IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0468768
(2012-05-10)
|
등록번호 |
US-8353482
(2013-01-15)
|
발명자
/ 주소 |
- Miller, Daniel N.
- McCallum, Brent N.
- Jenkins, Stewart A.
- Wells, David M.
|
출원인 / 주소 |
- Lockheed Martin Corporation
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
3 |
초록
▼
Systems to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of nano-scale effectors connected to the outer surface of the aerodynami
Systems to provide distributed flow control actuation to manage the behavior of a global flow field, are provided. An example of a system can include an aerodynamic structure having an outer surface, and an array of a plurality of nano-scale effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing, to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure.
대표청구항
▼
1. A system to provide distributed flow control to manage the behavior of a global flow field, the system comprising: an array of a plurality of nano-effectors connected to a surface of an aerodynamic structure to be in fluid contact with a primary fluid flow structure when operationally flowing and
1. A system to provide distributed flow control to manage the behavior of a global flow field, the system comprising: an array of a plurality of nano-effectors connected to a surface of an aerodynamic structure to be in fluid contact with a primary fluid flow structure when operationally flowing and positioned to alter a secondary flow structure in a viscous wall sublayer of a turbulent boundary layer of the primary fluid flow structure with the plurality of nano-effectors to induce controlled, globally distributed disturbances at the viscous wall sublayer of the turbulent boundary layer of the primary fluid flow structure when operationally flowing and to manipulate fluid behavior of the primary fluid flow structure to thereby substantially reduce pressure loss associated with the incipient separation of the primary fluid flow structure from portions of the aerodynamic structure, the array of nano-effectors having a subset positioned at a location at or adjacent an expected point of incipient separation from the surface of the aerodynamic structure of at least portions of the primary fluid flow structure, a subset positioned substantially upstream of the expected point of incipient separation, and a subset distributed therebetween to thereby configure the array of the plurality of nano-effectors as a single two-dimensional array. 2. A system as defined in claim 1, wherein the plurality of nano-effectors are sized and spatially oriented to substantially concentrate direct physical effects of the plurality of nano-effectors at the viscous wall sublayer and to substantially minimize direct physical effects at fluid flow levels experiencing a substantially higher momentum than that experienced at the viscous wall sublayer. 3. A system as defined in claim 2, wherein total pressure loss due to parasitic drag resulting from the two-dimensional array of nano-effectors when connected to the surface of the aerodynamic structure is less than approximately ¼%, with a total RMS turbulence level reduction of approximately between 10% and 50% adjacent a nominal limit of the boundary layer at a station distance upstream of the expected point of incipient separation of between approximately 0 and 5.0 as normalized by boundary layer height at the expected point of incipient separation, when the fluid flow is operationally flowing at a rate of between approximately mach 0.05 and mach 2.0. 4. A system as defined in claim 2, wherein a baseline uncontrolled condition Reynolds Number for the turbulent boundary layer is between approximately 106 and 109 when the fluid flow is operationally flowing;wherein the plurality of nano-effectors include a plurality of nano-vanes having a height of approximately between 1% and 5% of a height at a nominal limit of an expected boundary layer thickness at the expected point of incipient separation and positioned at a station distance upstream of the expected point of incipient separation of between approximately 0.0 and 5.0, the station distance normalized by boundary layer thickness; andwherein the nano-vanes are oriented at an angle of incidence to the primary fluid flow structure of between approximately 13 degrees and 36 degrees. 5. A system as defined in claim 1, wherein at least substantial portions of the array of the plurality of nano-effectors is positioned upstream of an inlet connected to a serpentine duct extending into the aerodynamic structure; andwherein the array of nano-effectors is positioned laterally a distance of approximately between 60% and 90% with respect to a width of the inlet. 6. A system as defined in claim 1, wherein the array of a plurality of the nano-effectors is a first array of a first plurality of nano-effectors, and wherein at least substantial portions of the first array of the first plurality of nano-effectors is positioned upstream of an inlet connected to a serpentine duct extending into the aerodynamic structure; the system further comprising: a second array of a second plurality of nano-effectors connected within the serpentine duct and positioned to alter a ducted secondary flow structure in a viscous wall sublayer of a turbulent boundary layer of a ducted primary fluid flow structure channeled within the serpentine duct. 7. A system as defined in claim 1, wherein the plurality of nano-effectors are nano jet actuators having a diameter of approximately between 1% and 5% of boundary layer height at a nominal limit of the boundary layer at the expected point of incipient separation, the system further comprising: a controller configured to perform the following operations: determining static pressure at one or more locations within the array,controlling the mass flow of the plurality of nano-jet actuators responsive to the determined static pressure to thereby alter the secondary flow structure. 