Aircraft outflow valve

Outflow valves for use in an aircraft are described. In one example, an outflow valve for use in an aircraft includes a frame configured for coupling to an aircraft and a gate pivotally coupled to said frame. The frame includes a forward flange extending above the frame. The gate is pivotally moveable between a closed position to substantially block airflow between an interior of the aircraft and an exterior of the aircraft and an exhaust position to direct airflow from the interior toward the exterior of the aircraft. The forward edge of the gate is located adjacent the frame forward flange as the gate is pivoted between the closed position to the exhaust position.

BACKGROUND

The field of the disclosure relates generally to valves, and more specifically to outflow valves for use in an aircraft.

In aircraft pressurizing and ventilating systems, an air pressure source is typically provided to supply pressurized air to the cabin. Air pressure within the cabin is maintained at the required pressure by controlling the flow of air from the cabin through one or more outflow valves positioned in an opening or openings defined in the body of the aircraft. Air provided by the air pressure source is sometimes also used to cool various electronic devices within the aircraft.

Failures interrupting the supply of pressurized air from these air pressure sources may result in increased cabin temperatures, increased cabin humidity, an increased concentration of undesired gasses (such as carbon dioxide), and/or an increased likelihood of overheating equipment. Consequently, at least some aircraft include an alternate air supply device for use in ventilating the aircraft and cooling the electronic control and navigation devices in the event of a failure of the primary pressurized air system. However, alternate air supply systems generally increase the cost, weight, and complexity of an aircraft.

BRIEF DESCRIPTION

In one aspect, an outflow valve for use in an aircraft is provided. The outflow valve includes a frame configured for coupling to an aircraft and a gate pivotally coupled to the frame. The frame defines an interior direction towards an interior of the aircraft, and an exterior direction towards an exterior of the aircraft. The gate is configured for pivotal movement between a closed position and an exhaust position to direct airflow from the interior of the aircraft to the exterior of the aircraft. A forward portion of the frame includes a flange extending in the interior direction to maintain a limited gap between a forward edge of the gate and the frame forward portion while the gate is pivotally moved between the closed position and the exhaust position.

In another aspect, an outflow valve for use in an aircraft includes a frame configured for coupling to an aircraft and a gate pivotally coupled to said frame. The frame includes a forward flange extending above the frame. The gate is pivotally moveable between a closed position to substantially block airflow between an interior of the aircraft and an exterior of the aircraft and an exhaust position to direct airflow from the interior toward the exterior of the aircraft. The forward edge of the gate is located adjacent the frame forward flange as the gate is pivoted between the closed position to the exhaust position.

In yet another aspect, a method of exhausting air from an aircraft is described. The method includes pivotally opening a gate coupled to a frame of an outflow valve from a closed position substantially parallel with an external surface of an aircraft to an exhaust position defining an angle to the external surface of the aircraft greater than zero to permit airflow from an interior of the aircraft to an exterior of the aircraft between the frame and a rear edge of the gate. The method includes maintaining a substantially constant gap between a forward edge of the gate and a flange extending from the frame toward an interior of the aircraft to substantially minimize airflow into the interior of the aircraft between the forward edge of the gate and the frame.

DETAILED DESCRIPTION

Exemplary outflow valves are described herein. The exemplary outflow valves described herein provide greater net airflow than some known outflow valves. Moreover, the exemplary outflow valves limit the amount of air that flows through the valve opposite to a direction that is the desired direction of flow, and thus provide a greater net airflow at each valve. The increased airflow may provide sufficient airflow for ventilation and cooling in an aircraft during a loss of inflow condition such that a separate backup system is not needed. As such, the outflow valves described herein may reduce the cost, the complexity, and/or the weight of an associated aircraft.

Referring more particularly to the drawings, embodiments of the disclosure may be described in the context of an aircraft100as shown inFIG. 1. In the exemplary embodiment, aircraft100includes a forward outflow valve102and a rearward or aft outflow valve104coupled by an airflow conduit106. Outflow valves102and104are used to control the flow of air out of aircraft100. The airflow controlled by outflow valves102and104may be used to control the climate, including the air pressure, within aircraft100, and/or to ventilate and/or cool electronics (not shown) within aircraft100. Moreover, in the event of failure of one or more other systems, such as the aircraft air conditioning systems (not shown), outflow valves102and104may be one of the only sources of air flow into and through aircraft100via airflow conduit106.

During a Loss of Inflow (LOI) condition (e.g., cabin depressurization condition during the malfunction of the air-conditioning packs), the airflow used for the occupants of the airplane and for the cooling of the electronic equipment may be provided through outflow valves102and104. More specifically, one valve102or104(typically rear valve104) will be in an intake or scoop configuration (not shown inFIG. 1) and the remaining valve104or102(typically forward valve102) will be in an exhaust configuration (not shown inFIG. 1). More specifically, the exhaust configuration and scoop configuration will be further described below with reference toFIGS. 2-9. During such a condition, air generally enters the aircraft through the outflow valve102or104in the scoop configuration, and exits aircraft100through outflow valve104or102in the exhaust configuration. In each configuration, however, outflow valves102and104may allow air to enter or exit aircraft100in addition to the desired exhaust or intake of air by that particular outflow valve102or104. Thus, each valve102and104has a net airflow, i.e. the difference between the airflow into and out of that particular valve102or104. Further, the airflow through aircraft as a result of outflow valves102and104is a result of the net airflow for each valve102and104and the net airflow between valves102and104. The net airflow between outflow valves102and104generally depends on the pressure differential at the location of each valve102and104. Various embodiments of outflow valves described herein may provide increased net airflow for individual outflow valves as compared to some known valves, such that total airflow thorough aircraft100is facilitated to be increased.

FIGS. 2-5each illustrate an exemplary outflow valve200for use in an aircraft, such as aircraft100. More specifically,FIG. 2is a perspective view of outflow valve200in an exhaust configuration201andFIG. 3is a simplified cross-sectional side view of outflow valve200in the exhaust configuration201.FIG. 4is a simplified cross sectional side view of outflow valve200in a closed configuration203.FIG. 5is a simplified cross sectional side view of outflow valve200in a scoop configuration205.

Generally, outflow valve200controls airflow interchange between an interior of aircraft100and an exterior of aircraft100. When installed in aircraft100and in the closed configuration203(shown inFIG. 4), valve200substantially prevents air from flowing into or out of aircraft100through outflow valve200. Air from inside aircraft100is exhausted to the exterior of aircraft100when valve200is in the exhaust configuration201(shown inFIGS. 2 and 3). Conversely, when in the scoop configuration205(shown inFIG. 5), outflow valve200directs external air into aircraft100.

In the exemplary embodiment, outflow valve200includes a frame202, a ground gate204, a control gate207, and an actuator206. Moreover, in the exemplary embodiment, frame202includes a forward portion208, a rearward portion210, and a pair of opposing sides212that extend between forward portion208and rearward portion210. Frame202is configured for mounting to aircraft100and defines an interior direction214towards an interior of aircraft100, and an exterior direction216towards exterior of aircraft100.

Gate204includes a forward edge220, an aft or rearward edge222(shown inFIG. 3), an inner surface224, and an outer surface226. Because gate204is pivotally coupled to frame202, forward edge220is not always located closer to forward portion208than to rearward portion210. For example, in the scoop configuration205(shown inFIG. 5), forward edge220is closer to rearward portion210than forward portion208. Similarly, inner surface224and outer surface226are not always oriented towards an interior or exterior, respectively, of aircraft100in all configurations. The terms “forward”, “rearward”, “inner”, and “outer” are generally assigned based on the closed configuration203(shown inFIG. 4) of outflow valve200. More specifically, when gate204is in the closed position203, forward edge220is located adjacent the forward portion208, rearward edge222is located adjacent to the rearward portion210, inner surface224is oriented towards interior direction214, and outer surface226is oriented towards exterior direction216.

In the exemplary embodiment, frame202includes a flange228that extends inwardly214from frame forward portion208. When gate204is in a position other than the closed position203, a gap230(shown inFIGS. 3 and 5) is defined between forward edge220and flange228. Flange228is configured, e.g., sized, shaped, etc., to limit the size of gap230when gate204is moved between the closed position203and the exhaust position201. With reference toFIG. 3, in the exhaust position201, airflow from the interior of aircraft100is exhausted to the exterior of aircraft100in exhaust direction232. The air being exhausted passes between gate204inner surface224and control gate207at frame202rearward portion210. Air from outside aircraft100may attempt to flow into the interior of aircraft100through gap230. Flange228facilitates minimizing an amount of external air that may flow into aircraft100through outflow valve200when outflow valve200is not in an intake or scoop configuration205. It should be noted that, flange228may be a monolithic portion of frame202, may be formed integrally with frame202, or may be a separately coupled to frame202.

