Modular composite cascade assembly
US4778110A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 30, 1982 |
| Grant date | Oct 18, 1988 |
| Priority date | — |
| Expiry date | Sep 30, 2002 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cascade assembly for directing the gases externally of a jet aircraft engine in a forwardly direction when the engine is in a gas reversing mode. The cascade assembly comprises a plurality of cascade panel sections positioned in a side by side relationship over an opening in the engine nacelle. The panel sections have a plurality of spaced apart curvilinear vanes angled from the centerline of the engine. Longitudinal beams are positioned over the longitudinal edges and adjacent ends of at least one cascade panel section to secure it in place. The beam is "T" configured in the cross-section with feet or pads on each end to overlay the longitudinal outer edge and adjacent end surfaces of the cascade panel section or sections which it is securing in place. The pads or feet on the beam ends include apertures therethrough for securing the beams to aircraft structure. Both the cascade panel sections and beams are constructed of molded plastic or cured composite materials.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.