A study of hydrogen/air combustor using NCC

Shih, Tsan‐Hsing; Norris, Andrew T.; Iannetti, Anthony; Marek, C. J.; Smith, Timothy D.; Liu, N.-S.; Povinelli, Louis A.

doi:10.2514/6.2001-808

Cited by 10 publications

(6 citation statements)

References 1 publication

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“…10 Work was conducted to compare experimental results from Anderson 8 with the numerical predictions. 11 Once the comparison was completed, the code was used to perform preliminary modeling of fuel injector concepts. 12 Work was also completed to examine the flame structure of a conceptual fuel nozzle at ambient conditions, 13 where data was collected using advanced laser diagnostic techniques which could then be used with computer code development and validation efforts.…”

Section: Introductionmentioning

confidence: 99%

Low Emission Hydrogen Combustors for Gas Turbines Using Lean Direct Injection

Marek

Smith²,

Kundu³

2005

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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One of the key technology challenges for the use of hydrogen in gas turbine engines is the performance of the combustion system, in particular the fuel injectors. To investigate the combustion performance of gaseous hydrogen fuel injectors flame tube combustor experiments were performed. Tests were conducted to measure the nitrogen oxide (NO x ) emissions and combustion performance at inlet conditions of 600 to 1000 °F, 60 to 200 psia, and equivalence ratios up to 0.48. All the injectors were based on Lean Direct Injection (LDI) technology with multiple injection points and quick mixing. One challenge to hydrogen based premixing combustion systems is flashback since hydrogen has a reaction rate over seven times that of Jet-A. To reduce the risk, design mixing times were kept short and velocities high to minimize flashback. Five fuel injector designs were tested in 2.

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Section: Introductionmentioning

confidence: 99%

Low Emission Hydrogen Combustors for Gas Turbines Using Lean Direct Injection

Marek

Smith²,

Kundu³

2005

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Figure 1 shows an example of the speedup that has been achieved with the code on an SGI Origin 2000 [1]. This 3-D test case uses 1.3 million tetrahedral elements for simulation of a premixed hydrogen/air combustor [2], using the Intrinsic Low Dimensional Manifold (ILDM) kinetics module [3,4]. The parallel speedup metric is calculated by taking the ratio of the time per iteration for the serial case versus the time per iteration for the parallel case.…”

Section: Computational Methodmentioning

confidence: 99%

Numerical Prediction of Non-Reacting and Reacting Flow in a Model Gas Turbine Combustor

Davoudzadeh

Liu

2004

Volume 1: Turbo Expo 2004

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The three-dimensional, viscous, turbulent, reacting and non-reacting flow characteristics of a model gas turbine combustor operating on air/methane are simulated via an unstructured and massively parallel Reynolds-Averaged Navier-Stokes (RANS) code. This serves to demonstrate the capabilities of the code for design and analysis of real combustor engines. The effects of some design features of combustors are examined. In addition, the computed results are validated against experimental data. The numerical model encompasses the whole experimental flow passage, including the flow development sections for the air annulus and the fuel pipe, twelve channel air and fuel swirlers, the combustion chamber, and the tail pipe. A cubic non-linear low-Reynolds number K-e turbulence model is used to model turbulence, whereas the eddy-breakup model of Magnussen and Hjertager is used to account for the turbulence combustion interaction. Several RANS calculations are performed to determine the effects of the geometrical features of the combustor, and of the grid resolution on the flow field. The final grid is an all-hexahedron grid containing approximately two and one half million elements. To provide an inlet condition to the main combustion chamber, consistent with the experimental data, flow swirlers are adjusted along the flow delivery inlet passage. Fine details of the complex flow structure such as helicalring vortices, recirculation zones and vortex cores are well captured by the simulation. Consistent with the experimental results, the computational model predicts a major recirculation zone in the central region immediately downstream of the fuel nozzle, a second recirculation zone in the upstream corner of the combustion chamber, and a lifted flame. Further, the computed results predict the experimental data with reasonable accuracy for both the cold flow and for the reacting flow. It is also shown that small changes to the geometry can have noticeable effects on the combustor flowfield.

