Accession Number : AD0005159


Title :   EFFECT OF AXIALLY STAGED FUEL INTRODUCTION ON PERFORMANCE OF ONE-QUARTER SECTOR OF ANNULAR TURBOJET COMBUSTOR


Descriptive Note : Research memo.


Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH GLENN RESEARCH CENTER


Personal Author(s) : Zettle, Eugene V ; Mark, Herman


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/005159.pdf


Report Date : 30 Mar 1953


Pagination or Media Count : 32


Abstract : An investigation was conducted to determine the effect of staging the fuel introduction in the primary zone on the performance of a one-quarter sector of a single-annulus turbojet combustor. Pressure-atomized liquid fuel was introduced simultaneously through hollow-cone spray nozzles spraying axially from the upstream face of the combustor and through small fan spray nozzles spraying radially into the combustor and located on the walls of the combustor as much as 5 inches downstream of the main fuel manifold. The investigation was made at a constant combustor-inlet pressure of 15 inches of mercury absolute, at two combustor-inlet-air temperatures (80 deg and 270 deg F) and over a range of air flows from 1.5 to 3.6 pounds per second per square foot.


Descriptors :   *TURBOJET ENGINES , *COMBUSTION CHAMBERS , ANNULAR BURNERS , FUEL INJECTION , COMBUSTORS , AIR FLOW , MANIFOLDS(ENGINES)


Subject Categories : Jet and Gas Turbine Engines
      Combustion and Ignition


Distribution Statement : APPROVED FOR PUBLIC RELEASE