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Theoretical comparison of several methods of thrust augmentation for turbojet engines (Document No: 20050080716)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1948 |
| Description | A theoretical investigation has been made of various methods of thrust augmentation for turbojet engines. The method investigated were tail-pipe burning, water injection at the compressor inlet, a combination of tail-pipe burning and water injection, bleedoff in conjunction with water injection at the compressor inlet, and rocket assist. The effect of ratio of augmented-to-normal total liquid consumption, flight conditions, and design compressor pressure ratio on the augmentation produced by each method were determined. A comparison was also made for a given time of operation of the weight of an augmented engine plus fuel and additional liquids to the weight of a standard engine plus fuel producing the same thrust. |
| File Size | 2274635 |
| Page Count | 41 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050080716 |
| Archival Resource Key | ark:/13960/t6h17bz75 |
| Language | English |
| Publisher Date | 1948-10-27 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