As shown inFIG. 2, in the exemplary embodiment, flange228extends from forward portion208around a portion of sides212. Thus, in addition to limiting gap230, flange228also limits the size of gaps (not shown) defined between gate204and sides212when gate204is moved between the closed position203and the exhaust position201. In other embodiments, flange228may not extend around sides212and/or may extend further along sides212than is illustrated.

With reference toFIG. 3, in the exhaust configuration201gate204is positioned at an opening angle234of about forty-five degrees relative to frame202. In other embodiments, opening angle234may be smaller or larger than forty-five degrees. Moreover, in some embodiments, opening angle234may be selectively varied to facilitate controlling the flow of air from the interior of aircraft100to the exterior of aircraft100. Flange228generally extends to limit gap230for a range of opening angles234from about zero degrees to the maximum opening angle234of each particular embodiment.

Outflow valve200includes a rear cover236. As shown inFIGS. 2-4, rear cover236is generally maintained a distance from gate204when outflow valve200is in the closed and/or exhaust configurations203(shown inFIG. 4) and 201(shown inFIGS. 2 and 3), respectively. When outflow valve200is in the scoop or intake configuration205(shown inFIG. 5), however, rear cover236is used to facilitate minimizing an amount of air exhausted from interior of aircraft100through outflow valve200. When valve200is in the scoop configuration205, gate204is pivoted such that forward edge220is closer to frame rearward portion210than to frame forward portion208, and gap230, defined between forward edge220and flange228, is relatively large. A rearward gap238defined between forward edge220and control gate207is substantially closed by rear cover236. In this configuration, air from outside aircraft100is scooped into aircraft100in the intake direction240and flows between gate outer surface226and frame forward portion208. Rear cover236may have any shape suitable for substantially closing rearward gap238including, for example, a flat shape, a curved shape, a convex shape, a concave shape, etc.

Another exemplary outflow valve300is shown inFIGS. 6-9. Outflow valve300is similar to outflow valve200and the same reference numerals will be used to identify common components.FIG. 6is a simplified cross-sectional side view of exemplary outflow valve300installed in aircraft100, and in a closed configuration303.FIG. 7is a side view of exemplary outflow valve300in an exhaust configuration301.FIG. 8is a simplified cross-sectional side view of outflow valve300in the exhaust configuration301.FIG. 9is a simplified cross-sectional side view of outflow valve300in a scoop configuration305.

Outflow valve300includes a flange328extending inwardly214from frame forward portion208. Unlike exemplary flange228, flange328is curved. More specifically, flange328is curved to substantially match a path, or arc, traced by gate forward edge220when gate204moves between the closed position303(shown inFIG. 6) and the exhaust position301(shown inFIGS. 7 and 8). Thus, flange328limits gap230when gate204moves between the closed position303and the exhaust position301, and limits inflow of air through gap230. Moreover, because flange328is curved to substantially match the path of forward edge220, gap230remains substantially constant, and relatively small, for all opening angles234between the closed position303and the exhaust position301. It should be noted that flange328may be a monolithic portion of frame202, may be integrally constructed with frame202, or may be a separately coupled to frame202.

As shown inFIG. 7, in the exemplary embodiment, flange328extends from forward portion208around a portion of sides212. Thus, in addition to limiting gap230, flange328limits the size of gaps (not shown) defined between gate204and sides212when gate204is moved between the closed position303and the exhaust position301. In other embodiments, flange328may not extend around sides212, and/or may extend further along sides212than is illustrated.

With reference toFIG. 7, in the exhaust configuration301, gate204is positioned at an opening angle234of about forty-five degrees relative to frame202. In other embodiments, opening angle234may be smaller or larger than forty-five degrees. Moreover, in some embodiments, opening angle234may be selectively varied to control the flow of air from the interior of aircraft100to the exterior of aircraft100. Flange328generally limits gap230for a range of opening angles234from zero degrees to the maximum opening angle234of each particular embodiment.

The above described outflow valves provide greater net airflow than is possible in at least some known outflow valves. The exemplary outflow valves limit the amount of air that flows through the valve in the opposite direction to the desired direction of flow. Thus, a greater net airflow is achieved at each valve, and the net airflow through the associated aircraft is facilitated to be increased. Moreover, the increased net airflow may provide sufficient airflow for ventilation and cooling in an aircraft during a loss of inflow condition such that a separate backup system is not needed. Elimination of a backup ventilation system may reduce the cost, complexity, and/or weight of an aircraft including the exemplary outflow valves described herein.