Summary Of the Invention
It is an object of the present invention to provide an environment control system that overcomes the above-noted deficiencies in the prior art.
It is a further object of the present invention to provide an environment control system capable of inhibiting moist cabin air from contacting cold surfaces of the envelope, thereby reducing moisture condensation within the envelope, and associated "rain-in-the-plane", electrical failures, corrosion, microbial growth, and dead weight.
It is a further object of the present invention to provide an environment control system capable of reducing infiltration of smoke from the envelope into the interior cabin space, thereby increasing passenger and crew safety during an in-flight fire situation.
It is a further object of the present invention to provide an environment control system capable of improving cabin indoor air quality (IAQ) by at least partially removing contaminants from ventilation air prior to entering the cabin.
Accordingly, an aspect of the present invention provides an environment control system for an aircraft including at least a pressure shell, an interior space including one or more of a cabin and a cargo hold, an envelope extending between the interior space and the pressure shell and a liner disposed between the interior space and the envelope. The environment control system comprises an envelope air distribution system having a plurality of nozzles located at spaced intervals and adapted to distribute an envelope air stream within the envelope in such a manner as to at least partially offset stack effect pressures.
Another aspect of the present invention provides an environment control system for an aircraft including at least a pressure shell, an interior space including one or more of a cabin and a cargo hold, an envelope extending between the interior space and the pressure shell and a liner disposed between the interior space and the envelope. The environment control system comprises an envelope air distribution system adapted to supply an envelope air stream to the envelope; and one or more flow-blockers adapted to at least partially block a flow of air within the envelope.
Another aspect of the present invention provides an environment control system for an aircraft including at least a pressure shell, an interior space including one or more of a cabin and a cargo hold, an envelope extending between the interior space and the pressure shell and a liner disposed between the interior space and the envelope. The environment control system comprises an envelope air distribution system adapted to supply an envelope air stream within the envelope; and sealing means adapted to at least partially seal the liner against leakage of air between the interior space and the envelope.
In embodiments of the invention, one or more flow-blockers are provided, and adapted to at least partially block a flow of air within the envelope. The envelope air distribution system may include a plurality of nozzles located at spaced intervals and adapted to distribute the envelope air stream within the envelope in such a manner as to at least partially offset stack effect pressures. Sealing means adapted to at least partially seal the liner against leakage of air between the interior space and the envelope may be included.
In embodiments of the invention, the envelope air distribution system may further include: at least one envelope supply duct; and at least one respective ventilation air branch line in communication with the envelope supply duct and one or more respective nozzles.
An insulation blanket may be disposed within the envelope between the liner and the pressure shell. At least one nozzle may be a shell-side nozzle adapted to inject envelope air between the insulation jacket and the pressure shell. At least one nozzle may be a cabin-side nozzle adapted to inject envelope air between the insulation jacket and the liner.
In embodiments of the invention, an air supply is adapted to generate the envelope air stream. The air supply may include an air supply duct adapted to conduct bleed air from a compressor stage of an engine of the aircraft into the body of the aircraft as ventilation air. The air supply may also include an airflow control device adapted to divide the flow of ventilation air into the envelope air stream and a cabin air stream. An air conditioner pack adapted to cool the ventilation air may also be included. The airflow control device may include at least one valve adapted for controlling the envelope air stream and the cabin air stream to maintain a predetermined pressure difference between the cabin and the envelope.
In embodiments of the invention, a cabin air distribution system is adapted to distribute the cabin air stream within the interior space of the aircraft body. The cabin air distribution system may include: an air conditioner communicating with the airflow control device for receiving at least a portion of the cabin air stream, and adapted to condition the cabin air stream to create cabin supply air; and a cabin supply air duct adapted to direct the cabin supply air into the cabin. The air conditioner may be adapted to control the relative humidity of the cabin supply air, e.g. to maintain a cabin relative humidity level in excess of 20%.
In embodiments of the invention, the sealing means is adapted to limit a leakage area of the cabin liner such that a predetermined pressure difference between the interior space and the envelope can be maintained at a predetermined minimum ventilation rate. The minimum ventilation rate may be about 0.55lbs per passenger or less. The leakage area may be equivalent to about 73cm2 per passenger, or less.
In embodiments of the invention, at least one flow blocker is arranged to reduce stack effect air flows within the envelope. The flow-blockers may be arranged to divide the envelope into one or more sections. In such cases, the envelope air distribution system may be adapted to control envelope ventilation within a section independently of other sections. At least one section may formed by dividing at least a portion of the envelope longitudinally, e.g. to form at least one section within a crown of the envelope. At least one section may be formed by dividing the envelope laterally, e.g. to form at least one section within a cockpit portion of the envelope. At least one section may formed by dividing the envelope both longitudinally and laterally, to form at least one section within the envelope proximal a food preparation area of the cabin.
In embodiments of the invention, a return air control unit is capable of drawing a return air stream from a selected one of the interior space and the envelope. The return air control unit may include a housing, a first opening defined in the housing and in communication with the envelope, a second opening defined in the housing and in communication with the interior space, and a damper capable of selectively closing one of the first opening and the second opening. An outflow valve may be adapted to divide the return air stream into an exhaust air stream and a recirculation air stream, the exhaust air stream being vented out of the aircraft, and the recirculation air stream being supplied back to the cabin. The recirculation air stream may be supplied to the cabin via an air conditioner.
