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Off-design performance analysis of hybridised aircraft gas turbine

Published online by Cambridge University Press:  08 August 2019

X. Zhao Open the ORCID record for X. Zhao [Opens in a new window] ,
S. Sahoo ,
K. Kyprianidis ,
J. Rantzer  and
M. Sielemann
X. Zhao*
Affiliation:
Future Energy Center School of Business, Society and Engineering Mälardalen University Västerås, Sweden
S. Sahoo
Affiliation:
Future Energy Center School of Business, Society and Engineering Mälardalen University Västerås, Sweden
K. Kyprianidis
Affiliation:
Future Energy Center School of Business, Society and Engineering Mälardalen University Västerås, Sweden
J. Rantzer
Affiliation:
Modelon AB Lund, Sweden Modelon Deutschland GmbH München, Germany
M. Sielemann
Affiliation:
Modelon AB Lund, Sweden Modelon Deutschland GmbH München, Germany
*
[email protected]
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Abstract

An advanced geared turbofan with year 2035 technology level assumptions was established and used for the hybridisation study in this paper. By boosting the low-speed shaft of the turbofan with electrical power through the accessory gearbox, a parallel hybrid concept was set up. Focusing on the off-design performance of the hybridised gas turbine, electrical power input to the shaft, defined as positive hybridisation in this context, generally moves the compressor operation towards surge. On the other hand, the negative hybridisation, which is to reverse the power flow direction can improve the part-load operations of the turbofan and minimise the use of compressor handling bleeds. For the pre-defined mission given in the paper, negative hybridisation of descent, approach and landing, and taxi operations with 580 kW, 240 kW and 650 kW, respectively was found sufficient to keep a minimum compressor surge margin requirement without handling bleed.

Looking at the hybridisation of key operating points, boosting the cruise operation of the baseline geared turbofan is, however, detrimental to the engine efficiency as it is pushing the cruise operation further away from the energy optimal design point. Without major modifications to the engine design, the benefit of the hybridisation appears primarily at the thermomechanical design point, the hot-day take-off. With the constraint of the turbine blade metal temperature in mind, a 500kW positive hybridisation at hot-day take-off gave cruise specific fuel consumption (SFC) reduction up to 0.5%, mainly because of reduced cooling flow requirement. Through the introduction of typical electrical power system performance characteristics and engine performance exchange rates, a first principles assessment is illustrated. By applying the strategies discussed in the paper, a 3% reduction in block fuel burn can be expected, if a higher power density electrical power system can be achieved.

Keywords

Parallel hybridGeared turbofanOff-design performance
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1270 , December 2019 , pp. 1999 - 2018
Copyright
© Royal Aeronautical Society 2019 

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Footnotes

A version of this paper was presented at the 24th ISABE Conference in Canberra, Australia, September 2019.

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