Language selection

Government of Canada / Gouvernement du Canada

Search

Turbojet cycle analysis: the effects of liquid injection at several points in the cycle

From National Research Council Canada

Download
  1. (PDF, 5.4 MiB)
DOIResolve DOI: https://doi.org/10.4224/40003664
AuthorSearch for: 1
Affiliation
  1. National Research Council Canada. National Aeronautical Establishment
FormatText, Technical Report
Physical description36 p.
Abstract
The effects of injecting an evaporating liquid into the gas stream in a turbojet engine are calculated for liquid injection both upstream and downstream of the turbine. The response of the peak cycle temperature, engine fuel flow, tailpipe pressure, gross thrust and turbine pressure ratio, to the liquid injection are presented for a range of liquid latent heats and gas Mach numbers. It is shown that pre-turbine injection, unlike tailpipe injection, automatically requires that the engine be overheated when operating with a fixed propelling nozzle.
Publication date
PublisherNational Research Council Canada
Series
  • Laboratory Report (National Research Council Canada. National Aeronautical Establishment. Engine Laboratory), no. LR-164 (April 1956).
LanguageEnglish
Peer reviewedNo
Export citationExport as RIS
Report a correctionReport a correction (opens in a new tab)
Record identifier066c8934-7e28-483a-92d2-63c9edbe5ad9
Record created2025-08-28
Record modified2025-11-03
Date modified: