An insight into some innovative cycles for aircraft propulsion

Corchero, G.; Montañés, J. L.; Pascovici, Daniele; Ogaji, Stephen

doi:10.1243/09544100jaero346

Cited by 13 publications

(9 citation statements)

References 45 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In addition, a feasibility analysis of the intercooled recuperated aero engine was presented in the work of Fanourakis (2006) in order to investigate the applicability of this technology in various setups. Similar efforts are presented in the works of Hepperle (2007), Corchero et al (2008) and Gonser (2008). A detailed presentation of the most promising heat recuperator geometries, including the one used in the IRA cycle, and their characteristics is presented in the work of Min et al (2009).…”

Section: Introductionsupporting

confidence: 56%

Modelling Operation of System of Recuperative Heat Exchangers for Aero Engine with Combined Use of Porosity Model and Thermo-Mechanical Model

Yakinthos

Missirlis

Sideridis

et al. 2012

Engineering Applications of Computational Fluid Mechanics

View full text Add to dashboard Cite

The present work describes an effort to model the operation of a system of recuperative heat exchangers of an aero engine for real engine operating conditions. The modelling was performed with the combined use of a porous medium model and a thermo mechanical model. The porous medium model was taking into account the heat transfer and pressure loss behaviour of the heat exchangers while the thermo mechanical one was used for the calculation of the wall temperature distribution of the elliptic tubes of the heat exchangers. As it is presented, the combined use of these models can provide a useful tool which can help in the prediction of the macroscopic behaviour of the system of recuperative heat exchangers of the aero engine which can be used for optimization purposes and numerical studies.

show abstract

Section: Introductionsupporting

confidence: 56%

Modelling Operation of System of Recuperative Heat Exchangers for Aero Engine with Combined Use of Porosity Model and Thermo-Mechanical Model

Yakinthos

Missirlis

Sideridis

et al. 2012

Engineering Applications of Computational Fluid Mechanics

View full text Add to dashboard Cite

show abstract

“…The simultaneous use of both techniques allows to increase the available power, while the fuel consumption can remain nearly constant. Some studies have been done on the possibility of introducing regeneration and intercooling on gas turbine aero engines, in particular turboprops and high bypass turbofan engines [1][2][3][4][5][6][7][8][9][10][11][12][13] . It seems logical, as consequence, to think to introduce the two practices also in gas turbine engines for UAV propulsion systems.…”

Section: Introductionmentioning

confidence: 99%

Low-Fuel Consumption Gas Turbine Engines for Extended-Range UAVs

Andriani

Ingenito

Gamma

et al. 2014

52nd Aerospace Sciences Meeting

View full text Add to dashboard Cite

In the last years the interest in Unmanned AirVehicle systems has greatly raised, thanks to their extended operation capabilities. Among the reasons of this growing interest there is the development of very efficient and reliable guiding systems, that allow a thorough remote vehicle control. The endurance capability is certainly one of the most important UAV characteristics, because some missions are supposed to last even more than one day. For this reason, the engine fuel consumption becomes a fundamental aspect. The turboprop engine is commonly used in this kind of missions, with powers in the range between 300-900 kW. To extend the flight range and the endurance characteristics, it is important to have low-fuel consumption propulsion systems. At this purpose, a turboprop engine with intercooling and regeneration has been studied. A thermodynamic numeric program that simulates the behavior of a turboprop with regeneration and intercooling at different engine and operating conditions has been developed. The program allows to compute the thermodynamic working cycle and hence the main engine performances, as specific power, thermal efficiency and specific fuel consumption. An off-design analysis is performed to evaluate the engine behavior when operating at different conditions respect to the design point. An example case, showing the saved fuel for a particular mission profile, is then reported.

show abstract

“…These two techniques, intercooling and regeneration, are com monly used in ground placed power plants, and have the effects to increase the output power (intercooling) and reduce fuel consumption (regeneration). Different studies on the possibility and the consequent benefits of the use of these techniques on aero engines have been done in the last years, and the results show a sensible performance improvement and a fuel consumption reduction [1][2][3][4][5][6][7][8][9][10][11][12][13]. The main difficulty related to the introduction on an air craft engine is represented by the need of installating the heat exchangers.…”

Section: Introductionmentioning

confidence: 99%

Performance of a Turboprop Engine with Heat Recovery in Off-Design Conditions

Andriani

Ghezzi

Gamma

et al. 2013

Int. J. Turbo Jet-Engines

View full text Add to dashboard Cite

The research for fuel consumption and pollution reduction in new generation aero engines has indicated intercooling and regeneration as very effective methods for this purpose. Hence, different countries have joined their efforts in common research programs, to develop new gas turbine engines able to reduce considerably the fuel consumption and the ambient impact by means of these two techniques. To study their effects on the engine performance and characteristics, a thermodynamic numerical program that simulates the behavior of a turboprop engine with intercooling and regeneration in different operating conditions has been developed. After the parametric study, and the definition of the design conditions, the off-design analysis is carried on, comparing the main characteristics of the intercooled-regenerated turboprop with those of a conventional engine. Then, once a particular mission profile was fixed, the engine performance, in particular the equivalent power, the fuel consumption and the heat exchanger weight were discussed

show abstract

An insight into some innovative cycles for aircraft propulsion

Cited by 13 publications

References 45 publications

Modelling Operation of System of Recuperative Heat Exchangers for Aero Engine with Combined Use of Porosity Model and Thermo-Mechanical Model

Modelling Operation of System of Recuperative Heat Exchangers for Aero Engine with Combined Use of Porosity Model and Thermo-Mechanical Model

Low-Fuel Consumption Gas Turbine Engines for Extended-Range UAVs

Performance of a Turboprop Engine with Heat Recovery in Off-Design Conditions

Contact Info

Product

Resources

About