A system for controlling the geometry of a variable geometry compressor. The system having: a mechanical linkage operable to vary the compressor geometry; a first fluid-powered actuator arranged to operate the linkage and configured to be powered by a pressurised supply of an incompressible fluid; and a second fluid-powered actuator arranged to operate the linkage and configured to be powered by a pressurised supply of a compressible fluid. Wherein the first and second actuators are further arranged to operate in combination on the mechanical linkage such that a first actuator force exerted by the first actuator on the mechanical linkage sums with a second actuator force exerted by the second actuator on the mechanical linkage.

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

A bushing apparatus includes: a housing with first and second ends, the housing having an outer bore passing therethrough from the first end to the second end, wherein the bore includes a reduced-diameter band located between the first and second ends; and a bushing received in the outer bore, the bushing having first and second ends and an inner bore passing therethrough from the first end to the second end of the bushing, wherein the bushing includes an outer surface having a reduced-diameter groove located between the first and second ends, wherein the band is received in the groove in a radially overlapping relationship, so as to block movement of the bushing relative to the housing.

A turbomachinery vane includes a vane body defining a longitudinal axis, a trunnion extending from the vane body and defining a pivot point for pivoting the vane body about the longitudinal axis, and a lock system operatively connected to the trunnion and configured to lock the vane body in a plurality of locked positions. A gas turbine engine includes a turbomachinery component including a row of actuated stators, wherein the actuated stator row includes a plurality of the turbomachinery vanes. A method of actuating a vane by aerodynamic loads includes moving the vane about a pivot point from a first position to a second position by a first set of by aerodynamic loads.

A vane arm connection system for a gas turbine engine includes a vane stem having a head with flat contact surfaces; a vane arm having a claw, the claw having opposed arms having inwardly facing surfaces engaging the flat contact surfaces of the head; and a torque transfer member having a body defining an opening for engaging the flat contact surfaces of the head of the vane stem, and at least one arm extending from the body to contact the claw, whereby load from torque is transferred away from the inwardly facing surfaces.

A bypass turbine engine including an inner casing, an inter-duct casing and an outer casing, wherein a primary duct is defined between the inter-duct casing and the inner casing, wherein a secondary duct is defined between the inter-duct casing and the outer casing wherein a rotary shaft includes, at the upstream end, a movable fan including radial blades of which the free ends face the outer casing of the turbine engine so as to compress an air flow at least in the secondary duct, wherein a plurality of variable-pitch radial stator vanes are mounted upstream of the movable fan, the variable-pitch vanes being configured to deflect the incident axial air, wherein the movable fan is configured to axially rectify the air deflected in the secondary duct, and the turbine engine not being provided with stator vanes in the secondary duct downstream of the movable fan.

A bushing includes a cylindrical bushing body with a lubricant aperture and a dry lubrication source. The bushing defines a main bushing bore therethrough along a longitudinal axis. The lubricant aperture is defined in the bushing body along an angle relative to the longitudinal axis. The dry lubrication source is disposed in the lubricant aperture. A variable vane system includes a cylindrical case, a plurality of vanes projecting radially inward from the case, and a plurality of bushings. Each vane includes a respective vane stem operatively connecting an end of each vane to the case. Each bushing is disposed on one of the respective vane stems between the vane stem and the case. The respective vane stem is disposed within the main bushing bore and each bushing is slidingly engaged with the case.

A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine that drives a low pressure compressor from the exhaust gas from the high pressure turbine, where the low pressure compressor supplies compressed air to the high pressure compressor. Variable inlet guide vane assemblies are used in the low pressure turbine and the low pressure compressor so that the high spool can operate at full power even during a hot day. The low spool is designed to operate at a higher speed than at the normal temperature conditions so that a high mass flow can be produced for the high spool during the hot day conditions.

A system for controlling an angular position of a component of an aircraft includes a component having a shaft that includes at least one magnet. The system also includes a housing configured to receive the shaft and including at least one coil configured to generate a magnetic field based on a current through the at least one coil.

A turbomachine includes a compressor including variable-pitch stationary vanes each extending radially between a rotary hub and a stationary casing surrounding this rotary hub, each variable-pitch vane including a blade having a base spaced apart by a first radial gap from a stationary wall of the casing, and a tip spaced apart by a second radial gap from a rotary wall of the rotary hub. The stationary wall of the casing or the rotary wall of the rotary hub includes at the blade a shape treatment arranged to channel an air leak passing through the corresponding gap.