Deutsches Zentrum Fuer Luft-und Raumfahrt E.v

Deutsche Forschungsanstalt Fur Luft-und Raumfahrt E.v.

Hermann Hald

Markus Ortelt

Oskar Haidn

Peter Winkelmann

Wolfgang Kitsche

Andreas Haberzettl

Michael Lezuo

Manfred Schlenger

The invention relates to a thrust chamber device comprising a thrust chamber with a thrust space having a first portion, a second portion adjacent thereto, and a third portion adjacent to the second portion, the thrust space being delimited in all three portions by an outer nozzle wall having an outer thrust space surface, which outer thrust space surface tapers in the first and second portion toward the third portion, widens in the third portion away from the second portion, and has a narrowest point at the transition from the second portion to the third portion, the first portion being delimited by an inner nozzle wall with an inner thrust space surface, which tapers toward the second portion, an annular combustion chamber being formed between the inner thrust space surface and the outer thrust space surface and extending over the first portion.

Thrust chamber device and method for operating a thrust chamber device

A sliding bearing device is proposed which comprises a bearing seating having a first sliding surface and a bearing body having a second sliding surface, wherein the bearing body is accommodated by the bearing seating and the first sliding surface and the second sliding surface face each other, wherein the bearing seating and/or the bearing body is made of an open-pore fiber composite material at least in a sliding region which forms the respective sliding surface.

Sliding bearing device

In order to provide a combustion chamber, in particular for a rocket engine, comprising a combustion area, an inner shell surrounding the combustion area, an outer shell surrounding the inner shell and coolant passages formed between the inner shell and the outer shell, the casing of which has an improved thermal stability and an increased mechanical bearing strength, it is suggested in accordance with the invention that the outer shell be formed from a fibrous ceramic material and the inner shell be formed from a fibrous ceramic material or from graphite.

Combustion chamber for rocket engine

To reduce the mass of internally or externally toothed gears, a thin metal ring having internal or external toothing is made and bonded to a ring of fibrous composite material. Furthermore, to make rings for gears having internal or external toothing, fabric hoses of fibrous composite materials having a fibre orientation of .+-.45.degree. are applied in a number of layers in the peripheral direction to the bottom and side flanks of a U-shaped groove-like depression of a rotating production device; the remaining free space in the interior of the applied fabric hose layers is filled with a unidirectionally wound roving, thereby forming an integral ring after the curing or hardening. Moreover, to make rings for gears having internal or external toothing, two thin-walled rings of fabric laminates serving as shear walls and having a fibre orientation of .+-.45.degree. for taking up the shear load and comprising carbon-fibre-reinforced plastics or plastics with other reinforcing fibres are adhesively bonded after the curing to a unidirectional winding applied between the annular shear walls of the rings for taking up the bending load.

Growing community of inventors

Leonberg, Germany

Hermann Hald