Patent Description:
One purpose of an environmental control system is to distribute air through the main passenger cabin of the aircraft. Generally, air is supplied through ducts in the cabin ceiling and then flows through return air grills located near the cabin floor in the sidewall of each aisle. In many known configurations, the return air grills are built into decompression panel assemblies and are identical to each other along the cabin such that each return air grill provides a substantially similar airflow restriction therethrough. At least some known environmental control systems also include various components, such as filters, fans, and air conditioning packs that draw air through the return air grills. These components are positioned at various locations along the aircraft and so they draw air primarily through the return air grills from the aisles around which the component is located. Because each of the return air grills have a similar flow restriction, there tends to be a cross-aisle airflow in the aft or forward direction toward the nearest component of the environmental control system drawing air through the return air grills. In such a configuration, the airflow entering the return air grills in the aisle nearest the drawing component may have passed through one or more adjacent aisles, thus exposing the passengers in the component aisle to more cross-aisle airflow than passengers seated in aisle further from the drawing component of the environmental control system.

<CIT>, according to its abstract, relates to an aircraft passenger cabin airflow metering apparatus and system. The apparatus includes a blowout disc designed to release at a predetermined air pressure differential on opposite sides of the blowout disc. The blowout disc may include a cutout to allow a desired amount of airflow during normal operation. The apparatus is affixed to an existing structure in a frame bay at the perimeter of the passenger cabin floor level of the aircraft. The airflow metering system includes a combination of airflow metering apparatuses placed within discrete rooms of an aircraft passenger cabin to achieve positive pressure in the passenger cabin and the desired amount of airflow exhaust from the passenger cabin during normal operation across all areas of the aircraft and to also achieve the desired amount of airflow during abnormal operation when the air pressure on either side of the airflow metering apparatus exceeds a predetermined threshold.

<CIT> according to its first sentence, relates to improvements in air conditioning systems and registers.

<CIT> according to its first sentence, relates to a combination ventilator and dehumidifier, such as is applicable for use in homes, but is primarily adapted for usage in warehouse, garages, and particularly barns, chicken and hog houses.

This section is intended to introduce the reader to various aspects of art that may be related to various aspects of the disclosure, which are described and/or claimed below.

According to the invention, an aircraft is provided comprising a first row of seats, a second row of seats and an environmental control system, the environmental control system comprising: a first decompression panel assembly comprised in the first row of the aircraft and comprising a first array of apertures that defines a first airflow restriction, a second decompression panel assembly comprised in the second row of the aircraft and comprising a second array of apertures that defines a second airflow restriction different than the first airflow restriction, at least one component positioned along a length of the aircraft and designed for drawing air through the first and second decompression panel assemblies; wherein the first and second arrays of apertures are formed on interchangeable inserts; wherein the arrays of the decompression assemblies are based on the location of the corresponding decompression panel assembly along the length of the aircraft relative to the at least one component; and wherein the first airflow restriction is configured to provide a first mass flow of air through the first decompression panel assembly, wherein the second airflow restriction is configured to provide a second mass flow of air through the second decompression panel assembly and the first mass flow and the second mass flow are substantially similar.

Preferred embodiments are identified in the dependent claims.

Examples described below include an environmental control system that facilitates minimizing airflow between passengers within confined spaces, such as aircraft passenger cabins. Example systems described provide decompression panel assemblies that include different flow restrictions based on their location along the length of the aircraft and proximity to other components of the environmental control system. In one example, the aircraft includes a first aisle having a first decompression panel assembly with a first array of apertures that define a first airflow restriction. Similarly, a second aisle includes a second decompression panel assembly having a second array of apertures that define a second airflow restriction different than the first airflow restriction. The different air flow restrictions are configured to provide a substantially similar mass flow through both the decompression panel assemblies. Having a similar mass flow through the decompression assemblies in each aisle facilitates limiting cross-circulation between passengers seated in adjacent aisles. Example systems facilitate reducing the spread of airborne contaminants between nearby occupants, reducing noise and undesirable drafts, and limiting the formation of stagnant zones of circulation within the confined space.

