Flow diverter system for multiple streams for gas turbine engines
US5816042A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 27, 1996 |
| Grant date | Oct 6, 1998 |
| Priority date | — |
| Expiry date | Dec 27, 2016 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K1/06
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.