Sub-idle speed control apparatus for an airplane turbine engine
US4541237A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Oct 17, 1983 |
| Grant date | Sep 17, 1985 |
| Priority date | — |
| Expiry date | Oct 17, 2003 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/071
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A sub-idle speed control apparatus for reducing the thrust of an airplane turbine engine is provided. The subject invention reduces the compressor discharge pressure measured by an existing pressure sensing means which proportionally reduces the fuel flow to the engine. Hence, the engine speed is reduced resulting in a lower engine thrust. A switch activates the apparatus which closes a normally open valve in the existing pressure line between the compressor and the pressure sensing means and diverts the pressure through a by-pass line having a restrictor. The by-pass line is connected to the existing pressure line on the compressor side and the pressure sensing side of the normally open valve. A normally closed valve and a spring loaded valve respectively are connected to the existing pressure line and the by-pass line at the connection point nearest the pressure sensing means. When the apparatus is activated the normally closed valve is opened simultaneously with the closing of the normally open valve. The spring loaded valve maintains the flow of pressure through the restrictor which acts to reduce the pressure flowing through the restrictor and thus reducing the pressure measur…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.