Abstract: A vapor separation system including a cooler having an inlet configured to receive an air-oil-water mixture, and an outlet configured to discharge separated oil and water in two different phases of matter. A first sensor is at the outlet of the cooler. A controller is communicatively coupled to the cooler, wherein the controller is configured to receive temperature feedback from the first sensor, and increase or reduce the amount of cooling, with the cooler and based on the temperature feedback, the oil-water mixture to a separation temperature configured to liquefy at least a portion of the oil in the air-oil-water mixture, while maintaining at least a portion of the water in the air-oil-water mixture in a vaporized state.

Abstract: A vapor separation system including a cooler having an inlet configured to receive an air-oil-water mixture, and an outlet configured to discharge separated oil and water in two different phases of matter. A first sensor is at the outlet of the cooler. A controller is communicatively coupled to the cooler, wherein the controller is configured to receive temperature feedback from the first sensor, and increase or reduce the amount of cooling, with the cooler and based on the temperature feedback, the oil-water mixture to a separation temperature configured to liquefy at least a portion of the oil in the air-oil-water mixture, while maintaining at least a portion of the water in the air-oil-water mixture in a vaporized state.

Abstract: 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.

Abstract: 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.

Abstract: Systems and methods include one or more fluid lines configured to flow a fluid in a first direction in the gas turbine system. The systems and methods also include an eductor configured to reverse flow of the fluid in the one or more fluid lines during a reverse purge of the gas turbine system.

Abstract: Systems and methods include one or more fluid lines configured to flow a fluid in a first direction in the gas turbine system. The systems and methods also include an eductor configured to reverse flow of the fluid in the one or more fluid lines during a reverse purge of the gas turbine system.

Abstract: A ventilation system for a turbomachine enclosure includes: a bladeless airflow amplifier configured to pass an airflow through at least a portion of the turbomachine enclosure; and an amplifier airflow source fluidly coupled to the bladeless airflow amplifier for providing an operative airflow to operate the bladeless airflow amplifier. The ventilation system may be employed with or without a conventional vent fan system.

Abstract: A ventilation system for a turbomachine enclosure includes: a bladeless airflow amplifier configured to pass an airflow through at least a portion of the turbomachine enclosure; and an amplifier airflow source fluidly coupled to the bladeless airflow amplifier for providing an operative airflow to operate the bladeless airflow amplifier. The ventilation system may be employed with or without a conventional vent fan system.