SLAVED FUEL CONTROL FOR MULTI-ENGINED AIRCRAFT

• US 3,811,273 A
• Filed: 03/08/1973
• Issued: 05/21/1974
• Est. Priority Date: 03/08/1973
• Status: Expired due to Term

• Current Assignee: Anthony N. Martin
• Original Assignee: Anthony N. Martin
• Inventors: Martin, Anthony N.
• Primary Examiner(s): Freeh, William L.
• Assistant Examiner(s): Garrett, Robert E.
• Application Number:
  US05/339,479
• Time in Patent Office: 439 Days
• Field of Search: 60/224,223,243,39.15,39.28R,39.28P,97P,97R,39.9R
• US Class Current: 60/39.15
• CPC Class Codes: B64D 31/12 for equalising or synchronising power plants
• CPC Class Codes: F02C 9/42 specially adapted for the control of two or more plants simultaneously
• CPC Class Codes: F02C 9/46 Emergency fuel control

Abstract

When a failure occurs in a fuel control for a turbine engine in a multi-engine aircraft, the fuel metering valve for the engine with the failed fuel control is connected to operate in a slaved mode in response to the control signal produced by the prime fuel control of one of the other aircraft engines. For slaved mode operation, the control signal produced by the prime fuel control is slightly attenuated and lag compensation is applied thereto before the control signal is fed to the fuel metering valve of the slaved engine in order to compensate for variations in engine characteristics and to provide additional safety margin.

Claims

1. In an apParatus powered by a plurality of engines, each of said engines having associated therewith a fuel control unit producing a control signal for scheduling the flow of fuel to said engine, the improvement comprising switch means operable upon a malfunction in the fuel control unit of one of said engines for disabling the control signal therefrom, and means connected with said switch means for simultaneously connecting to said one engine the control signal from one of said other engine fuel control units.

2. Apparatus as in claim 1 and including attenuator means connected in series with the control signal from said other fuel control unit for attenuating the said other control signal.

3. Apparatus as in claim 2 in which said attenuator means includes means for applying compensation to said other control signal.

4. Apparatus as in claim 3 in which said means for applying compensation includes a lag circuit.

5. Apparatus as in claim 1 in which said engines are gas turbine engines in a multi-engine aircraft.

6. A fuel control system comprising a first engine to which fuel is supplied through a metering valve, a first fuel control unit producing a first control signal for scheduling the position of said metering valve, a second engine having associated therewith a second fuel control unit producing a second control signal for scheduling the flow of fuel to said second engine, and switch means connected between said first fuel control unit and said fuel metering valve for disconnecting said first control signal from said fuel metering valve and connecting said fuel metering valve to receive said second control signal.

7. Apparatus as in claim 6 and including attenuator means connected between said switch means and said second fuel control unit for attenuating said second control signal.

8. Apparatus as in claim 7 in which said attenuator means includes means for applying compensation to said second control signal.