Abstract: The invention relates to a vane ring of a turbo engine, particularly a gas turbine, comprising a vane support ring and several guide vanes that are mounted on the vane support ring. According to the invention, the vane support ring and the guide vanes are made of different materials, the materials of which the guide vanes are made being of a higher quality than the material of which the vane support ring is made.

Abstract: A method for manufacturing components, preferably of a gas turbine, by powder injection molding is disclosed. In powder injection molding, first a metal powder is combined with a binder to form a homogeneous mass, and then at least one molded article is manufactured from the homogeneous mass by injection molding and the molded body or each molded body is then subjected to a debinding process. The molded body or each molded body is compacted by sintering to yield at least one component having the desired geometric properties. Several molded articles are joined together by a diffusion process during sintering to manufacture a component. The molded articles to be joined together are preferably brought into surface contact, especially into form-fitting surface contact, at least during sintering on sections that are to be joined together. A pressure is applied to the molded articles to be joined together during sintering.

Abstract: Device for the differential cooling or temperature control of inside and outside walls or wall areas of a component, more particularly of a turbomachine component. The device has nozzle arrays or spray pipes under locally separate and/or phased control for the admission of thermally controlled medium. Use of various media and differential temperatures and pressures. Transportation of the component from treatment station to treatment station in its passage.