The invention relates to a control device for a turbocharger, comprising an exhaust gas conducting section through which fluid can flow and which includes a bypass duct for bypassing a turbine wheel that is rotatably arranged in the exhaust gas conducting section, and comprising an adjusting arm (3) for accommodating a valve element (2) provided for opening or blocking a flow cross-section of the bypass duct; the adjusting arm (3) is movably accommodated in the exhaust gas conducting section; furthermore, a flexible element (14) is provided at least for securing the valve element (2) in place on the adjusting arm (3). According to the invention, the flexible element (14) is designed to be retained radially and axially by the valve element (2).

Blade assemblies for gas turbine engines are described. The blade assemblies include a fan blade having a first tab extending from a leading edge and a second tab extending from a trailing edge. A first platform is affixed to a first side of the fan blade at the first and second tabs and a second platform is affixed to a second side of the fan blade at the first and second tabs. At least one first fastener is arranged to connect the first platform, the first tab, and the second platform at a first end and at least one second fastener is arranged to connect the first platform, the second tab, and the second platform at a second end.

A Laminar Inducing Apparatus (LIA) inducing laminar airflow to a turbine engine or a propulsion fan. The LIA produces turbulent-free airflow with a light aerospace structure that can replace single purpose structure in the wing or empennage. Laminar airflow to the propulsion fan or the turbine engine is ensured in a greater number of flight conditions and angles of attack. Active control of flight can be enhanced by the manipulating the turbulent boundary surface as a flight control surface. LIA simply reduces the risk of FOD or bird strike damage. In addition to the engineered, laminar benefits, LIA provides greater safety from ground ingested FOD and more silent vertical take-off and landing. In summary, LIA ensures laminar airflow and acoustic attenuation to a propulsion fan or a turbine engine for a greater number of flight conditions, angles of attack, and from ground ingested FOD during vertical takeoff and landing.

Embodiments of systems and methods for air recovery are disclosed. The diverted pressurized air may be used to supply a hydrostatic purge to the unutilized portion of a turbine engine fuel manifold circuit to ensure that exhaust gases from the utilized side of the fuel manifold circuit do not enter the portion of the alternative fuel manifold circuit rack. The assembly used to remove compressor section pressurized air may include a flow control orifice, line pressure measuring instrumentation, non-return valves, isolation valves and hard stainless-steel tubing assemblies. In some embodiments, a turbine compressor section diverter system may include a small air receiver used to increase the volume of air supplying the manifold to aid in potential pressure and flow disruptions from a turbine engine compressor section.

A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.

A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.

The present disclosure relates to a novel gas turbine system having applications, for example, in thermal power generation in an environmentally friendly manner. The multiloop gas turbine system may have multiple functional units each comprising a compressor, a regenerator, a combustion unit, and a turbine. Typically, exhaust flow of a turbine of a preceding loop may be routed to the combustion unit of the next loop, allowing mixing of exhaust flow with hot compressed air of the next loop, and the expanded exhaust from the turbine of the ultimate loop is fed back into the regenerators of each loop to recover exhaust heat.

The invention relates to a control device for a turbocharger, comprising an exhaust gas conducting section through which fluid can flow and which includes a bypass duct for bypassing a turbine wheel that is rotatably arranged in the exhaust gas conducting section, and comprising an adjusting arm (3) for accommodating a valve element (2) provided for opening or blocking a flow cross-section of the bypass duct; the adjusting arm (3) is movably accommodated in the exhaust gas conducting section; furthermore, a flexible element (14) is provided at least for securing the valve element (2) in place on the adjusting arm (3). According to the invention, the flexible element (14) is designed so as to be radially slidable in order to reduce adjustment forces.

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

A hybrid power system, includes at least one first isolation transformer having an input configured to be connectable to an output of a power supply; an energy storage system having at least one energy storage device and a power conversion system having at least one DC-to-AC converter connected to the at least one energy storage device; and at least one second isolation transformer configured as a step-up isolation transformer having an input connected to an output of the storage system.