A Second Generation Swirl-Venturi Lean Direct Injection Combustion Concept

Tacina, Kathleen M.; Chang, Clarence T.; He, Ze; Lee, Phil; Dam, Bidhan; Mongia, H. C.

doi:10.2514/6.2014-3434

Cited by 32 publications

(34 citation statements)

References 2 publications

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“…A computational averaging of the values of NOx across the entire exit plane was deemed an acceptable best-practice for comparison with experimental data of [Tacina 2014b]. …”

Section: No Computations and Einox Comparisonsmentioning

confidence: 99%

CFD Computations of Emissions for LDI-2 Combustors with Simplex and Airblast Injectors

Ajmani¹,

Mongia²,

Lee³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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An effort was undertaken to perform CFD analysis of fluid flow in Lean-Direct Injection (LDI) combustors with axial swirl-venturi elements for the next-generation LDI-2 design. The National Combustion Code (NCC) was used to perform non-reacting and reacting flow computations on several LDI-2 injector configurations in a thirteen-element injector array for different operating conditions. All computations were performed with a consistent approach of mesh-optimization, spray-modeling, ignition and kinetics-modeling with the NCC. Computational predictions of emissions (EINOx, EICO and UHC) were compared with the two sets of experimental data representing respectively low-pressure and highpressure engine cycle conditions.

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“…A computational averaging of the values of NOx across the entire exit plane was deemed an acceptable best-practice for comparison with experimental data of [Tacina 2014b]. …”

Section: No Computations and Einox Comparisonsmentioning

confidence: 99%

CFD Computations of Emissions for LDI-2 Combustors with Simplex and Airblast Injectors

Ajmani¹,

Mongia²,

Lee³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…The emissions and performance characteristics for NASA Glenn led LDI efforts for the 1 st generation (LDI-1) are summarized by [Tacina 2005] followed by the 2 nd generation LDI-2 by [Tacina 2014] and [Zink 2014]. …”

Section: Introductionmentioning

confidence: 99%

“…Experimental measurements of emissions for axial-swirler LDI-2 configurations involving both pressure atomizing and airblast injectors of 13-element sector designs were performed at Woodward FST (for low P 3 ) and at NASA Glenn Research Center (GRC) for moderately high P 3 conditions [Tacina 2014]. The empirical design of the three LDI-2 injectors was based on the experience of the nine-element LDI-1 arrays involving axial-swirlers [Tacina 2005].…”

Section: Introductionmentioning

confidence: 99%

Parametric Design of Injectors for LDI-3 Combustors

Ajmani¹,

Mongia

Lee

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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Application of a partially calibrated National Combustion Code (NCC) for providing guidance in the design of the 3 rd generation of the Lean-Direct Injection (LDI) multi-element combustion configuration (LDI-3) is summarized. NCC was used to perform non-reacting and two-phase reacting flow computations on several LDI-3 injector configurations in a single-element and a five-element injector array. All computations were performed with a consistent approach for mesh-generation, turbulence, spray simulations, ignition and chemical kinetics-modeling. Both qualitative and quantitative assessment of the computed flowfield characteristics of the several design options led to selection of an optimal injector LDI-3 design that met all the requirements including effective area, aerodynamics and fuel-air mixing criteria. Computed LDI-3 emissions (namely, NOx, CO and UHC) will be compared with the prior generation LDI-2 combustor experimental data at relevant engine cycle conditions. INTRODUCTIONNASA's Environmentally Responsible Aviation (ERA) program has revived interest in defining the 2 nd generation LDI concepts (LDI-2) for meeting the N+2 technology goals of emissions and performance. The emissions and performance characteristics for NASA Glenn led LDI efforts for the 1 st generation (LDI-1) are summarized by [Tacina 2005] followed by the 2 nd generation LDI-2 by [Tacina 2014] and [Zink 2014]. Experimental measurements of emissions for axial-swirler LDI-2 configurations involving both pressure atomizing and airblast injectors of 13-element sector designs were performed at Woodward FST (for low P 3 ) and at NASA Glenn Research Center (GRC) for moderately high P 3 conditions [Tacina 2014]. The empirical design of the three LDI-2 injectors was based on the experience of the nine-element LDI-1 arrays involving axial-swirlers [Tacina 2005]. The experimental activities on LDI-1 and LDI-2 along with empirical correlation development effort have recently been complemented by NCC calibration works with both single and multi-element configurations, as summarized by [Ajmani 2013] for LDI-1, and [Ajmani 2014a, 2014b] for two LDI-2 configurations.NCC is a reacting flow CFD computational code formulated, developed and validated at NASA Glenn Research Center (GRC). NCC has been used extensively to analyze a single-injector LDI geometry [Liu 2011, Liu 2013 and multiple-injector LDI-1 configurations [Davoudzadeh 2006, Iannetti 2008, Ajmani 2013. These works helped establish best practices for CFD analysis of LDI systems with NCC, similar to FLUENT-based methodology summarized by [Mongia 2008] for application of CFD in combustion system design and development process. The best practices evolved through LDI-1 computations provided the basis for calibrating NCC with the LDI-2 data as summarized by [Ajmani 2014a], a first publication that is planned to be followed by some future articles describing more extensive calibration with all the three LDI-2 configurations tested at NASA.This paper provides a summary on the use of the partially cali...

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“…Others utilized multiple injectors more closely resembling an actual engine configuration and were experimentally evaluated at inlet conditions close to actual engine conditions. [14][15][16].…”

Section: I Introductionmentioning

confidence: 99%

Comparison of Combustion Dynamic Characteristics of Two Advanced Multi-Cup Fuel Injectors

Acosta

Chang

2018

2018 Joint Propulsion Conference

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An experimental investigation of the combustion dynamic characteristics of two advanced multi-cup lean direct injectors (LDI) under simulated gas turbine combustor conditions was conducted. The objective was to gain a better understanding of the physical phenomena inside a pressurized flame tube combustion chamber and study the effects of injector flow number on combustion dynamics. The injectors are known as Three-zone Injectors one and two or 3ZI-1 and 3ZI-2, respectively. The injectors were experimentally evaluated at inlet pressures up to 1.724 MPa, non-vitiated air temperatures up to 828K, and adiabatic flame temperatures up to 1975K. Dynamic pressure measurements were taken upstream of the injectors and in the combustion zone. The combustion dynamic behavior of the two injectors was measured over a range of inlet pressures, inlet temperatures, fuel air ratios, and fuel flow splits.

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A Second Generation Swirl-Venturi Lean Direct Injection Combustion Concept

Cited by 32 publications

References 2 publications

CFD Computations of Emissions for LDI-2 Combustors with Simplex and Airblast Injectors

CFD Computations of Emissions for LDI-2 Combustors with Simplex and Airblast Injectors

Parametric Design of Injectors for LDI-3 Combustors

Comparison of Combustion Dynamic Characteristics of Two Advanced Multi-Cup Fuel Injectors

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