An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a second rail, which collectively define a diaphragm cavity. The first rail defines a first rail aperture. A manifold is positioned in the diaphragm cavity. The manifold and the diaphragm collectively define a manifold chamber in fluid communication with the first rail aperture. A tube extends through the internal passage defined by the airfoil and into the diaphragm cavity. The tube is in fluid communication with the manifold chamber. Compressed air flows through the tube into the manifold chamber and exits the chamber through the first rail aperture.

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes an axially elongated ring. In the open position, the radially outer surface of the ring is spaced from a tapering inner surface of the air inlet so that air can flow in an annular passage between the tapering surface and the ring. In the closed position, the ring abuts the tapering surface to close off the annular passage, whereby the effective inlet diameter is then defined by the inner diameter of the ring at its trailing edge. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes an axially elongated ring. In the open position, the radially outer surface of the ring is spaced from a tapering inner surface of the air inlet so that air can flow in an annular passage between the tapering surface and the ring. In the closed position, the ring abuts the tapering surface to close off the annular passage, whereby the effective inlet diameter is then defined by the inner diameter of the ring at its trailing edge. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

The present disclosure relates to systems and methods that are useful in control of one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants, methods of starting power production plants, and methods of generating power with a power production plant wherein one or more control paths are utilized for automated control of at least one action. The present disclosure more particularly relates to power production plants, control systems for power production plants, and methods for startup of a power production plant.

The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide systems and ways for improving the life and reducing start-up time necessary for bringing gas turbine engines online and up to full power.

The invention relates generally to gas turbine engines used for electrical power generation. More specifically, embodiments of the present invention provide systems and ways for improving the life and reducing start-up time necessary for bringing gas turbine engines online and up to full power.

The invention relates to a method for monitoring the operating state of an overpressure valve of a turbine engine, the turbine engine comprising a fluid circuit, at least one pressure sensor for the fluid in the fluid circuit, a temperature sensor for the fluid in the fluid circuit, said overpressure valve being configured to limit the maximum fluid pressures in the fluid circuit, and the method comprising the following steps:—(E2) determining an opening or closing indicator of the overpressure valve on the basis of the change in the fluid pressure over time;—(E3) determining an operating state of the valve as a function of a fluid threshold temperature and of the determined opening or closing indicator of the overpressure valve.

A highly efficient gas turbine engine is a system wherein the fan of the gas turbine engine is driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.

An exhaust-gas turbocharger having a compressor with a compressor wheel, a turbine with a turbine wheel, a shaft on which the compressor wheel and the turbine wheel are arranged, a control rod for actuating an adjustment apparatus of the exhaust-gas turbocharger, and an actuator for moving the control rod. A damping apparatus with an elastic element is fixedly connected to the control rod and projects in two opposite directions from the control rod.

An exhaust-gas turbocharger having a compressor with a compressor wheel, a turbine with a turbine wheel, a shaft on which the compressor wheel and the turbine wheel are arranged, a control rod for actuating an adjustment apparatus of the exhaust-gas turbocharger, and an actuator for moving the control rod. A damping apparatus with an elastic element is fixedly connected to the control rod and projects in two opposite directions from the control rod.