EXPERIMENTAL AND DESIGN STUDIES FOR TURBO-RAMJET COMBINATION ENGINE. VOLUME VII - COMBUSTION TESTS AT SACLAY.
Abstract
This volume deals with the tests carried out on the combustion chamber developed during the test program on the 15,000 HP bench at The Gatines. The Air supply permitted the simulation of flight conditions at: freestream Mach No. = 1.5 in pure turbofan operation (the ramjet secondary duct was closed and the primary flow was supplied in air at the bench generating temperature); freestream Mach No. = 2 in turbofan-ramjet operation (with a mixture of the fan and ramjet secondary flows); and freestream Mach no. = 2.5, 3, 3.5 and 4 when operating with the ramjet alone (the fan secondary duct was closed and the turbofan primary flow was nil). The altitudes simulated for each configuration were such that the range covered included the limit zone where the combustion chamber inlet pressure was low, i.e. the most unfavourable condition for combustion. In these conditions, the results obtained have enabled us to plot the combustion efficiency values in various points for a relatively unfavourable flight path for combustion considerations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1966
- Accession Number
- AD0484776
Entities
People
- A. Gozlan
- M. Ravel
- P. Chaulin