Blocker door frame pressure structure for translating cowl of cascade thrust reverser for aircraft jet engine
US5927647A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 24, 1997 |
| Grant date | Jul 27, 1999 |
| Priority date | — |
| Expiry date | Sep 24, 2017 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/34
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An improvement in the translating cowl of a cascade type thrust reverser for a high bypass aircraft jet engine that provides a novel blocker door frame arrangement for the inner panel of such cowl. A plurality of forwardly opening spaced circumferentially arranged apertures are provided in the inner panel of the translating cowl and an outer edge portion of a one piece imperforate blocker door frame is sealingly inserted in each such opening by extending the edge portion between the facing sheets of the inner panel for bonding thereto. Each blocker door frame is configured to receive a blocker door that is hinged to such frame at the forward portion of the frame and which is connected by a drag link to a core cowl of the aircraft engine. An annular reinforcing section is secured to the inner surfaces of the blocker door frames and to an end slider portion of the translating cowl for longitudinal reciprocal motion. Another reinforcing section is secured to the forward portion of the blocker door frames and receives an annular seal that engages a fixed portion of the thrust reverser to preclude leakage of the fan duct air flow when the translating cowl is stowed. The two reinforcing …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.