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“…The combination of these features is usually not available in other CFD codes and gives the NCC an advantage when computing recirculating, turbulent, reacting, spray flows. Previously, the NCC has undergone extensive validation studies for simple flows 14 , complex flows 15 , NO x emissions prediction performance 16 , and traditional gas turbine combustor/injectors 17 .…”

Section: The National Combustion Codementioning

confidence: 99%

NASA Numerical and Experimental Evaluation of UTRC Low Emissions Injector

Hicks

Tedder²,

Anderson³

et al. 2014

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

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Computational and experimental analyses of a PICS-Pilot-In-Can-Swirler technology injector, developed by United TechnologiesResearch Center (UTRC) are presented. NASA has defined technology targets for near term (called "N+1", circa 2015), midterm ("N+2", circa 2020) and far term ("N+3", circa 2030) that specify realistic emissions and fuel efficiency goals for commercial aircraft. This injector has potential for application in an engine to meet the Pratt & Whitney N+3 supersonic cycle goals, or the subsonic N+2 engine cycle goals. Experimental methods were employed to investigate supersonic cruise points as well as select points of the subsonic cycle engine; cruise, approach, and idle with a slightly elevated inlet pressure.Experiments at NASA employed gas analysis and a suite of laser-based measurement techniques to characterize the combustor flow downstream from the PICS dump plane. Optical diagnostics employed for this work included Planar Laser-Induced Fluorescence of fuel for injector spray pattern and Spontaneous Raman Spectroscopy for relative species concentration of fuel and CO 2 .The work reported here used unheated (liquid) Jet-A fuel for all fuel circuits and cycle conditions. The initial tests performed by UTRC used vaporized Jet-A to simulate the expected supersonic cruise condition, which anticipated using fuel as a heat sink.Using the National Combustion Code a PICS-based combustor was modeled with liquid fuel at the supersonic cruise condition. All CFD models used a cubic non-linear k-epsilon turbulence wall functions model, and a semi-detailed Jet-A kinetic mechanism based on a surrogate fuel mixture. Two initial spray droplet size distribution and spray cone conditions were used: 1) an initial condition (Lefebvre) with an assumed Rosin-Rammler distribution, and 7 degree Solid Spray Cone; and 2) the Boundary Layer Stripping (BLS) primary atomization model giving the spray size distribution and directional properties. Contour and line plots are shown in comparison with experimental data (where this data is available) for flow velocities, fuel, and temperature distribution. The CFD results are consistent with experimental observations for fuel distribution and vaporization.Analysis of gas sample results, using a previously-developed NASA NOx correlation, indicates that for sea-level takeoff, the PICS configuration is predicted to deliver an EINOx value of about 3 for the targeted supersonic aircraft. Emissions results at supersonic cruise conditions show potential for meeting the NASA goals with liquid fuel. NomenclatureAST = Advanced Subsonic Technology CFD = computational fluid dynamics CFL = Courant-Friedrichs-Lewy condition C p = specific heat CPU = central processing unit  = turbulent dissipation EINOX = emission index for oxides of nitrogen ERA = environmentally responsible aviation FAR = fuel-to-air ratio FWHM = full width at half maximum JST = Jameson-Schmidt-Turkel dissipation scheme k = turbulent kinetic energy LTO = landing-takeoff cycle  = molecular vibrational energy NCC = National...

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A study of hydrogen/air combustor using NCC

Cited by 10 publications

References 1 publication

Low Emission Hydrogen Combustors for Gas Turbines Using Lean Direct Injection

Low Emission Hydrogen Combustors for Gas Turbines Using Lean Direct Injection

Numerical Prediction of Non-Reacting and Reacting Flow in a Model Gas Turbine Combustor

NASA Numerical and Experimental Evaluation of UTRC Low Emissions Injector

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