Alternative Concepts for Advanced Energy Conservative Transport Engines

Hirschkron, R.; Neitzel, R. E.

doi:10.4271/760536

Cited by 6 publications

(3 citation statements)

References 3 publications

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“…There has been some interest in heat exchanged turbofan engine configurations for more than three decades, and early studies were essentially carried out to explore their potential (Kentfield, 1975; Young, 1975; Gray and Witherspoon, 1976; Hirschkron and Neitzel, 1976; Bennett, 1983; Miura and Sakurai, 1984). Later studies (Papadopoulos and Pilidis, 2000; Lundbladh and Sjunnesson, 2003; Colmenares et al , 2007) extended this work in an era when large simple cycle turbofans were dominant in commercial airline service.…”

Section: Large Heat Exchanged Turbofan Enginementioning

confidence: 99%

Recuperated gas turbine aeroengines. Part III: engine concepts for reduced emissions, lower fuel consumption, and noise abatement

McDonald

Massardo

Rodgers³

et al. 2008

Aircraft Engineering and Aerospace Technology

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PurposeThis paper seeks to evaluate the potential of heat exchanged aeroengines for future Unmanned Aerial Vehicle (UAV), helicopter, and aircraft propulsion, with emphasis placed on reduced emissions, lower fuel burn, and less noise.Design/methodology/approachAeroengine performance analyses were carried out covering a wide range of parameters for more complex thermodynamic cycles. This led to the identification of major component features and the establishing of preconceptual aeroengine layout concepts for various types of recuperated and ICR variants.FindingsNovel aeroengine architectures were identified for heat exchanged turboshaft, turboprop, and turbofan variants covering a wide range of applications. While conceptual in nature, the results of the analyses and design studies generally concluded that heat exchanged engines represent a viable solution to meet demanding defence and commercial aeropropulsion needs in the 2015‐2020 timeframe, but they would require extensive development.Research limitations/implicationsAs highlighted in Parts I and II, early development work was focused on the use of recuperation, but this is only practical with compressor pressure ratios up to about 10. For today's aeroengines with pressure ratios up to about 50, improvement in SFC can only be realised by incorporating intercooling and recuperation. The new aeroengine concepts presented are clearly in an embryonic stage, but these should enable gas turbine and heat exchanger specialists to advance the technology by conducting more in‐depth analytical and design studies to establish higher efficiency and “greener” gas turbine aviation propulsion systems.Originality/valueIt is recognised that meeting future environmental and economic requirements will have a profound effect on aeroengine design and operation, and near‐term efforts will be focused on improving conventional simple‐cycle engines. This paper has addressed the longer‐term potential of heat exchanged aeroengines and has discussed novel design concepts. A deployment strategy, aimed at gaining confidence with emphasis placed on assuring engine reliability, has been suggested, with the initial development and flight worthiness test of a small recuperated turboprop engine for UAVs, followed by a larger recuperated turboshaft engine for a military helicopter, and then advancement to a larger and far more complex ICR turbofan engine.

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Section: Large Heat Exchanged Turbofan Enginementioning

confidence: 99%

Recuperated gas turbine aeroengines. Part III: engine concepts for reduced emissions, lower fuel consumption, and noise abatement

McDonald

Massardo

Rodgers³

et al. 2008

Aircraft Engineering and Aerospace Technology

View full text Add to dashboard Cite

show abstract

“…In this time frame compressor pressure ratios were modest, and with very low-by-pass ratios it was felt that, while a small reduction in fuel consumption could be realised, it would more than likely be offset by the drag increase associated with the incorporation of the bulky recuperator. Studies done a decade or so later (Kentfield, 1975;Young, 1975;Gray and Witherspoon, 1975;Hirschkron and Neitzel, 1976) also found no real benefits of recuperating turbofan engines.…”

Section: Heat Exchanged Turbofan Conceptsmentioning

confidence: 99%

Recuperated gas turbine aeroengines, part II: engine design studies following early development testing

McDonald

Massardo

Rodgers³

et al. 2008

Aircraft Engineering and Aerospace Technology

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Purpose -To advance the design of heat exchanged gas turbine propulsion aeroengines utilising experience gained from early development testing, and based on technologies prevailing in the 1970-2000 time frame. Design/methodology/approach -With emphasis on recuperated helicopter turboshaft engines, particularly in the 1,000 hp (746 kW) class, detailed performance analyses, parametric trade-off studies, and overall power plant layouts, based on state-of-the-art turbomachinery component efficiencies and high-temperature heat exchanger technologies, were undertaken for several engine configuration concepts. Findings -Using optimised cycle parameters, and the selection of a light weight tubular heat exchanger concept, an attractive engine architecture was established in which the recuperator was fully integrated with the engine structure. This resulted in a reduced overall engine weight and lower specific fuel consumption, and represented a significant advancement in technology from the modified simple-cycle engines tested in the late 1960s. Practical implications -While heat exchanged engine technology advancements were projected, there were essentially two major factors that essentially negated the continued study and development of recuperated aeroengines, namely again as mentioned in Part I, the reduced fuel consumption was not regarded as an important economic factor in an era of low-fuel cost, and more importantly in this time frame very significant simple-cycle engine performance advancements were made with the use of significantly higher pressure ratios and increased turbine inlet temperatures. Simply stated, recuperated variants could not compete with such a rapidly moving target. Originality/value -Establishing an engine design concept in which the recuperator was an integral part of the engine structure to minimise the overall power plant weight was regarded as a technical achievement. Such an approach, together with the emergence of lighter weight recuperators of assured structural integrity, would find acceptance around the year 2000 when there was renewed interest in the use of more efficient heat exchanged variants towards the future goal of establishing "greener" aeroengines, and this is discussed in Part III of this paper.

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“…One of the earliest discussions on the subject of improving engine fuel efficiency is provided by Gray & Witherspoon (1976), looking at conventional and heat exchanged cores, as well as non-steady flow combustion processes and open rotor configurations. A similar study focusing on geared and open rotor arrangements as well as heat exchanged cycles is presented by Hirschkron & Neitzel (1976). An interesting discussion on how specific thrust levels were expected to evolve in the mid-70's based on the economic and technological projections of that time period is given by Jackson (1976); the author has also provided an update to that discussion based on current economical and technological projections (Jackson, 2009).…”

Section: An Evolving Visionmentioning

confidence: 99%

Future Aero Engine Designs: An Evolving Vision

Konstantinos¹

2011

Advances in Gas Turbine Technology

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Alternative Concepts for Advanced Energy Conservative Transport Engines

Cited by 6 publications

References 3 publications

Recuperated gas turbine aeroengines. Part III: engine concepts for reduced emissions, lower fuel consumption, and noise abatement

Recuperated gas turbine aeroengines. Part III: engine concepts for reduced emissions, lower fuel consumption, and noise abatement

Recuperated gas turbine aeroengines, part II: engine design studies following early development testing

Future Aero Engine Designs: An Evolving Vision

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