Gas turbine engine shaft break mitigation

Patent metadata

Field	Value
Publication number	US-11629613-B2
Application number	US-202016744622-A
Country	US
Kind code	B2
Filing date	Jan 16, 2020
Priority date	Feb 4, 2019
Publication date	Apr 18, 2023
Grant date	Apr 18, 2023

Abstract

A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

First claim

What is claimed is:

1. A method of controlling a gas turbine engine, the method including steps of:
detecting a break has occurred in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and
in response to the detecting, activating a shaft break mitigation system which introduces a fluid into a core gas flow of the gas turbine engine downstream of the turbine, wherein the fluid is different from a reheat fuel for a reheat system, or
increases an amount of the fluid being provided into the core gas flow of the gas turbine engine downstream of the turbine,
whereby the fluid reduces an effective area of a nozzle for the core gas flow so as to reduce a mass flow rate of the core gas flow through the turbine.

2. The method of claim 1 , wherein the method further includes, preliminary to the detecting and activating steps, steps of:
predicting a likely occurrence in the future of a shaft break in the shaft, and
in response to the predicting, priming the shaft break mitigation system.

3. The method of claim 2 , wherein the priming of the shaft break mitigation system includes priming one or more pumps operable to pump the fluid.

4. The method of claim 1 wherein the activating of the shaft break mitigation system also includes varying a geometry of a nozzle so as to further reduce the effective area of the nozzle.

5. A gas turbine engine, comprising:
an engine core comprising a turbine, a compressor, and a shaft system connecting the turbine to the compressor; and
an electronic engine controller, wherein
the electronic engine controller is configured to, in response to detecting a break has occurred in the shaft system, activate a shaft break mitigation system which introduces a fluid into a core gas flow of the gas turbine engine downstream of the turbine, wherein the fluid is different from a reheat fuel for a reheat system, or
increases an amount of the fluid being provided into the core gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for
the core gas flow so as to reduce a mass flow rate of the core gas flow through the turbine.

6. The gas turbine engine of claim 5 , wherein the gas turbine engine includes a shaft break prediction system which predicts a likely occurrence in the future of a shaft break in the shaft, and wherein in response to the shaft break prediction system predicting a likely occurrence in the future of a shaft break in the shaft, the electronic engine controller is configured to prime the shaft break mitigation system.

7. The gas turbine engine of claim 6 , wherein the electronic engine controller is configured to prime the shaft break mitigation system by activating one or more pumps operable to pump the fluid.

8. The gas turbine engine of claim 5 , wherein the gas turbine engine includes a nozzle having a variable geometry, and the electronic engine controller is further configured to perform a step, in response to the detecting of the shaft break event, of further reducing the effective area of the nozzle by varying a geometry of the nozzle.

9. An aircraft, including the gas turbine engine of claim 5 .

10. A non-transitory computer readable storage medium storing a computer program comprising code which, when run on a computer, causes the computer to perform the method as claimed in claim 1 .

11. A computer system programmed to perform the method as claimed in claim 1 .

Assignees

• Rolls Royce Plc

Inventors

• Wong Natalie C

Classifications

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F02K3/10

  by after-burners (F02K3/105 takes precedence) · CPC title

• F02C9/46

  Emergency fuel control · CPC title

• F02K1/06

  Varying effective area of jet pipe or nozzle (by using fluid jets to influence the jet flow F02K1/30) · CPC title

• F05D2260/80

  Diagnostics · CPC title