Fuel flow system

Details Fuel flow system Fuel flow system

1974-07-30

1976-11-09

Gill, James J.

Measuring and testing

Volume or rate of flow

Expansible chamber

G01F 112

Patent

active

039903052

ABSTRACT:
A fuel flow measuring system for measuring the flow rate of the fuel in an aircraft and including a turbine flow transmitter which is inserted in the fuel line of the aircraft and produces an output frequency representing a functional relationship to the volume of fuel passing through the flow transmitter, the functional relationship being referred to as the K factor. A control circuit receives the output frequency and converts it into a DC valve representing the flow rate of the fuel. The flow rate is then displayed on an indicator such as a flow meter. A resistor is located in the flow transmitter and is electrically coupled to the control circuit. The resistor is set at a value to compensate for variation in the functional relationship whereas a temperature sensor, also inserted into the transmitter and electrically coupled to the control circuit, serves as a temperature compensator.

REFERENCES:
patent: 2137133 (1938-11-01), Dallmann
patent: 3176514 (1965-04-01), Foster
patent: 3425274 (1969-02-01), Clement et al.
patent: 3610898 (1971-10-01), Yamamoto et al.
patent: 3688573 (1972-09-01), Garrett
patent: 3729995 (1973-05-01), Kovacs et al.

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