Abstract: An expandable exhaust cone assembly is described which is able to move from a collapsed position to an expanded position.

Abstract: A compressor for use in a gas turbine engine is disclosed herein. The compressor includes a case, vanes, and a vane actuation system. The vanes are arranged circumferentially adjacent to one another about a central axis inside the case and each one of the vanes is configured for rotation about a vane axis generally perpendicular to the central axis. The vane actuation system is configured to cause rotation of at least one of the vanes about the vane axis.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along an outer surface of an engine case of a gas turbine engine. The distribution manifold may include a plurality of outlets defined on the distribution manifold to direct a thermal fluid received by the distribution manifold onto an outer surface of the engine case of the gas turbine engine. The system may further include a variable blower configured to blow the thermal fluid into the distribution manifold at a flow rate controlled by the variable blower. The flow rate through the variable blower may be adjustable over a range of non-zero target flow rates.

Abstract: A disc for use in a turbine rotor is provided including a hub, a plurality of webs extending outwardly from the hub, and a plurality of rims. Each of the plurality of webs are separate from each other by a gap. Each rim is positioned at an outward end of one of the webs. Each rim is configured to receive a respective set of turbine blade.

Abstract: A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.

Abstract: An apparatus and methods for controlling tip clearance in gas turbine engines may be provided. The apparatus and methods may include situating fins on a surface of a turbine case included in a turbine section of the gas turbine engine. The fins may act as a means for maintaining tip clearance by, for example, controlling the thermal expansion of the turbine case. The turbine case may shroud turbine blades, and the turbine blades may include tips at a radial end of the blades. During operation of the gas turbine engine, the clearance between the tips and the turbine case is desirably as small as possible while avoiding contact in order to optimize efficiency of the gas turbine engine.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along an outer surface of an engine case of a gas turbine engine. The distribution manifold may include a plurality of outlets defined on the distribution manifold to direct a thermal fluid received by the distribution manifold onto an outer surface of the engine case of the gas turbine engine. The system may further include a variable blower configured to blow the thermal fluid into the distribution manifold at a flow rate controlled by the variable blower. The flow rate through the variable blower may be adjustable over a range of non-zero target flow rates.

Abstract: A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.

Abstract: A radial turbine rotor for a gas turbine engine may be provided. The radial turbine rotor may include a hub and a plurality of radial turbine blades. The hub may include an outer surface. The outer surface of the hub may include a plurality of discrete bonding surfaces. The radial turbine blades may be bonded to a corresponding one of the discrete bonding surfaces of the hub. Each of the radial turbine blades may be separate and distinct from the other radial turbine blades that are bonded to the radial turbine rotor. The corresponding discrete bonding surface may include a planer surface to receive the radial turbine blade.

Abstract: A compressor shroud assembly in a turbine engine having a dynamically moveable shroud for encasing a rotor segment. The rotor segment comprises a bladed disc. The compressor shroud assembly maintains a clearance gap between the shroud and the blade tips of the bladed disc. The assembly comprises a static compressor casing, a shroud mounted to the casing, and an actuator mounted to the casing. The shroud comprises a flowpath boundary member spaced radially inward from the casing, the flowpath boundary member being moveable relative to the casing in a radial direction. The actuator is coupled to the shroud for effecting the movement of the flowpath boundary member.

Abstract: An expandable exhaust cone assembly is described which is able to move from a collapsed position to an expanded position.

Abstract: A compressor for use in a gas turbine engine is disclosed herein. The compressor includes a case, vanes, and a vane actuation system. The vanes are arranged circumferentially adjacent to one another about a central axis inside the case and each one of the vanes is configured for rotation about a vane axis generally perpendicular to the central axis. The vane actuation system is configured to cause rotation of at least one of the vanes about the vane axis.

Abstract: An axial compressor comprises a plurality of compressor stages positioned axially adjacent one another within a casing. Each of the plurality of compressor stages comprise a rotor segment and a banded stator segment positioned axially adjacent the rotor segment. An annulus is formed between the casing and an outer flowpath ring of the stator segment. A vane of each stator segment comprises a member extending into the annulus.

Abstract: An axial flow compressor comprises a tubular casing which encases a rotatable shaft, a pair of rotor segments coupled to the rotatable shaft and each comprising a bladed disc, and a banded stator segment disposed between the pair of rotor segments and comprising a plurality of stator vanes extending between an outer flowpath ring and an inner flowpath ring. A method of assembling an axial flow compressor comprises installing a rotor segment inside a tubular compressor casing, installing a vane segment adjacent the installed rotor segment, and repeating the steps of installing a rotor segment and vane segment until a desired number of rotor segment and vane segment pairs are installed.

Abstract: An axial compressor comprises a plurality of compressor stages positioned axially adjacent each other within a casing. Each of the plurality of compressor stages includes a rotor segment and a banded stator segment. An annulus is formed between the casing and an outer flowpath ring of the banded stator segment. A pathway may be provided that establishes an air flowpath between the annulus and another annulus formed by an adjacent stage.

Abstract: An axial compressor comprises a plurality of compressor stages positioned axially adjacent within a casing. Each of the plurality of compressor stages comprise a rotor segment and a banded stator segment positioned axially adjacent the rotor segment. An annulus is formed between the casing and an outer flowpath ring of the stator segment. A pathway is provided that establishes an air flowpath between an entry pathway in a first stage and an exit pathway in a second stage.

Abstract: According to one aspect, a clutch mechanism includes a control member. The control member is adapted to receive motive power and includes a first dry clutch member and a first viscous clutch member. The clutch mechanism further includes an output member that includes a second dry clutch member and a second viscous clutch member. The first and second dry clutch members form a dry clutch and the first and second viscous clutch members form a viscous clutch. The clutch mechanism further includes an actuation arm coupled to at least one of the control and output members. The actuation arm is selectively controllable to effect relative movement of the control and output members such that one of the dry and viscous clutches is selectively engaged.