阅读说明：本技术 用于引擎机舱的自适应流控制 (Adaptive flow control for nacelle ) 是由 布拉德利·J·拉弗蒂 马修·C·德福雷 阿里·格列泽尔 博扬·武卡西诺维克 德雷克·A·尼科 于 2021-05-07 设计创作，主要内容包括：本公开涉及用于引擎机舱的自适应流控制。一种入口流畸变控制系统采用形成集成在入口内表面中的至少一个阵列的多个流控制装置。至少一个阵列相对于入口的法向流动轴在方位角范围上延伸,并且具有与入口的突出部分以增加的距离间隔开的多个周向行。控制系统可操作地连接到流控制装置,并且适于响应于预定的飞行状况来激活阵列的所选子阵列中的流控制装置。(The present disclosure relates to adaptive flow control for a nacelle. An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated in an inner surface of an inlet. At least one array extends in an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distances from the protruding portion of the inlet. The control system is operatively connected to the flow control devices and adapted to activate the flow control devices in selected sub-arrays of the array in response to predetermined flight conditions.)

1. An inlet flow distortion control system comprising:

a plurality of flow control devices integrated in an inner surface of the inlet, forming at least one array extending azimuthally with respect to a normal flow axis of the inlet and having a plurality of circumferential rows spaced at increasing axial distances from a protruding portion of the inlet; and

a control system operably connected to the plurality of flow control devices, the control system adapted to activate the flow control devices in selected sub-arrays of the at least one array in response to an inlet flow condition indicated by a predetermined flight condition or a flow parameter measured within the inlet.

2. The inlet flow distortion control system of claim 1, wherein the at least one array comprises a right array having an azimuth angle range determined based on a right side wind flow separation domain and a left array having an azimuth angle range determined based on a left side wind flow separation domain.

3. The inlet flow distortion control system of claim 1 or 2, wherein the at least one array comprises an array extending over a range of azimuth angles of a bottom of the inner surface of the inlet to accommodate control of flow distortion due to high angles of attack or ground vortices.

4. The inlet flow distortion control system of claim 2, wherein the left and right arrays each include a plurality of circumferential rows spaced at increasing first, second, third, and fourth axial distances from the projecting portion of the inlet.

5. The inlet flow distortion control system of claim 4, wherein, for each of the right and left arrays, a first one of the plurality of circumferential rows includes flow control devices extending over the azimuthal extent of each of the right and left arrays, a second one of the plurality of circumferential rows includes flow control devices extending over a reduced azimuthal extent of each of the right and left arrays, and a third one of the plurality of circumferential rows includes flow control devices extending over a further reduced azimuthal extent of each of the right and left arrays.

6. The inlet flow distortion control system of claim 5, wherein the control system comprises:

a controller that receives a status signal or condition input for crosswind or angle of attack;

a mass flow input to the controller; and

one or more activation devices receiving an output signal from the controller in response to the mass flow input and the status signal or the condition input, the one or more activation devices configured to activate a flow control device in one of the selected subarrays.

7. The inlet flow distortion control system of claim 6, wherein the one or more activation devices comprise:

one or more concentric cylinders spaced between the inner surface of the inlet and a pressure chamber, the one or more concentric cylinders having an array of apertures rotatable from a closed position into alignment with one or more rows of control jets; and the number of the first and second groups,

a pressure source connected to the pressure chamber.

8. The inlet flow distortion control system of claim 7, wherein the pressure source is an exhaust system.

9. The inlet flow distortion control system of claim 7, wherein the one or more concentric cylinders comprise a plurality of concentric cylinders, each concentric cylinder aligned with a respective one of the one or more rows of control jets to open one of the selected subarrays to the pressure chamber.

10. The inlet flow distortion control system of claim 6, wherein the one or more activation devices comprise one or more valves, each valve connecting a respective flow control device of the plurality of flow control devices.

11. The inlet flow distortion control system of claim 10, further comprising at least one manifold connecting one of the one or more valves to a selected sub-array of the at least one array of the plurality of flow control devices.