8. A system as defined in claim 1, wherein the plurality of nano-effectors include a plurality of nano jet actuators, wherein the expected point of incipient separation is operably within a range of locations along a longitudinal axis of the aerodynamic structure, wherein the array of the plurality of nano jet actuators is also positioned to extend from a station location adjacent a most downstream location of the expected point of incipient separation and a station location substantially upstream of a most upstream location of the expected point of incipient separation, the system further comprising: a controller configured to perform the following operations: detecting static pressure along a plurality of separate and spaced apart longitudinal locations within the array,determining a station location of the expected point of incipient separation responsive to the detected static pressure, andseparately controlling the mass flow of at least a subset of the plurality of nano-jet actuators responsive to the determined location of the expected point of incipient separation and responsive to the determined static pressure or pressures. 9. A system as defined in claim 1, wherein the plurality of nano-effectors are further positioned according to one or more of the following: at least a subset of the plurality of nano-effectors is embedded in a paint or coating positioned on the outer surface of the aerodynamic structure;at least a subset of the plurality of nano-effectors is embedded in a sheet of laminate material bonded or co-bonded to the aerodynamic structure to at least partially form the outer surface; andat least a subset of the plurality of nano-effectors is embedded in an adhesive positioned adjacent the outer surface of the aerodynamic structure. 10. A system to provide distributed flow control to manage the behavior of a global flow field, the system comprising: an aerodynamic structure having an outer surface; andan array of a plurality of nano-effectors connected to the outer surface of the aerodynamic structure to be in fluid contact with a flowing fluid when operationally flowing to induce controlled, globally distributed disturbances at a viscous wall sublayer of a turbulent boundary layer of the flowing fluid when operationally flowing and to manipulate fluid behavior of the flowing fluid to thereby substantially reduce pressure loss associated with incipient separation of the fluid flow from portions of the aerodynamic structure, the array of nano-effectors having a subset positioned adjacent a station line located at an expected point of incipient separation of at least portions of the flowing fluid from the outer surface of the aerodynamic structure, a subset positioned substantially upstream of the expected point of incipient separation, and a subset positioned therebetween to thereby configure the array of the plurality of nano-effectors as a single two-dimensional array. 11. A system as defined in claim 10, wherein total pressure loss due to parasitic drag resulting from the array of the plurality of nano-effectors is less than approximately ¼%, with a total RMS turbulence level reduction of approximately between 10% and 30% adjacent a nominal limit of the boundary layer at a station distance upstream of the expected point of incipient separation of between approximately 0 and 5.0 as normalized by boundary layer height at the expected point of incipient separation, when the fluid flow is operationally flowing at a rate of between approximately mach 0.05 and mach 2.0. 12. A system as defined in claim 10, wherein the aerodynamic structure includes a ducted inlet having a serpentine configuration; andwherein at least substantial portions of the array of the plurality of nano-effectors are positioned upstream of the ducted inlet. 13. A system as defined in claim 12, wherein the array of nano-effectors extends laterally a distance of approximately between 60% and 90% with respect to a width of the inlet. 14. A system as defined in claim 10, wherein a baseline uncontrolled condition Reynolds number for the turbulent boundary layer is between approximately 106 and 109 when the fluid flow is operationally flowing; andwherein the plurality of nano-effectors comprise nano-vanes having a height of approximately between 1% and 8% of a height at a nominal limit of an expected boundary layer thickness at the expected point of incipient separation and are positioned at a station distance upstream of the expected point of incipient separation of between approximately 0.0 and 5.0, the station distance normalized by boundary layer thickness. 15. A system as defined in claim 10, wherein each of the plurality of nano-effectors has: a height of approximately between 1% and 8% of a height at a nominal limit of an expected boundary layer thickness at the expected point of incipient separation;a chord length of approximately between 10% and 100% of boundary layer thickness; andan angle of incidence to the fluid flow of approximately between 14 and 36 degrees. 