A particle separator system for a turbine engine having an engine inlet. The particle separator system includes an inlet particle separator located within the engine inlet and configured to remove particles from an incoming airflow. The particle separator system also includes a barrier filter located within an enclosure of the turbine engine downstream of the inlet particle separator, the barrier filter being configured to intercept particles not scavenged by the inlet particle separator.

A fitting for forming a double-walled tube includes an inner fitting having a first inner weld lip, a second inner weld lip, and an inner body extending from the first inner weld lip to the second inner weld lip and having an outer surface with a first threading. The fitting also includes an outer fitting having a first outer weld lip, a second outer weld lip, and an outer body extending from the first outer weld lip to the second outer weld lip and having an inner surface with a second threading that is configured to mate with the first threading.

A jet engine screen assembly for protecting a jet engine from debris includes a mounting ring which forms a closed loop thereby facilitating the mounting ring to be mounted to an intake of a jet engine. A grate is hingedly disposed on the mounting ring. The grate is comprised of a plurality of intersecting members that are arranged to define a plurality of holes to facilitate air to pass through the grate. The grate is comprised of a rigid material to inhibit debris from entering into the jet engine. The grate is positionable in a closed position has the grate covering the intake of the jet engine. Conversely, the grate is positionable in an open position having the grate being displaced from the intake of the jet engine.

A jet engine screen assembly for protecting a jet engine from debris includes a mounting ring which forms a closed loop thereby facilitating the mounting ring to be mounted to an intake of a jet engine. A grate is hingedly disposed on the mounting ring. The grate is comprised of a plurality of intersecting members that are arranged to define a plurality of holes to facilitate air to pass through the grate. The grate is comprised of a rigid material to inhibit debris from entering into the jet engine. The grate is positionable in a closed position has the grate covering the intake of the jet engine. Conversely, the grate is positionable in an open position having the grate being displaced from the intake of the jet engine.

In one embodiment, a system includes an inlet grid configured to reduce distortion of an incoming airflow. The system may also include a vibration device coupled to the inlet grid and a controller communicatively coupled to the vibration device. The controller may transmit a vibration signal to the vibration device causing the vibration device to vibrate the inlet grid such that the inlet grid resonates at a natural frequency inducing a mode shape in the inlet grid. The mode shape may break up and prevent ice on the inlet grid.

In one embodiment, a system includes an inlet grid configured to reduce distortion of an incoming airflow. The system may also include a vibration device coupled to the inlet grid and a controller communicatively coupled to the vibration device. The controller may transmit a vibration signal to the vibration device causing the vibration device to vibrate the inlet grid such that the inlet grid resonates at a natural frequency inducing a mode shape in the inlet grid. The mode shape may break up and prevent ice on the inlet grid.

A method for inhibiting particulate ingress in a combustion system includes acquiring particulate ingress data, determining a probable particulate ingress location on an air inlet of the combustion system in dependence upon the particulate ingress data, and deploying a filter screen at the determined probable particulate ingress location to inhibit particulate ingress at the determined probable particulate ingress location.

A method for inhibiting particulate ingress in a combustion system includes acquiring particulate ingress data, determining a probable particulate ingress location on an air inlet of the combustion system in dependence upon the particulate ingress data, and deploying a filter screen at the determined probable particulate ingress location to inhibit particulate ingress at the determined probable particulate ingress location.

A filter system and clamp system for a gas turbine air inlet uses a single clamp system that allows for securing in place both a first element and a second element on the grid of the gas turbine air inlet. The clamp system can be released to allow for services of the first filter element, while the second filter element remains in sealing engagement with the grid.

A segmented augmented turbine assembly for generating electricity from a fluid in motion, the assembly comprising a segmented annular ducted channel extending between an inlet receiving the fluid and an outlet, the channel comprising a convergent accelerating the fluid, a segmented turbine-rotor section comprising blades and guide vanes rotating about a central shaft coupled to a generator, and a diffuser section configured to decelerate the fluid, wherein the channel comprises solid inserts attached to an outside face of the turbine-rotor section, the flow stream passing through open flow-through segments positioned between the solid inserts.