Astrium Gmbh

Daimler-benz Aerospace Ag

Deutsche Aerospace Ag

Eads Space Transportation Gmbh

Astruim Gmbh

Joachim Kretschmer

Peter Bichler

G&uuml;nther Schmidt

Hans Immich

Extendible exhaust nozzle bell for rocket engine of aircraft or spacecraft includes a first part with smaller diameter fixedly arranged on motor of engine and a second part with larger diameter arranged in flexible manner with respect to first part. In a front stowed position, second part is located surrounding first part closer to the rocket motor and, in a rear operating position, first part is arranged further away from the rocket motor. A closed volume that can be acted on by a gaseous fluid causes an extension of the second part of the exhaust nozzle bell from the stowed position into the operating position. The closed volume is formed at least in part by a deformable rolling bellows arrangement coupled between the flexibly arranged second part of the exhaust nozzle bell and a fixed part of the rocket engine or of the aircraft or spacecraft.

Extendible exhaust nozzle bell for a rocket engine

A combustion chamber for a rocket engine expels a hot stream of gas and has a cooling device. The inner wall of the combustion chamber adjoins the cooling device and contains depressions formed in such a way that the stable outer layer of the stream of gas that forms in the proximity of the inner wall of the combustion chamber during operation of the combustion chamber is destabilized in the area of the depressions.

Rocket engine combustion chamber with enhanced heat transfer to cooling jacket

A regeneratively coolable nozzle for a rocket engine is formed by winding a tubular material ( ) onto a winding mandrel to produce a helical composite structure ( ), through which a coolant can flow during operation of the nozzle. The spiral composite structure ( ) is fixed temporarily and the fixed composite structure ( ) is removed from the winding mandrel. Then an inner heat resistant, load bearing layer ( ) is applied to the radially inner hot-gas facing surface (H) of the fixed composite structure ( ). The present nozzle is lightweight and withstands a high coolant pressure.

Method for producing a nozzle for a rocket engine

Device for supplying fuel for a rocket propulsion unit has a first and at least a second fuel circuit for respective different fuels. Each fuel is brought to an increased energy level by a pump and is supplied for combustion by way of injection elements. The first fuel is heated in cooling channels extending in a propulsion chamber wall before the fuel is supplied for combustion, and the first fuel is subsequently fed to at least the turbines assigned to the pumps. A heat exchanger is provided in which the fuel coming from the turbines is in a heat exchange with a fuel coming from a pump. A heat exchanger especially usable in the device for supplying fuel is provided.

Device for supplying fuel for a rocket propulsion unit and heat exchanger to be used in said device

A regeneratively coolable nozzle for a rocket engine is formed by winding a tubular material ( ) onto a winding mandrel to produce a helical composite structure ( ), through which a coolant can flow during operation of the nozzle. The spiral composite structure ( ) is fixed temporarily and the fixed composite structure ( ) is removed from the winding mandrel. Then an inner heat resistant, load bearing layer ( ) is applied to the radially inner hot-gas facing surface (H) of the fixed composite structure ( ). The present nozzle is lightweight and withstand a high coolant pressure.

Coolable nozzle and method for producing such a nozzle for a rocket engine

A fluidic nozzle which is flown through by a singular injection jet and which periodically deflects the injection jet. The nozzle has a nozzle channel, whose cross section is expanded in relation to the injection jet, and with control openings opening into the nozzle channel downstream close to the neck of the nozzle for injecting a control fluid that brings about the deflection of the jet. The nozzle channel has a channel cross section, which is two-dimensionally expanded in height and width in relation to the cross section of the jet, with a cross-section contour corresponding to the desired distribution cross section, and it is provided with a number of control openings. The control openings are arranged offset in relation to one another in the circumferential direction of the nozzle channel and are activated one after another in sequence to generate a jet movement rotating along the circumference of the nozzle channel.

Injection device

A jet engine having at least one combustion chamber with a propelling nozzle connected behind it, achieves in a constructionally simple manner and with a high propulsion effect a cross-sectional configuration of a hot gas flow duct bounded by the propelling nozzle that is highly variable with respect to the nozzle throat area as well as to the outlet area. The propelling nozzle contains a divergent lengthening part which is axially movable for the outlet-side expansion of the hot-gas flow duct. In the moved-out position, the lengthening part connects essentially in the corresponding shape to the divergent outlet end of the nozzle outer wall fixed to the engine and, in the moved-in condition, forms together with it an air outlet duct which encloses the fixed nozzle wall end in a ring-shaped manner and whose cross-section can be regulated. In the lower flying speed range, where the propelling nozzle lengthening is not required for the expansion of the outer contour of the hot gas flow duct, a secondary air injection takes place that is uniform along the whole outer circumference of the fixed nozzle end, and in addition, in the interior of the propelling nozzle, for the interior bounding of the hot gas flow duct, a mushroom-shaped central body is arranged which, with its largest cross-section can be axially adjusted between the plane of the smallest cross-sectional surface of the fixed nozzle outer wall and the outlet plane of the moved-out nozzle lengthening.

Growing community of inventors

Feldafing, Germany

Joachim Kretschmer