Abstract: 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.

Abstract: An exemplary flow control device assembly for a turbomachine includes a flow control device configured to move between a first position and a second position. The flow control device in the first position forces more flow through a plurality of cooling holes than the flow control device in the second position. The plurality of cooling holes are upstream the flow control device relative a direction of flow through the turbomachine.

Abstract: 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.

Abstract: 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.

Abstract: A device for use with a gas turbine engine having an augmentor downstream includes a variable area mixing plane upstream of the turbine exhaust case for receiving core stream flow and fan stream flow. A swirl vane induces swirl in the fan stream flow and directs that stream flow to a mixing cavity to mix with the core stream and flow to the turbine exhaust case. A splitter proximate the swirl inducing vane diverts fan stream flow to an exhaust line to cool the fan case during operation of the augmentor.

Abstract: 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.

Abstract: A device for use with a gas turbine engine having an augmentor downstream includes a variable area mixing plane upstream of the turbine exhaust case for receiving core stream flow and fan stream flow. A swirl vane induces swirl in the fan stream flow and directs that stream flow to a mixing cavity to mix with the core stream and flow to the turbine exhaust case. A splitter proximate the swirl inducing vane diverts fan stream flow to an exhaust line to cool the fan case during operation of the augmentor.

Abstract: An exemplary flow control device assembly for a turbomachine includes a flow control device configured to move between a first position and a second position. The flow control device in the first position forces more flow through a plurality of cooling holes than the flow control device in the second position. The plurality of cooling holes are upstream the flow control device relative a direction of flow through the turbomachine.

Abstract: A gas turbine engine is provided, which includes a first compressor rotor coupled to a first shaft, a second compressor rotor downstream of the first compressor and coupled to a second shaft. A combustor is disposed downstream of the compressor rotors. A turbine is disposed downstream of the combustor and coupled to the second shaft. A gear is configured to be driven by the second shaft. The second shaft is configured for driving the first shaft through the gear, whereby the turbine drives the first compressor rotor at a different rotational speed than the turbine.

Abstract: A gas turbine engine is provided, which includes a first compressor rotor coupled to a first shaft, a second compressor rotor downstream of the first compressor and coupled to a second shaft. A combustor is disposed downstream of the compressor rotors. A turbine is disposed downstream of the combustor and coupled to the second shaft. A gear is configured to be driven by the second shaft. The second shaft is configured for driving the first shaft through the gear, whereby the turbine drives the first compressor rotor at a different rotational speed than the turbine.