Mtu Aero Engines Ag

Mtu Aero Engines Ag & Co. Kg

Norbert Schinko

Manfred Feldmann

Janine Sangl

Christian Eichler

Sebastian Kaltenbach

Stephan Klaen

Markus Schlemmer

Alexander Buck

Joachim Lorenz

Stefan Sasse

Stephan Klän

Sandra Muschkorgel

An apparatus for absorption of an impact energy from at least one blade fragment is disclosed. The impact energy acts on an element that is inserted into an opening in a turbo-machine. The opening passes radially through a housing section in a region of a row of rotating blades. The apparatus has a holder for holding the element in an ideal position and releasing the element beyond a preset maximum load and has a cage at a rear to secure the element in a radially outward-directed displacement. A turbo-machine having such an apparatus, as well as a method for multistage energy absorption, is also disclosed.

Apparatus for energy absorption, a turbo-machine and a method for energy absorption

A ceramic component for a turbomachine, the ceramic component () being configured to be destroyed in response to a contacting with another component () of the turbomachine that moves relative to the ceramic component (). A turbomachine component pairing and a turbomachine including such a ceramic component.

Ceramic component for a turbomachine

A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall () and an inner wall () defining the flow channel; and a hollow space () being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (); a movable wire element (slide ring seal) ('), which is adapted to rest against the contact faces (), being configured in the hollow space for purposes of the separation.

Slide ring seal

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 stator vane segment () of a fluid flow machine, having an upstream casing-side attachment () and/or a downstream casing-side attachment (), and a platform (). The attachments are provided on the platform (). The platform () has a first sealing section () and extends in the direction of flow beyond a connection region () that connects the rearward attachment () to the platform (). The first sealing section () that is located in a section () downstream of the connection region () has a first slot () which is continuous in the circumferential direction. The present invention also relates to a turbine having at least one stator vane segment ().

Stator vane segment of a fluid flow machine and turbine

The invention relates to a guide vane arrangement and a method for mounting a guide vane. The guide vane arrangement has at least one guide vane having a radially inner journal, which engages in a borehole of a bushing. The bushing is disposed in a borehole of an inner ring segment. The journal is connected to the bushing in a rotation-resistant manner and a slide mounting is provided between the bushing and the inner ring borehole. For mounting the guide vane in an inner ring segment, the journal of the guide vane is introduced into the borehole of the bushing. Further, the journal is fastened to the bushing in a rotation-resistant manner, and the bushing is slide-mounted with the inner ring segment. The slide mounting is conducted prior to or simultaneously with or after the fastening of the journal to the bushing in a rotation-resistant manner.

Guide vane arrangement and method for mounting a guide vane

A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook.

Sealing of the flow channel of a turbomachine

A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening.

Seal carrier attachment for a turbomachine

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

Norbert Schinko