Accession Number : ADA324956

Title :   Oscillations in Gas-Turbine Combustors; Control of Rumble, Pattern Factor and Emissions.

Descriptive Note : Final technical rept.,

Corporate Author : EUROPEAN RESEARCH OFFICE LONDON (UNITED KINGDOM)

Personal Author(s) : Whitelaw, J. H.

PDF Url : ADA324956

Report Date : DEC 1996

Pagination or Media Count : 11

Abstract : The proposal which led to the above contract required that measurements be obtained in the combustor of a small gas turbine so as to determine the extent to which oscillations of the gaseous fuel supply would lead to reductions in NO(x) emissions and improvements in pattern factor. The 60 degree sector of the annular combustor in which the measurements were obtained is shown on figure 1 and has been used for many previous steady-state experiments, see for example Bicen, Senda and Whitelaw (1988). It operated with a single primary-zone vortex driven by three film-cooling wall jets and curtailed by the five primary jets. Dilution was achieved with four jets from the outer diameter and two from the inner diameter and directly opposite to two of the outer jets. Results were obtained with and without a turn-around duct, as used in the helicopter for which the engine was designed. The air was supplied through a plenum chamber surrounding the main combustor and a second plenum surrounding the turn-around duct with its own film cooling.

Descriptors :   *EMISSION, *COMBUSTORS, *GAS TURBINES, *NITROGEN OXIDES, *OSCILLATION, STEADY STATE, REACTION TIME, GASES, REDUCTION, FUELS, HELICOPTERS, DUCTS, PATTERNS, FILM COOLING, ANNULAR BURNERS, PLENUM CHAMBERS.

Subject Categories : Inorganic Chemistry
      Combustion and Ignition
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE