[특허]Suprression of shock-induced airflow separation

Lockheed Martin Corporation

Suprression of shock-induced airflow separation

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-021/04 F02C-007/04 F15D-001/00 B64C-021/02 B64D-033/02
출원번호	US-0952088 (2013-07-26)
등록번호	US-10054048 (2018-08-21)
발명자 / 주소	Baruzzini, Dan J. Miller, Daniel N. Domel, Neal D. Hakes, Jeff G.
출원인 / 주소	Lockheed Martin Corporation
대리인 / 주소	Reising Ethington P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 32

초록 ▼

An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.

대표청구항 ▼

1. An apparatus for suppressing shock-induced separation of airflow, the apparatus comprising; an engine inlet; andan actuator configured to alternately inhale and exhale fluid, the actuator being positioned to inhale fluid from a boundary layer separation bubble induced on a wall of the inlet by a shock wave in a fluid mass flowing along the wall. 2. An apparatus as defined in claim 1 in which the actuator is positioned to direct exhaled fluid back into the boundary layer in a generally downstream exhalation direction. 3. An apparatus as defined in claim 1 in which the actuator is a zero-net-mass-flux (ZNMF) actuator. 4. An apparatus as defined in claim 2 in which the apparatus includes a phased actuator array comprising at least two actuators disposed adjacent one another and arranged along the wall transverse to a flow direction of the fluid mass, each actuator of the array being configured to alternately inhale and exhale fluid in an operation cycle of each actuator, and each actuator of the array being positioned to alternately inhale fluid from the boundary layer separation bubble and exhale fluid into the boundary layer, the operation cycles of the actuators being phased with one another such that the cycle of each actuator leads ahead of at least one other actuator of the array and lags behind at least one other actuator of the array. 5. An apparatus as defined in claim 4 in which the length of an inhalation portion of each actuator's operation cycle is adjustable relative to the length of an exhalation portion. 6. An apparatus as defined in claim 4 in which the apparatus includes a plurality of phased actuator arrays disposed adjacent one another and distributed along the wall transverse to the flow direction of the fluid mass, in respective locations where the boundary layer separation bubble forms along the wall when the fluid mass is flowing. 7. An apparatus as defined in claim 6 in which the wall is a generally continuous interior wall of an engine inlet and the plurality of phased actuator arrays are distributed around the generally continuous interior wall of the engine inlet. 8. An apparatus as defined in claim 7 in which the wall is a generally continuous interior wall of an axisymmetric mixed compression inlet. 9. An apparatus as defined in claim 4 in which the actuators of the phased actuator array are positioned and oriented to inhale and exhale boundary layer fluid through a downstream-facing step in the wall. 10. An apparatus as defined in claim 4 in which the actuators of the phased actuator array are positioned and oriented to inhale and exhale boundary layer fluid through a recessed wall port. 11. A method for suppressing shock-induced airflow separation, the method including the steps of: drawing a fluid mass into an engine inlet such that a supersonic shock wave propagates in the fluid mass and induces a boundary layer separation bubble in a portion of the fluid mass flowing along a wall of the inlet; anddrawing fluid from the boundary layer separation bubble. 12. The method of claim 11 including the additional step of directing fluid back into the boundary layer in a generally downstream exhalation direction. 13. The method of claim 11 in which the step of drawing fluid from a boundary layer separation bubble includes causing a ZNMF actuator to inhale fluid from the boundary layer separation bubble during an inhalation portion of an operation cycle of the ZNMF actuator. 14. The method of claim 12 in which the step of directing fluid back into the boundary layer includes causing the ZNMF actuator to direct fluid back into the boundary layer in a generally downstream exhalation direction during an exhalation portion of the operation cycle of the ZNMF actuator. 15. The method of claim 12 including the additional step of causing the ZNMF actuator to alternately inhale fluid from and exhale fluid into the boundary layer. 16. The method of claim 15 in which the drawing, directing, and alternating steps include causing each of at least two ZNMF actuators to alternately inhale fluid from and exhale fluid into the boundary layer during respective operation cycles of the actuators, the operation cycles of the actuators being phased with one another such that the cycle of each actuator leads ahead of at least one other actuator of the array and lags behind at least one other actuator of the array. 17. The method of claim 12 in which the step of alternating the drawing and directing steps includes the additional step of slowing or speeding the actuator during one of the drawing step and the directing step such that one of the drawing step and the directing step takes more time to complete than the other. 18. The method of claim 17 in which the step of alternating the drawing and directing steps includes slowing the drawing step or speeding the directing step such that the drawing step takes more time to complete than the directing step. 19. An apparatus as defined in claim 1 in which the actuator is positioned to inhale fluid from a boundary layer separation bubble induced along the wall of the inlet by a supersonic shock wave reflected from the wall. 20. A method as defined in claim 11 in which the step of drawing a fluid mass into an engine inlet such that a supersonic shock wave propagates in the fluid mass and induces a boundary layer separation bubble, includes drawing the fluid mass into an engine inlet such that the supersonic shock wave induces the boundary layer separation bubble to form where the shock wave is reflected from the inlet wall.

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