Systems, assemblies, and methods to enhance the efficiency of operation of a gas turbine engine may include a turbine housing positioned to at least partially enclose the gas turbine engine, and a filtration assembly connected to the turbine housing to supply at least partially filtered intake air to an inlet assembly associated with the gas turbine engine. The filtration assembly may include a pre-cleaner including one or more inertial separators configured to separate a first portion of particles and/or liquid from ambient air supplied to the gas turbine engine, thereby to provide at least partially filtered intake air, and one or more filters positioned downstream of the pre-cleaner to separate a second portion of the particles and/or liquid from the at least partially filtered intake air.

Systems, assemblies, and methods to enhance the efficiency of operation of a gas turbine engine may include a turbine housing positioned to at least partially enclose the gas turbine engine, and a filtration assembly connected to the turbine housing to supply at least partially filtered intake air to an inlet assembly associated with the gas turbine engine. The filtration assembly may include a pre-cleaner including one or more inertial separators configured to separate a first portion of particles and/or liquid from ambient air supplied to the gas turbine engine, thereby to provide at least partially filtered intake air, and one or more filters positioned downstream of the pre-cleaner to separate a second portion of the particles and/or liquid from the at least partially filtered intake air.

An aircraft system includes a turbine engine having a compressor, a combustor having an inlet and an outlet, and a turbine having an inlet portion and an outlet portion. An auxiliary power unit (APU) is operatively connected to the turbine engine. The APU includes a compressor portion, a generator, and a turbine portion. The compressor portion is operatively connected to the turbine portion through the generator. A source of cryogenic fluid is operatively connected to the turbine engine and the APU. A heat exchange member includes an inlet section operatively connected to the source of cryogenic fluid, a first outlet section operatively connected to the turbine engine and a second outlet section operatively connected to the compressor portion.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

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 engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

A system comprises a gas turbine engine. The gas turbine engine has a flow diffuser system, a combustor, a modified compressor section, and a turbine coupled to a shaft. The system includes a low pressure intercooled compressor, a high pressure intercooled compressor, a recuperator, and a compressed air storage tank. The compressed air storage tank is in selective fluid communication with the low pressure intercooled compressor via the high pressure intercooled compressor, and the recuperator. The high pressure intercooled compressor is configured to selectively receive compressed air from the low pressure intercooled compressor and is further configured to selectively compress the compressed air to a highly compressed air for storage in the compressed air storage tank. Each of the compressed air storage tank and the low pressure intercooled compressor is selectively and fluidly coupled to the gas turbine engine.