Gas turbine engine shaft break mitigation
US11428117B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 22, 2020 |
| Grant date | Aug 30, 2022 |
| Priority date | — |
| Expiry date | Dec 24, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/304
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method is provided of controlling a gas turbine having a shaft connecting a compressor to a turbine, as well as having a reheat system, and a gas turbine. The method includes the steps of: operating the engine using the reheat system to provide a mass flow rate of reheat fuel into a gas flow of the gas turbine engine downstream of an exit of the turbine; detecting a shaft break event in the shaft; and in response to this detection, maintaining the mass flow rate of the reheat fuel being provided into the gas flow downstream of the turbine exit, whereby the maintained mass flow rate of reheat fuel raises a back pressure downstream of the turbine and thereby reduces a rotational speed of the turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.