Shaft decouple logic for gas turbine engine

• US 6,293,085 B2
• Filed: 11/29/2000
• Issued: 09/25/2001
• Est. Priority Date: 06/05/1998
• Status: Expired due to Term

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Nobre, Antonio Hernani, Thompson, Andrew Hayes, Lisio, Carmine
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US09/725,090
• Publication Number:
  US 20010000090A1
• Time in Patent Office: 300 Days
• Field of Search: 60/390.3, 60/390.91, 60/391.61, 60/392.81
• US Class Current: 60/773
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F01D 21/06 Shutting-down
• CPC Class Codes: F02C 9/46 Emergency fuel control
• CPC Class Codes: F05D 2240/60 Shafts
• CPC Class Codes: F05D 2270/021 to prevent overspeed
• CPC Class Codes: F05D 2270/09 to cope with emergencies
• CPC Class Codes: F05D 2270/091 in particular sudden load loss
• CPC Class Codes: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/304 Spool rotational speed
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The present invention is addressed to a control logic for determining the occurrence of shaft decoupling in a gas turbine engine. The control logic in the preferred embodiment receives inputs for shaft rotational speed and/or compressor pressure and uses these parameters for making a determination of shaft decoupling in fractions of a second, before serious damage to the gas turbine engine can occur. The control logic also utilizes multiple interval sampling, and sampling over multiple channels to verify any determination of shaft decoupling. Once a shaft decouple has been verified, fuel flow to the engine is cut off, thus shutting down the engine.

Claims

1. A method for controlling a turbine engine containing first and second coaxial rotatable shafts, a first row of blades connected to the first shaft and a second row of blades connected to the second shaft downstream of the first row of blades, the method comprising the steps of:

i) sensing the rotational speed of the first row of blades;

ii) sensing the rotational speed of the second row of blades;

iii) processing the signals received from the sensing steps of i) and ii); and

iv) determining the shutting of fuel flow to the engine if the signal of one of i) and ii) indicates that the speed of one of the first row of blades and the second row of blades decelerates below a minimum required level relative to the speed of the other of the first and second row of blades.

2. The method claimed in claim 1, wherein the minimum required level is about 27-28% of maximum speed for the first row of blades when the second row of blades is rotating at between 61%-65% of maximum speed for the second row of blades.

3. An apparatus for controlling a turbine engine containing first and second coaxial rotatable shafts, a first row of blades connected to the first shaft and a second row of blades connected to the second shaft downstream of the first row of blades, characterized by;

a speed sensor to sense rotational speed of the first row of blades;

a speed sensor to sense rotational speed of the second row of blades;

a processor to receive signals received from the speed sensors; and

a fuel controller adapted to shut off fuel flow to the engine in response to a signal received from the processor indicating a rate of change of rotational speeds of one of the first and second shafts caused by decelerating of one shaft below a minimum speed level in proportion to the rotational speed of the other of the first and second shafts.

4. The apparatus claimed in claim 3, wherein at least one of the speed sensors is adapted to sense shaft rotational speed upstream of and adjacent to a row of blades in the compressor.

5. The apparatus claimed in claim 3, further comprising a pressure sensor, wherein the processor is further adapted to receive and compare signals received from the pressure sensor and wherein the fuel flow controller is further adapted to confirm the signal received from the processor with a signal from the pressure sensor before shutting off fuel flow to the engine.

6. The apparatus claimed in claim 3, wherein a pressure sensor is adapted to sense pressure downstream of the compressor.

7. The apparatus claimed in claim 4, wherein the processor is a digital system.

8. The apparatus claimed in claim 5, wherein the processor is a full authority digital engine control.

9. The apparatus claimed in claim 6, wherein the fuel controller includes a rapid response gate array system controlling one or more fuel control valves.