Overspeed protection system and method

Patent metadata

Field	Value
Publication number	US-11053861-B2
Application number	US-201615059378-A
Country	US
Kind code	B2
Filing date	Mar 3, 2016
Priority date	Mar 3, 2016
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.

First claim

What is claimed is:

1. A method for providing overspeed protection for a gas turbine engine, the gas turbine engine comprising an engine core, an engine shaft, and a spool valve, the method comprising:
determining an overspeed condition of the gas turbine engine; and
reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce a rotational speed of the engine shaft,
wherein the gas turbine engine defines a flowpath and comprises a variable geometry component positioned in the flowpath, the variable geometry component comprising an actuator,
wherein reducing the airflow through the engine core in response to the determined overspeed condition includes positioning the variable geometry component to reduce an effective cross sectional area of the flowpath in response to the determined overspeed condition, which includes rerouting a hydraulic fluid through the spool valve to the actuator of the variable geometry component in response to the determined overspeed condition, and
wherein rerouting the hydraulic fluid through the spool valve includes moving the spool valve from a routine state position in which the hydraulic fluid from an inlet is supplied to a first outlet that is open and that is connected to a combustion line to an overspeed state position in which the first outlet is closed and the hydraulic fluid from the inlet is supplied to a second outlet that is open and that is connected to the actuator of the variable geometry component.

2. The method of claim 1 , wherein the variable geometry component is a fan blade of a fan of the gas turbine engine.

3. The method of claim 1 , wherein the variable geometry component is a guide vane.

4. The method of claim 1 , wherein rerouting the hydraulic fluid includes overriding a fluid signal to the actuator of the variable geometry component.

5. The method of claim 1 ,
wherein the gas turbine engine comprises an engine fuel pump, and
wherein the hydraulic fluid includes a fuel from the engine fuel pump.

6. The method of claim 1 , wherein reducing the airflow through the gas turbine engine core further includes securing the actuator of the variable geometry component to maintain the reduced effective cross sectional area of the flowpath in which the variable geometry component is positioned.

7. The method of claim 6 ,
wherein the gas turbine engine comprises a control circuit for porting the hydraulic fluid to the variable geometry component, and
wherein securing the actuator includes cycling the hydraulic fluid through a portion of the control circuit.

8. A method for providing overspeed protection for a gas turbine engine, the gas turbine engine comprising an engine shaft, a spool valve, a combustion section, and a variable geometry component comprising an actuator, the method comprising:
determining an overspeed condition of the engine shaft;
restricting a fuel flow from the combustion section of the gas turbine engine in response to the overspeed condition;
directing the fuel flow to the actuator of the variable geometry component in response to the determined overspeed condition; and
positioning the variable geometry component in an airflow inhibiting position with the actuator to reduce a rotational speed of the engine shaft in response to the determined overspeed condition, which includes rerouting a hydraulic fluid through the spool valve to the actuator of the variable geometry component in response to the determined overspeed condition,
wherein rerouting the hydraulic fluid through the spool valve includes moving the spool valve from a routine state position in which the hydraulic fluid from an inlet is supplied to a first outlet connected to the combustion section to an overspeed state position in which the first outlet is closed and the hydraulic fluid from the inlet is supplied to a second outlet connected to the actuator of the variable geometry component,
wherein the gas turbine engine defines a flowpath, and
wherein positioning the variable geometry component in the airflow inhibiting position includes reducing an effective cross sectional area of the flowpath.

9. The method of claim 8 , wherein the variable geometry component includes a fan of the gas turbine engine.

10. The method of claim 8 , wherein the variable geometry component includes an inlet guide vane.

11. The method of claim 8 , wherein directing the fuel flow includes directing the fuel flow through the spool valve to the actuator of the variable geometry component.

12. The method of claim 8 , further comprising securing the actuator at the airflow inhibiting position of the variable geometry component,
wherein securing the actuator at the airflow inhibiting position includes cycling a hydraulic fluid through a portion of a control circuit, the hydraulic fluid including the fuel flow.

Assignees

• Gen Electric

Inventors

• Moster David Anthony
• Mailander William James
• Gutz David Allen

Classifications

• F01L21/02

  Piston or piston-rod used as valve members {(F01L25/066 takes precedence)} · CPC title

• F02C9/50

  with control of working fluid flow · CPC title

• F01D21/02

  Shutting-down responsive to overspeed · CPC title

• F02C9/46

  Emergency fuel control · CPC title

• F02C9/00 Primary

  Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) · CPC title