Mixing in the dome region of a staged gas turbine combustor

Sowa, W. A.; Brady, Ryan; Samuelsen, G. S.

doi:10.2514/3.23678

Cited by 3 publications

(3 citation statements)

References 11 publications

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“…Since the momentum of their liquid fuel sheet was likely to be higher than that of our gaseous propane annular jet, their observations on combustor wall heating and combustion instability were absent in our tests. Also, as Sowa et al (1993) have pointed out, shorter combustor dome length required to confine this type of flame may suppress the formation and strength of large-scale turbulent eddies which trigger combustion instabilities. As shown in Fig.…”

Section: Discussionmentioning

confidence: 98%

“…In these experiments it was observed that, compared to the counter-swirling arrangement, the co-swirling flow spread the fuel-air mixture to the combustor walls and produced a slightly shorter flame, a lower LBO value, and less variability of the combustion characteristics with changes in hardware and flow conditions. For a co-swirl arrangement, , , and Sowa et al (1993) have observed an excessive transport of liquid fuel to the combustor walls resulting in unstable operation. Since the momentum of their liquid fuel sheet was likely to be higher than that of our gaseous propane annular jet, their observations on combustor wall heating and combustion instability were absent in our tests.…”

Section: Discussionmentioning

confidence: 99%

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Studies of Lean Blowout in a Step Swirl Combustor

Durbin

Ballal

1994

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

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The design requirements of a modem gas turbine combustor are increasingly dictated by wide stability limits, short flame length, and uniform mixing. To achieve the best trade-off between the above three factors, flame characteristics (length, shape, mixedness), lean blowout (LBO), and optimum combustor configuration should be investigated over a wide range of inner and outer air velocities, inner and outer vane angles, and co- vs. counter-swirl arrangements. Such an investigation was performed in a step swirl combustor (SSC) designed to simulate the fuel-air mixing pattern in a gas turbine combustor dome fitted with an airblast atomizer. It was found that an increase in the outer vane angle and a decrease in inner air velocity decreased the flame length. LBO was improved when outer flow swirl intensity was increased. An optimum hardware and velocity configuration for the SSC was found for inner swirl = 45°, outer swirl = 60°, co-swirl direction, and inner air velocity = outer air velocity = 16 m/s. This optimum SSC configuration yielded: (i) low values of LBO, (ii) short flame length, (iii) uniformly mixed stable flame, and (iv) little or no variation in these characteristics over the range of operation of SSC. Finally, the co- vs. counter-swirl arrangements and the operation of the optimized combustor configuration were discussed.

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Section: Discussionmentioning

confidence: 98%

Section: Discussionmentioning

confidence: 99%

Studies of Lean Blowout in a Step Swirl Combustor

Durbin

Ballal

1994

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

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show abstract

“…The development of staged combustors with fixed geometry [16][17][18][19] and conventional combustors with variable geometry [20,21], makes it possible to properly control the equivalence ratio of the primary zone at different power settings.…”

Section: Introductionmentioning

confidence: 99%

Hydrogen injection as additional fuel in gas turbine combustor. Evaluation of effects

Juste

2006

International Journal of Hydrogen Energy

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Studies of Lean Blowout in a Step Swirl Combustor

Durbin

Ballal

1996

Journal of Engineering for Gas Turbines and Power

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The design requirements of a modern gas turbine combustor are increasingly dictated by wide stability limits, short flame length, and uniform mixing. To achieve the best trade-off between these three factors, flame characteristics (length, shape, mixedness), lean blowout (LBO), and optimum combustor configuration should be investigated over a wide range of inner and outer air velocities, inner and outer vane angles, and co- versus counterswirl arrangements. Such an investigation was performed in a step swirl combustor (SSC) designed to simulate the fuel–air mixing pattern in a gas turbine combustor dome fitted with an airblast atomizer. It was found that an increase in the outer vane angle and a decrease in inner air velocity decreased the flame length. LBO was improved when outer flow swirl intensity was increased. An optimum hardware and velocity configuration for the SSC was found for inner swirl = 45 deg, outer swirl = 60 deg, coswirl direction, and inner air velocity = outer air velocity = 16 m/s. This optimum SSC configuration yielded: (i) low values of LBO, (ii) short flame length, (iii) uniformly mixed stable flame, and (iv) little or no variation in these characteristics over the range of operation of SSC. Finally, the co- versus counterswirl arrangements and the operation of the optimized combustor configuration are discussed.

show abstract

Mixing in the dome region of a staged gas turbine combustor

Cited by 3 publications

References 11 publications

Studies of Lean Blowout in a Step Swirl Combustor

Studies of Lean Blowout in a Step Swirl Combustor

Hydrogen injection as additional fuel in gas turbine combustor. Evaluation of effects

Studies of Lean Blowout in a Step Swirl Combustor

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