Automatic turbine engine bleed valve control for enhanced fuel management
US5313778A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 10, 1992 |
| Grant date | May 24, 1994 |
| Priority date | — |
| Expiry date | Dec 10, 2012 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/07
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A bleed air control system for an aircraft gas turbine engine operates in a fuel saving mode in response to operation of the aircraft in a steady-state cruise condition (215,350) within a threshold flight envelope (202,310) during steady-state engine operation above a threshold range. During operation in the fuel saving mode, a gas turbine engine compressor bleed valve (10) is closed. The rate of bleed valve closure is determined as a function of bleed valve position (12,20) and gas generator speed (26,30) at the instant the fuel savings mode is initiated. The bleed air control system is returned to normal operation in response to actual or commanded engine acceleration above respective threshold magnitudes, in response to aircraft load factor differing from a reference load factor by a threshold magnitude, and in response to the discontinued operation of the aircraft at steady-state cruise conditions, discontinued steady-state operation of the engine above the transient range, or operation of the aircraft outside of the threshold flight envelope.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.