High altitude start of a gas turbine engine using fuel pulsing and starter toggling

Patent metadata

Field	Value
Publication number	US-9267439-B2
Application number	US-201213418983-A
Country	US
Kind code	B2
Filing date	Mar 13, 2012
Priority date	Mar 13, 2012
Publication date	Feb 23, 2016
Grant date	Feb 23, 2016

Abstract

A system for starting a gas turbine engine includes an engine controller and a fuel controller. The engine controller varies the engine speed between a minimum start speed and a maximum start speed until light-off of the engine occurs. The fuel controller operates a fuel command to vary fuel provided to a combustion chamber of the engine until light-off of the engine occurs.

First claim

The invention claimed is:

1. A system for starting a gas turbine engine, the system comprising:
an engine controller for controlling speed of the engine, wherein the engine controller is configured to vary the speed of the engine between a minimum speed value and a maximum speed value for at least two cycles during lighting of the engine, and wherein each of the at least two cycles of varying the speed of the engine includes toggling a starter motor on such that the speed of the engine accelerates to the maximum speed value, and toggling the starter motor off such that the speed of the engine decelerates to the minimum speed value, until light-off of the gas turbine engine has occurred;
a fuel controller for controlling delivery of fuel to a combustor of the engine, wherein the fuel controller is configured to vary the delivery of fuel to the combustor of the engine between a minimum fuel value and a maximum fuel value during the lighting of the engine, and wherein varying the delivery of fuel occurs concurrently with the at least two cycles of varying the speed of the gas turbine engine; and
temperature sensors for monitoring a temperature of an exhaust of the gas turbine engine to determine when the light-off of the gas turbine engine has occurred;
wherein the engine controller is further configured to accelerate the engine to a self-sustaining speed upon determining the light-off of the gas turbine engine has occurred.

2. The system of claim 1 , further comprising a starter motor for controlling the speed of the engine, wherein the engine controller operates the starter motor to spool the engine between the minimum speed value and the maximum speed value.

3. The system of claim 2 , wherein the engine controller is further configured to operate the starter motor to vary the speed of the engine between the minimum speed value and the maximum speed value at a first frequency.

4. The system of claim 3 , wherein the fuel controller is further configured to pulse the fuel command at a second frequency.

5. The system of claim 4 , wherein the second frequency is greater than the first frequency.

6. The system of claim 1 , further comprising one or more igniters for continuously sparking while the engine controller varies the speed of the engine and the fuel controller varies the fuel command of the engine.

7. The system of claim 1 , wherein the engine controller is configured to vary the speed of the engine and the fuel controller is configured to vary the delivery of fuel to the combustor of the engine until the temperature sensors detect a predetermined rise in exhaust temperature of the engine indicative of the light-off of the gas turbine engine.

8. A method of starting a gas turbine engine, the method comprising:
varying a speed of the gas turbine engine between a minimum speed value and a maximum speed value for at least two cycles, wherein each of the at least two cycles of varying the speed of the gas turbine engine includes toggling a starter motor on such that the speed of the engine accelerates to the maximum speed value, and toggling the starter motor off such that the speed of the engine decelerates to the minimum speed value, until light-off of the gas turbine engine has occurred;
varying a fuel command between a minimum fuel value and a maximum fuel value to vary an amount of fuel delivered to a combustor of the engine, wherein varying the fuel command occurs concurrently with the at least two cycles of varying the speed of the gas turbine engine;
monitoring a temperature of an exhaust of the gas turbine engine to determine when the light-off of the gas turbine engine has occurred; and
accelerating the engine to a self-sustaining speed upon determination of the light-off of the gas turbine engine.

9. The method of claim 8 , wherein varying the fuel command between the minimum fuel value and the maximum fuel value comprises pulsing delivery of fuel from fuel nozzles at a first frequency.

10. The method of claim 9 , wherein pulsing the fuel command at a first frequency comprises:
providing a puff of fuel to a combustion chamber for a first time period at the maximum fuel value; and
providing a flow of fuel to the combustion chamber for a second time period at the minimum fuel value.

11. The method of claim 10 , wherein providing a flow of fuel at the minimum fuel value comprises providing no fuel to the combustion chamber.

12. The method of claim 8 , wherein prior to varying the fuel command between a minimum fuel value and a maximum fuel value, a fill routine is performed.

13. The method of claim 8 , wherein monitoring a temperature of an engine exhaust to determine when the gas turbine engine has lit comprises monitoring the engine exhaust for a rise in temperature of 100° F.

Assignees

• Corson Michael
• Winston Kenneth W
• Hamilton Sundstrand Corp

Inventors

• Corson Michael
• Winston Kenneth W

Classifications

• F02C9/26

  Control of fuel supply (F02C9/48 takes precedence; fuel valves F02C7/232) · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C7/26 Primary

  Starting; Ignition · CPC title

• F02C7/268

  Starting drives for the rotor {, acting directly on the rotor of the gas turbine to be started} · CPC title

• F02C7/262

  Restarting after flame-out · CPC title