Abstract: A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust.

Abstract: A system for cooling a generator mounted in the tail-cone of an engine. The system comprises a fairing, which receives through an inlet thereof air from a bypass duct and directs the bypass air towards a cavity of the tail-cone for cooling the generator. The bypass air is then expelled through an outlet of a support strut positioned in fluid communication with the tail-cone cavity. The fairing inlet and the strut outlet are both positioned in a plane substantially perpendicular to a longitudinal plane of the engine. In this manner, circulation of the bypass air through the fairing, the tail-cone cavity, and the strut may be achieved. The bypass air directed through the fairing further enables cooling of service lines accommodated in the fairing. A lobe mixer is further used to direct the fairing and shield the latter from core exhaust.

Abstract: Systems and methods for pressurization of a generator in a gas turbine engine. The system may include a fluid valve for permitting or inhibiting airflow into a housing of the generator. The fluid valve may be in fluid communication with an air source within the engine, and may be configured to permit airflow into the housing of the generator when pressure within the housing is below a preset pressure threshold or range.

Abstract: A fire detection switch for use in a fire detection circuit of a aircraft engine, having: a first resistor and a second resistor disposed in series between a common terminal and an alarm terminal; and a thermally-sensitive element having a different resistance at low temperature than at high temperature, the thermally-sensitive element disposed in series with the second resistor and in parallel with the first resistor.

Abstract: A fire detection switch for use in a fire detection circuit of a aircraft engine, having: a first resistor and a second resistor disposed in series between a common terminal and an alarm terminal; and a thermally-sensitive element having a different resistance at low temperature than at high temperature, the thermally-sensitive element disposed in series with the second resistor and in parallel with the first resistor.