Referring to the drawings, <FIG> is a cross-sectional view of an aircraft <NUM> having an example environmental control system (ECS) <NUM>. Aircraft <NUM> includes a forward end <NUM>, an aft end <NUM>, and a passenger cabin <NUM> extending therebetween. Cabin <NUM> is separated from a lower lobe <NUM> of aircraft <NUM> by a cabin floor <NUM>. In the embodiment, ECS <NUM> circulates air through cabin <NUM> to provide the passengers with cool, clean air. ECS <NUM> includes a main distribution duct <NUM> defined in the crown volume <NUM> above cabin <NUM>. From main distribution duct <NUM>, air is channeled to each row or aisle <NUM> in cabin <NUM> such that a generally uniform distribution air airflow is distributed to cabin <NUM> from main distribution duct <NUM>.

In the embodiment, ECS <NUM> includes a variety of components <NUM> located in lower lobe <NUM> that draw air from cabin <NUM> through a return air grill defined in a decompression panel assembly <NUM> in each aisle <NUM>. More specifically, components <NUM> include a cooling filter <NUM> positioned proximate forward end <NUM>. A recirculation filter <NUM>, a mixing manifold <NUM>, and at least one air conditioning pack <NUM> are positioned proximate a wing box <NUM> of aircraft <NUM>. Additionally, an outlet valve <NUM> is positioned at aft end <NUM>. Generally, components <NUM> are positioned along the length of the aircraft <NUM> between forward end <NUM> and aft end <NUM> at any location that facilitates operation of ECS <NUM> as described herein.

In operation, each component <NUM> of ECS <NUM> draws air through decompression panel assemblies <NUM>. However, the pressure of the draw or suction force <NUM> through each decompression panel assembly <NUM> will vary based on its location relative to one of components <NUM>. Specifically, decompression panel assemblies <NUM> closest to each component will have a higher suction or draw force because of the close proximity. For example, cooling filter <NUM> and outlet valve <NUM> exert a higher draw force on decompression panel assemblies in aisles <NUM> at forward end <NUM> and aft end <NUM>, respectively. Similarly, recirculation filter <NUM> and air conditioning pack <NUM> cause a higher suction force at decompression panel assemblies <NUM> in aisles <NUM> closer thereto. As such, the suction force through decompression panel assemblies <NUM> in aisles <NUM> that are distanced from components <NUM> is relatively lower. This idea is illustrated in <FIG> by showing the suction force of selected aisles in broken lines. The thicker and denser the line, the higher the suction force on the corresponding decompression panel assembly <NUM>.

<FIG> is a schematic view of ECS <NUM> illustrating example decompression panel assemblies <NUM>. More specifically, <FIG> is a schematic illustration of a first aisle 118A having a first decompression panel 120A, a second aisle 118B having a second decompression panel 120B; and a third aisle 118C having a third decompression panel 120C. As described above, each aisle 118A, 188B, and 118C has a different suction force, ΔP, due to its proximity to various components of ECS <NUM>. Specifically, aisles 118A and 118C have higher suction forces ΔPA and ΔPC due to their relative proximity to cooling filter <NUM> and recirculation filter <NUM>. Aisle 118B has a lower suction force ΔPC because it is spaced further from cooling filter <NUM> and recirculation filter <NUM>. Additionally, each aisle 118A, 118B, and 118C has a constant structure flow restriction ΔR through lower lobe <NUM>.

