• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    An aircraft inlet channel (102) comprising an annular air intake structure defined by an inner surface and an outer surface, a plurality of perforations (110) formed in the outer surface of the inlet channel of aircraft (102), a plenum (202) located within the aircraft inlet channel (102) and configured to receive air entering the plurality of perforations (110), and / or a plurality of sensors (112) disposed around the outer surface of the aircraft inlet channel (102), each sensor (112) being associated with a region of the plurality of perforations (110). Each sensor (112) may include a hot film anemometer. The aircraft inlet channel (102) may further comprise a regulator (204) coupled at one end to the plenum (202) and at another end to a pump (206), the regulator (204) regulating an aspiration produced by the pump (206).
    公开号:FR3020345A1
    申请号:FR1553622
    申请日:2015-04-23
    公开日:2015-10-30
    发明作者:Steven M Kestler；Prithvi Sundar；Yuan Li
    申请人:Rohr Inc；
    IPC主号:
    专利说明:

    [0001] The present disclosure relates to the control of a laminar flow on an aircraft nacelle, and more particularly the control of a laminar flow on the nacelle inlet channel. BACKGROUND Airflow immediately adjacent to the surface of an aircraft nacelle may be referred to as boundary layer airflow. The manner in which the boundary air layer flows over the surface of an aircraft nacelle can impact the operational efficiency of the aircraft. For example, if the boundary layer airflow is not laminar, but turbulent (swirling throughout the boundary layer), the operational efficiency of the aircraft may decrease in response to the drag produced by the boundary layer. turbulent flow (eg frictional drag against the outer surface of the aircraft nacelle). On the other hand, if the flow on the nacelle is laminar, the operational efficiency of the aircraft can be expected to increase as the air in the boundary layer flows smoothly over the nacelle, reducing the trail. SUMMARY An aircraft inlet channel comprising an annular air intake structure defined by an inner surface and an outer surface, a plurality of perforations formed in the outer surface of the nacelle inlet channel, a plenum located within the nacelle inlet channel and configured to receive air entering the plurality of perforations and / or a plurality of sensors disposed around the outer surface of the aircraft inlet channel, each sensor being associated to a region of the plurality of perforations. Each sensor may include a hot film anemometer. The aircraft inlet channel may further comprise a regulator coupled at one end to the plenum and at another end to a pump, wherein the regulator regulates a suction produced by the pump.
    [0002] The aircraft inlet channel may further include a pressure relief member coupled to the pump. Each sensor can be configured to monitor a cooling rate and / or the airflow rate (including its fluctuations) on its surface. The aircraft input channel may further comprise a control unit which receives a signal from each of the plurality of sensors. The control unit can adjust a regulator coupled to a pump to control the suction of the pump. Also disclosed is a nacelle inlet channel comprising an annular air intake structure defined by an inner surface and an outer surface; a perforation formed in the outer surface of the aircraft inlet channel, the perforation being associated with a region of the outer surface of the aircraft inlet channel; a plenum located within the aircraft inlet channel and configured to receive air entering the perforation associated with the region; a pump coupled to the plenum and configured to remove air from the plenum such that air external to the aircraft inlet channel is entrained in the perforation associated with the region; a sensor disposed around the outer surface of the aircraft inlet channel, the sensor being associated with the region of the perforation, wherein a regulator coupled to the pump controls a suction of the pump relative to the region of the perforation . The sensor may be a hot film anemometer, and the hot film anemometer may not interfere with the laminar flow on the outer surface of the air intake structure. The nacelle inlet channel may further include a control unit coupled to the sensor, wherein the control unit receives sensor data associated with an airflow rate on the sensor. The control unit can adjust the regulator based on airflow rate data. The nacelle inlet channel may further include a pressure relief member coupled to the pump. The control unit may increase suction in a region based on a fluctuating air velocity reading and / or may not change suction in a region based on a velocity readout. non-fluctuating air. BRIEF DESCRIPTION OF THE DRAWINGS The object of the present disclosure is clearly indicated in the conclusion of the description. Above all, it is possible to have a more complete understanding of the present disclosure, however, with reference to the detailed description when examined in connection with the figures, wherein like references designate like elements. FIG. 1 illustrates, in accordance with various embodiments, a perspective view of an aircraft nacelle having a plurality of microperforations or apertures distributed around the surface of an aircraft nacelle entry channel; and FIG. 2 illustrates, in accordance with various embodiments, a side sectional view of an aircraft nacelle inlet channel. DETAILED DESCRIPTION The detailed description of exemplary embodiments herewith refers to the accompanying drawings. which show exemplary embodiments for illustrative purposes and their best mode. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the inventions, it is to be understood that other embodiments can be realized and that logical, chemical and mechanical devices may be carried out without departing from the scope of the inventions. Thus, the present detailed description is presented by way of illustration only and not limitation. For example, the steps mentioned in any of the method or method descriptions can be executed in any order and are not necessarily limited to the presented order. In addition, any reference to the singular includes plural embodiments, and any reference to more than one component or more than one step may include an embodiment or a singular step. Likewise, any reference to attached, attached, bound, or the like may include a permanent, removable, temporary, partial, whole, and / or other attachment option. In addition, any reference to "contactless" (or similar expressions) may include reduced contact or minimal contact. A nacelle 100 is shown in FIG. 1. By way of example, a nacelle 100 typically encloses a motor and is positioned outside the engine that propels the aircraft to which it is coupled. The pod 100, as shown, can be divided into four sections generally. These are the inlet channel 102, the fan cowl 104, the thrust reverser 106 and the escapement 108. Although the examples given here relate generally to the front portion of the basket - the channel The structures, systems and methods described herein may apply to any of the sections described above. In various embodiments, the inlet channel may be perforated to form a plurality (possibly millions) of perforations. These perforations can be grouped into regions, as described here. By examining FIG. 1, these perforations are generally represented by the element number 110 (and its associated leading arrow). As the air flows into the boundary layer on the inlet channel 102, it can become turbulent and begin to swirl and spin within the boundary layer. As described above, this turbulence can increase drag which can in turn reduce efficiency. To compensate for this effect, conventional systems have incorporated perforations, such as the perforations 110. The air can be entrained or collected in these perforations by a pump located somewhere within the pod 100. Conventional systems can nevertheless collect the air in the perforations at a constant rate. However, since boundary layer turbulence may vary during flight, aspiration through perforations at a constant rate may not account for these variations. Thus, steady-state suction can, in fact, and in some situations, worsen the boundary layer turbulence. As a result, with continued reference to FIG. 1, a plurality of sensors 112 can be distributed over the surface of a portion of the inlet channel 102. These sensors 112 can measure, at different points around the circumference of the channel. 102, the turbulence occurring around the perforations 110 formed in the inlet channel 102. Specifically, each of a plurality of sensors 112 may be associated with a plurality of perforations defining a region of perforations. In various embodiments, these sensors 112 may include hot-film anemometers. In general, hot film anemometers include very sensitive temperature sensors (see below). As described above, the turbulent air comprises swirling and swirling air in the boundary layer. Thus, as it swirls and swirls, the turbulent air can flow more slowly over the sensors 112 than the air. laminarly flowing over the sensors 112. The slower moving air (e.g., turbulent) may not cool the sensors 112 as efficiently as a laminar airflow. Thus, the sensors 112 can detect these slight changes in their heat exchange or cooling rates to determine whether turbulence is occurring and / or a degree of turbulence. Specifically, during a laminar flow condition in the boundary layer, the air should not substantially swirl and spin in the boundary layer. Thus, during a laminar flow condition, the sensors 112 can detect a relatively constant rate of cooling or heat exchange. On the other hand, as the air velocity changes during turbulent conditions in the boundary layer, the sensors 112 can detect slight changes in their cooling or heat exchange rhythms to determine that turbulent conditions exist. In various embodiments, the sensors 112 may also determine the magnitude of the turbulence based on the rate of cooling or heat exchange experienced by the sensors 112. In addition, since any number of sensors 112 may be distributed around the circumference of the inlet channel 102, it is possible to detect laminar and turbulent flow conditions on any number of regions or sections of the nacelle inlet channel 102. To detail, anemometers may be used hot film film for measuring the instantaneous velocity of a flowing fluid, such as air. Hot-film anemometers typically comprise a film comprising a material having a high thermal coefficient of resistance such as, for example, platinum, tungsten, etc. Temperature variations can be measured in several ways. For example, a feedback system may attempt to maintain a constant current through the anemometer (corresponding to a constant anemometer temperature). As the current required to maintain the temperature of the anemometer varies, a measure of turbulence can also be obtained. In addition, in various embodiments, the sensor can transmit a signal indicating a level of turbulence to the cockpit and / or otherwise to a pilot. Put differently, the sensor 112 can detect the amount of heat that is evacuated by the air flowing on it. For example, as air flowing over the sensor 112 moves more slowly, it dissipates less heat as faster moving air expels more heat. The sensor 112 is able to capture this because it can be set at a constant temperature above that of the air temperature, and as it tries (by a feedback loop, as described here) to maintain this temperature under different conditions, the signal it sends can represent the amount of energy it takes to maintain this temperature. When this signal is almost constant, the flow on the sensor 112 is laminar because the velocity is generally constant in a laminar flow. Nevertheless, when the signal is erratic, the flow is turbulent because there is a mixture of high and low speed air on the sensor affecting the amount of heat dissipation from the anemometer. In general, hot-wire and hot-film anemometers may be soldered, soldered, epoxidically and nacelle-like, and may, in the form of a film, include thicknesses between 1 micron and 5 microns. In addition, in various embodiments, a protective coating may be placed on each sensor 112, particularly when the heat transfer coefficient is known. The protective coating may be resistant to lightning strikes as well as other damaging conditions (eg bird strike). Hot film anemometers can thus comprise slices or films of very fine material. Thus, the positioning of the sensors 112 of this type on the outer surface of the inlet channel 102 may not interfere with the flow of air on the outer surface of the nacelle 100. In other words, sensors 112 may do not interrupt the laminar flow on the outer surface of the nacelle 100. The outer surface of the nacelle 100 can be defined as the surface of the nacelle 100 most radially distant from a center line of the nacelle 100. In other words, as a nacelle 100 includes a thickness, the inner surface of the nacelle 100 may be radially closer to the engine, while the outer surface may, relative to the inner surface, be radially further away from the engine. In addition, sensors 112 of this type may not be as sensitive to ambient noise and be more convenient to implement than many other types of turbulence sensors, such as microphones, which can perform inaccurate turbulence readings based on on the ambient noise. Similarly, hot film anemometers may not require the hardware and space required by sensors such as microphones placed within or without the pod, and are, in addition, lighter than other types of sensors. which reduces the weight associated with such systems. Referring now to FIG. 2, there is shown a sectional view of an inlet channel 102. As shown, the inlet channel 102 may comprise the plurality of perforations 110 as well as the sensor 112 (again, each of a plurality of perforations may be associated with a particular sensor, the plurality of perforations thus comprising a region within which a temperature may be determined). The inlet channel may further comprise, in its thickness, one or more plenums 202 (each associated with a region of perforations). The fan cowl 104 and / or the inlet channel 102 may also comprise one or more valves and / or regulators 204 (each associated with a region of perforations), a pump 206, a pressure relief element 208 and / or or a control unit or microcontroller 210. In various embodiments, the amount of air entrained through the perforations is calibrated to be optimal (i.e. not too large and not too small) for maintain a laminar flow on the surface of the nacelle 100. In various embodiments, it may be possible to determine that a system malfunction has occurred, for example, by determining a substantial turbulence area, which could be caused by the adherence of an insect or other debris on the outer surface of the pod 100. The valves and / or regulators 204, the pump 206 and a pressure relief member 208 and / or the control unit 21 Alternatively, any of these structures may be disposed on an inner surface of the inlet channel 102 and / or the blower hood 104. In various modes of the invention, any of these structures may be disposed on an inner surface of the inlet channel 102 and / or the blower hood 104. In that embodiment, the pump 206 may be coupled between a regulator 204 and the pressure relief member 208 and in fluid communication therewith, such as by a channel or a piece of tubing 212. A plenum 202 may be coupled to a regulator 204 and in fluid communication therewith by a similar or identical type of channel or tubing end 212. In operation, the pump 206 may drive air through a plurality of perforations and from a chamber. 202 associated with these perforations to create a pressure differential between a plenum 202 and the outer surface of the nacelle 100. When this occurs, the air in the boundary layer can be entrained in the plenum 202 through the plurality of perforations 110 in the inlet channel surface 102 to soothe eddy currents and turbulence in the boundary layer A sensor 112 disposed near the plenum 202 can detect a quantity or level of turbulence occurring in the vicinity of the sensor 112, outputting this reading to the control unit 210 which can, based on a preprogrammed instruction set, adjust, via the regulator 204, the quantity the suction pump applied to the plenum 202 by the pump 206. For example, when a sensor 112 reads a substantial velocity fluctuation in the boundary layer (indicating turbulence around the location of the sensor 112), the sensor 112 can deliver this data to the control unit 210, which can cause the regulator 204 to increase the suction applied by the pump 206. Similarly, when the sensor 11 2 reads a relatively constant fluid velocity in the boundary layer, the sensor 112 can deliver these data to the control unit 210, which can cause the regulator 204 to decrease, eliminate or leave unchanged the suction applied by the pump 206. As the air passes through the pump 206, it can continue to pass through a channel or tube 212 to exit the nacelle 100 via the pressure evacuation member 208. In addition, as described above, above, a plurality of sensors 112 may be placed around the circumference of the inlet channel 102, each associated with a particular perforated region of the inlet channel 102. Thus, each sensor 112 may provide a localized survey, thereby enabling regulation localized suction pump 206 around the circumference of the input channel 102. A control unit 210 may include a computing device (for example a processor) and an associated memory. The memory may comprise a manufactured article including a tangible and non-transitory computer readable storage medium on which are stored instructions which, in response to execution by a computing device (eg a processor), bring the computing device to perform various instructions. Benefits, other benefits, and solutions to problems have been described herein in connection with specific embodiments. In addition, the connecting lines shown in the various figures contained herein are intended to represent examples of functional relationships and / or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. Nevertheless, the benefits, advantages, solutions to problems and all elements that may cause the occurrence or enhancement of any benefit, advantage or solution should not be interpreted as critical, required or essential features or elements of the inventions. According to the present invention, a reference to an element in the singular is not meant to mean "one and only one" unless explicitly stated otherwise, but rather "one or more". In addition, when an expression similar to "at least one of A, B or C" is used, the expression should be interpreted to mean that A alone may be present in one embodiment, B alone may be present in one embodiment, only C may be present in one embodiment, or any combination of the elements A, B and C may be present in only one embodiment; for example A and B, A and C, B and C, or A and B and C. Different hatches are used throughout the figures to designate different parts but not necessarily to designate identical or different materials. Systems, methods and apparatus are provided here. In the present detailed description, references to "various embodiments", "an embodiment", "an exemplary embodiment", etc., indicate that the described embodiment may include a feature, structure or a particular feature, but each embodiment may not necessarily include the particular feature, structure or feature. Moreover, such expressions do not necessarily refer to the same embodiment. In addition, where a particular feature, structure or feature is described in relation to an embodiment, it is believed that it is within the skill of a person skilled in the art to assign such a feature, structure or feature to other embodiments, whether or not explicitly described. After reading the description, the manner of implementing the disclosure in alternative embodiments will be apparent to those skilled in the art. As used herein, the terms "includes", "including" or any variations thereof, are intended to cover a non-exclusive inclusion, such that a method, method, article or apparatus that includes a The list of elements does not only include these elements but may include other elements not expressly listed or inherent in such a method, method, article or apparatus.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. A nacelle inlet channel (102) comprising: an annular air intake structure defined by an inner surface and an outer surface; a perforation (110) formed in the outer surface of the inlet channel (102); a plenum (202) located within the inlet channel (102) and configured to receive air entering the perforation (110); and a sensor (112) disposed around the outer surface of the inlet channel (102), the sensor (112) being associated with the perforation (110).
