Rolls-Royce Deutschland Ltd & Co. Kg

Fraunhofer-Gesellschaft Zur Foerderung Der Angewandten Forschung E.v.

Leistrits Turbinenkomponenten Remscheid Gmbh

Dan Roth-Fagaraseanu

Thomas Wunderlich

Karl Schreiber

Frank Brueckner

Alexander Schult

Lothar Knippschild

Peter Janschek

Susanne Schruefer

Lukas Schruefer

Mirko Riede

Yannick Cadoret

Frank BRÜCKNER

A method for manufacturing a part includes metal injection molding of metal powder mixed with a binder to produce individual components of the part as separately molded green compact sections which are then debindered to form brown compact sections. At least one of the brown compact sections is subjected to a pre-sintering process to undergo a first shrinkage. The pre-sintered brown compact section and a further brown compact section are joined together to form a multi-part brown compact which is subsequently subjected to a main sintering process, where the pre-sintered brown compact section undergoes less shrinkage than the further brown compact section to draw together and firmly connect the pre-sintered brown compact section and the further brown compact section.

Method for manufacturing a part by metal injection molding

A method for manufacturing a thermally deformable component for high thermal loads, includes: providing a first area of the component with a first metallic material by a generative laser process, or making the first area of the first metallic material; providing a second area of the component with a second metallic material by a generative laser process, or making the second area of the second metallic material; where at least one of the metallic materials is deposited by the generative laser process, and a ratio of a linear expansion coefficient &#x3b1;of the first metallic material and of a linear expansion coefficient &#x3b1;of the second metallic material is as: where x=0.5 to 1; T=mean operating temperature on a hot side; T=reference temperature; T=mean operating temperature on a cold side.

Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component

A component, especially contrived and designed for being used in a turbomachine, includes a high-temperature coating being arranged above a base of the component. The base has at least one structural element for connecting it to the high-temperature coating, with the cross-section of the at least one structural element having at least three different widths, i.e. a base width at the lower end of the at least one structural element, a center width above it, and a tip width above that, where on average the center width is greater than or equal to the base width, but less than four times the base width, in particular less than or equal to three times the base width.

Component and turbomachine having a component

A method for manufacturing thermally stressed engine components having a geometrically complex structure includes metal injection molding metal powder mixed with a binder to form green compacts of individual parts, which are debindered to form brown compact sections which are joined together to form a multi-part brown compact which are sintered in the assembled state. The brown compact sections have differing shrinkage properties in the sintering process, depending on the metal powder used, with a greater shrinking first brown compact section being automatically pressed against a second brown compact section during sintering. Connecting elements having positively engaging projections and recesses are provided at joining surfaces of the brown compact sections and have differing shrinkage such that during sintering of the assembled brown compact, the brown compact section with projections undergoes a greater shrinkage than the brown compact section with recesses.

Method for producing engine components with a geometrically complex structure

A method for the manufacture of highly loadable components by precision forging, e.g., of gas turbine compressor blades with different stress zones, initially provides for the production of a preform in a one-step forming operation, e.g., casting or sintering, with further deformable volume zones with a certain volume concentration in the highly loaded areas. The preform is subsequently finish-forged at a deformation rate which is limited by the respective volumes and is merely directed to the load and strength-specific recrystallization and structural requirements in the critical stress zones of the component.

Method for the manufacture of highly loadable components by precision forging

On an aircraft engine with a shroudless rotor wheel arranged in a flow duct, the flow duct includes a shroud segment () formed by a ceramic rubbing coating () which, while having good thermal conductivity, is highly-temperature resistant, attaches firmly to the metallic substrate () and is abradable by the tips of the rotor wheel to form a sealing gap as narrow as possible, this rubbing coating, owing to the lack of self-insulation, being coolable from a free side of the metallic substrate and, therefore, permitting for working gas temperatures occurring in high-pressure turbines and coating thicknesses sufficient for abrasion.

Shroud segment for a turbomachine

The invention relates to a method for producing components with a high load capacity from &#x3b1;+&#x3b3; TiAl alloys, especially for producing components for aircraft engines or stationary gas turbines. According to this method, enclosed TiAl blanks of globular structure are preformed by isothermal primary forming in the &#x3b1;+&#x3b3;&#x2212; or &#x3b1; phase area. The preforms are then shaped out into components with a predeterminable contour by means of at least one isothermal secondary forming process, with dynamic recrystallization in the &#x3b1;+&#x3b3;&#x2212; or &#x3b1; phase area. The microstructure is adjusted by solution annealing the components in the &#x3b1; phase area and then cooling them off rapidly.

Growing community of inventors

Stahnsdorf, Germany

Dan Roth-Fagaraseanu