Abstract: A turbomachine comprises a hub and a plurality of blade elements. Each blade element comprises a blade, a platform, and a tang. The plurality of blade elements are arranged circumferentially around the hub, each interlocking or affixed with an adjacent blade element and retained in position by the hub. Each blade elements formed from a single stamped blank to provide an inexpensive method of manufacture, for low cost turbomachinery.

Abstract: A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.

Abstract: An integrated propulsion system comprising at least two gas turbine engines, at least one fan, and a transmission assembly coupling the at least two gas turbine engines to the at least one fan wherein the at least two gas turbine engines are disposed within a main body of an airframe comprising the main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.

Abstract: A high-Mach engine includes a gas turbine core, an inlet assembly, and a transmission. The inlet assembly including an inlet turbine and the transmission configured to couple the inlet turbine and a core turbine of the gas turbine core cooperate to control air moving through the high-Mach engine.

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: 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 inlet assembly for a high-mach engine includes a gas turbine core, an inlet turbine, and a core-flow director. When in a closed position, the core-flow director forces air to interact with the inlet turbine before entering the gas turbine core.

Abstract: A turbomachine comprises a hub and a plurality of blade elements. Each blade element comprises a blade, a platform, and a tang. The plurality of blade elements are arranged circumferentially around the hub, each interlocking or affixed with an adjacent blade element and retained in position by the hub. Each blade elements formed from a single stamped blank to provide an inexpensive method of manufacture, for low cost turbomachinery.

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: A system for directing the flow of a fluid which comprises a channel for containing the fluid; an articulating vane positioned within the channel for directing the flow of the fluid, the vane comprising a fixed segment rigidly connected to the channel and a first moveable segment operably connected to the fixed segment by a first hub, the first hub configured to allow relative articulation between the segments; an actuator member operably connected to the moveable segment to articulate the moveable segment about the first hub; and wherein the vane further comprises a second moveable segment operably connected to the vane by a second hub, wherein the actuator member articulates the first and second moveable segments by applying a single moment to the first hubs.

Abstract: A composite rotatable assembly for an axial flow compressor comprises a spool having a plurality of blade assemblies arranged in stages on the spool and attached thereto by a wound band. Each blade assembly comprises a blade and a base, with the base having a forward tang extending axially forward of a leading edge of the blade and an aft tang extending axially aft of a trailing edge of the blade. The band is wound over at least a portion of the forward and aft tangs of the plurality of blade assemblies to hold the blade assemblies to the spool under centrifugal loading. An abradable layer may be added over the wound band.

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: 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: 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.

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

Abstract: A turbomachine comprises a hub and a plurality of blade elements. Each blade element comprises a blade, a platform, and a tang. The plurality of blade elements are arranged circumferentially around the hub, each interlocking or affixed with an adjacent blade element and retained in position by the hub. Each blade elements formed from a single stamped blank to provide an inexpensive method of manufacture, for low cost turbomachinery.

Abstract: A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.

Abstract: A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.

Abstract: A composite turbomachine comprises a hub comprised of fiber and resin and a plurality of blade assemblies. Each blade assembly comprises a blade, a base, and a tang. The plurality of blade assemblies are arranged circumferentially around the hub, each interlocking with an adjacent blade assembly and retained in position by the hub and a band overwrapping the respective tang of each of the plurality of blade assemblies.