An Overview of Low-Emission Combustion Research at NASA Glenn

Reddy, Dhanireddy R.; Lee, Chi-Ming

doi:10.1115/gt2016-56100

Cited by 11 publications

(10 citation statements)

References 10 publications

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“…A comparison of OpenNCC CFD emissions predictions for a 'baseline', three-cup, nineteen injector element LDI-3 flametube array was reported in [5]. The comparison between OpenNCC CFD and experimental data [6] focused on two low-power cycle conditions (7% and 30% power).…”

Section: Nineteen Element Flametube -Pilot Injector Redesignmentioning

confidence: 99%

“…Some details of a thirdgeneration multi-point Lean-Direct injection configuration (LDI-3) to meet NASA's N+3 goals were described in [2] 4 . The three-cup flame-tube design proposed by Woodward FST Inc consisted of three multi-element modules (or cups), and leveraged several lessons learned from extensive experimental testing [3] 5 and CFD evaluation [4] 6 of NASA's previous generation N+2 combustor designs [5] 7 .…”

Section: Introductionmentioning

confidence: 99%

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Pilot Injector Redesign to Reduce N+3 Cycle Emissions For A Gas-Turbine Combustor

Ajmani¹,

Lee

Chang

et al. 2019

AIAA Propulsion and Energy 2019 Forum

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An overview is given of an effort for the use of CFD analysis to complement design and configuration definition of third generation Lean-Direct Injection combustion concepts (LDI-3) for NASA's N+3 program. The National Combustion Code (OpenNCC) was used to perform non-reacting and two-phase reacting flow computations for a three-cup, nineteen-element flametube array with redesigned pilot injectors to improve spray and emissions characteristics when compared to a previous LDI-3 design. All computations were performed with a consistent approach to mesh-generation, spray modeling, ignition and kinetics modeling for a 'medium-power' cycle condition. Computational predictions of the aerodynamics of a new pre-filming pilot injector were used to arrive at an optimized aerothermal design that meets effective area and fuel-air mixing criteria. The newly designed pilot injectors were shown to provide considerable improvements in aerodynamic stability, flame-tube pattern factor and NOx emissions, when compared to the original design.

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Section: Nineteen Element Flametube -Pilot Injector Redesignmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Pilot Injector Redesign to Reduce N+3 Cycle Emissions For A Gas-Turbine Combustor

Ajmani¹,

Lee

Chang

et al. 2019

AIAA Propulsion and Energy 2019 Forum

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“…The new TAPS concept will focus on further reduction in NOx emissions, aiming to achieve the NASA N+3 goals. To attain this goal, an even larger proportion of air greater than 70% compared to previous TAPS [73], would be employed for ultra-lean combustion. At the same time, the focus of the research is also placed on further enhancement of fuel-air mixing.…”

Section: Zero Dilution Zonesmentioning

confidence: 99%

“…The recent TAPS III technology adopts Ceramic Matrix CMC liner in a TRA project and by the end of the phase I, a 5 sector testing was performed that has achieved the project emissions goals of NOx (i.e. 75% reduction relative to CAEP/6) at TRL level of 4 [73]. Figure 30 summarises the testing results.…”

Section: Technology Applicationmentioning

confidence: 99%

Review of modern low emissions combustion technologies for aero gas turbine engines

Liu

Sun

Sethi

et al. 2017

Progress in Aerospace Sciences

251

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Pollutant emissions from aircraft in the vicinity of airports and at altitude are of great public concern due to their impact on environment and human health. The legislations aimed at limiting aircraft emissions have become more stringent over the past few decades. This has resulted in an urgent need to develop low emissions combustors in order to meet legislative requirements and reduce the impact of civil aviation on the environment. This article provides a comprehensive review of low emissions combustion technologies for modern aero gas turbines. The review considers current high Technologies Readiness Level (TRL) technologies including Rich-Burn Quick-quench Lean-burn (RQL), Double Annular Combustor (DAC), Twin Annular Premixing Swirler combustors (TAPS), Lean Direct Injection (LDI). It further reviews some of the advanced technologies at lower TRL. These include NASA multi-point LDI, Lean Premixed Prevaporised (LPP), Axially Staged Combustors (ASC) and Variable Geometry Combustors (VGC). The focus of review is placed on working principles, a review of the key technologies (includes the key technology features, methods of realising the technology, associated technology advantages and design challenges, progress in development), technology application and emissions mitigation potential. The article concludes the technology review by providing a technology evaluation matrix based on a number of combustion performance criteria including altitude relight auto-ignition flashback, combustion stability, combustion efficiency, pressure loss, size and weight, liner life and exit temperature distribution.

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“…It is less likely to suffer from combustion instabilities and flashback than the Lean Premixed Prevaporised (LPP) combustor. However, current research including those by the National Aeronautics and Space Administration (NASA) and Rolls-Royce have only reached Technology Readiness Levels (TRLs) of up to 6 and 4, respectively (2,3) . Neither in-service engine application has been achieved, nor have design methodologies been published.…”

Section: Introductionmentioning

confidence: 99%

Preliminary aerodynamic design methodology for aero engine lean direct injection combustors

Li¹,

Sun

Liu

et al. 2017

Aeronaut. j.

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The Lean Direct Injection (LDI) combustor is one of the low-emissions combustors with great potential in aero-engine applications, especially those with high overall pressure ratio. A preliminary design tool providing basic combustor sizing information and qualitative assessment of performance and emission characteristics of the LDI combustor within a short period of time will be of great value to designers. In this research, the methodology of preliminary aerodynamic design for a second-generation LDI (LDI-2) combustor was explored. A computer code was developed based on this method covering the design of air distribution, combustor sizing, diffuser, dilution holes and swirlers. The NASA correlations for NOxemissions are also embedded in the program in order to estimate the NOx production of the designed LDI combustor. A case study was carried out through the design of an LDI-2 combustor named as CULDI2015 and the comparison with an existing rich-burn, quick-quench, lean-burn combustor operating at identical conditions. It is discovered that the LDI combustor could potentially achieve a reduction in liner length and NOxemissions by 18% and 67%, respectively. A sensitivity study on parameters such as equivalence ratio, dome and passage velocity and fuel staging is performed to investigate the effect of design uncertainties on both preliminary design results and NOxproduction. A summary on the variation of design parameters and their impact is presented. The developed tool is proved to be valuable to preliminarily evaluate the LDI combustor performance and NOxemission at the early design stage.

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An Overview of Low-Emission Combustion Research at NASA Glenn

Cited by 11 publications

References 10 publications

Pilot Injector Redesign to Reduce N+3 Cycle Emissions For A Gas-Turbine Combustor

Pilot Injector Redesign to Reduce N+3 Cycle Emissions For A Gas-Turbine Combustor

Review of modern low emissions combustion technologies for aero gas turbine engines

Preliminary aerodynamic design methodology for aero engine lean direct injection combustors

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