12. The inlet flow distortion control system of claim 6, wherein the plurality of flow control devices each comprise a synthetic jet, and further comprising:

power is connected to each synthetic jet; and the number of the first and second groups,

a horizontal controller, connected to each synthesis jet through the repeater, is controllable to generate a selected sub-array of the at least one array.

13. The inlet flow distortion control system of any of claims 6-12, wherein the plurality of flow control devices each comprise an expanded vortex generator, and wherein the one or more activation devices each comprise a solenoid operator.

14. A method for flow control in a spout inlet, the method comprising:

receiving the status signal and the mass flow signal in the controller;

providing a control output from the controller to one or more of a plurality of flow control devices in an array on an inner surface of an inlet in response to the status signal and the mass flow signal; and

reducing flow distortion in the inlet.

15. The method of claim 14, further comprising:

receiving, in the controller, a condition signal from one or more condition sensors; wherein the step of reducing flow distortion comprises

Modulating the plurality of flow control devices to form subarrays responsive to the mass flow signal or condition signal to optimize reduction of flow distortion in the inlet.

16. The method of claim 15, wherein modulating the plurality of flow control devices comprises selectively aligning concentric cylinders with an array of orifices to connect respective sub-arrays of the plurality of flow control devices to a pressure source.

17. The method of claim 15, wherein modulating the plurality of flow control devices comprises:

is selectively opened

A pressure source and one or more of the plurality of flow control devices to form the sub-array, or

A pressure source and one or more manifolds connected to the subarrays of the plurality of flow control devices.

18. The method of claim 15, wherein the plurality of flow control devices includes a synthesizing device, and modulating the plurality of flow control devices includes selectively activating the synthesizing device to form the subarray.

19. The method according to any of claims 15-18, wherein the plurality of flow control devices includes an expanded vortex generator and the step of modulating the plurality of flow control devices includes selectively expanding and collapsing the expanded vortex generators to form the sub-array.

Technical Field

The present invention relates generally to the field of aircraft fan jet propulsion employing an inlet having a low ratio of inlet length to engine fan diameter (L/D), and more particularly to an inlet flow control system employing an array of flow control devices on the inner surface of the fan inlet for mitigating flow distortion in the inlet at low speed operation due to crosswind, high angle of attack, and ground vortices.

Background

Modern commercial aircraft have primarily employed fan jet engines. Current inlet designs have high inlet length to engine fan diameter (L/D) values. Greater than 0.5L/D is typical of current engines to maintain the desired flow profile of the fan surface during crosswind and other flight conditions. Future entrances are expected to employ L/D lower than 0.5. The lower limit of L/D appears to exist in current inlet design capabilities based on the inlet length required to mitigate inlet inflow distortion under low speed takeoff and landing conditions. However, an L/D less than the current lower limit will aerodynamically improve all other parts of the mission (97% mission profile of a 1 hour commercial flight profile). The improved aerodynamic performance reduces fuel consumption of the aircraft due to the lower L/D. Current inlet designs meet the above-described low speed takeoff and landing requirements (typical commercial aircraft fly for about two minutes) and are therefore over-designed during the climb/cruise/descent flight phase. This "over-design" can result in a penalty in fuel consumption for the remainder of the overall mission due to increased drag and weight.

Current flow control solutions applied to aircraft inlets provide a non-modular design with a fixed flow control device configuration. Any given flow control input may become less efficient (or may be ineffective) due to the fact that the separated flow regions are dynamic and may move within the inlet. Thus, existing flow control solutions may "lack" a separation region. Such a system configuration requires that, in order to continue to successfully oppose flow separation under different flight conditions, the output of the flow control system be increased, thereby increasing the input (e.g., higher input mass flow rate for a pneumatic flow control system). Thus, such systems may impact size, weight, and power requirements.

Disclosure of Invention

An exemplary embodiment of an inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an inner surface of an inlet. At least one array extends in an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distances from a projection (highlight) of the inlet. The control system is operatively connected to the flow control devices and adapted to activate the flow control devices in selected sub-arrays of the array in response to predetermined flight conditions.

The exemplary embodiments provide a method for flow control in a low L/D fan injection inlet. A status signal and a mass flow signal are received in a controller. In response to the status and mass flow signals, control outputs from the controller are sent to one or more of the plurality of flow control devices in the array on the inner surface of the inlet and flow distortion in the inlet is reduced.

Drawings

The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments further details of which can be seen with reference to the following description and drawings.

FIG. 1 is a diagrammatic view of a commercial aircraft having a high bypass ratio turbofan engine in which an exemplary embodiment of nacelle adaptive flow control is employed;

FIG. 2 is a diagrammatic view of a nacelle inlet illustrating an array of flow control devices employed in an exemplary embodiment;

FIG. 3 is a schematic plan view of a lateral array of flow control devices implemented on a corner segment (angular segment) of an inlet;

FIG. 4 is a representation of flow distortion patterns in the inlet at various mass flow rates and crosswind conditions;

FIG. 5 is a graph of inlet distortion coefficients for no crosswind and 30 knots crosswind conditions;

6A-6C are schematic plan views of sub-arrays of flow control devices for activation for cross-wind compensation at different mass flow rates;

FIGS. 7A-7C are graphs of maximum entry distortion coefficients corresponding to the activation of the subarrays of FIGS. 6A-6C;

FIG. 8A is a graph of maximum inlet distortion correction by activating different subarrays at a selected mass flow rate;

FIG. 8B is a representation of improved flow distortion patterns in the inlet at various inlet mass flow rates with 30kt crosswind conditions and applied control as shown in FIG. 8A;

FIG. 9 is a plan schematic view of a bottom array of flow control devices for flow control in a high angle of attack or ground vortex scenario;

FIG. 10 is a block diagram of an example control system;

11A-11D are representations of concentric cylinders spaced between the inlet inner surface and the pressure chamber for controlling the jet actuation of a flow jet as a flow control device;

11E-11O are representations of annular perforated plates that control flow communication through conduits between the inlet inner surface and the pressure chamber for controlling jet actuation of flow jets as flow control devices;

FIG. 12 is a representation of individual control of the flow jets forming an array of flow control devices;

FIG. 13 is a representation of control of a manifold flow jet as a flow control device;

FIG. 14 is a representation of the control of a single synthesis jet forming an array of flow control devices;

FIG. 15 is a representation of the control of a single expanded vortex generator as an array of flow control devices; and

FIG. 16 is a flow chart of a method for flow control in a low L/D fan injection inlet.

Detailed Description

Embodiments described herein provide one or more azimuthal radial flow control device arrays integrated at an inner surface of an inlet. The total azimuthal-radial coverage of the flow control array is determined based on the flow separation domain over the full flight envelope, and a subset of the array or control configuration may be activated under the flow conditions of a particular implementation.

Referring to the drawings, FIG. 1 depicts a large commercial aircraft 10 employing a high bypass ratio turbofan engine 12 with an ultra-short nacelle 14, wherein embodiments as described herein are employed. Although the embodiments described herein relate to commercial aircraft, the present disclosure is applicable to any low L/D application or other inlet having asymmetric flow distortion. As seen in fig. 2, a plurality of flow control devices 16 are integrated into the inner surface 18 of the inlet 20 of the ultra-short nacelle 14, forming one or more arrays (described in more detail below) extending axially rearward from a ledge 21 (or edge) of the inlet. The inlet 20 has a normal flow axis (normal flow axis) 15. As defined herein, a "flow control device" may include a combination of a pneumatic jet, a fluidic oscillator, a stable jet, an unsteady pulsed jet, a non-pneumatic based flow control system, and a zero net mass flow device, such as an electronic synthetic jet or an identification system. In alternative embodiments, an array of deployable vortex generators or other mechanical devices (pins, etc.) may replace the holes of the fluid jets. These devices can be stowed flush with the inner surface of the inlet and then deployed in a pattern within the array to achieve the desired flow pattern. Such mechanisms may also be deployed and stowed periodically at varying frequencies. A control system (described in more detail later) operatively connected to the flow control devices 16 is adapted to activate or modulate the flow control devices in the selected sub-array in response to inlet flow conditions indicated by predetermined flight conditions or measured flow parameters within the inlet 20.

FIG. 3 shows left and right arrays 22a, 22b of flow control devices on the inner surface 18 of the inlet 20 in a floor plan view. The right array 22a extends over an azimuth angle range 23a (between 40 ° and 150 ° with respect to the normal flow axis 15 for the exemplary embodiment) determined based on an example flow separation field of the right side wind (defined herein as flowing from right to left with respect to the drawing), while the left array 22b extends over an azimuth angle range 23b (between 40 ° and 150 ° for the exemplary embodiment) determined based on a flow separation field of the left side wind (defined herein as flowing from left to right with respect to the drawing). Each array 22a, 22b employs a plurality of circumferential rows 24a, 24b, 24c, 24d spaced apart by increasing first, second, third and fourth axial distances 26a, 26b, 26c, 26d from the inlet's ledge (highlight) 21. Describing left array 22b, circumferential rows 24a and 24b have a first arrangement of flow control devices that extend over the entire angular range of the array. Row 24c has a reduced azimuthal extent centered at 270 and extending between 260 and 280, while row 24d has a further reduced azimuthal extent (a single jet at 270 in the illustrated example). For the exemplary embodiment, each row has a flow control device 16 at every 10 ° azimuth angle within the range. Although shown as circular holes in the figures for the exemplary embodiments, flow control devices 16 may have slotted holes or alternative geometric configurations.

The embodiment shown in FIG. 3 provides left and right arrays for responding to vector components of the left and right side wind flows relative to the normal flow axis 15. FIG. 4 shows the flow at mass flow rate (defined asDimensionless as mass flow rate divided by maximum mass flow rate at the inlet) ofFIG. 401;a diagram 402; andvisualization of flow distortion in the left wind component inlet of the crosswind with 0kt of graph 403. The figure shows very little distortion of the inflow into the inlet in the case of 0kt crosswind. However, when the flow rate isFIG. 404;FIG. 405; andat graph 406, a crosswind component having 30kt existsAnd significant distortion.

For the purpose of quantitatively describing flow distortion herein, the inlet distortion coefficient IDC is defined asWherein the content of the first and second substances,is the mean pressure, P_minIs the minimum pressure on the ith ring (measured on a circumferential ring of constant radius). Is defined as IDC_maxCorresponds to the maximum IDC and produces the maximum circumferential distortion seen by the inlet. FIG. 5 provides IDCs for 0kt condition (trace 502) and 30kt condition (trace 504) without activating the baseline condition of flow control device 16 in the depicted embodiment_maxThe figure (a).

As shown in fig. 6A-6C, selective activation of the flow control devices 16 in the sub-arrays within the left array 22b is accomplished to mitigate flow distortion resulting from the left wind component described with respect to fig. 4 and 5. For the example shown in the figure, activation of the first sub-array 28a shown in FIG. 6A results in IDCs over the entire mass flow range of the traces 701 as shown in FIG. 7A_maxModification of (2). Similarly, activation of the second sub-array 28B shown in FIG. 6B results in IDCs that are traces 702 as shown in FIG. 7B_maxAnd activation of the third sub-array 28C shown in fig. 6C results in IDCs shown in fig. 7C as traces 703_maxModification of (2). In one example control scenario, switching between activated subarrays is dependent on mass flow range; the first subarray 28a is activated at a mass flow rate between 0 and 0.48, the second subarray 28b is activated at a mass flow rate between 0.48 and 0.82, and the third subarray 28c is activated at a mass flow rate between 0.82 and 1. This results in an IDC as shown in fig. 8_maxWherein the trace segment 801 is aligned with the IDCs over a flow range of 0 to 0.48 that activates the first sub-array 28a_maxModification is relevant in that trace segment 802 is associated with activating IDCs over a flow range of 0.48 to 0.82 for the second sub-array 28b_maxModifications are relevant and trace segment 803 is related to IDC over a stream range of 0.82 to 1.0 activating the third sub-array 28c_maxIt is related. IDC over the entire stream range_maxThe overall reduction of (c) is optimized. The resulting reduction in flow distortion is shown in fig. 8B. In other embodiments (or in alternative operation of the illustrated embodiment), various combinations of flow control devices in a sub-array and single or combined activation of the sub-arrays may be employed to adjust flow corrections based on changing conditions of cross-wind velocity and inlet mass flow rate.