In embodiments of the invention, an anti-corrosion/VOC sorption treatment is applied to an interior surface of the aircraft structure within the envelope. The anti-corrosion/VOC sorption treatment may be formulated to provide acceptable characteristics of: adhesion to metal surfaces; hydrophobic; low flammability; and low off-gassing at typical envelope temperatures during cruising flight. The anti-corrosion/VOC sorption treatment is formulated to: resist solidification within the aircraft envelope; sorb ventilation air VOCs at typical envelope temperatures during cruising flight and desorb said ventilation air VOC's at warmer temperatures substantially without hysteresis.
In embodiments of the invention, a fire suppression system is provided in communication with the envelope air distribution system. The fire suppression system is preferably capable of releasing a flow of chemical fire suppressant into at least the envelope air distribution system when smoke or fire is detected in the envelope. The fire suppression system and the envelope air distribution system may be adapted to cooperate to flood at least a portion of the envelope with the chemical fire suppressant. The fire suppression system may include a container of chemical fire suppressant, a supply line in communication with the container and the envelope air distribution system for conducting the chemical fire suppressant between the container and the envelope air distribution system, and a valve capable of controlling a flow of chemical fire suppressant from the container. The chemical fire suppressant may be any one or more of Halon, carbon dioxide, nitrogen, and other fire suppressant agents, or mixtures of these.
A further aspect of the present invention provides a method of controlling the environment within an aircraft including at least a pressure shell, an interior space including one or more of a cabin and a cargo hold, an envelope extending between the interior space and the pressure shell, and a liner disposed between the interior space and the envelope, the method comprising a step of distributing an envelope air stream within the envelope through a plurality of nozzles so as to at least partially offset stack effect pressures.
Another aspect of the present invention provides a method of controlling the environment within an aircraft body including at least a pressure shell, an interior space including one or more of a cabin and a cargo hold, an envelope extending between the interior space and the pressure shell, and a liner disposed between the interior space and the envelope. The method comprises the steps of: distributing an envelope air stream within the envelope; and providing one or more flow-blockers within the envelope and adapted to at least partially block a flow of air within the envelope.
Another aspect of the present invention provides a method of controlling the environment within an aircraft body including at least a pressure shell, an interior space including one or more of a cabin and a cargo hold, an envelope extending between the interior space and the pressure shell, and a liner disposed between the interior space and the envelope. The method comprises the steps of: distributing an envelope air stream within the envelope; and at least partially sealing the liner against leakage of air between the envelope and the interior space, such that a predetermined pressure difference between the envelope and the interior space can be maintained at a predetermined minimum ventilation rate.
In embodiments of the invention, the envelope air stream is distributed within the envelope through a plurality of nozzles so as to at least partially offset stack effect pressures. At least a portion of the envelope air stream may be injected into a space between the pressure shell and an insulation jacket. At least a portion of the envelope air stream may be injected into a space between an insulation jacket and the liner.
In embodiments of the invention, a return air stream may be drawn from a selected one of the envelope and the cabin. The return air stream may be divided into an exhaust air stream and a recirculation air stream, the exhaust air stream being vented from the aircraft and the recirculation air stream being supplied back to the cabin.
In embodiments of the invention, a supply air stream is divided into the envelope air stream and a cabin air stream. The cabin air stream is supplied to the cabin; and the envelope air stream and the cabin air stream are controlled to maintain a predetermined pressure difference between the cabin and the envelope.
In embodiments of the invention, the cabin air is humidified, and the humidified cabin air is supplied to the cabin.
In embodiments of the invention, during a cruising portion of a flight cycle, the predetermined pressure difference is selected such that the envelope is at a higher pressure than the cabin. In such cases, the return air stream may be drawn from the cabin. Similarly, a portion of the return air stream can be vented out of the aircraft, and a remaining portion of the return air stream recirculated back into the cabin.
In embodiments of the invention, during a taxi and ascent portion of a flight cycle, the predetermined pressure difference is selected such that the envelope is at a lower pressure than the cabin. In such cases, the return air stream can be drawn from the envelope, and substantially all of the return air stream may be vented out of the aircraft.
In embodiments of the invention, during an in-flight fire and/or pyrolysis within the envelope or in the cabin, the predetermined pressure difference is selected such that the envelope is at a lower pressure than the cabin. In such cases, at least a portion of the envelope can be flooded with a chemical fire suppressant, and the cabin air stream may include substantially all of the total flow of ventilation air. The return air stream may be drawn from the envelope, and substantially all of the return air stream vented out of the aircraft.
In embodiments of the invention, during ground operations of the aircraft, the return air stream is drawn from the envelope and substantially all of the return air stream is vented out of the aircraft. In such cases, the ventilation air stream may be heated to accelerate volatilization of VOCs and any moisture within the envelope.
The environment control system of the invention can be incorporated into new aircraft construction, or installed as an upgrade or retrofit in an existing aircraft.
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