Reverse-flow combustor for small gas turbines with pressure-atomizing fuel injectors
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Reverse-flow combustor for small gas turbines with pressure-atomizing fuel injectors

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield, Va .
Written in English

Subjects:

  • Gas-turbines -- Combustion.,
  • Combustion engineering.,
  • Injectors.

Book details:

Edition Notes

StatementCarl T. Norgren, Edward J. Mularz, Stephen M. Riddlebaugh.
SeriesNASA technical paper ; 1260, NASA technical paper -- 1260.
ContributionsMularz, Edward J., Riddlebaugh, Stephen M., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.
The Physical Object
Pagination27 p. :
Number of Pages27
ID Numbers
Open LibraryOL17537448M

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Gas Turbine Reverse-Flow Combustor Research. GE 7FA Gas Turbine. Objective. Investigate the aerothermal behavior in the dump diffuser and the revered-flow combustor with and without jet impingement sheath to achieve more effective coolin. g and reduced aerod. ynamic losses. Reverse-flow Combustor Advantages •. A reverse flow combustor suitable for a small gas turbine (2 to 3 kg/s mass flow) was used to evalute the effect of pressure atomizing fuel injectors on combustor performance. In these tests an. A commercially available natural gas fueled gas turbine engine was operated on hydrogen. Three sets of fuel injectors were developed to facilitate stable operation while generating differing levels of fuel∕air premixing. One set was designed to produce near uniform mixing while the others have differing degrees of tonyasgaapartments.com by: A fuel injector for a combustor and a gas turbine engine, wherein the combustor includes a combustor wall defining a combustion chamber tube surrounded by pressurized air. The injector comprises a nozzle tip assembly protruding through the combustor wall into the chamber, the nozzle tip including a first air passage forming an annular array of individual air passages spaced radially from Cited by:

Abstract. A series of tests have been carried out using a single segment of a tuboannular, aircraft-type, gas turbine combustion chamber to investigate the influences of operating conditions and fuel injection method on exhaust tonyasgaapartments.com by: Abstract Development of a small gas-turbine combustor for ㎾ class APU(Auxiliary Power Unit) has been performed. This combustor is a reverse-annular type and has a tangential swiller . The use of coal as a fuel for a modified gas turbine with a pressurised fluidised bed in place of its normal can– annular combustor system was pioneered in Europe. The pressurised fluidised-bed combustion (PFBC) gas turbine was developed over a 20 year period with funding from the International Energy Agency (IEA) and the UK, German and US Governments. Gas Turbine Fuel Systems and Fuels Other Fuels For industrial engines other fuels have been considered for specific applications/projects, but none have managed to take a significant share of the market. Extensive efforts over many decades have been spent on developing coal as a fuel for gas turbine engines; however, to date success has been.