Mtu Aero Engines Ag

Berns Engineering Consulting Gmbh

Christian Eichler

Manfred Feldmann

Norbert Schinko

Lutz Friedrich

Martin Pernleitner

Krzysztof Skura

Sebastian Kaltenbach

Dieter Freno

Klaus Wittig

Stephan Staudacher

Martin Rose

Björn Weigel

Sandra Muschkorgel

Johannes Linhard

A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.

Rotor blade with blade root contour having a straight portion provided in a concave contour portion

A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.

Method for machining a blade and a blade for a turbomachine

The invention refers to a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade having an outer surface having at least one circumferential web arranged thereon, at least one pocket recessed in the outer surface and a hardfacing provided on at least one edge of the shroud wherein a pocket recessed in the outer surface is arranged adjacent to the hardfacing and a side face of the pocket joins the supporting wall with a radius corresponding at least to the length of the shorter extension of the supporting wall and at most to 1.5 times the length of the larger extension of the supporting wall.

Blade for a turbomachine

A turbomachine having a flow channel () and a housing () which radially surrounds the flow channel, at least one sealing or lining element () being situated between the flow channel and the housing, at least one clamping ring () being provided, which is situated circumferentially around the flow channel and which is situated in such a way that it abuts at least one contact surface () of the at least one sealing or lining element ().

Clamping ring for a turbomachine

A fast response temperature probe which may be used for a method for measuring an instantaneous temperature of a periodically changing fluid flow within a gas turbine is proposed. The temperature probe includes a substrate and a resistive element arranged at a surface of the substrate. Therein, at least at a surface of the substrate contacting the resistive element, the substrate comprises an insulating material having a thermal product of less than 1.5 kJ/(mK sqrt(s)). The substrate or at least its surface is made from polyamide-imide such as for example fiber-reinforced Torlon&#xa9; 5030. The temperature probe may allow measurements of instantaneous local temperatures of very fast fluctuations of more than 50 kHz at high spatial resolutions of, e.g., less than 0.5 mm. The instantaneous temperature of a periodically changing fluid flow may be determined by correlating first and second sets of temperature measurements taking into account the periodicity of the periodically changing fluid flow.

Fast response temperature measurement within a gas turbine

A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel () in which guide vanes and rotor vanes are arranged. The housing structure has an inner wall () that delimits the flow channel and an outer wall () that is closed off vis-&#xe0;-vis the environment. A heat-protection plate () is arranged on the radial outside of the inner wall, and insulation () is arranged between the heat-protection plate and the outer wall. At least one cooling-air channel () is formed between the insulation and the radial inside of the outer wall, the cooling-air channel () having at least one air-guiding element () resting against the insulation.

Cooling-air guidance in a housing structure of a turbomachine

A gas turbine jet engine having a main flow channel and a housing structure which radially surrounds this main flow channel. A housing gas flow flows in the same direction as the main flow in the main flow channel, the housing structure having a flow conducting assembly. The flow of the housing gas flow to and/or along the main flow channel may be adjusted by adjusting a flow conducting sheet.

Growing community of inventors

Munich, Germany

Christian Eichler