Digital Computer Methods for Prediction of Gas Turbine Dynamic Response

Fawke, A. J.; Saravanamuttoo, H. I. H.

doi:10.4271/710550

Cited by 45 publications

(40 citation statements)

References 3 publications

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“…17, Saravanamuttoo and Fawke 18 discussed the applicationof both analogand digitalcomputermethodsfor simulating dynamics of a twin-spool turbojet with variable nozzle, compared the relative merits of analog and digital simulation, and highlighted the simulation requirements. Fawke and Saravanamuttoo 19 veried that results from digital simulation 17,18 are in good agreement with the engine test bed running, indicating that the proposed simulation technique is an invaluable tool in the development of new engines.…”

Section: Detailed Engine Simulationsupporting

confidence: 67%

Survey of Advancements in Jet-Engine Thermodynamic Simulation

Sanghi

Lakshmanan

Sundararajan

2000

Journal of Propulsion and Power

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The art of engine simulation has come into existence with the advent of analog and digital computers and has become an integral part of any engine development program. It has attracted considerable attention from researchers because of the tremendous bene ts it offers not only in terms of cost reduction, but also because of the con dence it induces into the behavior of gas turbine being designed. A substantial number of works have been carried out in the eld of engine simulation and its design applications during the past 50 years. The present paper intends to give a comprehensive overview of the attempts that have been made by the earlier researchers, and the considerable amount of knowledge, database, and the expertise that has been made available. Nomenclature= mass ow rate W F = fuel ow rate c = ratio of speci c heats D = change/error in a quantity g m = spool mechanical ef ciency r = total pressure loss coef cient Subscripts ACC = engine accessories BP = bypass duct H, HP = high-pressurespool HPC = high-pressurecompressor HPT = high-pressureturbine L, LP = low-pressure spool LPC = low-pressure compressor LPT = low-pressure turbine nz = nozzle a = ambient conditions 1, 2, 3, = engine stations 4, 5, 6, . . .

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Section: Detailed Engine Simulationsupporting

confidence: 67%

Survey of Advancements in Jet-Engine Thermodynamic Simulation

Sanghi

Lakshmanan

Sundararajan

2000

Journal of Propulsion and Power

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“…Off-design matching was achieved using the generic match ing procedure presented in Ref. [30]. All thermodynamic calcula tions were based on the assumption of an ideal gas (i.e., variable specific heat capacity); therefore, the main thermodynamic equa tion used was the Gibbs equation.…”

Section: Introductionmentioning

confidence: 99%

On the Optimization of a Geared Fan Intercooled Core Engine Design

Kyprianidis

Rolt

2014

Journal of Engineering for Gas Turbines and Power

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Reduction of CO2 emissions is strongly linked with the improvement of engine specific fuel consumption (SFC), as well as the reduction of engine nacelle drag and weight. One alternative design approach to improving SFC is to consider a geared fan combined with an increased overall pressure ratio (OPR) intercooled core performance cycle. Thermal benefits from intercooling have been well documented in the literature. Nevertheless, there is little information available in the public domain with respect to design space exploration of such an engine concept when combined with a geared fan. The present work uses a multidisciplinary conceptual design too! to further analyze the option of an intercooled core geared fan aero engine for long haul applications with a 2020 entry into service technology level assumption. The proposed design methodology is capable, with the utilized tool, of exploring the interaction of design criteria and providing critical design insight at engine-aircraft system level. Previous work by the authors focused on understanding the design space for this particular configuration with minimum SFC. engine weight, and mission fuel in mind. This was achieved by means of a parametric analysis, varying several engine design parameters-but only one at a time. The present work attempts to identify "globally " fuel burn optimal values for a set of engine design parameters by varying them all simultaneously. This permits the nonlinear interactions between the parameters to be accounted for. Special attention has been given to the fuel burn impact of the reduced high pressure compressor (HPC) efficiency levels associated with low last stage blade heights. Three fuel optimal designs are considered, based on different assumptions. The results indicate that it is preferable to trade OPR and pressure ratio split exponent, rather than specific thrust, as means of increasing blade height and hence reducing the associated fuel consumption penalties. It is interesting to note that even when considering the effect of HPC last stage blade height on efficiency there is still an equivalently good design at a reduced OPR. This provides evidence that the overall economic optimum could be for a lower OPR cycle. Customer requirements such as take off distance and time to height play a very important role in determining a fuel optimal engine design. Tougher customer requirements result in bigger and heavier engines that burn more fuel. Higher OPR intercooled engine cycles clearly become more attractive in aircraft applications that require larger engine sizes.

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“…characteristics as well as empirical correlations (Walsh and Fletcher, 1998 Fawke and Saravanamuttoo (1971).…”

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confidence: 99%

Techno-economic viability assessments of greener propulsion technology under potential environmental regulatory policy scenarios

et al. 2015

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PostprintThis is the accepted version of a paper published in Applied Energy. This paper has been peer-reviewed but does not include the final publisher proof-corrections or journal pagination. Citation for the original published paper (version of record):Nalianda, D., Kyprianidis, K., Sethi, V., Singh, R. (2015) Techno-economic viability assessments of greener propulsion technology under potential environmental regulatory policy scenarios.Applied Energy, http://dx.doi.org/10.1016/j.apenergy. 2015.07.017 Access to the published version may require subscription. N.B. When citing this work, cite the original published paper. Permanent link to this version:http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-28786 59The aviation sector has played a significant role in shaping the world into what it is today. The rapid 60 growth of global economies and the corresponding sharp rise in the number of people now wanting to 61 travel on business and for pleasure, has largely been responsible for the development of this industry. 62However the significantly large increase in air passengers over the years has led to an increase in air 63 traffic and a corresponding rise in fuel consumption, aviation emissions and noise. 64Over the years, the industry has consistently invested in improving technology and introducing it into 65 commercial applications, with the aim to always remain profitable. With fuel expenses being a 66 significant part of an airline's operating cost, the core focus of technology development in the past has 67 been to constantly improve fuel economy. This has been accomplished whilst actively striving to lower 68 costs (production and maintenance) reduce weight, maintain Landing and Take-Off (LTO) cycle noise 69 and NOx within certification limits and improve safety and reliability. However, with aviation 70 emissions now becoming a cause for growing global concern and various emission mitigation policies 71 coming into focus, the industry is actively pursuing even "greener" and quieter solutions for the future. 95The primary objective of the current work is to specifically assess economic viability and the 96 boundaries within which a particular energy efficiency improvement technology is financially 97 sustainable. In more detail, the work introduces an integrated methodology that may be used to 98 assess economic viability by demonstrating the sensitivity of operating cost to uncertain acquisition 99 prices and maintenance costs of futuristic technology. 100The focus of the work is to combine energy efficiency technology assessments with concepts of Net 101Present Value (NPV) and Internal Rate of Return (IRR) within an investment cost analysis approach. 102The study will first utilise and further develop a Techno-economic Environmental Risk Analysis 103(TERA) framework to produce a set of assessments (Kyprianidis, et al., 2008; Pascovici, D.S, 2008; 104 Kyprianidis, 2010). These assessments will compare a novel technology with competing conventional 105 solutions and establish its benefits in term...

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Digital Computer Methods for Prediction of Gas Turbine Dynamic Response

Cited by 45 publications

References 3 publications

Survey of Advancements in Jet-Engine Thermodynamic Simulation

Survey of Advancements in Jet-Engine Thermodynamic Simulation

On the Optimization of a Geared Fan Intercooled Core Engine Design

Techno-economic viability assessments of greener propulsion technology under potential environmental regulatory policy scenarios

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