Effect of jet noise reduction on gas turbine engine efficiency

Doulgeris, Georgios; Korakianitis, Theodosios; Avital, Eldad; Pilidis, Pericles; Laskaridis, Panagiotis

doi:10.1177/0954410012456925

Cited by 3 publications

(4 citation statements)

References 25 publications

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“…Following the aforementioned principle, Guha et al used Equation (4) in order to select the optimum diameter for their turbofan design studies. In similar conventional turbofan optimisation studies, the method of Gerend and Roundhill was used, either in its original version (37) , or extrapolated at higher bypass ratios (38) , or recalibrated around a more modern turbofan (36,39) . The main disadvantage of even the most complete 'whole engine based' analysis, such as the one of Gerend and Roundhill, is their dependency on engine data, which many times are not coherent and involve numerous uncertainties.…”

Section: Methods Qualitative Analysismentioning

confidence: 99%

Evaluation of aero gas turbine preliminary weight estimation methods

Lolis

Giannakakis

Sethi

et al. 2014

Aeronaut. j. (1968)

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The estimation of gas turbine engine weight during the preliminary or conceptual design phase is a key part of a Techno-economic Environmental Risk Analysis (TERA). Several methods that are available in the public domain are analysed and compared, in order to establish the physics driving them and their suitability for the weight estimation of modern gas turbine engines. Among the tested methods, only WATE managed to achieve acceptable accuracy for engine optimisation studies. This work demonstrates that the age and restrictions of existing 'whole engine based' methods, along with their dependency on old engine databases make them unsuitable for future and novel aero engines. A hybrid weight modelling approach is proposed as a solution permitting the creation of simple 'whole engine based' methods that do not depend on the availability of existing engine data, which are also subject to uncertainties and incoherencies.

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Section: Methods Qualitative Analysismentioning

confidence: 99%

Evaluation of aero gas turbine preliminary weight estimation methods

Lolis

Giannakakis

Sethi

et al. 2014

Aeronaut. j. (1968)

View full text Add to dashboard Cite

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“…13 Hermes is based on aircraft performance theory explained in Jenkinson et al 14 The software consists of six modules as illustrated in Figure 5, which also shows the interactions of these modules. The input data module includes the geometric characteristics such as the span, swept angle, wing area, tip-to-chord ratio, fuselage length and diameter that enables the estimation of aircraft drag and performance.…”

Section: The Engine and Aircraft Modellingmentioning

confidence: 99%

“…The aircraft model implemented is Hermes, another in-house model that accounts for the aerodynamic, structural and loading characteristics of the airframe; all linked with Turbomatch and hence enables the calculation of thrust settings and engine performance for the different flight segments and deviation mission. 13 Hermes is based on aircraft performance theory explained in Jenkinson et al. 14 The software consists of six modules as illustrated in Figure 5, which also shows the interactions of these modules.…”

Section: The Engine and Aircraft Modellingmentioning

confidence: 99%

Aero engine compressor fouling effects for short- and long-haul missions

Igie

Goiricelaya

Nalianda

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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The impact of compressor fouling on civil aero engines unlike the industrial stationary application has not been widely investigated or available in open literature. There are questions about the impact of fouling for short-and long-haul missions comparatively, given their unique operational requirements and market. The aim of this study is to quantify the effects of different levels of fouling degradation on the fan, for two different aircraft with different two-spool engine models for their respective typical missions. Firstly, the study shows the increase in turbine entry temperature for both aircraft engines, to maintain the same level of thrust as their clean condition. The highest penalty observed is during takeoff and climb, when the thrust setting is the highest. Despite take-off and climb segment being a larger proportion in the short-haul mission compared to the long-haul mission, the percentage increase in fuel burn due to fouling are similar, except in the worst case fouling level were the former is higher by 0.8% points. In addition to this, for all the cases, the additional fuel burn due to fouling and its cost is shown to be small. Likewise, the increase in turbine entry temperature for both missions at take-off are similar, except in the worst case fouling level for the short-haul mission were the turbine entry temperature is 7 K higher than the corresponding long-haul mission for the same level of degradation. The study infers that the penalty due to rise in temperature is of more concern than the additional fuel burn. Hence the blade technology (cooling and material) and engine thrust rating are key factors in determining the extent to which blade fouling would affect aero engine performance in short-and long-haul missions.

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“…Therefore, several studies have concentrated on preliminary design for noise reduction (5)(6)(7) . As an example, Doulgeris et al (8) introduced a new methodology for the preliminary design of jet engines, featuring noise reduction as the main design objective.…”

Section: Introductionmentioning

confidence: 99%

Emission prediction in conceptual design of the aircraft engines using augmented CRN

Saboohi

Ommi

2017

Aeronaut. j.

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The semi-analytical prediction of pollutants emissions from gas turbines in the conceptual design phase is addressed in this paper. The necessity of this work arose from an urgent need for a comprehensive model that can quickly provide data in the conceptual design phase. Based on the available inputs data in the initial phases of the design process, a chemical reactor network (CRN) is defined to model the combustion with a detailed chemistry. In this way, three different chemical mechanisms are studied for Jet-A aviation fuel. Furthermore, the droplet evaporation for liquid fuel and the non-uniformity in fuel-air mixture are modelled. The results of a developed augmented modelling tool are compared with the pollutants data of two annular engine's combustors. The CRN results have good agreement with the actual engine test rig emissions output. In conclusion, the augmented CRN has shown to be efficient in predicting engine emissions with a very short executing time (few seconds) using a small CPU requirement such as a personal computer.

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Effect of jet noise reduction on gas turbine engine efficiency

Cited by 3 publications

References 25 publications

Evaluation of aero gas turbine preliminary weight estimation methods

Evaluation of aero gas turbine preliminary weight estimation methods

Aero engine compressor fouling effects for short- and long-haul missions

Emission prediction in conceptual design of the aircraft engines using augmented CRN

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