Failsafe electronic control systems

• US 4,718,229 A
• Filed: 09/30/1986
• Issued: 01/12/1988
• Est. Priority Date: 10/30/1985
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Riley, Paul H.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US06/913,364
• Time in Patent Office: 469 Days
• Field of Search: 60/39.091, 60/39.281
• US Class Current: 60/39.281
• CPC Class Codes: F02C 7/25 Fire protection or prevention in general A62
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02C 9/46 Emergency fuel control
• CPC Class Codes: F05D 2270/094 by using back-up controls

Abstract

For flight safety reasons in gas turbine aeroengines it is desireable that in the event of malfunction of an electronic control system--such as a fuel control system--caused, for example, by overheating due to fire, the control system should protect the engine and the aircraft against the consequences of such a malfunction. In the present invention this is achieved by arranging that the control system is provided with a failsafe unit which monitors the condition of the control system and puts the engine into a failsafe control mode if a control system condition signal generated by the failsafe unit varies beyond a predetermined limit. Thus, to ensure safety under overheating conditions, the control system condition signal is representative of the temperature experienced by the fuel control system and the failsafe control mode is a speed-limiting control mode. Specific control mode sequences and corresponding control unit takeover ranges and constructions are disclosed which are effective to ensure that any control system failures have safe predictable results.

Claims

1. A fuel control system for a gas turbine aeroengine, including:

(a) means for sensing the rotational speed of the engine and producing a speed signal representative thereof,

(b) fuel flow metering means for metering the fuel flow to the engine,

(c) first, electronic, control means operative in conjunction with the fuel flow metering means to exercise a first and normal control mode over fuel flow to the engine, and

(d) second, electronic, control means operative in conjunction with the fuel flow metering means to exercise a second and speed limiting control mode over fuel flow to the engine in response to said speed signal, the arrangement being such that the second control means takes over control of fuel flow from the first control means whenever the speed signal exceeds a predetermined value indicating overspeed and retains such control until the speed signal falls below the predetermined value;

wherein the fuel control system is adapted to prevent overspeed of the engine due to failure of electronic components when the fuel control system is subjected to higher than normal operating temperatures, the control system further including means for sensing the temperature of the control system and producing a temperature signal representative thereof, and third control means operative to exercise a third and speed limiting failsafe control mode over fuel flow to the engine in response to said temperature signal, the third control means being adapted to irreversibly take over control of fuel flow from the first and second control means if the temperature of the control system exceeds a predetermined value indicative of likely failure of the first and second control means.

3. A fuel control system according to claim 1 or claim 2 wherein the third control means comprises temperature-controlled electronic switching means and fuel flow restriction means, the electronic switching means being arranged to remove control of fuel flow from the first and second control means when the temperature of the control system exceeds said predetermined value and the fuel flow restriction means being adapted automatically to restrict the fuel flow to a low flow rate when said removal of control occurs, said low flow rate preventing overspeed of the engine from occuring at any condition of the engine.

4. A fuel control system according to claim 3, the electronic switching means comprising:

temperature sensing means for generating a sensed temperature signal expressive of the temperature experienced by the switching means;

temperature datum means for generating a datum temperature signal expressive of said predetermined value of temperature;

comparator means for comparing the sensed temperature signal with the datum temperature signal and outputting a switching signal when the sensed temperature signal exceeds the datum temperature signal; and

a semiconductor switching device connected to remove control of the fuel flow metering means from at least the first control means.

5. A fuel control system according to claim 3 wherein the fuel flow restriction means comprises spring bias means, valve means and associated valve stop means in the fuel flow metering means, the position of said valve means normally being controlled by the first electronic control means to control the flow through the fuel flow metering means, whereby when the electronic switching means removes control of said valve means from the first electronic control means, said valve means is automatically moved against said valve stop means by the spring bias means to establish said low flow rate.

6. A fuel control system according to claim 4 wherein the fuel flow restriction means comprises spring bias means, valve means and associated valve stop means in the fuel flow metering means, the position of said valve means normally being controlled by the first electronic control means to control the flow through the fuel flow metering means, whereby when the electronic switching means removes control of said valve means from the first electronic control means, said valve means is automatically moved against said valve stop means by the spring bias means to establish said low flow rate.

7. A fuel control system according to either of claims 1 or 2 wherein the first control means comprises a digital electronic controller for exercising a normal control mode comprising full authority digital control of the engine.

8. A fuel control system according to either of claims 1 or 2 wherein the second control means causes valve means in the fuel flow metering means to substantially cut off the flow of fuel to the engine when the engine overspeeds, said flow of fuel remaining substantially cut off until the engine speed falls below a predetermined safe value.

9. A fuel control system according to claim 1, wherein the first control means comprises components rated at a first (lower) peak operating temperature and the second and third control means comprise components rated at a second (higher) peak operating temperature, said predetermined value of temperature being slightly less than the second peak operating temperature.

2. A fuel control system for a gas turbine aeroengine, including

(a) first, electronic, control means for generating a first fuel flow control signal for maintaning a normal control mode of the engine,

(b) second, electronic, control means for generating a second fuel flow control signal for preventing overspeed of the engine when said first fuel flow control signal fails to prevent such overspeed, and

(c) fuel flow metering means for metering the fuel flow to the engine in response to the first and second fuel flow control signals;

wherein the fuel control system further includes third speed-limiting failsafe control means adapted to monitor the temperature of the control system and take over control of fuel flow from the first and second electronic control means if the temperature exceeds a predetermined dangerous value.