Translating sleeve for cascade type thrust reversing system for fan gas turbine engine for an aircraft
US6170254A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Mar 2, 1999 |
| Grant date | Jan 9, 2001 |
| Priority date | — |
| Expiry date | Mar 2, 2019 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A translating sleeve structure for a cascade type thrust reverser system for controlling fan air for a turbofan aircraft gas turbine jet engine, such translating sleeve having a plurality of circumferentially arranged spaced blocker doors, each of which is hingedly connected to a door receptacle bonded into a single layer honeycomb panel inner wall of the sleeve at a longitudinal position which is aft of bleed ports positioned in the core cowl of the engine for periodically expelling gases from the engine at elevated temperatures and pressures. Positioning such blocker doors aft of the bleed ports precludes injury to the blocker doors or to their hinged connections to the core cowl and permits smaller uniformly sized doors to be used. A fan air flow deflector positioned at the leading inner portion of the inner wall of the translating sleeve assists in turning the flow of the reversed fan air through a cascade structure and access doors provided in the sleeve are vented to permit any fan air that may enter the interior of the sleeve when it is deployed to vent to the exterior without any air pressure buildup within such sleeve.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.