Fan similarity model for the fan-intake interaction problem

Mauro Carnevale, Feng Wang, Anthony B. Parry, Jeffrey S. Green, Luca Di Mare

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

Very high-bypass ratio turbofans with large fan tip diameter are an effective way of improving the propulsive efficiency of civil aero-engines. Such engines, however, require larger and heavier nacelles, which partially offset any gains in specific fuel consumptions. This drawback can be mitigated by adopting thinner walls for the nacelle and by shortening the intake section. This binds the success of very high-bypass ratio technologies to the problem of designing an intake with thin lips and short diffuser section which is well matched to a low speed fan. Consequently the prediction of the mutual influence between the fan and the intake flow represents a crucial step in the design process. Considerable effort has been devoted in recent years to the study of models for the effects of the fan on the lip stall characteristics and the operability of the whole installation. The study of such models is motivated by the wish to avoid the costs incurred by full, three-dimensional CFD computations. The present contribution documents a fan model for fan-intake computations based on the solution of the double linearization problem for unsteady, transonic flow past a cascade of aerofoils with finite mean load. The computation of the flow in the intake is reduced to a steady problem, whereas the computation of the flow in the fan is reduced to one steady problem and a set of solutions of the linearised model in the frequency domain. The nature of the approximations introduced in the fan representation is such that numerical solutions can be computed inexpensively, whilst the main feature of the flow in the fan passage, namely the shock system and an approximation of the unsteady flow encountered by the fan are retained. The model is applied to a well-documented test case and compares favourably with much more expensive three-dimensional, time domain computations.

Original languageEnglish
Title of host publicationAircraft Engine; Fans and Blowers; Marine; Honors and Awards
Subtitle of host publicationVolume 1
PublisherAmerican Society of Mechanical Engineers (ASME)
Pages1-10
Number of pages10
ISBN (Electronic)9780791850770
DOIs
Publication statusPublished - 1 Jan 2018
EventASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 - Charlotte, USA United States
Duration: 26 Jun 201730 Jun 2017

Conference

ConferenceASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
CountryUSA United States
CityCharlotte
Period26/06/1730/06/17

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Carnevale, M., Wang, F., Parry, A. B., Green, J. S., & Di Mare, L. (2018). Fan similarity model for the fan-intake interaction problem. In Aircraft Engine; Fans and Blowers; Marine; Honors and Awards: Volume 1 (pp. 1-10). [GT2017-63868] American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/GT2017-63868

Fan similarity model for the fan-intake interaction problem. / Carnevale, Mauro; Wang, Feng; Parry, Anthony B.; Green, Jeffrey S.; Di Mare, Luca.

Aircraft Engine; Fans and Blowers; Marine; Honors and Awards: Volume 1. American Society of Mechanical Engineers (ASME), 2018. p. 1-10 GT2017-63868.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Carnevale, M, Wang, F, Parry, AB, Green, JS & Di Mare, L 2018, Fan similarity model for the fan-intake interaction problem. in Aircraft Engine; Fans and Blowers; Marine; Honors and Awards: Volume 1., GT2017-63868, American Society of Mechanical Engineers (ASME), pp. 1-10, ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017, Charlotte, USA United States, 26/06/17. https://doi.org/10.1115/GT2017-63868
Carnevale M, Wang F, Parry AB, Green JS, Di Mare L. Fan similarity model for the fan-intake interaction problem. In Aircraft Engine; Fans and Blowers; Marine; Honors and Awards: Volume 1. American Society of Mechanical Engineers (ASME). 2018. p. 1-10. GT2017-63868 https://doi.org/10.1115/GT2017-63868
Carnevale, Mauro ; Wang, Feng ; Parry, Anthony B. ; Green, Jeffrey S. ; Di Mare, Luca. / Fan similarity model for the fan-intake interaction problem. Aircraft Engine; Fans and Blowers; Marine; Honors and Awards: Volume 1. American Society of Mechanical Engineers (ASME), 2018. pp. 1-10
@inproceedings{957541f49dd34aa88bfc08ad1c78fcbc,
title = "Fan similarity model for the fan-intake interaction problem",
abstract = "Very high-bypass ratio turbofans with large fan tip diameter are an effective way of improving the propulsive efficiency of civil aero-engines. Such engines, however, require larger and heavier nacelles, which partially offset any gains in specific fuel consumptions. This drawback can be mitigated by adopting thinner walls for the nacelle and by shortening the intake section. This binds the success of very high-bypass ratio technologies to the problem of designing an intake with thin lips and short diffuser section which is well matched to a low speed fan. Consequently the prediction of the mutual influence between the fan and the intake flow represents a crucial step in the design process. Considerable effort has been devoted in recent years to the study of models for the effects of the fan on the lip stall characteristics and the operability of the whole installation. The study of such models is motivated by the wish to avoid the costs incurred by full, three-dimensional CFD computations. The present contribution documents a fan model for fan-intake computations based on the solution of the double linearization problem for unsteady, transonic flow past a cascade of aerofoils with finite mean load. The computation of the flow in the intake is reduced to a steady problem, whereas the computation of the flow in the fan is reduced to one steady problem and a set of solutions of the linearised model in the frequency domain. The nature of the approximations introduced in the fan representation is such that numerical solutions can be computed inexpensively, whilst the main feature of the flow in the fan passage, namely the shock system and an approximation of the unsteady flow encountered by the fan are retained. The model is applied to a well-documented test case and compares favourably with much more expensive three-dimensional, time domain computations.",
author = "Mauro Carnevale and Feng Wang and Parry, {Anthony B.} and Green, {Jeffrey S.} and {Di Mare}, Luca",
year = "2018",
month = "1",
day = "1",
doi = "10.1115/GT2017-63868",
language = "English",
pages = "1--10",
booktitle = "Aircraft Engine; Fans and Blowers; Marine; Honors and Awards",
publisher = "American Society of Mechanical Engineers (ASME)",
address = "USA United States",

