Integrated CFD modeling of gas turbine combustors

Fuller, Eric; Smith, Clifford E.

doi:10.2514/6.1993-2196

Cited by 9 publications

(4 citation statements)

References 5 publications

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“…In the turbulence model the mixing process is described by the tur bulent diffusion and its coefficient Dr exceeding the molecular diffu sion usually by orders of magnitude. It is well known, that the k-E turbulence model underpredicts the mixing intensity (see Bain et al, 1992 andFuller andSmith, 1993). Turbulent fuel mixing and heat con- Prandtl and Schmidt numbers, which are of the oder of 1.…”

Section: Comments On Numerical Issuesmentioning

confidence: 99%

“…Specifically in gas turbine combustion cham bers the fuel nozzle is of major importance for the flowand mixrure field in the primary combustion zone. As shown by Fuller and Smith (1993) the CFD results are very sensitive to the fuel nozzle boundary specification. Varying the turbulence level at the fuel nozzle-combustor interface they obtained strongly different pattern factors of the exit tem perature traverse using, however, only 70000 computational grid cells.…”

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confidence: 99%

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CFD Liquid Spray Combustion Analysis of a Single Annular Gas Turbine Combustor

Smiljanovski

Brehm

1999

Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

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In this paper CFD analysis of the steady two-phase turbulent combusting flow in a single annular low-NOx combustor is presented. For this purpose the commercial code CFD-ACE (1998) was used, where Eulerian equations are solved for the gas phase and the liquid spray fuel droplets are treated in a Lagrangian frame of reference allowing for evaporation of droplets and providing source terms for the gas phase. The standard k-ε model was used for turbulence and an assumed shape probability density function was used for the instantaneous chemistry in the conserved scalar combustion model. Thermal NOx is assumed to be the only source of NOx production and is decoupled from the gas phase reacting flow and calculated in a postprocessing step. The calculation is done on a block structured multi-domain computational grid. Particular attention has be paid to the detailed modeling of the fuel injector having multiple air swirler passages starting from the trailing edge of the air swirler vanes and utilizing up to 400000 computational grid cells for the entire model. The model represents the single annular low-NOx combustor for the BR700 aircraft engine family, which is based on a Rich Burn - Quick Quench - Lean Burn (RQL) concept. CFD analysis is done for high power reduced take off conditions and is compared with full annular rig test results for the temperature traverse and the integral EINOx. The results imply satisfactory prediction capability for the EINOx and the average radial temperature distribution. The prediction of the details of the temperature traverse is not satisfactory and will remain a challenge for the future.

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Section: Comments On Numerical Issuesmentioning

confidence: 99%

mentioning

confidence: 99%

CFD Liquid Spray Combustion Analysis of a Single Annular Gas Turbine Combustor

Smiljanovski

Brehm

1999

Volume 2: Coal, Biomass and Alternative Fuels; Combustion and Fuels; Oil and Gas Applications; Cycle Innovations

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“…With the development of numerical computing technologies, numeric simulation plays an increasingly important role in the study on engine steady-state performance. At present, the three-dimensional model [28][29][30] and zero-dimensional model [26,31,32] of an engine are commonly used in the numeric simulation processes. The steady-state performance numeric simulation with three-dimensional model is a method to simulate the engine by establishing a fine engine flow channel model according to the specific structure and size of the engine [28][29][30]33,34] and using computational fluid dynamics (CFD) technologies to carry out thermodynamical calculation of the whole engine [35][36][37].…”

Section: Introductionmentioning

confidence: 99%

“…At present, the three-dimensional model [28][29][30] and zero-dimensional model [26,31,32] of an engine are commonly used in the numeric simulation processes. The steady-state performance numeric simulation with three-dimensional model is a method to simulate the engine by establishing a fine engine flow channel model according to the specific structure and size of the engine [28][29][30]33,34] and using computational fluid dynamics (CFD) technologies to carry out thermodynamical calculation of the whole engine [35][36][37]. This method has high complexity, requires a huge amount of calculation, and it depends on the specific structure of the engine, and the accuracy of both the model and the CFD algorithms will have a direct impact on the calculation results [35][36][37].…”

Section: Introductionmentioning

confidence: 99%

A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems

Meng¹,

Zhu²,

Chen³

et al. 2021

Energies

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In the process of studying the steady-state performance and component matching of adaptive cycle engines with convertible fan system, it was found that the front fan and aft fan stage have a unique matching problem when the mode select valve is closed and engine is operating at higher Mach number conditions. The cause of this matching problem was studied with numeric simulation in this paper. Based on the features of adaptive cycle engines with convertible fan system, the possible methods and their feasibilities of solving this matching problem were also discussed. According to the results, the flow rate adjustment capacity of the aft fan stage directly determines the occurrence and severity of this matching problem. The matching problem can be ameliorated in some extent by either reducing the design second bypass ratio or adjusting the variable geometry mechanisms, but it cannot be completely solved at the aspect of component matching mechanism.

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Conjugated heat transfer and temperature distributions in a gas turbine combustion liner under base-load operation

et al. 2010

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Prediction of temperature distributions on hot components is important in development of a gas turbine combustion liner. The present study investigated conjugated heat transfer to obtain temperature distributions in a combustion liner with six combustion nozzles. 3D-numerical simulations using FVM commercial codes, Fluent and CFX were performed to calculate combustion and heat transfer distributions. The temperature distributions in the combustor liner were calculated by conjugation of conduction and convection (heat transfer coefficients) obtained by combustion and cooling flow analysis. The wall temperature was the highest on the attachment points of the combustion gas from combustion nozzles, but the temperature gradient was high at the after shell section with low wall temperature.

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Integrated CFD modeling of gas turbine combustors

Cited by 9 publications

References 5 publications

CFD Liquid Spray Combustion Analysis of a Single Annular Gas Turbine Combustor

CFD Liquid Spray Combustion Analysis of a Single Annular Gas Turbine Combustor

A Matching Problem between the Front Fan and Aft Fan Stages in Adaptive Cycle Engines with Convertible Fan Systems

Conjugated heat transfer and temperature distributions in a gas turbine combustion liner under base-load operation

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