In order to prevent or reduce cross-aisle airflow and expose passengers of each aisle <NUM> only to air from their aisle <NUM>, the mass flow, ṁ, through each decompression panel <NUM> should be the same. Because of the difference in suction forces ΔP, in the embodiment, each decompression panel assembly <NUM> may have a different airflow restriction constant K. More specifically, decompression panel assemblies <NUM> positioned closer to components <NUM> of ECS <NUM> include an airflow restriction constant K that is higher than decompression panel assemblies <NUM> spaced from components <NUM>. For example, referring to <FIG>, the relatively higher suction force ΔPA in aisle 118A means that decompression panel 120A will have a higher airflow restriction constant KA than airflow restriction constant KB of decompression panel 120B in aisle 120B, which is subjected a lower suction force ΔPB. In such a configuration, the difference in airflow restriction constants KA and KB result in the mass flow ṁA through decompression panel assembly 120A of aisle 118A being substantially similar to the mass flow ṁB through decompression panel assembly 120B of aisle 118B. Similarly, the airflow restriction constant Kc of decompression panel 120C is tailored such that the mass flow the through decompression panel assembly 120C of aisle 118C is substantially similar to the mass flows ṁA and ṁB. As such, the airflow restriction constant K of each decompression panel assembly <NUM> is tailored based on its location along aircraft and proximity to components <NUM> of ECS <NUM> such that the mass flow ṁ of aisles 118A, 118B, and 118C are substantially similar. In the event of decompression, the decompression panel assembly <NUM> at least partially separates from a frame or grill (not shown) to allow a higher mass flow of air therethrough.

Referring to <FIG>, each decompression panel assembly <NUM> includes a predetermined array <NUM> of apertures <NUM> that provide that decompression panel assembly <NUM> with a predetermined airflow restriction constant K that will combine with the suction force ΔP at the location of the decompression panel assembly <NUM> to result in a mass flow ṁ substantially similar to the mass flows ṁ of each other aisle <NUM>. As described herein, when each aisle <NUM> has a substantially similar mass flow ṁ, cross-aisle airflow is reduced or prevented. <FIG> illustrates a decompression panel assembly <NUM> having a first array 138A. Similarly, <FIG> illustrates a decompression panel assembly <NUM> having a second array 138B. The number, location, and configuration of arrays 138A and 138B are based on the location of decompression panel assemblies <NUM> and <NUM> along aircraft <NUM>. The location along aircraft <NUM> determines the proximity to one of components <NUM> of ECS <NUM> and the corresponding suction force associated therewith. As described herein, decompression panel assemblies <NUM> located closer to components <NUM> will generally have an array <NUM> with a lower number of apertures <NUM>, and decompression panel assemblies <NUM> located farther from components <NUM> will generally have an array <NUM> with a higher number of apertures <NUM>. Generally, decompression panel assemblies <NUM> may have an array <NUM> with any number of apertures <NUM> positioned anywhere on decompression panel assembly <NUM>, and in any configuration to facilitate substantially similar mass flows and operation of ECS <NUM> as described herein.

In one embodiment, as shown in <FIG>, decompression panel assemblies <NUM> and <NUM> are manufactured with corresponding arrays 138A and 138B, while the remainder of the panel is solid material. In another embodiment, shown in <FIG>, a decompression panel assembly <NUM> is manufactured with a plurality of perforations <NUM> that define apertures <NUM> once they are removed. In such an embodiment, decompression panel assemblies <NUM> are manufactured identical to one another and then modified once its position in aircraft <NUM> is determined. Specifically, once the location is determined, a technician can remove the tabs defined by perforations <NUM> to provide the decompression panel assembly <NUM> with a predetermined array <NUM> of apertures <NUM> that correspond to the determined location.

<FIG> is a front perspective view of an alternative decompression panel assembly <NUM> that may be used in ECS <NUM> (shown in <FIG>). <FIG> is a rear perspective view of decompression panel assembly <NUM>. In the embodiment, decompression panel assembly <NUM> includes a housing <NUM>, a frame <NUM> coupled to housing <NUM>, and an inlet grill <NUM> coupled to frame <NUM>. In another embodiment, inlet grill <NUM> is coupled to housing <NUM>. Housing <NUM> includes at least a top wall <NUM> and a rear wall <NUM>. Decompression panel assembly <NUM> also includes a pair of decompression flaps <NUM> pivotably coupled to rear wall <NUM> via a hinge <NUM>. In the embodiment, each decompression flap <NUM> extends between rear wall <NUM> and one of inlet grill <NUM> or frame <NUM> at an oblique angle such that decompression panel assembly <NUM> is substantially trapezoidal.

