One embodiment of a seating arrangement of a transportation vehicle includes at least two rows of upper-level seats in a first zone extending a longitudinal direction, a left row of lower-level seats in a second zone on the left of the upper-level seats, and a right row of lower-level seats in a third zone on the right side of the upper-level seats, with the seats arranged either in an acute or an obtuse angle relative to the longitudinal direction, and with the upper-level seats and the lower-level seats being staggered. In the embodiment, the three zones are substantially isolated from one another. For example, going from one zone to the next, a person can go through a door, and each zone can have its substantially separate air ventilation system. In another embodiment, each of the second and the third zones includes single-level seats, with at least an aisle between the single-level seats and the corresponding lower-level seats. The transportation vehicle can be a plane.

An embodiment of an electric motor assembly includes a stator assembly extending generally along the longitudinal axis and at least partially enclosing a rotor assembly also extending along the longitudinal axis. The rotor assembly includes a rotating portion and one or more sets of rotor windings. The stator assembly includes a stationary housing having at least an inner wall and an outer wall, and one or more sets of stator windings in electromagnetic communication with the one or more sets of rotor windings. A heat exchanger is integrally formed into the housing, and includes a plurality of dividing walls extending between the inner and outer housing walls. The plurality of dividing walls are arranged at least partially circumferentially around the longitudinal axis to define, with the inner and outer walls, a corresponding plurality of integral heat exchanger channels arranged at least partially circumferentially around the one or more sets of stator windings. A plurality of rib turbulators are disposed on at least a channel-facing surface of the inner wall.

An aircraft propulsion system including a turbojet and heat exchanger system including a heat exchanger. A supply connection and evacuation connection are forward, and aft are a transfer connection and a scoop connection, a supply pipe connected to the supply connection, and which bleeds hot air from the compression stages. A transfer pipe connected to the transfer connection transfers hot air to an air management system. A scoop connected to a scoop connection bleeds cold air from a fan duct and an evacuation pipe, including an inlet connected to the evacuation connection and an outlet, which emerges on the outside, where hot air through the heat exchanger from the supply pipe to the transfer pipe passes along a first transfer direction and cold air passes through the heat exchanger from each scoop to the inlet along a second transfer direction parallel to the first transfer direction in the opposite direction.

There is provided a gas turbine engine comprising a blower system for supplying pressurised air to an airframe via an airframe port. The blower system comprises a compressor configured to receive air from a bypass duct or a core of the gas turbine engine and to discharge compressed air into a delivery line extending from the compressor to the airframe port. The blower system also comprises a heat exchanger configured to transfer heat from the compressed air to a coolant and a valve arrangement configured to switch between operation of the blower system in a baseline mode and a cooling mode, the valve arrangement being configured to: selectively divert the compressed air within the delivery line to the heat exchanger for operation in the cooling mode; and/or selectively provide the coolant to the heat exchanger for operation in the cooling mode.

An environmental control system is provided including a ram air circuit having a ram air duct and at least one heat exchanger arranged within the ram air duct. The ram air duct is curved about a ram axis. A compression device includes a compressor and at least one turbine operably coupled by a shaft rotatable about a shaft axis. The ram axis is arranged coaxially with the shaft axis.

An environmental control system for an aircraft includes a first conduit, a second conduit, and a connector assembly. The connector assembly is coupled to the first conduit and the second conduit for controlling a flow of air. The connector assembly includes a connector, a connector ring, and an orifice plate. The connector includes at least one wall including a ridge defining a receptacle and a connector slot defined within the ridge. The connector ring is attached to the connector and defines a connector ring slot and a covering portion. The connector ring slot aligns with the connector slot and the orifice plate is inserted into through the connector ring slot and the connector slot into the receptacle during installation of the orifice plate. The covering portion covers the connector slot and retains the orifice plate within the receptacle during operation of the environmental control system.

A fixture configured to secure a component in a vehicle includes a panel separating an internal cabin from an external compartment. The panel has a first side facing the internal cabin and a second side facing the external compartment. A hole is disposed within the panel. The component is configured for mounting to the panel via the hole. The component includes a flange configured for abutting the first side of the panel and a coupling feature configured to extend through the hole into the external compartment. A fastener is configured to removably couple with the coupling feature and abut the second side of the panel for fastening the component to the panel.

Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.

Disclosed is a heat exchanger for a thermal management system of an aircraft assembly, the heat exchanger including: a core including a first side with a first core inlet, a second side opposing the first side and includes a first core outlet, the first core inlet is in fluid communication with the first core outlet, a third side having a second core inlet and a fourth side opposing the third side and includes a second core outlet, the second core inlet is in fluid communication with the second core outlet, and a screen wrapped around the core, the screen covering the first core inlet and the first core outlet, and a plurality of rollers disposed between the core and the screen for movably securing the screen to the core, the rollers engaging the screen and movement of at least one of the rollers moves the screen about the core.

A louvre system controls a flow of cooling air to a heat-generating element mounting inside a wing of an aircraft. The louvre system includes a louvre operably connected to the wing and structured to be rotatable to control airflow through an air intake of the wing into an interior of the wing. A louvre actuation mechanism is operably connected to the louvre and configured to control rotation of the louvre. A memory is communicably coupled to a processor and stores a louvre control module configured to autonomously control operation of the louvre actuation mechanism to control rotation of the louvre responsive to a temperature of a heat-generating element mounted in the wing interior.