The subject matter of this specification can be embodied in, among other things, a lock apparatus that includes a latch hook having a catch at a first latch end, a first pivotal mount at a second latch end opposite the first latch end, and a second pivotal mount, a rotary actuator configured to selectably rotate a rotor shaft in a first rotary direction and in a second rotary direction opposite the first rotary direction, a rotor arm coupled to the rotor shaft at a first arm end and extending radially outward from the rotor shaft to a second arm end opposite the first arm end, and a link arm pivotably connected to the second arm end at a first link end, and pivotably connected to the second pivotal mount at a second link end opposite the first link end.

A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount.

The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.

A fan assembly for use in a sidewall of an animal house. The fan assembly includes an impeller, a motive force configured to rotate the impeller about a fan assembly axis, and a butterfly shutter. A shutter operation mechanism moves the butterfly doors of the shutter between the closed position and the open position in synchrony with an operating speed of the impeller. The shutter operating mechanism includes pushrods connected to the butterfly doors, and a linkage between the impeller and the second pushrods. The linkage includes at least one weight configured to rotate with the impeller about the fan assembly axis, wherein rotation of the at least one weight causes the linkage to exert a force on the pushrods to push the butterfly doors toward the open position when the impeller is rotating.

A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.

A gas turbine engine includes a fan driven by a fan shaft and retractable axial retainer of the shaft mounted on a stator element and movable between a first operational position and a second non-operational position. The retractable axial retainer may include a fluid supply configured for supplying at least one cavity with fluid. In some examples, the retractable axial retainer is mounted movably or slidingly so as to generate movement of the retractable axial retainer between the operation and non-operational positions.

Combustion sections and sealing systems for fuel ignition assemblies of gas turbine engine combustion sections are provided. For example, a sealing system comprises a ferrule positioned on an outer surface of a ceramic matrix composite (CMC) combustor liner an aperture defined in the CMC liner; a sleeve positioned within an adapter of the fuel ignition assembly such that an inner end portion of the sleeve is in contact with the ferrule, the sleeve having an end wall that forms an inner boundary of a cavity defined by the sleeve; and a biasing member positioned within the cavity. The biasing member extends between a bushing and the end wall of the sleeve. The biasing member continuously urges the sleeve into contact with the ferrule to seal the aperture against fluid leakage therethrough. The exemplary sealing system may be part of a fuel ignition assembly of a gas turbine engine combustion section.

A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

The present disclosure concerns a thrust reverser system for a turbojet engine and a method for unlocking a thrust reverser system. The thrust reverser system includes a movable cowl mounted on a nacelle of the turbojet engine that is displaceable between a closed position in which the thrust reverser system is inactivated and an open position in which the thrust reverser system is activated. The thrust reverser system includes a locking system having a first and second locking element mounted on the movable cowl and a fixed structure. The first and second locking elements lock and unlock relative to each other to lock the movable cowl on the fixed structure in the closed position. The locking system is shaped so that a controlled displacement of the movable cowl from its closed position to a reclosed position triggers unlocking of the first and second locking elements.

A gas turbine engine including a torque frame is provided. The torque frame includes an inner shroud defined circumferentially around the axial centerline, an outer shroud surrounding the inner shroud and defined circumferentially around the axial centerline, and a structural member extended along the radial direction and coupled to the inner shroud and the outer shroud. The torque frame is configured to rotate around the axial centerline.