Abstract: A system and method are provided for reducing vibrations and loads in one or more rotor blades on a rotor hub of a wind turbine when the rotor hub is in a locked or idling condition. A mass damper is attached at a fixed location on one or more of the rotor blades and is maintained on the rotor blades during the locked or idling condition of the rotor hub. The mass damper includes a movable mass component that is responsive to changes in the vibrations or oscillations induced in the rotor blades during the locked or idling condition of the rotor hub.

Abstract: An example compressor includes a casing having a main portion and an outer skirt collectively defining an annular plenum, an outlet guide vane coupled to the main portion, an actuator mounted outside the outer skirt, and a linkage coupled to the actuator and the outlet guide vane through the annular plenum.

Abstract: An example compressor includes a casing having a main portion and an outer skirt collectively defining an annular plenum, an outlet guide vane coupled to the main portion, an actuator mounted outside the outer skirt, and a linkage coupled to the actuator and the outlet guide vane through the annular plenum.

Abstract: A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.

Abstract: A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine within a nozzle segment comprising an outer and inner band and at least one vane extending between the outer and inner band. The outer band includes a forward and aft cavity. The apparatus comprises a forward impingement baffle located within the forward cavity comprising a forward cooling chamber and an aft impingement baffle located within the aft cavity comprising an aft cooling chamber. Cooling air introduced into the forward cooling air chamber passes through impingement holes of the forward impingement baffle into a forward impingement chamber then passes through an aperture to the aft cooling air chamber, and then passes through the impingement holes of the aft impingement baffle into an aft impingement chamber.

Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.

Abstract: A turbine nozzle includes radially inner and outer bands integrally joined to opposite ends of an airfoil. The outer band has forward and aft hooks extending radially outwardly at axially opposite ends. And the hooks have different prechorded circumferential curvatures.

Abstract: A turbine nozzle includes radially inner and outer bands integrally joined to opposite ends of an airfoil. The outer band has forward and aft hooks extending radially outwardly at axially opposite ends. And the hooks have different prechorded circumferential curvatures.