摘要:
A single-ended infrared emitter may be provided, having at least one glass tube, in which a heating element is accommodated, wherein at least one insulated current return line is arranged spaced apart from the glass tube.
摘要:
A process for manufacturing a honeycomb seal is disclosed. The process includes the following steps: a) the honeycomb structure is brought to the desired three-dimensional form and is fixed in this form; b) then the honeycomb structure is filled with a filler material; c) then the honeycomb structure filled with the filler material is machined on a side on which a carrier element is arranged, such that this side has the desired contour and that the end edges of the honeycomb structure are sealed flushly with the filler compound; d) then the side contoured in this way is coated with a coating; e) next the carrier element is applied to the coating, preferably by laser powder build-up welding.
摘要:
A guide blade segment of a gas turbine, having at least one guide blade and having an inner cover band assigned to the radially inner end of the or each guide blade, is disclosed. An integral constituent part of the inner cover band of the guide blade segment is a sealing element, which serves to seal a radially inner gap between the guide blade segment and a gas turbine rotor.
摘要:
A sealing device is e.g., for a gas turbine, such as an aircraft engine. The sealing device, is used for sealing a gap between a rotor and a stator, e.g., for sealing a gap between radially inside ends of fixed vanes and a rotor and/or a gap between radially outer ends of rotating rotor blades and a fixed housing, a honeycomb seal including a plurality of honeycomb seal cells being assigned to the stator, and the honeycomb seal cells being separated from one another by walls. At least the walls of the honeycomb seal cells that extend transversely to the direction of rotation of the rotor are placed radially at a slant in the direction of rotation of the rotor.
摘要:
The invention relates to a method for the connecting of components, namely for the connecting of at least one pipe-shaped or rod-shaped component with a wall-type component, with the following steps: a) providing a wall-type component (11), whereby the wall-type component (11) comprises a sandwich-type structure of two plate-shaped or pipe-shaped elements (12, 13) with a layer (14) of an expandable foamable metal material positioned therebetween; b) providing at least one pipe-shaped or rod-shaped component (10); c) introducing at least one opening in the wall-type component (11) for the receiving of the or each pipe-shaped or rod-shaped component (10); d) inserting of the or each pipe-shaped or rod-shaped component (10) in a corresponding opening of the wall-type component (11); e) heating of the arrangement of the wall-type component (11) and the or each pipe-shaped or rod-shaped component (10) with foaming-up expansion of the expandable foamable metal material for the connecting of the or each pipe-shaped or rod-shaped component (10) with the wall-type component (11).
摘要:
The invention relates to a gas turbine component, namely static gas turbine component, especially for an aircraft engine. According to the invention, the static gas turbine component is formed at least region-wise of metal foam.
摘要:
A supply lead (7) for a halogen incandescent lamp is bent in a U-shaped fashion and comprises a base (15) and two limbs (16). The ends of the limbs engage in the end region (6) of the luminous element by means of hook parts (20). A section (11) at the end, on the side of the luminous element, of the associated foil is folded back and forms a fold (12) in which the base (15) is held mechanically.
摘要:
A component, in particular a component of a gas turbine, is described composed of at least two metallic structural elements, the first structural element having a first joining surface, and the second structural element having a second joining surface, and the structural elements being joined via their joining surfaces by an inductive high-frequency pressure welding. One of the joining surfaces is shaped to widen peripherally in comparison to the other joining surface, and an upsetting deformation produced in a join region in response to the joining of the structural elements rests virtually entirely within and, in particular, on a peripheral collar formed by the peripheral widening of the one joining surface. A method is described for joining metallic structural elements, in particular structural elements of a gas turbine, an inductive high-frequency pressure welding being used to join corresponding joining surfaces of the structural elements.
摘要:
A gas turbine component of an aircraft engine having a base body, which comprises at least a first material, and a thermal barrier coating that is applied to the base body and consists of or includes an oxide ceramic, is disclosed. Micro-defects and/or nano-defects are included in the oxide ceramic in order to reduce the thermal conductivity of the thermal barrier coating.
摘要:
A method is provided for joining blades to blade roots or rotor disks when manufacturing and/or repairing gas turbine blades or integrally bladed gas turbine rotors. A blade and a blade root or rotor disk that is to be joined to the blade are supplied, and provided with a thickening in sections that are to be joined together. The sections of the blade and the blade root or rotor disk that are to be joined together are machined so as to form recesses and; c) are then aligned relative to each other, opposite recesses defining at least one groove-shaped seam preparation. The blade and the blade root or rotor disk are joined in the area of the or each seam preparation by means of laser power build-up welding and the joined blade and blade root or rotor disk are machined so as to provide a gas turbine blade or an integrally bladed gas turbine rotor having a predefined geometrical profile.