Abstract: A surgical device comprising: a closure assembly including: (a) a latch unit comprising: (A) a hook latch, having a home position, (B) a forward bias constraint, (C) a rearward bias constraint, and (D) a bias member extending between the forward bias constraint and the rearward bias constraint so that the bias member has a pre-load when the hook latch is in the home position; (b) a movement unit including a bar that is movable relative to the latch unit so that the bar is movable in a prescribed motion into contact with the latch unit to create a locked state; and wherein the bar moves into contact with the hook latch driving the hook latch in a first direction, away relative to the home position, and then the hook latch is moved by the bar in a second direction relative to the home position, and a loading of the bias member is increased from the pre-load when the hook latch is moved in either the first direction away from the home position or the second direction away from the home position.

Abstract: Forceps including a housing, a first body, a second body and a drive shaft. The first body has a passageway extending therethrough. The drive shaft extending through the passageway and connected to the first body such that the first body and the drive shaft are slidable with respect to the housing to drive jaws located at a distal portion of the drive shaft between an open position and a closed position. The second body having a second passageway. The drive shaft extending through the second passageway such that the second body is guided by the drive shaft and is slidable relative to the first body and the drive shaft to displace a blade shaft between a retracted position and an extended position.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: A turbine frame for a gas turbine engine according to an example of the present disclosure includes a turbine case, a bearing support housing that defines a receptacle, and a tie rod preloaded in compression between the turbine case and the bearing support housing.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: A gas turbine engine includes a first rotor shaft and a second rotor shaft around the first rotor shaft. A knife edge seal is radially between the first rotor shaft and the second rotor shaft, and is connected to one of the first rotor shaft or the second rotor shaft. The knife edge seal is sized radially to form a gap between the knife edge seal and the other of the first rotor shaft or the second rotor shaft. A plurality of blades having a general airfoil shape is between the first rotor shaft and the second rotor shaft proximate the knife edge seal. The plurality of blades is connected to the first rotor shaft or the second rotor shaft, and a second gap is formed radially between the plurality of blades and the other of the first rotor shaft or the second rotor shaft.

Abstract: A turbine frame for a gas turbine engine according to an example of the present disclosure includes a turbine case, a bearing support housing that defines a receptacle, and a tie rod preloaded in compression between the turbine case and the bearing support housing.

Abstract: A gas turbine engine includes a first rotor shaft and a second rotor shaft around the first rotor shaft. A knife edge seal is radially between the first rotor shaft and the second rotor shaft, and is connected to one of the first rotor shaft or the second rotor shaft. The knife edge seal is sized radially to form a gap between the knife edge seal and the other of the first rotor shaft or the second rotor shaft. A plurality of blades having a general airfoil shape is between the first rotor shaft and the second rotor shaft proximate the knife edge seal. The plurality of blades is connected to the first rotor shaft or the second rotor shaft, and a second gap is formed radially between the plurality of blades and the other of the first rotor shaft or the second rotor shaft.

Abstract: A variable vane assembly for a gas turbine engine includes at least one synchronization ring, a plurality of variable vanes connected to the synchronization ring, a plurality of torque boxes disposed circumferentially about the synchronization ring, a drive ring coupled to each of the torque boxes such that the drive ring causes an approximately identical torque to be applied to the synchronization ring from the torque boxes simultaneously, and an actuator coupled to one of the plurality of torque boxes and operable to drive the drive ring through the torque box.

Abstract: A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.

Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.

Abstract: A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.

Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures that extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.

Abstract: A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve assembly also includes a second member having openings. The second member resides adjacent the first member to receive the cooling air from the first member. Finally, the valve assembly includes actuator for moving the first member from a first position, which allows a first flow rate of cooling air to pass through the openings, to a second position, which allows a second flow rate of cooling air to pass through the openings. The second flow rate is less than the first flow rate.

Abstract: A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve assembly also includes a second member having openings. The second member resides adjacent the first member to receive the cooling air from the first member. Finally, the valve assembly includes actuator for moving the first member from a first position, which allows a first flow rate of cooling air to pass through the openings, to a second position, which allows a second flow rate of cooling air to pass through the openings. The second flow rate is less than the first flow rate.

Abstract: The flaps of the C/D exhaust nozzle for a gas turbine engine are arranged to obtain synchronous movement relative to each other and the interconnecting fulcrum links are attached to a coaxially mounted combined piston/sync ring by an H-shaped link. One link from one convergent flap is connected to one of the fulcrum links and the adjacent convergent flap is connected to the same fulcrum link. The redundant synchronization provided by the H-shaped links and flap connections provide damping of the flap train. The fulcrum links are judiciously mounted between adjacent convergent flaps.

Abstract: A gap seal for convergent/divergent flap hinge ends to spaced disc and wall surfaces in a 2-D nozzle of a gas turbine engine is provided. The seal employs at least two cups resiliently mounted to the hinge ends, which cups independently translate axially and resiliently to contact the spaced surfaces at different or varying gaps to seal same. The translating cup seals of the invention thus maintain a constant seal in the gaps between the hinge ends and such surfaces at varying C/D hinge positions and varying operating conditions in the 2-D nozzle. That is, the cups independently maintain their seals across gaps as they expand or contract due to thermal changes as well as across gaps of different sizes.