A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module.

A system, as well as associated methods, for increasing the efficiency of a gas turbine including an inlet assembly and a compressor may include a housing configured to channel airstream towards the inlet assembly, an air treatment module positioned at a proximal end the housing, and at least one air conditioning module mounted downstream of the air treatment module for adjusting the temperature of the airstream entering the compressor. The air treatment module may include a plurality of inlet air filters and at least one blower configured to pressurize the air entering the air treatment module.

An air intake system for an aircraft, which is switchable between a performance mode and a filtered mode, includes a duct forming filtered air inlet slits. The air intake system also includes interconnected gills adjacent to the filtered air inlet slits. The gills are movable between various gill positions including a closed position substantially covering the filtered air inlet slits and an open position substantially exposing the filtered air inlet slits. The air intake system also includes an actuator configured to move the gills into the closed position in the performance mode and the open position in the filtered mode.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

An inlet particle separator system includes a shroud section and a hub section that is at least partly surrounded by the shroud section. The hub section is spaced apart from the shroud section. The inlet particle separator system also includes a flow passageway with an air inlet defined between the hub section and the shroud section. The flow passageway branches downstream of the air inlet into a main passage and a pre-cleaner passage. The main passage is defined between the hub section and the shroud section. The pre-cleaner passage includes a pre-cleaner inlet and extends at least partially through the hub section. Furthermore, the system includes a splitter that divides the main passage into scavenge and engine flow paths. The pre-cleaner inlet is partly defined by a first surface of the hub section. The first surface faces substantially in an upstream direction toward the air inlet.

An inlet particle separator system includes a shroud section and a hub section that is at least partly surrounded by the shroud section. The hub section is spaced apart from the shroud section. The inlet particle separator system also includes a flow passageway with an air inlet defined between the hub section and the shroud section. The flow passageway branches downstream of the air inlet into a main passage and a pre-cleaner passage. The main passage is defined between the hub section and the shroud section. The pre-cleaner passage includes a pre-cleaner inlet and extends at least partially through the hub section. Furthermore, the system includes a splitter that divides the main passage into scavenge and engine flow paths. The pre-cleaner inlet is partly defined by a first surface of the hub section. The first surface faces substantially in an upstream direction toward the air inlet.

A gas turbine engine includes an engine core includes at least one compressor, a combustor downstream of the compressor, and at least one turbine downstream of the combustor. A primary flowpath fluidly connects each of the compressor, the combustor, and the turbine. At least one particle extraction duct has an extraction duct inlet connected to the primary flowpath fore of the compressor and an extraction duct outlet connected to a bypass flowpath.

A system and method for preventing icing in the combustion inlet air path of a gas turbine system. An air intake system of the gas turbine system supplies intake air to a gas turbine engine. The air intake system includes an air filter inlet house to filter the intake air. The air filter inlet house includes at least one filter stage having an array of pulse filters, with each of the pulse filters being hydrophobic. A combustion inlet air path is in fluid communication with the air intake system and the gas turbine engine. The combustion inlet air path receives the filtered air from the air filter inlet house and supplies the filtered air as combustion inlet air to an inlet of the gas turbine engine. A surface of at least one component in the combustion inlet air path includes an anti-icing coating to prevent ice from forming thereon.

A system and method for preventing icing in the combustion inlet air path of a gas turbine system. An air intake system of the gas turbine system supplies intake air to a gas turbine engine. The air intake system includes an air filter inlet house to filter the intake air. The air filter inlet house includes at least one filter stage having an array of pulse filters, with each of the pulse filters being hydrophobic. A combustion inlet air path is in fluid communication with the air intake system and the gas turbine engine. The combustion inlet air path receives the filtered air from the air filter inlet house and supplies the filtered air as combustion inlet air to an inlet of the gas turbine engine. A surface of at least one component in the combustion inlet air path includes an anti-icing coating to prevent ice from forming thereon.

A method and apparatus for separating particles from an inlet airflow of a turbine engine has a centerbody with at least one radially outward scavenge conduit. The inlet airflow has entrained particulate matter, which can impact an impact surface defining part of the centerbody. The particulate matter is radially diverted outward through at least one inlet to a scavenge conduit, unable to make a turn defined by the shape of the centerbody.