Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position.

Abstract: A mount for a gas turbine engine unit. The mount comprises a unit interface for securing a unit to the mount. The unit interface comprises an internal cavity in communication with a cooling aperture to be overlaid by unit secured to the unit interface. The mount further comprises a structural framework for securing the mount to a gas turbine engine. The structural framework comprises an internal cooling conduit for delivering cooling airflow from an air source to the internal cavity of the unit interface.

Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position.

Abstract: A method, for detecting overpressure inside a compartment associated with a gas turbine nacelle, includes: a) measuring one or more predetermined operating conditions nominally affecting the temperature inside the compartment; b) determining a reference temperature for the compartment, corresponding to a nominal reference zone pressure, on the basis of the measured operating condition or conditions; c) measuring the actual temperature inside the compartment, corresponding to the actual compartment pressure; and d) using the measured actual temperature in the compartment and the determined reference temperature for the compartment to assess the gas pressure inside the compartment. A system for assessing the gas pressure inside the compartment caused by an associated pressure system failure includes using a quantified mass leakage flow to assess gas pressure inside the compartment.

Abstract: A method for detecting overpressure inside a compartment associated with a gas turbine nacelle, the method comprising: a) measuring one or more predetermined operating conditions nominally affecting the temperature inside the compartment; b) determining a reference temperature for the compartment, corresponding to a nominal reference zone pressure, on the basis of the measured operating condition or conditions; c) measuring the actual temperature inside the compartment, corresponding to the actual compartment pressure; and d) using the measured actual temperature in the compartment and the determined reference temperature for the compartment to assess the gas pressure inside the compartment. In one embodiment, there is disclosed a system for assessing the gas pressure inside the compartment caused by an associated pressure system failure, comprising using a quantified mass leakage flow to assess gas pressure inside the compartment.