Speed modification system for gas turbine engine to allow trimming of excess

• US 6,487,490 B1
• Filed: 02/18/2000
• Issued: 11/26/2002
• Est. Priority Date: 05/26/1999
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Rosenfeld, Taylor J., Kamath, Deepak M., Schings, Bruce G.
• Primary Examiner(s): LOUIS JACQUES, JACQUES H
• Application Number:
  US09/507,411
• Time in Patent Office: 1,012 Days
• Field of Search: 701/99, 701/100, 701/123, 602/04, 602/23, 602/43, 602/36, 602/38, 60/392.81, 602/35, 602/39, 602/33, 602/28, 60/391.4, 60/398.1, 60/397.6
• US Class Current: 701/100
• 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 2270/053 Explicitly mentioned power
• CPC Class Codes: F05D 2270/304 Spool rotational speed

Abstract

The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust performance measured at manufacture or overhaul. In one embodiment, the invention provides an analog speed signal to flight control apparatus. The invention may also be configured to provide a digital speed signal to engine power management control apparatus.

Claims

1. A system for providing a modified fan speed signal for a gas turbine engine having a hydromechanical fuel control system comprising:

a) a memory device for storing fan speed modification level data as a plurality of fan speed modification characteristics;

b) at least one speed monitor for measuring real time rotational fan speed of the gas turbine engine and providing an output signal representing real time speed;

c) an identification plug containing electrical circuitry for activating a fan speed modification characteristic output from said memory device determined by testing of the specific engine being controlled to match actual engine thrust for said specific engine to the nominal thrust profile; and

d) a signal processor for combining said fan speed modification characteristic output and said real time speed to generate a modified fan speed signal.

2. A system according to claim 1, wherein said fan speed modification characteristic output is empirically matched to a predetermined level of thrust performance provided by said engine at each nominal rotational speed.

3. A system according to claim 1 wherein said signal processor provides said modified fan speed signal to a power management control system.

4. A system according to claim 3 wherein said power management control system provides at least one of an analog and digital signal to a flight control apparatus.

5. A system according to claim 1 wherein said signal processor provides as an output said modified fan speed signal to a flight control apparatus.

6. A system according to claim 1 which provides for the transmission of an unmodified, real time fan speed signal in case of system failure.

7. A method for controlling a gas turbine engine having a hydromechanical fuel control system comprising the steps of:

a) sensing rotational fan speed using a speed monitor for providing a real time fan speed signal;

b) providing a predetermined one of a plurality of engine specific speed modification signals from a memory device for a particular engine being monitored, wherein said plurality of engine specific speed modification signals are based on individual engine test results; and

c) summing said real time fan speed signal and said predetermined one of said engine specific speed modification signals to provide a modified fan speed signal.

8. A method according to claim 7 further comprising the step of providing said modified fan speed signal to a flight control apparatus.

9. A method according to claim 7 further comprising the step of providing said modified fan speed signal to a power management control system.

10. A method according to claim 9 for providing at least one of an analog and digital signal to a flight control apparatus.