<FIG> is a top cross-sectional view of decompression panel assembly <NUM>. In the embodiment, housing <NUM> includes a first inner wall <NUM>, a second inner wall <NUM>, and a plurality of guide vanes <NUM>. Inner walls <NUM> and <NUM> combine with rear wall <NUM> to form a chamber <NUM> that receives airflow through inlet grill <NUM>. More specifically, in normal operation (that is, not during decompression) a return airflow flows through a portion (shown in <FIG>) of inlet grill <NUM>, into chamber <NUM>, and is pulled down through chamber <NUM> by components <NUM> of ECS <NUM>. During normal operation, decompression flaps <NUM> are in a closed position, as illustrated by solid lines in <FIG>, and block airflow through decompression panel assembly <NUM> except through chamber <NUM>. During decompression, a latch <NUM> that attaches the distal end of each decompression flap <NUM> to the inlet grill <NUM> or frame <NUM> is released, and decompression flaps <NUM> pivot via hinge <NUM> to their decompression position, shown in broken lines in <FIG>. In the decompression position, decompression flaps <NUM> open to abut against a sidewall interior <NUM> and to allow airflow through decompression panel assembly <NUM>. During decompression, guide vanes <NUM> direct the incoming airflow at an oblique angle with respect to the angle of the airflow through inlet grill <NUM>. Changing the direction of the airflow prevents recirculation back through inlet grill <NUM> and into cabin <NUM>.

<FIG> is a side cross-sectional view of decompression panel assembly <NUM>, and <FIG> is another side cross-sectional view of decompression panel assembly <NUM> illustrating a pair of example inserts <NUM>. During normal operation, when decompression panels <NUM> are closed, an airflow enters chamber <NUM> through a portion <NUM> of inlet grill <NUM> and is channeled or drawn in a downward direction by the suction forces of components <NUM>. In the embodiment, decompression panel assembly <NUM> includes an insert <NUM> positioned within chamber <NUM> and configured to provide a predetermined flow restriction to the airflow flowing therethrough based on the location of the insert <NUM> along the length of aircraft <NUM> and the proximity of insert <NUM> to various components <NUM> of ECS <NUM>.

Insert <NUM> is removably coupled to housing <NUM> and/or inlet grill <NUM>. More specifically, insert <NUM> is mechanically coupled to at least one wall <NUM>, <NUM>, and <NUM> of housing <NUM> with a fastening mechanism <NUM>. For example, insert <NUM> may be friction fit, attach with fastening mechanism <NUM>, such as a latch, or slide into a slot defined in chamber <NUM>. Generally, insert <NUM> is coupling within chamber <NUM> by any means that facilitates operation of decompression panel assembly <NUM> as described herein.

As described above, decompression panel assemblies <NUM> closest to each component <NUM> of ECS <NUM> will have a higher suction or draw force, also known as a differential pressure, because of the close proximity. In order to prevent or reduce cross-aisle airflow and expose passengers of each aisle <NUM> only to air from their own aisle <NUM>, the mass flow through each decompression panel <NUM>, and each insert <NUM>, specifically, should be the same. Because of the difference in suction forces, each decompression panel assembly <NUM> may have a different airflow restriction based on its location along the length of the aircraft. More specifically, decompression panel assemblies <NUM> positioned closer to components <NUM> of ECS <NUM> include an airflow restriction that is higher than decompression panel assemblies <NUM> spaced from components <NUM>.

As shown in <FIG>, each decompression panel assembly <NUM> includes an insert <NUM> having a predetermined array <NUM> of apertures <NUM> that provide that particular decompression panel assembly <NUM> with a predetermined airflow restriction that will combine with the suction force at the location of the decompression panel assembly <NUM> to result in a mass flow substantially similar to the mass flows of each other aisle <NUM>. As described herein, when each aisle <NUM> has a substantially similar mass flow, cross-aisle airflow is reduced or prevented.

