Ignition of Conventional and Alternative Fuel at Low Temperatures in a Single-Cup Swirl-Stabilized Combustor

Hendershott, Tyler; Stouffer, Scott D.; Monfort, Jeffrey R.; Diemer, Jacob; Busby, Kenneth; Corporan, Edwin; Wrzesinski, Paul J.; Caswell, Andrew W.

doi:10.2514/6.2018-1422

Cited by 13 publications

(3 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…These conditions were selected because they are some of the most extreme conditions that will be seen within an engine and are consistent with the tests required by ASTM D4054 (Colket et al, 2017;Coppola, 2018). Similar fuel dependencies have been noted for cold ground start, and altitude relight (Hendershott et al, 2018;Stouffer et al, 2020). Nine experimental rigs within the NJFCP, featuring a wide range of geometries and time scales were used to observe fuel effects (Colket and Heyne, 2021).…”

Section: Introductionmentioning

confidence: 65%

“…Experiments performed in the RR were completed at the Air Force Research Laboratory located at Wright-Patterson Air Force Base, and have been published elsewhere (Hendershott et al, 2018;Colborn et al, 2020). The Referee Rig is a non-proprietarty, single-cup, swirl-stabilized combustor designed by GE (this article's correspondance author) with input from four other leading engine manufacturers to simulate representative aerodynamic characteristics of both legacy and emerging, swirl-stabilized, combustors (Colket and Heyne, 2021).…”

Section: Referee Rig Experimentsmentioning

confidence: 99%

See 1 more Smart Citation

Comparing Alternative Jet Fuel Dependencies Between Combustors of Different Size and Mixing Approaches

2021

View full text Add to dashboard Cite

Analyses used to reveal fuel dependencies on lean blow out and ignition at specific operating conditions in specific combustors show inconsistent trends with each other. Such variety is however consistent with the occurrence of transitions between the governing physical phenomena as the ratios between evaporation, mixing, or chemical time scales with their respective residence times also vary with specific operating conditions and combustor geometry. It is demonstrated here that the fuel dependencies on LBO in a large, single-cup, swirl-stabilized, rich-quench-lean combustor varies with operating conditions such that a feature importance match is attained to fuel dependencies observed in a much smaller combustor at one end of the tested range, while a qualitative match to fuel dependencies observed in a lean, premixed, swirler-stabilized combustor of comparable size at the other end of the tested range. The same reference combustor, when tested at cold conditions, is shown to exhibit similar fuel dependencies on ignition performance as the much smaller combustor, when tested at both cold and warm conditions. The practical significance of these findings is that a reference rig, such as the Referee Rig, can capture fuel performance trends of proprietary industry combustors by tailoring the inlet air and fuel temperatures of the tests. It is, therefore, a trustworthy surrogate for screening and evaluating sustainable aviation fuel candidates, reducing the dependency on proprietary industrial combustors for this purpose, thereby increasing transparency within the evaluation process while also expediting the process and reducing cost and fuel volume.

show abstract

Section: Introductionmentioning

confidence: 65%

Section: Referee Rig Experimentsmentioning

confidence: 99%

Comparing Alternative Jet Fuel Dependencies Between Combustors of Different Size and Mixing Approaches

2021

View full text Add to dashboard Cite

show abstract

“…The referee combustor consists of all the features of a practical gas turbine combustor with a hybrid air blast fuel injector with multiple swirlers, primary and secondary rows of dilution holes, and a large number of patterned effusion cooling holes . 9,[27][28][29] The schematic drawing of the referee combustor and the three-dimensional computational domain with a Cartesian coordinate system, origin, and the axes are shown in Figure 1(a). The airflow passages through two sets of concentric axial swirlers and a set of radial swirlers are shown in Figure 1(b).…”

Section: Combustor Configurationmentioning

confidence: 99%

Numerical simulations and analysis of the turbulent flow field in a practical gas turbine engine combustor

Hasti

Kundu

Som

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

View full text Add to dashboard Cite

The turbulent flow field in a practical gas turbine combustor is very complex because of the interactions between various flows resulting from components like multiple types of swirlers, dilution holes, and liner effusion cooling holes. Numerical simulations of flows in such complex combustor configurations are challenging. The challenges result from (a) the complexities of the interfaces between multiple three-dimensional shear layers, (b) the need for proper treatment of a large number of tiny effusion holes with multiple angles, and (c) the requirements for fast turnaround times in support of engineering design optimization. Both the Reynolds averaged Navier–Stokes simulation (RANS) and the large eddy simulation (LES) for the practical combustor geometry are considered. An autonomous meshing using the cut-cell Cartesian method and adaptive mesh refinement (AMR) is demonstrated for the first time to simulate the flow in a practical combustor geometry. The numerical studies include a set of computations of flows under a prescribed pressure drop across the passage of interest and another set of computations with all passages open with a specified total flow rate at the plenum inlet and the pressure at the exit. For both sets, the results of the RANS and the LES flow computations agree with each other and with the corresponding measurements. The results from the high-resolution LES simulations are utilized to gain fundamental insights into the complex turbulent flow field by examining the profiles of the velocity, the vorticity, and the turbulent kinetic energy. The dynamics of the turbulent structures are well captured in the results of the LES simulations.

show abstract

Effect of Varying Internal Geometry on the Near-Field Spray Characteristics of a Swirl Burst Injector

Nasim

Qavi

Jiang

2023

Flow Turbulence Combust

View full text Add to dashboard Cite

Ignition of Conventional and Alternative Fuel at Low Temperatures in a Single-Cup Swirl-Stabilized Combustor

Cited by 13 publications

References 12 publications

Comparing Alternative Jet Fuel Dependencies Between Combustors of Different Size and Mixing Approaches

Comparing Alternative Jet Fuel Dependencies Between Combustors of Different Size and Mixing Approaches

Numerical simulations and analysis of the turbulent flow field in a practical gas turbine engine combustor

Effect of Varying Internal Geometry on the Near-Field Spray Characteristics of a Swirl Burst Injector

Contact Info

Product

Resources

About