GasProp: Reducing Blade Compressibility Effects Through Waste-Heat Recovery in Aircraft Engines

Journal article (2020)

Authors

J. Serpieri Aerodynamics - Aerospace Engineering
Andrea Ianiro Carlos III University of Madrid
Research Group
Aerodynamics (Aerospace Engineering) (TU Delft)
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Published Date

2020

Language

English

Reuse Rights

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Faculty

Aerospace Engineering

Department

Flow Physics and Technology

Research Group

Aerodynamics

Abstract

Gas-turbine aircraft engines use a gas turbine to produce high-pressure hot gasses. The available internal energy of the hot gasses is then converted into jet kinetic energy through nozzles or extracted from a turbine to produce thrust by means of fans and/or propellers. Propulsive-efficiency requirements have resulted in the continuous increase of engine bypass/core ratios experienced by modern high-bypass-ratio turbofans, turboprops, and unducted fans or propfans [1]; whereas the improvement of the core-compression ratios allows to obtain thermodynamic efficiencies higher than 0.6.

Files

1.J058616.pdf
(.pdf | 0.273 Mb)