The operation of the array 22a for the right side wind component is similar to the operation of the described array 22b for the left side wind component.

In an alternative embodiment, one or more flow control device arrays 22c may be employed in the azimuth angle range 23c on the inlet inner surface bottom, alone or in addition to the flow control device arrays 22a, 22b for crosswind distortion correction, e.g. 130 ° to 230 ° as shown as an example in fig. 9, to accommodate control of flow distortion due to high angle of attack (aircraft pitch) scenarios or ground vortex scenarios, where flow separation occurs substantially at the inner surface bottom or bottom surface of the inlet and one side or beam side of the inlet. The operation of array 22c may be analogous to that disclosed for array 22b and may be combined with the operation of either array 22a or array 22 b.

Although described herein with respect to specific flight conditions of crosswinds, angles of attack, and ground vortices, this embodiment provides flow control capability based on the generalized flight conditions of free-stream velocity (including the flow velocity constituting the instantaneous flight regime, flow angle relative to the engine, engine inlet mass flow rate, and altitude).

As shown in fig. 10, the control system 1002 employs a controller 1004 that receives condition inputs 1006 from one or more condition sensors 1008. The condition sensor 1008 may be a pressure sensor or other sensing system such as an optical or ultrasonic detector for boundary layer separation or internal turbulence in the inlet 20. Crosswind direction and velocity (or angle of attack) may be provided by various aircraft onboard systems or as external inputs to status signal 1009 received by controller 1004. One or more mass flow sensors 1010 also provide an inlet mass flow input 1012 to controller 1004. The inlet mass flow input 1012 may alternatively be derived from an external input, such as thrust rod position or fan speed. In response to the entry status determined by status signal 1009, condition sensor 1008 and mass flow sensor 1010, controller 1004 provides a control signal 1013 to one or more activation devices 1014, which activation devices 1014 are configured to activate flow control devices 16 in individual or sub-arrays of the array as previously described. As described in more detail subsequently, the control signal may also provide or modulate the injection flow rate or vortex generator deployment frequency for the flow control device 16. The controller may operate in an open loop based on the status signal 1009 and the inlet mass flow input 1012, or may utilize feedback from the status sensor 1008 and the mass flow sensor 1010 to provide closed loop control.

In an open loop implementation, the controller 1004 does not react to the conditions of the flow field. Instead, it only acts on a pre-planned schedule, targeting a particular actuation strength and position based on the then measured flight conditions, such as current engine inlet mass flow rate, flight speed, crosswind speed, and direction and altitude.

In a closed-loop implementation, the controller 1004 is responsive to a "condition" of the flow field in the inlet. Mass flow sensor 1010 and condition sensor 1008 provide continuous monitoring to controller 1004 so that the controller continuously provides updated control signal 1013 to activation device 1014. The flow control system is only activated when controller 1004 has determined that flow separation has occurred (or is expected to exist based on conditions).

For the above combination, in an open-loop configuration, the controller 1004 will actuate a predetermined array or subarray at an intensity of the flow control device 16 targeted to the desired flow separation region based on the status signal 1009, then switch to continuous monitoring of the mass flow sensor 1010 and the status sensor 1008 for a closed-loop configuration. The array or subarray in the closed loop configuration may be determined in real time and may include multiple or a single flow control device 16 responsive to the status sensor 1008 in real time, depending on the configuration of the activation device as described later.

