IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0428135
(2009-04-22)
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등록번호 |
US-8240616
(2012-08-14)
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발명자
/ 주소 |
- Miller, Daniel N.
- McCallum, Brent N.
- Jenkins, Stewart A.
- Wells, David M.
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
4 |
초록
▼
Systems and methods 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 effectors connected to the outer surface of the aerodynam
Systems and methods 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 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 method of providing distributed flow control to manage the behavior of a global flow field, the method comprising the steps of: connecting an array of a plurality of nano-effectors to a surface of an aerodynamic structure to be in fluid contact with a primary fluid flow structure when operation
1. A method of providing distributed flow control to manage the behavior of a global flow field, the method comprising the steps of: connecting an array of a plurality of nano-effectors to a surface of an aerodynamic structure to be in fluid contact with a primary fluid flow structure when operationally flowing, the array of nano-effectors having a subset positioned adjacent a station line located at an expected point of incipient separation from the surface of the aerodynamic structure of at least portions of the primary 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; andaltering 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 flow structure when operationally flowing flow and to manipulate fluid behavior of the primary flow structure to thereby substantially reduce pressure loss associated with the incipient separation of the primary flow structure from portions of the aerodynamic structure. 2. A method 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 sublayer and to substantially minimize direct physical effects at fluid flow levels experiencing a substantially higher momentum than that experienced at the viscous sublayer. 3. A method as defined in claim 2, wherein total pressure loss due to parasitic drag resulting from the steps of connecting and altering 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 method 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 step of connecting includes the step of orienting each of the nano-vanes at an angle of incidence to the primary flow structure of between approximately 13 degrees and 36 degrees. 5. A method as defined in claim 1, wherein the step of connecting includes the steps of: positioning at least substantial portions of the array of the plurality of nano-effectors upstream of an inlet connected to a serpentine duct extending into the aerodynamic structure; andpositioning the array of nano-effectors laterally a distance of approximately between 60% and 90% with respect to a width of the inlet. 6. A method 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 the method further comprises the steps of: positioning at least substantial portions of the first array of the first plurality of nano-effectors upstream of an inlet connected to a serpentine duct extending into the aerodynamic structure;connecting a second array of a second plurality of nano-effectors within the serpentine duct; andaltering 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 method 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; andwherein the step of altering a secondary flow structure includes the steps of: 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. 8. A method 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 step of connecting includes positioning the array of the plurality of nano-jet actuators 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 step of altering a secondary flow structure includes the steps of: 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 method as defined in claim 1, wherein the step of connecting includes performing one or more of the following steps: embedding at least a subset of the plurality of nano-effectors in a paint or coating positioned on the outer surface of the aerodynamic structure;embedding at least a subset of the plurality of nano-effectors in a sheet of laminate material bonded or co-bonded to the aerodynamic structure to at least partially form the outer surface; andembedding at least a subset of the plurality of nano-effectors in an adhesive positioned adjacent the outer surface of the aerodynamic structure. 10. A method of providing distributed flow control to manage the behavior of a global flow field, the method comprising the steps of: connecting an array of a plurality of nano-scale effectors 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 to influence performance of the serpentine duct, the array of the plurality of nano-scale effectors having a subset positioned adjacent a station line located at an expected point of incipient separation from the surface of the structure of at least portions of the primary flow structure, a subset positioned substantially upstream of the expected point of incipient separation, and a subset positioned therebetween; andaltering 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-scale effectors to induce controlled disturbances at the viscous wall sublayer of the turbulent boundary layer of the primary flow structure when operationally flowing flow and to manipulate fluid behavior of the primary flow structure. 11. A method as defined in claim 10, wherein total pressure loss due to parasitic drag resulting from the steps of connecting and altering 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 line 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 0.1 and mach 2.0. 12. A method as defined in claim 11, wherein the plurality of nano-scale effectors include a plurality of nano-vanes having a height of approximately between 1% and 5% 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. 13. A method as defined in claim 12, wherein the step of connecting includes the step of orienting each of the nano-vanes at an angle of incidence to the primary flow structure of approximately between 13 degrees and 36 degrees. 14. A method as defined in claim 11, wherein the plurality of nano-scale effectors include a plurality of nano-jet actuators, and wherein the step of altering a secondary flow structure includes the steps of: 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. 15. A method as defined in claim 1, 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. 16. A method as defined in claim 15, 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. 17. A method as defined in claim 16, wherein the step of connecting includes the step of: orienting each of the nano-vanes at an angle of incidence to the primary flow structure of between approximately 13 degrees and 36 degrees. 18. A method as defined in claim 1, 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. 19. A method as defined in claim 1, wherein the aerodynamic structure includes a ducted inlet having a serpentine configuration. 20. A method as defined in claim 19, wherein the step of connecting an array of a plurality of nano-effectors to a surface of an aerodynamic structure includes the steps of: positioning at least substantial portions of the array of the plurality of nano-effectors upstream of the ducted inlet; andpositioning the array of the plurality of nano-effectors laterally a distance of approximately between 60% and 90% with respect to a width of the inlet.
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