Fuel Performance in Reciprocating-piston Engines

Goodger, E. M.

doi:10.1007/978-1-349-02652-4_9

Cited by 2 publications

(2 citation statements)

References 2 publications

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“…Eric Goodger’s method is used. 20 The approach is capable of determining the gas temperatures for any carbon-hydro non-dissociated mixtures and dissociated mixtures. For dissociated all mixtures at higher temperatures, the degree of dissociation is temperature and pressure dependent.…”

Section: Methodology Developmentmentioning

confidence: 99%

Development and application of a preliminary design methodology for modern low emissions aero combustors

Liu

Sun

Sethi

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this article, a preliminary design framework containing a detailed design methodology is developed for modern low emissions aero combustors. The inter-related design elements involving flow distribution, combustor sizing, heat transfer and cooling, emission and performance are coupled in the design process. The physics-based and numerical methods are provided in detail, in addition to empirical or semi-empirical methods. Feasibility assessment on the developed work is presented via case studies. The proposed combustor sizing methodology produces feasible combustor dimensions against the public-domain low emissions combustors. The results produced by the physics-based method show a reasonable agreement with experimental data to represent NOx emissions at key engine power conditions. The developed emission prediction method shows the potential to assess current and future technologies. A two-dimensional global prediction on liner wall temperature distribution for different cooling systems is reasonably captured by the developed finite difference method. It can be of use in the rapid identification of design solutions and initiating the optimisation of the design variables. The altitude relight efficiency predicted shows that the method could be used to provide an indicative assessment of combustor altitude relight capability at the preliminary design phase. The methodology is applied and shows that it enables the automatic design process for the development of a conceptual lean staged low emissions combustor. The design evaluation is then performed. A sensitivity analysis is carried out to assess the design uncertainties. The optimisation of the air distribution and cooling geometrical parameters addresses the trade-off between the NOx emissions and liner wall cooling, which demonstrates that the developed work has potential to identify and solve the design challenges at the early stages of the design process.

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Section: Methodology Developmentmentioning

confidence: 99%

Development and application of a preliminary design methodology for modern low emissions aero combustors

Liu

Sun

Sethi

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

View full text Add to dashboard Cite

show abstract

“…Some general assumptions are made throughout all the simulations performed:All components are adiabatic.No mechanical losses are accounted for.Air is used for the cooling of the turbine blade rows.Diesel chemical proprieties are used in combustion calculations as discussed in Ref 12.Cycle performance is simulated at ISA ambient conditions with relative humidity of 80% (humidity in coastal areas).Cooling water temperature of 288.15 K.…”

Section: 0 Generation Of Training Data Setmentioning

confidence: 99%

Advanced gas turbine performance modelling using response surface methods

2018

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Surrogate models are widely used for dataset correlation. A popular application very frequently shown in public literature is in the field of engineering design where a large number of design parameters are correlated with performance indices of a complex system based on existing numerical or experimental information. Such an approach allows the identification of the key design parameters and their impact on the system’s performance. The generated surrogate model can become part of wider computational platforms and enable optimisation of the complex system without the need to run expensive simulations.In this paper, a number of design point simulations for a combined gas-steam cycle are used to generate a response surface. The generated response surface correlates a range of cycle’s key design parameters with its thermal efficiency while it also enables identification of the optimum overall pressure ratio and the high pressure level of the raised steam across a range of recuperator effectiveness, pinch temperature difference across the heat recovery steam generator and the pressure at the condenser. The accuracy of a range of surrogate models to capture the design space is evaluated using root mean square statistical metrics.

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Fuel Performance in Reciprocating-piston Engines

Cited by 2 publications

References 2 publications

Development and application of a preliminary design methodology for modern low emissions aero combustors

Development and application of a preliminary design methodology for modern low emissions aero combustors

Advanced gas turbine performance modelling using response surface methods

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