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Rotary turbomachine having a transonic compressor stage

A rotary turbomachine, and particularly a turbojet engine, has a compressor stage that is especially adapted for operation in the transonic region. The compressor stage includes a rotor (1) having a hub (2) and a plurality of compressor blades (3) extending radially therefrom, and a stator having a plurality of compressor blades extending radially between a stator hub and a housing. The hub (2) of the rotor (1), and/or the hub of the stator, and/or the housing of the stator, have a circumferential surface contour that is not continuously rotationally symmetrical. Namely, a concave contour (K) is provided in the circumferential surface of the hub near the base of each blade (3) on the pressure side (PS) thereof, while the circumferential surface on the suction side (SS) of the base of each blade has a contour that is linear, slightly convex, convex/concave, or slightly concave to a lesser degree than the concave contour (K) on the pressure side of each blade. The hub contour slopes and transitions smoothly radially outwardly from the concave contour (K) on the pressure side to the flatter or convex contour on the suction side. In this manner, fluid flow velocities on both the pressure side and the suction side of each blade are reduced, especially under transonic operating conditions, and compression shock losses can be minimized.
Owner:MOTOREN UND TURBINEN UNION MUNCHEN GMBH

Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft

This is an improvement of the 1968 Trailing Rotor V/STOL aircraft (Ref. 1). Rotors are mounted on wing-tip pods which can be tilted from the vertical to the horizontal aft position. Rotors are then stopped in the axial-flow condition and indexed to an azimuth position, aft of the wing trailing-edge. Rotor blades are then folded forward (blade-tips upstream of rotor-hubs) and locked into grooves in the tip-pods.
The main improvements over Ref. 1 are: a smaller shift of center-of-gravity during transition to cruise mode, and an easier task of locking blades into the tip-pods.
The main feature of the autorotative aft rotor tilt is that a soft-inplane rotor can be used, which reduces rotor weight. The blade-folding axis is also the blade-flapping axis.
The autorotative mode is used frequently by helicopters during descent. It has been found to be a good, stable mode with rpm-stability. During aft tilt on the UFR, the rotors provide pitching stability to the airframe. During stopping of the rotor, the stability of the autorotating rotor eases the task of passing thru rotor resonance.
Also, the wing can be swept back, which is desirable for 400 kt. cruise speeds and can be used for external stores such as fuel and weapons.
Owner:SAMBELL KENNETH WILLIAM
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