An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.

An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

An asymmetric inlet particle separator for a gas turbine engine includes an inlet having a first cross-sectional shape, and a duct downstream of the inlet. The duct includes a bend upstream from a splitter, a scavenge branch and an engine airflow branch. The splitter is outside of a line of sight from the inlet and the splitter separates the scavenge branch from the engine airflow branch. The asymmetric inlet particle separator includes an annulus downstream of the engine airflow branch configured to be coupled to the gas turbine engine. The annulus has a second cross-sectional shape, and the engine airflow branch transitions from the first cross-sectional shape to the second cross-sectional shape.

An asymmetric inlet particle separator for a gas turbine engine includes an inlet having a first cross-sectional shape, and a duct downstream of the inlet. The duct includes a bend upstream from a splitter, a scavenge branch and an engine airflow branch. The splitter is outside of a line of sight from the inlet and the splitter separates the scavenge branch from the engine airflow branch. The asymmetric inlet particle separator includes an annulus downstream of the engine airflow branch configured to be coupled to the gas turbine engine. The annulus has a second cross-sectional shape, and the engine airflow branch transitions from the first cross-sectional shape to the second cross-sectional shape.

A method for supplying air to an engine of an aircraft via an air supply system of the aircraft. A dynamic air intake vent of the system can be closed by a closure member that is movable between a closed position and an open position. A static air intake vent is equipped with a filter medium. During flight, the method comprises an unfiltered operating mode that comprises the following steps: positioning of the closure member in the open position, and, during a phase of forward travel of the aircraft, dynamic intake of a flow of air, then transfer of a first portion of the flow of air to the engine and a second portion of the flow of air to the filter medium in order to clean the filter medium.

A method for supplying air to an engine of an aircraft via an air supply system of the aircraft. A dynamic air intake vent of the system can be closed by a closure member that is movable between a closed position and an open position. A static air intake vent is equipped with a filter medium. During flight, the method comprises an unfiltered operating mode that comprises the following steps: positioning of the closure member in the open position, and, during a phase of forward travel of the aircraft, dynamic intake of a flow of air, then transfer of a first portion of the flow of air to the engine and a second portion of the flow of air to the filter medium in order to clean the filter medium.

A system and method for a frac pump. The system includes a turbine. The turbine can be 100% powered by natural gas or other fuels. The turbine, which can have an OEM controller, drives a frac pump. The frac pump is used for fracturing. The system has a controller which controls the system, including the OEM controller. The system has an air filtration system to treat the air entering the turbine. The air filtration system can include a system with no moving parts and no filters. The system fits within a trailer so it can be transported to remote locations. The system is self-sufficient.

A system and method for a frac pump. The system includes a turbine. The turbine can be 100% powered by natural gas or other fuels. The turbine, which can have an OEM controller, drives a frac pump. The frac pump is used for fracturing. The system has a controller which controls the system, including the OEM controller. The system has an air filtration system to treat the air entering the turbine. The air filtration system can include a system with no moving parts and no filters. The system fits within a trailer so it can be transported to remote locations. The system is self-sufficient.