In the example embodiment shown in the exploded illustration of fig. 11A and 11B, the flow control device 16 is a control jet and the activation device 1014 is one or more concentric cylinders 1102 or cylinder segments (the wall thicknesses of the components are exaggerated for clarity) spaced between the inner surface 18 of the inlet and the pressure chamber 1104. The pressure chamber 1104 is connected to an exhaust system 1105 or other pressure source. The concentric cylinder has an array of holes 1106a-1106D which can be rotated from the "closed" position shown in fig. 11C to align with the control orifices in the circumferential rows 24a-24D, thereby causing the sub-array 28a, 28b or 28C to open to the pressure chamber 1104 to obtain the orifice flow shown in fig. 11D. The activation device 1014 is a motor that engages the concentric cylinder 1102 to rotate the cylinder from the closed position to the aligned position. Although shown in fig. 11A-11D as having a single hole in one-to-one correspondence with the flow control devices in a corresponding row, each concentric cylinder may be rotated in multiple steps over a 10 ° interval of the device, with a stepped array having holes or blank closures to accommodate the different azimuthal ranges of a particular subset of the flow control devices in that row, to obtain the previously described sub-arrays 28a, 28b and 28 c. In alternative embodiments, a single sliding or rotatable door may provide both closed and open conditions for flow control device 16.

In a similar example embodiment shown in fig. 11E-11O, the flow control device 16 is a control jet and the activation device 1014 is one or more perforated annular plates 1110 or plate segments, substantially perpendicular to the normal flow axis 15, located between the inlet inner surface 18 and the outer surface 19, with conduits 1112 extending from a hub 1114 of the annular plates 1110 to the flow control device 16 on the inlet inner surface 18. The second port 1116 of the plate communicates with the pressure chamber 1118. As with the previous embodiment, the pressure chamber 1118 is connected to an exhaust system or other pressure source. The annular plate 1110 has an array of apertures 1120a-1120d as shown in FIG. 11F, which can be rotated from a "closed" position as shown in FIGS. 11E and 11N and 11O into alignment with the control orifices in the circumferential rows 24a-24d to open the various sub-arrays to the pressure chamber 1118 to obtain the jet flow as shown in FIGS. 11F and 11G, the full sub-array open partial sub-array as shown in FIGS. 11H and 11I, 11J and 11K, and 11L and 11M. Activation device 1014 is a motor that engages annular plate 1110 to rotate the plate about normal flow axis 15 from a closed position to a plurality of aligned positions. Although shown in fig. 11A-11D as having a single aperture in one-to-one correspondence with the flow control devices in a corresponding row, the annular plate 1110 may be rotated in multiple steps over a 10 ° interval of the device, with a stepped array having apertures or blank closures to accommodate the different azimuthal ranges of a particular subset of the flow control devices in that row, thereby obtaining multiple sub-arrays.

In another example embodiment, schematically represented in fig. 12, an electronic or hydraulic control valve 1202 provides an activation means to connect a respective one of the flow control devices 16 to a pressure source 1203, such as an exhaust system. The controller 1004 activates one or more selected valves 1202 using control signals 1013 for a predetermined array or sub-array of flow control devices. As shown in fig. 13, a manifold valve 1302 may be connected between the pressure source and one or more manifolds 1304 in fluid communication with the array or sub-array 28a, 28b of flow control devices 16, as opposed to the control of a single flow control device.

The embodiments as described with respect to fig. 11A-13 may also be applied as pneumatic-based flow control systems that employ suction instead of blowing, i.e., jetting, or a combination of suction and blowing.

As shown in FIG. 14, synthetic jets 1402 can be used as flow control devices at array locations on the inner surface 18 of the inlet 20, and can be directly activated by the controller 1004 to provide flow modification in the inlet. The power connection 1404 and the level control 1406 (e.g., Pulse Width Modulation (PWM) injection modulation) may be controlled directly by the controller 1004 through a relay 1408 or other suitable control element to activate each of the synthetic jets controllable by the controller 1004 to produce the selected sub-array 28a, 28b, 28 c.

