Turbojet-ramjet hypersonic aircraft engine
US5284014A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 15, 1992 |
| Grant date | Feb 8, 1994 |
| Priority date | — |
| Expiry date | Oct 15, 2012 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combination turbojet-ramjet engine for powering a hypersonic aircraft is disclosed wherein the intake duct for the ramjet portion of the engine is centrally located within the turbojet portion of the engine in order to improve the access from outside the engine to the turbojet engine portion, as well as to maximize the use of common components and to simplify the control systems for changing from turbojet operation to ramjet operation and vice versa. The ramjet intake duct extends generally parallel to the longitudinal axis of the hypersonic aircraft engine and is located radially inwardly of the compressor, the combustion chamber and the turbine wheel of the turbojet engine portion. Flow control devices are located on the turbojet engine air intake, as well as the ramjet intake duct to control the supply of air to the respective engine portions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.