<FIG> illustrates a decompression panel assembly <NUM> and a pair of interchangeable inserts 228A and 229B that each include a predetermined aperture array 234A and 234B, respectively. The number, location, and configuration of arrays 234A and 234B are based on the location of decompression panel assembly <NUM> along aircraft <NUM>. The location along aircraft <NUM> determines the proximity to one of components <NUM> of ECS <NUM> and the corresponding suction force associated therewith. As described herein, decompression panel assemblies <NUM> located closer to components <NUM> will generally have an array <NUM> with a lower number of apertures <NUM>, and decompression panel assemblies <NUM> located farther from components <NUM> will generally have an array <NUM> with a higher number of apertures <NUM>.

The interchangeability of inserts <NUM> allows for all decompression panel assemblies <NUM> to be manufactured independent of the final location of the decompression panel assembly <NUM> on the aircraft <NUM>. Once the location of a particular decompression panel assembly <NUM> is determined, a corresponding insert <NUM> can be positioned within chamber <NUM> that provides the decompression panel assembly <NUM> with the predetermined airflow restriction that combines with the suction force of components <NUM> to result in a mass flow substantially similar to mass flows of decompression panel assemblies <NUM> of surrounding aisles <NUM>.

Examples described include an environmental control system that facilitates minimizing airflow between passengers within confined spaces, such as aircraft passenger cabins. Example systems described provide decompression panel assemblies that include different flow restrictions based on their location along the length of the aircraft and proximity to other components of the environmental control system. In one example, the aircraft includes a first aisle having a first decompression panel assembly with a first array of apertures that define a first airflow restriction. Similarly, a second aisle includes a second decompression panel assembly having a second array of apertures that define a second airflow restriction different than the first airflow restriction. The different air flow restrictions are configured to provide a substantially similar mass flow through both the decompression panel assemblies. Having a similar mass flow through the decompression assemblies in each aisle facilitates limiting cross-circulation between passengers seated in adjacent aisles. Example systems facilitate reducing the spread of airborne contaminants between nearby occupants, reducing noise and undesirable drafts, and limiting the formation of stagnant zones of circulation within the confined space.

The systems and methods described are not limited to the specific embodiments described herein, but rather, components of the systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein.

Although specific features of various embodiments of the disclosure may be shown in some drawings and not in others, this is for convenience only.

As used herein, an element or step recited in the singular and proceeded with the word "a" or "an" should be understood as not excluding plural elements or steps unless such exclusion is explicitly recited. Furthermore, references to "one embodiment" of the present invention or the "example embodiment" are not intended to be interpreted as excluding the existence of additional embodiments that also incorporate the recited features.

Claim 1:
An aircraft (<NUM>) comprising a first row (118A) of seats, a second row (118B) of seats and an environmental control system (<NUM>), the environmental control system comprising:
a first decompression panel assembly (120A) comprised in the first row (118A) of the aircraft and comprising a first array (234A) of apertures (<NUM>) that defines a first airflow restriction,
a second decompression panel assembly (120B) comprised in the second row (118B) of the aircraft and comprising a second array (234B) of apertures (<NUM>) that defines a second airflow restriction different than the first airflow restriction,
at least one component (<NUM>) positioned along a length of the aircraft and designed for drawing air through the first and second decompression panel assemblies;
wherein the first and second arrays of apertures are formed on interchangeable inserts (<NUM>);
wherein the arrays of the decompression assemblies are based on the location of the corresponding decompression panel assembly (<NUM>; <NUM>) along the length of the aircraft relative to the at least one component (<NUM>); and
wherein the first airflow restriction is configured to provide a first mass flow of air through the first decompression panel assembly, wherein the second airflow restriction is configured to provide a second mass flow of air through the second decompression panel assembly and the first mass flow and the second mass flow are substantially similar.