Mixing and Combustion Enhancement in a Generic Combustion Chamber

Mäck, A.; Steelant, Johan; Hannemann, Klaus; Karl, Sebastian; Odam, Judith

doi:10.2514/6.2006-8134

Cited by 8 publications

(16 citation statements)

References 6 publications

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“…Nevertheless, all improvements discussed in [1,2] such as injection angle, injector shape and design, as well as injection Mach number seem to be valid also for the present §ow conditions. For a real application, a tilted injection should also be chosen due to a better overall net thrust on system level.…”

Section: Mixing Results With Generic Boundary Layer In §Owmentioning

confidence: 62%

“…First numerical investigations have shown that the turbulent boundary layer §ow interacting with the injected hydrogen fuel increases the mixing process drastically. This shows a larger impact than the previously investigated parameters in the generic ducts of [1] and [2].…”

Section: Introductionmentioning

confidence: 64%

“…Larger di¨erences occur at higher equivalence ratio (0.7), since the combustion process takes place mainly in the subsonic reverse §ow regime where turbulencecombustion coupling might play a larger role. Without spatially abundant presence of boundary-layer generated turbulence entering the duct, the in §uence of the turbulence was negligible independently from the turbulence model [2]. The combustion e©ciencies were in the range of 30%55% (5 × 5 5 × 20 duct, = 0.5 to 1).…”

Section: Sensitivity Of Numerical Modelingmentioning

confidence: 98%

“…In the past, mixing [1] and combustion [2] processes were systematically analyzed for full-scale combustion chambers at laminar §ow conditions in order to maximize the mixing and combustion e©ciency and, by this, reducing the required combustion chamber length. For generic ducts with homogenous undisturbed in §ow, di¨erent wall injection systems and injector spacings were investigated to maximize the performance.…”

Section: Introductionmentioning

confidence: 99%

“…For generic ducts with homogenous undisturbed in §ow, di¨erent wall injection systems and injector spacings were investigated to maximize the performance. It could be shown that the turbulent §ow generated by the wall boundary layers downstream of the injector and the shear layers of the injected fuel did not have a signi¦cant in §uence on mixing and combustion [2].…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Impact of intake boundary layer turbulence on the combustion behavior in a scramjet

Mäck¹,

Steelant²,

Togiti³

et al. 2009

Progress in Propulsion Physics

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The present investigations focus on the mixing and combustion enhancement capabilities of a boundary layer entering a combustion chamber. Numerical investigations for both a generic con¦guration and a real ramp compression intake of a full-scale vehicle with a combustion chamber height of 0.3 m were performed. The §ow condition is chosen according to possible conditions in a scramjet combustion chamber with 1300-kelvin static temperature, 1-bar static pressure, and a Mach number of 3. The results of this sensitivity study show that both mixing and combustion e©ciency are signi¦cantly increased due to the turbulence of the incoming boundary layer, whereas the required injector spacing to reach optimum mixing and combustion has to be increased. In addition to the classical porthole injection, an injection system with hypermixing capabilities was investigated which showed comparable sensitivities.

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Section: Mixing Results With Generic Boundary Layer In §Owmentioning

confidence: 62%

Section: Introductionmentioning

confidence: 64%

Section: Sensitivity Of Numerical Modelingmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Impact of intake boundary layer turbulence on the combustion behavior in a scramjet

Mäck¹,

Steelant²,

Togiti³

et al. 2009

Progress in Propulsion Physics

View full text Add to dashboard Cite

show abstract

Extrapolation of a generic scramjet model to flight scale by experiments, flight data and CFD

2009

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Multi-Objective Design Optimisation of Inlet and Combustor for Axisymmetric Scramjets

Ogawa¹,

Boyce²,

Isaacs³

et al. 2010

TOTHERJ

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Scramjet airbreathing propulsion is a promising technology for efficient and economical access-to-space. Flow compression in the inlet and fuel combustion in the combustor play a major role in scramjet mechanism, their efficiencies crucially influencing the overall scramjet performance. A double-objective shape optimisation for an axisymmetric inlet and combustor configuration using hydrogen as fuel premixed into air has been performed for minimum total pressure loss and maximum combustion efficiency in the present study. A state-of-the-art MDO (multi-objective design optimisation) capability with surrogate-assisted evolutionary algorithms has been employed, coupled with a CFD solver for inviscid flowfields involving chemical reactions represented by Evans & Schexnayder's model. The obtained Pareto optimal front suggests the possibility of substantial improvement in efficiency and the counteracting nature of the two objective functions. Geometries with higher combustion efficiency are characterised by a higher compression inlet with larger leading-edge radius and a longer combustor, whereas opposite trends are observed for configurations with smaller total pressure loss.

show abstract

Mixing and Combustion Enhancement in a Generic Combustion Chamber

Cited by 8 publications

References 6 publications

Impact of intake boundary layer turbulence on the combustion behavior in a scramjet

Impact of intake boundary layer turbulence on the combustion behavior in a scramjet

Extrapolation of a generic scramjet model to flight scale by experiments, flight data and CFD

Multi-Objective Design Optimisation of Inlet and Combustor for Axisymmetric Scramjets

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