Fig. 15 schematically illustrates an alternative embodiment with an expanded eddy current generator array or other mechanical device such as a pin 1502 that is extended and retracted by a solenoid operator 1504 or similar component acting as an activation device in response to a control signal 1013. The pins 1502 may be deployed and retracted periodically at varying frequencies to achieve the desired flow modification.

As shown in FIG. 16, the disclosed embodiments provide a method 1600 for flow control in a low L/D fan nozzle inlet. The controller receives the status signal and the ingress mass flow signal (step 1602). In response to the status and inlet mass flow signals, the controller provides a control output to one or more of a plurality of flow control devices in an array on the inner surface of the inlet for reducing flow distortion in the inlet (step 1604). The controller receives condition signals from one or more condition sensors (step 1606). In response to the inlet mass flow signal or the condition signal, the controller modulates the flow control devices to form subarrays to optimize reduction of flow distortion in the inlet (step 1608). For the various disclosed embodiments, the step of modulating the flow control device may be accomplished by: selectively aligning the concentric cylinders with the array of orifices to connect a respective sub-array of flow control devices to the pressure source, selectively opening valves between the pressure source and one or more flow control devices to form the sub-array, selectively opening valves between the pressure source and one or more manifolds connected to the sub-array of the plurality of flow control devices, selectively activating the synthesizing device to form the sub-array, or selectively deploying and stowing the deployed vortex generators to form the sub-array.

Having now described various embodiments in detail as required by the patent statutes, those skilled in the art will recognize modifications and substitutions to the specific embodiments disclosed herein. Such modifications are within the scope and intent of the appended claims. In the description and claims, the terms "comprising," "merging" or "merging," "including," or "including," "having," or "having," and "containing," "containing," or "containing" are intended to be openly stated and additional or equivalent elements may be present. The term "substantially" as used in the specification and claims means that the feature, parameter, or value being described need not be achieved exactly, but rather a deviation or variation, including for example tolerances, measurement error, measurement accuracy limitations and other factors known to those skilled in the art, may occur in an amount that does not preclude the effect that the characteristic is intended to provide. As used herein, the terms "right," "left," "front" and "rear," "upper" and "lower," and "clockwise" and "counterclockwise" are employed to describe relative positioning and movement with respect to the drawings, and in addition to the specific embodiments disclosed, the example embodiments may be replaced by or reversed with appropriate descriptors, such as "first" and "second," "top" and "bottom" or "left" and "right," depending on the orientation of the actual embodiment.

An inlet flow distortion control system, comprising: a plurality of flow control devices integrated in an inner surface of the inlet, forming at least one array extending azimuthally with respect to a normal flow axis of the inlet and having a plurality of circumferential rows spaced at increasing axial distances from a protruding portion of the inlet; and a control system operably connected to the plurality of flow control devices, the control system adapted to activate the flow control devices in selected sub-arrays of the at least one array in response to an inlet flow condition indicated by a predetermined flight condition or a measured flow parameter within the inlet.

Item 2. the inlet flow distortion control system of item 1, wherein the at least one array includes a right array having an azimuth angle range determined based on the right wind flow separation domain and a left array having an azimuth angle range determined based on the left wind flow separation domain.

Item 3. the inlet flow distortion control system of item 1 or 2, wherein at least one array comprises an array extending over the azimuthal extent of the bottom of the inner surface of the inlet to accommodate control of flow distortion due to high angles of attack or ground vortices.

Item 4. the inlet flow distortion control system of item 2 or 3, wherein the left and right arrays each comprise a plurality of circumferential rows spaced at increasing first, second, third, and fourth axial distances from the protruding portion of the inlet.