    [0002]
    The nacelle inlet channel of claim 1, wherein the sensor (112) comprises a hot-film anemometer.
    [0003]
    The nacelle inlet channel of claim 1 or 2, further comprising a regulator (204) coupled to a first end to the plenum (202) and a second end end to a pump (206), in a wherein the regulator (204) controls a suction produced by the pump (206).
    [0004]
    The nacelle inlet channel of claim 3, further comprising a pressure relief member (208) coupled to the pump (206).
    [0005]
    The nacelle inlet channel according to any one of the preceding claims, wherein the sensor (112) is configured to monitor air velocity fluctuations within the boundary layer.
    [0006]
    The nacelle inlet channel according to any one of the preceding claims, further comprising (210) a control unit which receives a signal from the sensor (112).
    [0007]
    The nacelle inlet channel of claim 6, wherein the control unit (210) adjusts a regulator (204) coupled to a pump (206) to control a pump suction (206). .
    [0008]
    A nacelle inlet channel (102) comprising: an annular air intake structure defined by an inner surface and an outer surface; a perforation (110) formed in the outer surface of the inlet channel (102), the perforation (110) being associated with a region of the outer surface of the inlet channel (102); a plenum (202) located within the inlet channel (102) and configured to receive air entering the perforation (110) associated with the region; a pump (206) coupled to the plenum (202) and configured to remove air from the plenum (202) such that air external to the inlet channel (102) is entrained in the perforation (110) associated with the region; a sensor (112) disposed around the outer surface of the inlet channel (102), the sensor (112) being associated with the region of the perforation (110), wherein a regulator (204) coupled to the pump (206) ) controls suction of the pump (206) relative to the region of the perforation (110).
    [0009]
    The nacelle inlet channel of claim 8, wherein the sensor (112) is a hot film anemometer.
    [0010]
    The nacelle inlet channel of claim 9, wherein the hot-film anemometer does not interfere with laminar flow on the outer surface of the air intake structure.
    [0011]
    The nacelle inlet channel according to claim 8, 9 or 10, further comprising a control unit (21) coupled to the sensor (112), wherein the control unit (210) receives data from the sensor ( 112) associated with an airflow rate on the sensor (112).
    [0012]
    The nacelle inlet channel of claim 11, wherein the control unit (210) adjusts the controller (204) based on airflow velocity data.
    [0013]
    The nacelle inlet channel of any one of claims 8 to 12, further comprising a pressure relief member (208) coupled to the pump (206).
    [0014]
    The nacelle inlet channel of any one of claims 8 to 13, wherein the control unit (210) increases suction in a region based on a fluctuating air velocity reading.
    [0015]
    The nacelle inlet channel according to any one of claims 8 to 14, wherein the control unit (210) provides no change to the suction in a region based on a speed reading. non fluctuating air.
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    同族专利:
    公开号 | 公开日
    FR3020345B1|2018-07-13|
    US9789954B2|2017-10-17|
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    法律状态:
    2016-03-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-24| PLSC| Search report ready|Effective date: 20170224 |
    2017-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/262,319|US9789954B2|2014-04-25|2014-04-25|Method of controlling boundary layer flow|
    US14262319|2014-04-25|
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