}

TY - GEN

T1 - Fan similarity model for the fan-intake interaction problem

AU - Carnevale, Mauro

AU - Wang, Feng

AU - Parry, Anthony B.

AU - Green, Jeffrey S.

AU - Di Mare, Luca

PY - 2018/1/1

Y1 - 2018/1/1

N2 - Very high-bypass ratio turbofans with large fan tip diameter are an effective way of improving the propulsive efficiency of civil aero-engines. Such engines, however, require larger and heavier nacelles, which partially offset any gains in specific fuel consumptions. This drawback can be mitigated by adopting thinner walls for the nacelle and by shortening the intake section. This binds the success of very high-bypass ratio technologies to the problem of designing an intake with thin lips and short diffuser section which is well matched to a low speed fan. Consequently the prediction of the mutual influence between the fan and the intake flow represents a crucial step in the design process. Considerable effort has been devoted in recent years to the study of models for the effects of the fan on the lip stall characteristics and the operability of the whole installation. The study of such models is motivated by the wish to avoid the costs incurred by full, three-dimensional CFD computations. The present contribution documents a fan model for fan-intake computations based on the solution of the double linearization problem for unsteady, transonic flow past a cascade of aerofoils with finite mean load. The computation of the flow in the intake is reduced to a steady problem, whereas the computation of the flow in the fan is reduced to one steady problem and a set of solutions of the linearised model in the frequency domain. The nature of the approximations introduced in the fan representation is such that numerical solutions can be computed inexpensively, whilst the main feature of the flow in the fan passage, namely the shock system and an approximation of the unsteady flow encountered by the fan are retained. The model is applied to a well-documented test case and compares favourably with much more expensive three-dimensional, time domain computations.

AB - Very high-bypass ratio turbofans with large fan tip diameter are an effective way of improving the propulsive efficiency of civil aero-engines. Such engines, however, require larger and heavier nacelles, which partially offset any gains in specific fuel consumptions. This drawback can be mitigated by adopting thinner walls for the nacelle and by shortening the intake section. This binds the success of very high-bypass ratio technologies to the problem of designing an intake with thin lips and short diffuser section which is well matched to a low speed fan. Consequently the prediction of the mutual influence between the fan and the intake flow represents a crucial step in the design process. Considerable effort has been devoted in recent years to the study of models for the effects of the fan on the lip stall characteristics and the operability of the whole installation. The study of such models is motivated by the wish to avoid the costs incurred by full, three-dimensional CFD computations. The present contribution documents a fan model for fan-intake computations based on the solution of the double linearization problem for unsteady, transonic flow past a cascade of aerofoils with finite mean load. The computation of the flow in the intake is reduced to a steady problem, whereas the computation of the flow in the fan is reduced to one steady problem and a set of solutions of the linearised model in the frequency domain. The nature of the approximations introduced in the fan representation is such that numerical solutions can be computed inexpensively, whilst the main feature of the flow in the fan passage, namely the shock system and an approximation of the unsteady flow encountered by the fan are retained. The model is applied to a well-documented test case and compares favourably with much more expensive three-dimensional, time domain computations.

U2 - 10.1115/GT2017-63868

DO - 10.1115/GT2017-63868

M3 - Conference contribution

SP - 1

EP - 10

BT - Aircraft Engine; Fans and Blowers; Marine; Honors and Awards

PB - American Society of Mechanical Engineers (ASME)

ER -