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An experimental investigation of the combustion dynamic characteristics of a research multi-element lean direct injection (LDI) combustor under simulated gas turbine conditions was conducted. The objective was to gain a better understanding of the physical phenomena inside a pressurized flametube combustion chamber under acoustically isolated conditions. A nine-point swirl venturi lean direct injection (SV-LDI) geometry was evaluated at inlet pressures up to 2,413 kPa and non-vitiated air temperatures up to 867 K. The equivalence ratio was varied to obtain adiabatic flame temperatures between 1388 K and 1905 K. Dynamic pressure measurements were taken upstream of the SV-LDI, in the combustion zone and downstream of the exit nozzle. The measurements showed that combustion dynamics were fairly small when the fuel was distributed uniformly and mostly due to fluid dynamics effects. Dynamic pressure fluctuations larger than 40 kPa at low frequencies were measured at 653 K inlet temperature and 1117 kPa inlet pressure when fuel was shifted and the pilot fuel injector equivalence ratio was increased to 0.72.

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NASA Technical Reports Server (NTRS)  

Autor(es)

Acosta, Waldo A. -  Chang, Clarence T. - 

Id.: 69703674

Versión: 1.0

Estado: Final

Tipo:  application/pdf - 

Palabras claveFluid Mechanics and Thermodynamics -  Aircraft Propulsion and Power - 

Cobertura:  Unclassified, Unlimited, Publicly available - 

Tipo de recurso: GRC-E-DAA-TN33702  -  AIAA/SAE/ASEE Joint Propulsion Conference; 25-27 Jul. 2016; Salt Lake City, UT; United States  - 

Tipo de Interactividad: Expositivo

Nivel de Interactividad: muy bajo

Audiencia: Estudiante  -  Profesor  -  Autor  - 

Estructura: Atomic

Coste: no

Copyright: sí

: No Copyright

Formatos:  application/pdf - 

Requerimientos técnicos:  Browser: Any - 

Relación: [IsBasedOn] CASI

Fecha de contribución: 11-mar-2017

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