专利汇可以提供RAM AIR FLOW MODULATION VALVE专利检索,专利查询,专利分析的服务。并且An aircraft temperature control system to control a temperature of an environmental control system includes a ram inlet (106) in fluid communication with an external area of the aircraft, and a ram outlet (108) in fluid communication with an internal area of the environmental control system within the aircraft. A heat exchanger assembly (104) is interposed between the ram inlet (106) and the ram outlet (108). A ram air flow modulation valve (114) is disposed downstream from the heat exchanger, and is configured to operate in a plurality of positions to regulate airflow delivered to the ram outlet. An electronic valve control module (116) is in electrical communication with the ram air flow modulation valve and at least one temperature sensor (118). The electronic valve control module (116) is configured to output an electrical signal that adjusts a position of the ram air flow modulation valve based on a temperature value output from the at least one temperature sensor (118).,下面是RAM AIR FLOW MODULATION VALVE专利的具体信息内容。
The present invention relates generally to vehicle environmental control systems, and more particularly, to a ram air flow modulation valve that regulates temperatures in an environmental control system package.
Environmental control systems (ECS) installed in larger commercial aircrafts typically leverage inlet and outlet doors integrated on the exterior skin of the aircraft. With respect to regional (i.e., small commercial) aircraft, however, the ram inlet and ram outlet doors are typically excluded from the outer skin to reduce the overall cost of the aircraft. Consequently, various areas of the ECS package installed in small regional aircrafts are exposed sub-freezing temperatures and can lead to ice accumulation when moisture exists. The resulting accumulation of ice can block the ram heat exchanger inlet, and/or condenser inlet. In turn, the blockages can create unintended high pressure drops within the ECS resulting in reduced ECS flow and imposing damaging loads on one or more components of the ECS.
According to claim 1 of the present invention, a ram air circuit for an environmental control system of an aircraft is provided.
The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
According to various embodiments of the invention, a ram air flow modulation valve is integrated in a ram air circuit of an ECS package installed in an aircraft. In this manner, temperatures of an ECS can be regulated despite the omission of traditional ram doors on the exterior skin of the aircraft. According to an embodiment, the ram air flow modulation valve includes a plurality of louvers that can be opened and or closed based on one or more sensed temperatures of the ECS. In this manner, the position of one or more louvers can be adjusted to control temperatures within the ECS. It should be appreciated that the closed valve position may include a minimum flow area to minimize the risk of fan/air surge. Since the temperatures of the ECS can be regulated using the ram air flow modulation valve, undesirable ACM conditions associated with ice accumulation within the ECS package can be reduced and/or eliminated. For example, the ram air flow modulation valve can regulate temperatures in the ECS package such that ice blockage at the condenser inlet and/or secondary outlet is reduced.
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The ram air circuit 102 is configured to cool bleed air 113 passing through the heat exchanger 104. For example, the bleed air 113 having air temperatures reaching as high as 250 °C may be output from a compressor stage (not shown), for example. The ram inlet 106 directs cool, outside air to the heat exchanger 104. As the bleed air 113 flows through the heat exchanger 104, the temperature of the bleed air 113 is cooled via the cold outside air, before being delivered to an air cycle machine unit integrated the ECS 100 which regulates the temperature and flow of air into the cabin (not shown) to maintain a comfortable environment. In turn, cool air entering the ram inlet 106 is warmed (i.e., exchanged) as it passes through over the bleed air 113. As a result, warm air exits the ram outlet 108 where it is directed to an overboard stage (not shown).
The ram air circuit 102 further includes a ram air flow modulation valve 114 and valve control module 116. The ram air flow modulation valve 114 is interposed between the heat exchanger assembly 104 (e.g., the primary heat exchanger) and the ram outlet 108. Since the ram air flow modulation valve 114 is disposed downstream from the heat exchanger 104, the ram air flow modulation valve 114 typically realizes warmer temperatures than what is realized upstream from the heat exchanger 104 at the ram inlet 106. The ram air flow modulation valve 114 includes a plurality of louvers (not shown in
The valve control module 116 receives temperature readings from one or more temperature sensors 118 disposed in the ECS 100 and/or outer skin of the aircraft, and controls the ram air flow modulation valve 114 to regulate the temperature within the ECS 100. Accordingly, the valve control module 116, temperature sensors 118, and ram air flow modulation valve 114 can form a temperature control system that controls one or more locations of the ECS 100. Although the valve control module 116 is shown to be installed on the ram air flow modulation valve 114, it should be appreciated that the valve control module 116 can be disposed separately and/or remotely from the ram air flow modulation valve 114. The valve control module may include a microprocessor and memory that stores one or more temperature threshold values corresponding to a location of one or more respective temperature sensors 118. In this manner, the valve control module 116 can compare the monitored temperature value from one or more sensors 118 to a respective temperature threshold value and controls the ram air flow modulation valve 114 to obtain a desired temperature at the location of the respective sensors 118. In addition, the valve control module 116 may control the ram air flow modulation valve 114 according to one or more schedules stored in memory. For example, the valve control module 116 may adjust the ram air flow modulation valve 114 into a first position during taxing of the aircraft, while adjusting the ram air flow modulation valve 114 into a second condition that throttles airflow through the ram air circuit 102 during flight.
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A plurality of louvers 120 are disposed sequentially along the length of the housing 122. Each louver 120 includes a first end movably coupled to a first length-side of the housing 122 and a second end movably coupled to a second length-side of the housing 122 located opposite the first length-side. In this manner, each louver 120 is configured to rotate about an axis (A) extending along the width of the housing 122. When fully adjusted into a first position (i.e., fully opened), the louvers 120 define a plurality of air passage 124 therebetween which extend along the width of the housing 122 (see
According to an embodiment, one or more first louvers 120a can be adjusted with respect to one or more second louvers 120b. As shown in
The ram air flow modulation valve 114 further includes one or more actuators 126 and one or more louver position sensors 128. Each of the actuators 126 and each of the louver position sensors 128 are in electrical communication with the valve control module 116. Each actuator 126 is configured to adjust a rotational position of a respective louver 120. Each louver position sensor 128 is configured to determine a rotational position of a respective louver 120 and output an electrical signal indicating the rotational position. In this manner, the valve control module 116 can output a control signal that controls one or more of the actuators 126, and in turn adjusts a position of one or more of respective louvers 120 about the axis (A) such that size of the air passages 124 can be adjusted and air flowing through the ram air flow modulation valve can be regulated. For example, the valve control module 116 can determine a temperature at one or more locations within the ECS and/or at the exterior skin of the aircraft based on the output of a respective temperature sensor (not shown in
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While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
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