moulded structure, to be produced in a reliable and economic manner.

Abstract: In order to develop a flow control body (6) for separate control of a cooling fluid inflow and a cooling fluid outflow for combustion chambers with a closed cooling system for turbines such that a simplified cooling fluid flow control is made possible in the combustion chamber wall, it is proposed with the invention that the flow control body (6) has a non-rotationally symmetrical cross-sectional shape (7) in a flow control section.