A gas turbine engine is disclosed having a tip clearance control system. The tip clearance control system has a cabin blower system, a casing arranged in use about a rotor of a gas turbine engine and a fluid delivery passage. The cabin blower system having a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and to compress fluid conducted via the fluid delivery passage into heat exchange with the casing.

A particle separation device to remove particulate matter from an exterior air flow for use with an environmental control system includes a curved airflow path with an inner radius and an outer radius, the curved air flow path to receive the exterior air flow, a particle passage disposed along at least one of the inner radius and the outer radius to receive the particulate matter from the exterior air flow, a circumferential volute to receive the particulate matter from the particle passage, and a duct to transport the particulate matter from the circumferential volute to a downstream region.

A ram air system includes a ram air inlet, a ram air outlet, a conduit fluidly coupling the ram air inlet to the ram air outlet, and a relief port disposed within the conduit. A method of controlling a ram air system includes disposing a relief port within a conduit of the ram air system, wherein the conduit fluidly couples a ram air inlet to a ram air outlet in order to minimize or otherwise reduce drag, and to control unstable airflow that can otherwise cause resonant instability.

Disclosed is an air mix valve including: a wall having at least three openings; and at least one airflow-regulating device. The airflow-regulating device includes: at least two shutters placed in the internal volume of the valve, at least one aerodynamic shutter of which is arranged with respect to one of the openings so as to be able to receive an airflow passing through this opening, and a linking mechanism between at least two shutters. Each of the shutters is arranged and guided so as to be able to be caused to move with respect to the wall. At least one airflow-regulating device, named aero-controlled regulation device, is mounted to be freely movable under the effect of aerodynamic energy from airflows passing through the openings.

A method of evaluating health of a control system with fluctuating parameters is provided. The method may include receiving session data including actual parameters and target parameters of the control system, segmenting the session data into one or more data segments, calculating a segment score for each data segment based on at least a linear regression correlation coefficient and an average parameter difference, generating a session score based on a combination of the segment scores, and generating a notification indicative of a comparison between the session score and a predefined threshold.

An airplane is provided. The airplane includes a pressurized medium, a turbine, and a valve. The turbine includes at least one nozzle. The valve is located upstream of the turbine. The valve provides the pressurized medium to the at least one nozzle of the turbine according to an operational mode.

Provided are an unmanned aerial vehicle executing relief work in an emergency such as a disaster, a relief system, and a relief method for performing relief work by using an unmanned aerial vehicle. An unmanned aerial vehicle capable of performing autonomous flight includes a receiving unit receiving an input of relief work from a user A2 and a control unit controlling the execution of the relief work based on content of the input received by the receiving unit.

A locking spanner assembly for an aircraft is disclosed. A clasp can be secured to an anchor by urging the clasp onto the anchor. The anchor contacts a trigger which opens a gate assembly to release a locking member which locks to the anchor. A lever arm allows for release which resets the clasp.

A compressed air conduit can have a cross-sectional area, and a valve, the valve having at least one arm being deployable laterally into the cross-sectional area of the conduit to restrict flow within the conduit.

An airplane is provided. The airplane includes a pack. The pack includes a shaft, a compressor, and a turbine coupled to the compressor via the shaft. The turbine receives and expands a first medium to provide power to the compressor via the shaft. The compressor receives and compresses a second medium in accordance with the power provided by the turbine via the shaft. The turbine is fluidly coupled to a heat exchanger of an air conditioning system.