Part-I - Controller General of Patents Designs and Trademarks

(12) PATENT APPLICATION PUBLICATION (21) Application No.2469/CHE/2013 A
(19) INDIA
(22) Date of filing of Application :06/06/2013 (43) Publication Date : 21/06/2013
(54) Title of the invention : AUTOMATED ACTIVE FLOW CONTROL SYSTEM BASED ON FLUIDIC OSCILLATORS
(51) International classification :F15C
(31) Priority Document No :NA
(32) Priority Date :NA
(33) Name of priority country :NA
(86) International Application No
:NA
Filing Date
:NA
(87) International Publication No : NA
(61) Patent of Addition to Application Number :NA
Filing Date
:NA
(62) Divisional to Application Number
:NA
Filing Date
:NA
(71)Name of Applicant :
1)FAYAZ RASHEED
Address of Applicant :KALPANA, PALACE WARD,
ALAPPUZHA - 688 011 Kerala India
(72)Name of Inventor :
1)FAYAZ RASHEED
(57) Abstract :
Active flow control technologies have been employed over the years, including the use of blowing and suction control techniques
for the control of separation of flow over a surface such as a wing surface can produce increase in the lift and increase in the
overall fuel efficiency of the aircraft. Fluidic oscillators are devices which produce oscillating output flow which can be used for
effective flow control. These fluidic devices have no moving parts and hence can be used for long periods with low maintenance
requirements. The present invention encompasses an automated system which can automatically control flow on the surface of an
aerofoil section such as an aircraft wing at varied free stream flow velocities and at varied angles of attack. The system comprises
of an array of fluidic oscillators with built-in feedback loop, a pressurization chamber, a dedicated on-board computer, pressure
regulator valves and pressure sensors. Use of an array of fluidic oscillator with built-in feedback loops in aircraft wings helps in
low-maintenance requirements over long periods of time. The required value of input pressure which are to be supplied to the
fluidic oscillator to obtain the desired flow separation control are preset in the on-board computer, for a give free stream velocity,
for a given angle of attack, for a given design of aerofoil section and for a given fluidic oscillator dimensions. The values of the
free stream velocity and the angle of attack are fed into the computer from the gyro sensors and the air speed sensors on-board the
aircraft. The corresponding pressure of air from the engine bleed valve can be released into the array of fluidic oscillators. The
fluidic oscillator then produces the necessary switching frequency and exit flow velocities so as to produce the required flow
control.
No. of Pages : 13 No. of Claims : 3
The Patent Office Journal 21/06/2013 13449