Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Mtu Motoren-und Turbinen-union

Mtu Munuch, Gmbh

Burkhard Simon

Franz Joos

Hubert Grieb

Johann Berger

Martin Albers

Martin Rohlffs

Gas turbine combustor

A fuel feed method and apparatus for a turboramjet engine having a combustion chamber operable as a turbine engine afterburner and as ramjet engine combustion chamber is disclosed which features the concurrent injection of kerosene and hydrogen. At low Mach numbers, kerosene is the predominant fuel injected, while at growing speeds, hydrogen is injected in increasing proportions. This provides for a short combustion chamber length while minimizing the on-board fuel load and benefits especially small-size hypersonic aircraft.

Fuel feed method and apparatus for a turboramjet engine

A fuel injection device having three concentric streams of air for the atomization of fuel sprayed onto a sleeve by an injector facing into the sleeve. The inner and outer streams of air are imparted with swirl in opposite direction, while the central stream of air is free of swirl. The two inner streams of air atomize the fuel as a result of shear forces, while the outer stream of air forms a stable recirculation region in a combustion chamber into which the fuel injector device extends.

Fuel injection apparatus and associated method

A reverse flow combustion chamber includes an annular chamber enclosed between flame tube wall sections to which cooling air is so supplied from an outer annular channel acted upon with secondary air opposite the main flow direction in the flame tube in such a manner that the cooling air that it is blown out in the opposite flow direction film-like against an adjoining flame tube wall. For the purpose of a cooling film with extremely great travel length which is homogeneous over the entire circumference, the annular chamber is to be constructed flat elliptically in the combustion chamber longitudinal direction in such a manner that together with air catching or collecting bores which terminate radially and essentially tangentially in the downstream end of the annular chamber--in relation to the secondary flow--, a part of the supplied cooling air produces an independent recirculation vortex following the elliptical annular chamber contour which is provided for the equalization of the main cooling air flow supplied by way of the air collecting bores and deflected into the flame tube through about 90.degree. in the direction of the main flow.

Reverse flow combustion chamber, especially reverse flow ring combustion

Growing community of inventors

Rohrmoos, Germany

Burkhard Simon