For more information on the project please contact the coordinator: Arvind Gangoli Rao

This project is made possible by


the EU

DisseminationTechnical papers

Off-Design Performance of an Interstage Turbine Burner Turbofan Engine

Abstract: This paper focuses on the off-design performance of a turbofan engine with an Interstage Turbine Burner (ITB). The ITB is an additional combustion chamber located between the high-pressure turbine and the low-pressure turbine. The objective is to evaluate the effects of the ITB on the off-design performance of a turbofan engine. The baseline engine is a contemporary classical turbofan. The effects of the ITB are evaluated on two aspects: firstly, the influences of an ITB on the engine cycle performance; secondly, the influences of an ITB on the component characteristics. The dual combustors of an ITB engine provide an extra degree of freedom for the engine operation. The analysis shows that a conventional engine has to be oversized to satisfy the off-design performance, for instance, the flat rating temperature. However, the application of an ITB eases the restrictions imposed by the off-design performance requirements on the engine design, implying that the off-design performance of an ITB engine can be satisfied without sacrificing the fuel efficiency. Eventually, the performance of the ITB engine exhibits superior characteristics over the baseline engine at the studied operating points over a flight mission.


Performance Analysis of an Aero Engine with Interstage Turbine Burner

Abstract: The historical trends of reduction in fuel consumption and emissions from aero engines have been mainly due to the improvement in the thermal efficiency, propulsive efficiency and combustion technology. The engine Overall Pressure Ratio (OPR) and Turbine Inlet Temperature (TIT) are being increased in the pursuit of increasing the engine thermal efficiency. However, this has an adverse effect on engine NOx emission. The current paper investigates a possible solution to overcome this problem for future generation Very High Bypass Ratio (VHBR)/Ultra-High Bypass Ratio (UHBR) aero-engines in the form of an Inter-stage Turbine Burner (ITB). The ITB concept is investigated on a next generation baseline VHBR aero engine to evaluate its effect on the engine performance and emission characteristics for different ITB energy fractions. It is found that the ITB can reduce the bleed air required for cooling the HPT substantially (around 80%) and also reduce the NOx emission significantly (> 30%) without penalizing the engine specific fuel consumption


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How ambiguous are climate metrics?

How can a new technology be evaluated with respect to its climate impact? Different climate metrics and time horizons are discussed. The paper clarifies how to deal with this question, proposes a five step approach and shows the procedure exemplarily for the AHEAD project.

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Feasibility of the hybrid combustion concept

The present report concerns the two types of combustors, at first, the hydrogen fueled combustor and thereafter the second combustor that is bio/fossil based jet fuel. It should be emphasized that during the whole of the study of the 2nd combustor, it always took into account that its inlet oxidant chemical composition are affected by the combustion process occurring in the 1st hydrogen fueled combustor.

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ANALYSIS: Hybrid vehicles move AHEAD

Please find here the Article from Flight Global on 'ANALYSIS: Hybrid vehicles move AHEAD'.


Numerical Investigations on the conceptual design of a ducted contra-rotating fan

The Advisory Council for Aeronautics Research in Europe (ACARE) has set an ambitious array of objectives to be accomplished by 2050. It is often claimed that complying with those targets will not require evolution but, rather, revolution. If the growth in aviation has to be sustained in the future then we must come up with radical aircraft and engine configurations which can meet the demands of future aviation.
The contra-rotating fan is one such system which can play an important role in the future engine configurations, such as the hybrid engine configuration that is being investigated in the EU confounded AHEAD project.

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Report on contrails and contrail cirrus climate effects from hybrid BWBs

This report describes the conditions for contrail formation for the AHEAD hybrid engine. Comparisons with contrail formation from a conventional jet engine driven by kerosene are presented and consequences are discussed.


Experimental Investigation of the Impact of Axial Air Injection on Swirl-Stabilized, Lean Premixed Hydrogen Flames

Lean premixed combustion allows for fuel-efficient, low emission combustion and is nowa-days state of the art in stationary gas turbines. In the long term, it is also a promising ap-proach for aero engines, when safety issues like flame flashback in the premixer can be overcome. We apply axial air injection in a swirl-stabilized burner in order to achieve a flow field that allows for flashback-proof combustion of premixed hydrogen.

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The AHEAD Project - Advanced Hybrid Enginges for Aircraft Development

Aviation is an ever-increasing market and more passengers and cargo are carried each year. The world is becoming ever more connected. However, this does come at a price: aviation has a marked influence on the environment. If aviation is to thrive in the future, breakthroughs in aircraft design and propulsion systems are needed. The AHEAD project is an attempt at achieving such a breakthrough.

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AHEAD: A research project on advanced hybrid engines for aircraft development - An intermediate report

This paper focuses on the intermediate results of the EC sponsored AHEAD project ( Advanced Hybrid Engines for Aircraft development). The project investigates the possibilities to develop an aircraft and hybrid engines for the future with very low CO2 and NOx emissions to achieve the target for 50% less CO2 emissions in 2050 compared to 2005 as set by IATA. The project is focusing on a hybrid engine that will burn both LNG or LH2 and traditional bio fuels.

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