A spring compression device comprises a spring sleeve configured to receive a spring; a spring adjustment member provided on and engaged with the spring sleeve and configured to abut a spring mounted on the spring sleeve, wherein the spring sleeve and spring adjustment member define an operating length (L) of the spring compression device, and the spring adjustment member is configured to be moved relative to the spring sleeve to adjust the operating length of the spring compression device; and at least one blocking component for blocking movement between the spring sleeve and the spring adjustment member.

There is described a method and system for in-flight start of an engine. The method comprises rotating a propeller; generating electrical power at an electric generator embedded inside a propeller hub from rotation of the propeller; transmitting the electrical power from the electric generator to an engine starter mounted on a core of the engine via an electric power link; and driving the engine with the engine starter to a sufficient speed while providing fuel to a combustor to light the engine to achieve self-sustaining operation of the engine.

A ram air turbine (RAT) system can include a generator configured to be turned by a RAT and to output an alternating current (AC) power, a generator control unit (GCU) configured to control an output of the generator, a rectifying module configured to rectify the AC power into a direct current (DC) power, and a DC load configured to receive the DC power from the rectifying module. The DC load can be operatively connected to the GCU to provide feedback from the DC load to the GCU. The GCU can be configured to control the output of the generator as a function of the feedback to prevent stalling of the RAT and/or doorbelling current and/or voltage in the system caused by disconnecting the generator from the DC load.

A seal plate for a rotary machine includes a hub centered on a central axis of the rotary machine, a disk portion extending radially outwards from the hub, and a variable lattice structure in an interior of the seal plate. The variable lattice structure includes a first region of the seal plate having a first lattice structure, and a second region of the seal plate having a second lattice structure. The second lattice structure bf the second region is denser than the first lattice structure of the first region. The second region is a deflection region, a stress region, or an energy containment region of the seal plate.

An engine system is provided that includes a compressor section, a combustor section, a turbine section, a flowpath and a flow regulator. The combustor section includes a combustion chamber. The flowpath extends sequentially through the compressor section, the combustor section and the turbine section. The flow regulator is configured to open the flowpath between the compressor section and the combustion chamber during a first mode of operation. The flow regulator is configured to at least substantially close the flowpath between the compressor section and the combustion chamber during a second mode of operation.

A ram air turbine release system including a turbine defining a rotational axis including at least one notch therein for receiving a plunger to prevent rotation of the turbine mechanically by moving between a first position and a second position, and a first bearing system contacting at least a portion of an outer surface of the plunger configured to reduce friction produced when the plunder moves between the first positon and the second position.

A strut system for a RAT includes a strut body, a strut first end is connected to the aircraft and rotate about a first axis, a strut second end is spaced apart from the strut first end by the strut body and is connected to the RAT turbine generator unit, the strut has a strut conduit extending from the strut first end toward the strut second end; and a damper rod that includes a rod body and disposed within the strut conduit, the damper rod having a rod first end that is fixed within the strut conduit at the strut first end, and a rod second end that is spaced apart from the rod first end by the rod body and is located intermediate the strut first end and the strut second end, wherein the rod second end moves along a second axis that is parallel to the first axis.

An actuator release mechanism comprising an axially moveable member such as a piston biased in a first axial position by a bias spring and driven to a second axial position by an actuation means such as a solenoid arranged in substantially the same axis as the axially moveable member.

A hydraulic damping device includes a housing defining a fluid inlet and a fluid outlet, a damping plate disposed within the housing, the damping plate including a plurality of damping holes defined therethrough and positioned to allow fluid communication between the fluid inlet and the fluid outlet, and a blocking member disposed within the housing and configured to rotate relative to the damping plate to progressively block the damping holes.

A ram air turbine is presented that includes a turbine having a blade and a turbine shaft, a strut removably coupled to the turbine, wherein the strut has a gearbox section and a drive section, a turbine shaft with a bevel gear oriented perpendicularly to the turbine shaft and positioned within the gearbox section of the strut, a driveshaft coupled to the generator and positioned within the drive section of the strut, and a pinion gear that engages with the bevel gear, wherein the pinion gear is secured to the driveshaft by a spanner nut, wherein the pinion gear utilizes a key configured to interact with the keyed joint of the driveshaft. The pinion gear is supported by a pinion bearing that may be press fit onto the pinion gear and by one of the generator bearings.