Item 5 the inlet flow distortion control system of item 4, wherein, for each of the right and left arrays, a first of the plurality of circumferential rows includes flow control devices extending over an azimuthal extent of each of the right and left arrays, a second of the plurality of circumferential rows includes flow control devices extending over a reduced azimuthal extent of each of the right and left arrays, and a third of the plurality of circumferential rows includes flow control devices extending over a further reduced azimuthal extent of each of the right and left arrays.

The inlet flow distortion control system of item 5, wherein the control system comprises: a controller that receives a status signal or condition input for crosswind or angle of attack; the mass flow is input to a controller; and one or more activation devices receiving an output signal from the controller in response to the mass flow input and the status signal or condition input, the one or more activation devices configured to activate the flow control device in one of the selected subarrays.

The inlet flow distortion control system of item 6, wherein the one or more activation devices comprise: one or more concentric cylinders spaced between the inner surface of the inlet and the pressure chamber, the one or more concentric cylinders having an array of apertures rotatable from a closed position into alignment with the one or more rows of control jets; and a pressure source connected to the pressure chamber.

The inlet flow distortion control system of item 7, wherein the pressure source is an exhaust system.

Item 9 the inlet flow distortion control system of item 7 or 8, wherein the one or more concentric cylinders comprise a plurality of concentric cylinders, each concentric cylinder aligned with a respective one of the one or more rows of control jets to open one of the selected subarrays to the pressure chamber.

The inlet flow distortion control system of any of items 6-9, wherein the one or more activation devices comprise one or more valves, each valve connected to a respective flow control device of the plurality of flow control devices.

The inlet flow distortion control system of item 10, further comprising at least one manifold connecting one of the one or more valves to a selected sub-array of at least one array of the plurality of flow control devices.

The inlet flow distortion control system of any of items 6-11, wherein the plurality of flow control devices each comprise a synthetic jet, and further comprising: power is connected to each synthetic jet; and a horizontal controller, connected to each synthesis jet through the repeater, controllable to generate a selected sub-array of the at least one array.

Item 13 the inlet flow distortion control system of any of items 6-12, wherein the plurality of flow control devices each comprise an expanded vortex generator, and wherein the one or more activation devices each comprise a solenoid operator.

Item 14: an injection engine, comprising: an inlet having a normal flow axis and an inner surface extending from the projection; a plurality of flow control devices forming at least one array integrated into the interior surface, the at least one array extending azimuthally with respect to a normal flow axis and having a plurality of circumferential rows spaced apart at increasing axial distances from the protruding portion of the inlet; and a control system operably connected to the plurality of flow control devices, the control system adapted to activate the flow control devices in a selected sub-array of the at least one array in response to a predetermined flight condition or inlet flow field.

A method for flow control in a spout inlet, the method comprising: receiving the status signal and the mass flow signal in the controller; providing a control output from the controller to one or more of the plurality of flow control devices in the array on the inner surface of the inlet in response to the status signal and the mass flow signal; and reducing flow distortion in the inlet.

The method of item 16, item 15, further comprising: receiving, in a controller, a condition signal from one or more condition sensors; wherein the step of reducing flow distortion comprises modulating the plurality of flow control devices to form subarrays responsive to mass flow signals or condition signals to optimize reduction of flow distortion in the inlet.

The method of item 17, wherein the step of modulating the plurality of flow control devices comprises selectively aligning the concentric cylinders with the array of orifices to connect respective sub-arrays of the plurality of flow control devices to the pressure source.

The method of item 16 or 17, wherein the step of modulating a plurality of flow control devices comprises: selectively opening a valve between the pressure source and one or more of the plurality of flow control devices to form a sub-array, or the pressure source and one or more manifolds connected to the sub-array of the plurality of flow control devices.

The method of any of items 16 to 18, wherein the plurality of flow control devices includes a synthesizing device, and the step of modulating the plurality of flow control devices includes selectively activating the synthesizing device to form the subarray.

Item 19. the method of any of items 16-19, wherein the plurality of flow control devices includes an expanded vortex generator and the step of modulating the plurality of flow control devices includes selectively expanding and collapsing the expanded vortex generator to form the sub-array.