The Fuel Flow Transducer measures flows of hydrocarbon fuels such as gasoline, kerosene, and #2 diesel fuel and other light transmitting, non-corrosive liquids of similar viscosity. Typical fuel flow applications include aircraft fuel monitoring systems; gasoline, diesel, and gas turbine engine test stands; and industrial furnaces.
The transducers give repeatable signals on gasoline across a 100 to 1 flow range down to 0.3 GPH. The higher viscosity of diesel fuel reduces signal repeatability at flow rates below 2 GPH. Pressure drops are very low compared to other turbine flow transducers. The transducer bearing system is rated for continuous operation at the upper end of the flow range.
The transducers produce a current pulse signal from an opto-electronic pickup with a preamplifier.
12 to 15 VDC between RED (+) wire and BLACK (-) wire. 30 to 50 mA at 12 VDC.
Open collector transistor output on WHITE wire. Sensor will pull-down to 1.0 volt with 10-15k ohm pull-up resistor installed.
- 1 Fuel Flow Transducer Model 201B- 9 (old264)
Here’s how it works in an aircraft; liquid enters through one side and enters the flow chamber. It follows a helical flow path, and exits vertically, thereby venting vapor bubbles that might form during the fuel flow. As the liquid flows, it has a velocity that can be measured and this velocity is directly proportional to flow rate.
Inside the fuel flow transducer, is a miniature neutrally buoyant rotor finely balanced on jeweled bearings. As the fuel flows past the arms of the rotor, it pushes against the arms of the rotor and so, the rotor begins to spin.
Now, on one side of the spinning rotor is an infrared light emitter while on the other side, is an infrared light detector. As the arms of the rotor spin, it interrupts an infrared light and this constant on-off is calculated to arrive at the spin rate and therefore, the fuel flow rate. Ingenious, simple and fool proof.
JPI FF transducers use a more sensitive but rugged version of a typical fuel flow transducer, suitable for a wide range of aircraft use.
Range (201) 0.6 to 60 GPH, (231) 3 to 90 GPH, (H) 3 to 120 GPH
K-factor (201) ~ 29.00, (231) ~19.50, (H) ~48.00
Pressure drop (201) 1.2 psi at 30 GPH, 4.8 psi at 60 GPH
Pressure drop (231) 0.31 psi at 30 GPH, 2.8 psi at 60 GPH
Pressure drop (H) 0.23 psi at 30 GPH, 0.8 psi at 60 GPH
Working pressure (201, 231) 200 psi, (H) 1500 psi
Maximum burst pressure 2000 psi
Temperature range, operating -55°C to 70°C
Temperature range, non-operating (201, 231) -65°C to 125°C, (H) -65°C to 100°C
Fuel ports (201, 231) 1/4 Female NPT (H) AN816-8-8
Make sure the transducer is Horizontal with the three wires up. Failure to do this will result in premature failure. Please refer to Report #503 that came with your EDM with Fuel Flow.
Mount in a horizontal position with the wires up, as this ensures that the rotor is in proper orientation to the flow of fuel just as it was calibrated.
Be sure there is no bend in the line closer than 6 inches before or after the transducer. Do not use aluminum fittings when installing the fuel flow transducer.
For carbureted engines, before the carburetor. If the transducer is higher than the carburetor, put an anti-siphon loop in the line that peaks higher than the transducer (see installation manual, but the diagram shows the transducer on its side, rather than the correct position which is with the wires coming off the top).
For injected engines, between the engine fuel pump and the servo regulator. For injected engines with vapor return lines (rare), between the servo regulator and the flow divider (spider).
Mounting the transducer between the electric boost pump and the mechanical pump is not recommended.
Do not hard mount the transducer to the engine. Vibration may damage the internal parts of the transducer or cause erratic readings.
Tighten fittings not more than 15 ft lb = 180 in lbs., or two full turns past hand tight.
** Do not use Teflon tape or thread sealent compound of any kind – this will void transducer warranty.** [ See “Report #503 Rev B: Date 03/14/97 under heading #2 “Initial Check Out” – line item #14. ]
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