16. A system as defined in claim 10, wherein the plurality of nano-effectors are nano-jet actuators having a diameter of approximately between 1% and 8% of boundary layer height at a nominal limit of the boundary layer at the expected point of incipient separation; andwherein the system further comprises: a plurality of static pressure taps positioned to receive static pressure within the array,a plurality of pressure sensors each in fluid communication with at least one of the plurality of pressure taps, anda controller operably coupled to the plurality of pressure sensors and configured to determine the static pressure within the array and to separately control the mass flow rate of at least a subset of the plurality of nano jet actuators responsive to determined static pressure. 17. A system as defined in claim 10, wherein the array of the plurality of nano-effectors include an array of a plurality of nano-jet actuators;wherein the expected point of incipient separation is operably within a range of locations along a longitudinal axis of the aerodynamic structure;wherein the array of the plurality of nano jet actuators is positioned to extend from a station location adjacent a most downstream location of the expected point of incipient separation and a station location substantially upstream of a most upstream location of the expected point of incipient separation; andwherein the system further comprises: a plurality of static pressure taps positioned to receive static pressure along a plurality of longitudinal locations within the array,a plurality of pressure sensors each in fluid communication with at least one of the plurality of pressure taps, anda controller operably coupled to the plurality of pressure sensors and configured to determine the static pressure at the plurality of separate and spaced apart longitudinal locations within the array, to determine a station location of the expected point of incipient separation responsive to the determined static pressure, and to control the mass flow of at least a subset of the plurality of nano jet actuators responsive to the determined location of the expected point of incipient separation. 18. A system as defined in claim 17, wherein the array of nano-jet effectors and the plurality of sensors are embedded in at least one of the following: a paint or coating positioned on the outer surface of the aerodynamic structure;an adhesive positioned adjacent the outer surface of the aerodynamic structure; anda sheet of laminate material bonded or co-bonded to the aerodynamic structure to at least partially form the outer surface. 19. A system as defined in claim 10, wherein a subset of the plurality of nano-effectors are positioned in at least one of the following locations: a leading edge of a lift producing surface of the aerodynamic structure; anda trailing edge of a lift producing surface of the aerodynamic structure. 20. A system of providing distributed flow control to manage the behavior of a global flow field, the system comprising: an array of a plurality of nano jet actuators connected to a surface of a structure upstream of a serpentine duct having an inlet extending through the surface of the structure to be in fluid contact with a primary fluid flow structure entering the inlet when operationally flowing and positioned to alter a secondary flow structure in a viscous wall sublayer of a turbulent boundary layer of the primary fluid flow structure with the plurality of nano-jet actuators to induce controlled disturbances at the viscous wall sublayer of the turbulent boundary layer of the primary fluid flow structure when operationally flowing and to manipulate fluid behavior of the primary fluid flow structure to influence performance of the serpentine duct, the array of the plurality of nano jet actuators having a subset positioned at a location at or adjacent an expected point of incipient separation from the surface of the structure of at least portions of the primary fluid flow structure, a subset positioned substantially upstream of the expected point of incipient separation, and a subset positioned therebetween; anda controller configured to perform the following operations: detecting static pressure along a plurality of separate and spaced apart longitudinal locations within the array,determining the location of the expected point of incipient separation responsive to the detected static pressure, andseparately controlling the mass flow of at least a subset of the plurality of nano-jet actuators responsive to the determined location of the expected point of incipient separation. 21. A system as defined in claim 20, wherein total pressure loss due to parasitic drag resulting from the two-dimensional array of nano-effectors when connected to the surface of the aerodynamic structure is less than approximately ¼%, with a total RMS turbulence level reduction of approximately between 10% and 50% adjacent a nominal limit of the boundary layer at a station distance upstream of the expected point of incipient separation of between approximately 0 and 5.0 as normalized by boundary layer height at the expected point of incipient separation, when the fluid flow is operationally flowing at a rate of between approximately mach 0.05 and mach 2.0.
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