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Research Papers: Gas Turbines: Turbomachinery

Off-Design Performance of an Interstage Turbine Burner Turbofan Engine

[+] Author and Article Information
Feijia Yin

Propulsion and Power,
Delft University of Technology,
Kluyverweg 1,
Delft 2629HS, The Netherlands
e-mail: F.yin@tudelft.nl

Arvind G. Rao

Propulsion and Power,
Delft University of Technology,
Kluyverweg 1,
Delft 2629HS, The Netherlands
e-mail: A.gangolirao@tudelft.nl

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received November 1, 2016; final manuscript received January 2, 2017; published online March 21, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(8), 082603 (Mar 21, 2017) (8 pages) Paper No: GTP-16-1516; doi: 10.1115/1.4035821 History: Received November 01, 2016; Revised January 02, 2017

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 (HPT) and the low-pressure turbine (LPT). The incorporation of ITB in an engine can provide several advantages, especially due to the reduction in the HPT inlet temperature and the associated NOx emission reduction. 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: first, the influences of an ITB on the engine cycle performance; second, 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 off-design performance requirement, like 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.

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Figures

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Fig. 1

Comparison of the engine configuration

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Fig. 2

Layout of the ITB engine model in GSP

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Fig. 3

Various engine design conditions

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Fig. 4

Typical flat rating at SLS condition

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Fig. 5

Engine flat rating at SLS condition for various engine types

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Fig. 6

Variation in Tt3 versus the ambient temperature

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Fig. 7

Variation in Tt4 versus the ambient temperature

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Fig. 8

Variations in N1 versus the ambient temperature

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Fig. 9

Variations in N2 versus the ambient temperature

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Fig. 10

Improved flat rating temperature of the baseline VHBR engine

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Fig. 11

Comparison of the TSFC of the ITB engine with respect to the revised baseline turbofan engine

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Fig. 12

Variation in Tt3 versus thrust at SLS ISA condition

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Fig. 13

Variation in Tt4 versus thrust at SLS ISA condition

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Fig. 14

Variation in N1 and N2 versus thrust at SLS ISA condition

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Fig. 15

Variation in the TSFC versus thrust at SLS ISA condition

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Fig. 16

Variation in the surge margin of the outer fan versus thrust at SLS ISA condition

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Fig. 17

Variations in the LPC surge margin versus thrust at SLS ISA condition

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Fig. 18

Variation in the HPC surge margin versus thrust at SLS ISA condition

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