Abstract: First and second axially adjustable rings, each ring having a front and rear end, function together in a telescopic manner for blocking and exposing an annular inflow surface in a combined turboramjet engine. The annular inflow surface is blocked by the device when a basic engine and fan are inoperative to direct ram air through a ring duct to a ramjet combustion chamber. When in an inoperative position, the first and second rings are moved above one another into an intermediate housing with their front ends and a flow divider forming a lug edge and, when in a blocking position of the annular inflow surface, each ring is moved out of the intermediate housing to a different degree. The first ring is moved out farthest and has an end surface mating with the local oblique contour of the front wall.

Abstract: A turbine ramjet engine is provided which has a ram pressure air duct shrouding the basic turbo-engine in an annular manner. When the ramjet operation is disconnected, this ram pressure air duct, while at the same time intake air is released into the basic engine, is blocked off with respect to the supply of ram pressure air. It is provided to unblock or block an intake-side air inflow cross-section of the basic engine by the axial adjustment of a drop-shaped body with respect to a flow divider. A ring slide is provided which is axially adjustable to always be opposite this body which blocks the ram pressure air duct when the inflow cross-section of the basic engine is unblocked and unblocks it when the inflow cross-section is blocked. In addition, the ram pressure air duct is to be widened in a multicornered manner in the upstream direction at the level of a blocking zone caused by a local overtravelling of countersurface of the mentioned body and the ring slide.

Abstract: A fiber-structured [guide] rotor blade is connected to a metallic rotor in that a supporting core, around which fiber layers are wound, and which extends over the whole blade width, has radial webs in its central section. This results in a form-locking fastening which utilizes the characteristics of the fiber materials.

Abstract: A bearing arrangement between shafts of a fluid flow engine, especially including a high pressure turbine and/or a lower pressure turbine, includes a damping gap for the controllable formation of a carrier film between an outer bearing race and a bearing mounting member. A damping fluid is introduced into the damping gap of a squirrel cage bearing. The outer bearing race rotates with an r.p.m. corresponding to that of the high pressure turbine shaft r.p.m. or to that of the low pressure turbine shaft r.p.m. The damping fluid is supplied through a channel passing through the low pressure turbine shaft and into an entrapment chamber just at the entrance end of the damping gap, whereby the rotation of the entrapment chamber compresses the damping fluid by a centrifugal force into the damping gap.