Fuel control system for gas turbine engine

• US 4,423,592 A
• Filed: 11/28/1980
• Issued: 01/03/1984
• Est. Priority Date: 11/28/1980
• Status: Expired due to Term

• Current Assignee: Aviation Electric Limited
• Original Assignee: Aviation Electric Limited
• Inventors: Evans, Rowland M.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US06/210,938
• Time in Patent Office: 1,131 Days
• Field of Search: 60/39.161, 60/39.281
• US Class Current: 60/792
• 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: F05D 2270/02 to control rotational speed (n)

Abstract

A fuel control system (11) for a gas turbine engine (10) is disclosed. The proportional control regulates the fuel flow Wf from a hydromechanical unit (36) based upon an error signal E representing the difference between a demanded speed signal Nd and an actual speed signal Ng. The demanded speed signal Nd is generated by an integrator (32) as the time integral of the difference between the demanded signal Nd and a scheduled speed signal Ngs. Additionally, the difference signal is limited between an upper limit Al and a lower limit Dl prior to the integration by a comparator (28) and limited circuit (30).

Claims

1. A fuel control system for a gas tubine engine comprising:

means for generating an actual speed signal proportional to the actual turbine speed of the gas turbine engine;

means for generating a scheduled speed signal proportional to a desired engine output power;

means for generating a demanded speed signal proportional to the time integral of a difference signal;

means for generating said difference signal proportional to the difference between said scheduled speed signal and said demanded speed signal;

means for generating an error signal proportional to the difference between said demanded speed signal and said actual speed signal; and

means for controlling the fuel flow to the gas turbine engine as a function of said error signal.

2. A fuel control system as defined in claim 1, further including:

means for limiting said difference signal before integration by said demanded signal generating means between an upper limit and a lower limit.

3. A fuel control system as defined in claim 2 wherein:

said upper limit is variable.

4. A fuel control system as defined in claim 3 wherein:

said lower limit is variable.

5. A fuel control system as defined in claim 1, wherein:

said error signal is generated as a function of Wf/Pc where Wf is the fuel flow delivered to the engine; and

Pc is the compressor output pressure.

6. A fuel control system as defined in claim 5, wherein said fuel controlling means includes:

means for multiplying said error signal by said pressure signal to yield the fuel flow input to the engine.

7. A fuel control system for a gas turbine engine of the free turbine type having a gas generator and a power turbine, characterized by:

means for generating an actual speed signal proportional to the actual turbine speed of the gas generator of the engine;

means for generating a scheduled speed signal proportional to the desired output power of the power turbine of the engine;

means for generating a demanded speed signal proportional to the time integral of a difference signal;

means for generating said difference signal proportional to the difference between said scheduled speed signal and said demanded speed signal;

means for generating an error signal proportional to the difference between said demanded speed signal and said actual speed signal; and

means for controlling the fuel flow to the gas generator of the free turbine engine as a function of said error signal.

8. A fuel control system as defined in claim 7, further including:

means for limiting said difference signal before integration by said demanded signal generating means between an upper limit and a lower limit.

9. A fuel control system as defined in claim 8, wherein:

said upper limit is variable.

10. A fuel control system as defined in claim 9, wherein:

said lower limit is variable.

11. A fuel control system as defined in claim 10, wherein:

said error signal is generated as a function of Wf/Pc where Wf is the fuel flow delivered to the engine; and

Pc is the compressor output pressure.

12. A fuel control system as defined in claim 11, wherein said fuel controlling means includes:

means for multiplying said error signal by said pressure signal to yield the fuel flow input to the engine.

13. A fuel control system as defined in claim 7 wherein:

said power turbine operably powers a rotor of a helicopter.

14. A fuel control system defined in claim 13, wherein:

said rotor speed is substantially constant and wherein said desired output power is demanded as a function of the pitch angle of the rotor.

15. A fuel control system for a gas turbine engine including an integrator for generating a demanded speed signal which is proportional to the time integral of an acceleration term;

means for generating an error signal proportional to the difference between the demanded speed signal and an actual speed signal indicative of the actual speed of the engine; and

means for controlling the fuel flow to the engine as a function of said error signal;

said fuel control system characterized by;

means for generating said acceleration term as the difference between said demanded speed signal and a scheduled speed signal indicative of a desired engine output power.