Gas turbine start system to enable rotor thermal stabilization with backup bleed bypass cooling mode
US10711700B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 1, 2017 |
| Grant date | Jul 14, 2020 |
| Priority date | — |
| Expiry date | Oct 29, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/85
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.