Abstract: The invention relates to a turbine wheel arrangement for a gas turbine comprising two successive turbine wheels (18, 20) rotating in opposite directions, wherein the first turbine wheel (18) comprises flow channels (42) of a Laval cross-sectional shape, distributed over the circumference and having radially inner gas inlets (43) and radially further out gas outlets (45), in each case with a substantially tangential flow direction component, wherein the gas outlets (45) act an the second axially or radially acting turbine wheel (20) in the direction of flow. This has the effect that the thermal energy and compressive energy of the gas at the nozzle inlet is largely converted into flow energy at the outlet of the turbine stage. The rotational speeds of the two rotors coupled to the turbine wheels can be set as desired, allowing the operational states of the two systems to be optimally set without adjusting systems.

Abstract: The invention relates to a blade for a turbo machine with a blade; the outer surface of the blade in contact with fluid is formed of an elastic cover which surrounds a supporting structure; a flowable inflating medium is located between the elastic cover and the supporting structure; measures are taken in order to facilitate an overflowing of the inflating medium from the one side of the blade to the other side.