The invention relates to an axial flow turbine and method of operating thereof. The turbine comprises a last stage of rotating blades located towards a downstream end of the turbine having a distal region at an end of the airfoil of the blades. A monitoring control system has at least one sensor in the distal region of at least one last stage blade for measuring at least one physical property of the airfoil and a control element that is capable of influencing at least one physical property of the distal region. The control system further includes a controller that adjusts the control element based on at least measured physical property so by controlling the at least one physical property.

A securing device with multiple securing segments for the axial retaining of at least one rotor blade at a disc wheel a rotor device of a continuous-flow machine. The securing device has at least one effective area that is arranged in a radially inner area and that in the mounted state is embodied for acting together with the disc wheel in the axial direction of the rotor device, and a further effective area that is arranged in a radially outer area at a securing segment and that in the mounted state is embodied for acting together with at least one rotor blade in the axial direction of the rotor device. At least one securing segment has an additional effective area, that in the mounted state is embodied for acting together with the disc wheel in the radial direction of the rotor device. What is further described is a rotor device with such a securing device.

A windage shield system is provided. The system includes an annular cavity having an inlet end and an outlet end. The annular cavity is configured to direct a flow of cooling fluid from the inlet end to the outlet end. The system also includes a source of a flow of cooling fluid coupled in flow communication with the annular cavity. The annular cavity is bounded by a stationary component and a rotating component, and the rotating component introduces heat into the annular cavity by windage effects. The system also includes a cooling channel coupled in flow communication with the outlet end, and a first windage shield extending from the outlet end towards the inlet end within the annular cavity.

A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.

A gas turbine engine is provided that includes compressor and combustor sections, inner and outer casings, an annular diffuser, an inner diffuser casing, a heat exchanger, and an HPT stator vane stage. An annular combustor is disposed radially inward of the outer casing and has inner and outer radial wall structures. The outer casing and the combustor outer radial wall structure define a diffuser OD flow path. The annular diffuser directs diffuser gas towards the combustor section. The inner diffuser casing is disposed radially inward of the annular combustor and spaced apart from the combustor inner radial wall structure. The inner casing is disposed radially inward of and spaced apart from the inner diffuser casing. The inner diffuser casing and the inner casing define an ICF passage. The heat exchanger is configured to produce intercooler gas. Intercooler gas is directed through the ICF passage and into the HPT stator vanes.

An intentional fluid manipulation apparatus (IFMA) assembly with a first thrust apparatus that imparts a first induced velocity to a local free stream flow during a nominal operation requirement. The first thrust apparatus creates a streamtube. A second thrust apparatus is located in a downstream portion of the streamtube. The second thrust apparatus imparts a second induced velocity to the local free stream flow. The second induced velocity at the location of the second thrust apparatus has a component in a direction opposite to the direction of the first induced velocity at the location of the second thrust apparatus.