An inlet particle separator system for a gas turbine engine includes a separator manifold. The separator manifold includes an inlet upstream from an outlet. The inlet is to receive an incoming airflow, and the outlet is to be fluidly coupled to an inlet of the gas turbine engine. The inlet particle separator system includes at least one dry fog nozzle coupled proximate the inlet so as to face at least partially away from the inlet. The dry fog nozzle is external to the separator manifold, and the dry fog nozzle is to direct a spray of dry fog in a direction transverse to the incoming airflow to agglomerate with fine particles in the incoming airflow to form agglomerated particles. The inlet particle separator system includes a scavenging system coupled to the separator manifold downstream from the inlet, and the scavenging system removes the agglomerated particles from the separator manifold.

An inertial particle separator (IPS) for a gas turbine engine, has: a plenum circumferentially extending about a central axis and defined between an outer wall and an inner wall, the plenum having an inlet facing a circumferential direction relative to the central axis, a radius of the outer wall decreasing in an axial direction relative to the central axis between the inlet and an annular splitter extending circumferentially around the central axis and located downstream of the inlet radially between the outer wall and the inner wall, a particle outlet including an annulus radially between the outer wall and the splitter, an air outlet fluidly connectable to a compressor of the gas turbine engine and defined radially between the splitter and the inner wall.

An inertial particle separator (IPS) for a gas turbine engine, has: a plenum circumferentially extending about a central axis and defined between an outer wall and an inner wall, the plenum having an inlet facing a circumferential direction relative to the central axis, a radius of the outer wall decreasing in an axial direction relative to the central axis between the inlet and an annular splitter extending circumferentially around the central axis and located downstream of the inlet radially between the outer wall and the inner wall, a particle outlet including an annulus radially between the outer wall and the splitter, an air outlet fluidly connectable to a compressor of the gas turbine engine and defined radially between the splitter and the inner wall.

An inertial particle separator (IPS) has: a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side; two inlet ducts extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; and a bypass duct communicating with the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another.

An inertial particle separator (IPS) has: a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side; two inlet ducts extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow; and a bypass duct communicating with the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another.

A particle separator associated with a compressor section of a gas turbine engine includes a duct that defines a fluid flow path from a diffuser to a deswirl section. The duct includes a curved portion between an outlet of the diffuser and an inlet of the deswirl section. The curved portion is configured to have at least one low velocity region and a high velocity region. The particle separator includes at least one cluster of inlet passages defined at the at least one low velocity region. The particle separator includes a scavenge plenum coupled to the duct and in fluid communication with the at least one cluster of inlet passages. At least one outlet slot is defined through the duct downstream of the at least one cluster of inlet passages in the high velocity region and is in fluid communication with the scavenge plenum.

In one embodiment, a computing device includes one or more processors configured to execute instructions that cause the one or more processors to acquire pressure data measured by at least one pressure sensor disposed proximate to a filter house in an intake of a gas turbine engine system, derive an airflow or an air mass flow through a duct of the intake using a thermodynamic model of the gas turbine engine system based at least on the pressure data, derive an intake pressure drop in the duct using at least the pressure data, derive a loss parameter of the filter house by combining the air mass or air mass flow, and the intake pressure drop, derive a pressure loss model based on the loss parameter over a period of time, and determine a condition of the filter house based on the pressure loss model.

In one embodiment, a computing device includes one or more processors configured to execute instructions that cause the one or more processors to acquire pressure data measured by at least one pressure sensor disposed proximate to a filter house in an intake of a gas turbine engine system, derive an airflow or an air mass flow through a duct of the intake using a thermodynamic model of the gas turbine engine system based at least on the pressure data, derive an intake pressure drop in the duct using at least the pressure data, derive a loss parameter of the filter house by combining the air mass or air mass flow, and the intake pressure drop, derive a pressure loss model based on the loss parameter over a period of time, and determine a condition of the filter house based on the pressure loss model.

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 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.