Advanced turbofan engine combustion system design and test verification

Sanborn, J. W.; Lenertz, James; Johnson, J. D.

doi:10.2514/3.23182

Cited by 2 publications

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Development of an Innovative High-Temperature Gas Turbine Fuel Nozzle

Myers¹,

Armstrong²,

White³

et al. 1991

Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

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The objective of the Innovative High-Temperature Fuel Nozzle Program was to design, fabricate, and test propulsion engine fuel nozzles capable of performance despite extreme fuel and air inlet temperatures. Although a variety of both passive and active methods for reducing fuel wetted-surface temperatures were studied, simple thermal barriers were found to offer the best combination of operability, cycle flexibility, and performance. A separate nozzle material study examined several nonmetallics and coating schemes for evidence of passivating or catalytic tendencies. Two pilotless airblast nozzles were developed by employing finite-element modeling to optimize thermal barriers in the stem and tip. Operability of these prototypes was compared to a current state-of-the-art piloted, prefilming airblast nozzle, both on the spray bench and through testing in a can-type combustor. The three nozzles were then equipped with internal thermocouples and operated at 1600F air inlet temperature while injecting marine diesel fuel heated to 350F. Measured and predicted internal temperatures as a function of fuel flow rate were compared. Results show that the thermal barrier systems dramatically reduced wetted-surface temperatures and the potential for coke fouling, even in an extreme environment.

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Development of an Innovative High-Temperature Gas Turbine Fuel Nozzle

Myers¹,

Armstrong²,

White³

et al. 1991

Volume 3: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

View full text Add to dashboard Cite

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A Study on Straight Flow Annular Combustor for Small Scale Turbojet Engine

Kong¹

2001

International Journal of Turbo and Jet Engines

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A combustor of a small scale turbojet engine for the a flight vehicle was studied and appropriateness for design requirements were evaluated through the cold test and the hot test. For the purpose of studying flame stability of a pilot atomizer under ignition, firing tests were carried out at various fuel supply pressures. As the result of the experiment and design revision, optimal combination of the air blast type the main fuel nozzle by design requirements was obtained without fuel splash phenomenon and unstable flame. The combustor was designed and evaluated with detailed investigation and experiments. As the result of the hot test, it was confirmed that the combustor in this study had proper profile factor, pattern factor, flammability limit, total pressure loss and combustor efficiency.

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Advanced turbofan engine combustion system design and test verification

Cited by 2 publications

References 0 publications

Development of an Innovative High-Temperature Gas Turbine Fuel Nozzle

Development of an Innovative High-Temperature Gas Turbine Fuel Nozzle

A Study on Straight Flow Annular Combustor for Small Scale Turbojet Engine

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