Startseite Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
Artikel
Lizenziert
Nicht lizenziert Erfordert eine Authentifizierung

Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition

  • Dawei Fu , Yong Wang , Haibo Zhang EMAIL logo und Qiangang Zheng
Veröffentlicht/Copyright: 14. August 2018
Veröffentlichen auch Sie bei De Gruyter Brill

Abstract

In order to describe how the variant BPR affects the flow performance, a qusi-2D fan model was proposed. In the model, the stage cumulative method was applied to compute axial flow and the simplified radial equilibrium equation was applied to compute radial flow, then a dual-level iteration program was proposed for the nominal performance calculation. To compute the non-nominal flow characteristics on non-nominal BPR, a triple-level iteration program with the compensation factor was proposed to obtain the radial profiles. On that basis, Blade angles were designed for this model on the design point. With the inflow deflection factor designed as 0.8 and the loss factor along blade as 0.95, the pressure ratio error is only 0.21 % and the isentropic efficiency error is 0.06 %. Simulation showed that the variant-BPR profiles and the overall characteristics of flow at fan exit or for bypass & core ducts could be well computed with much less time-consuming.

Funding statement: This work has been co-supported by the National Natural Science Foundation of China (Grant/Award Number: 51576096) and Foundation of Graduate Innovation Center in NUAA (Grant/Award Number: kfjj20170210). As well as Research Funds for Central Universities (No. NF2018003).

Nomenclature

Symbol

Explanation

ε

Inflow deflection factor

ζ

Loss factor along blade

π

Total pressure ratio

η

Isentropic efficiency

ξ

Static pressure recovery coefficient

Bˆ

Nominal bypass ratio

w(r)

Flow coefficient

W(r)

Flow Integral from hub to the target radius

μ(r)

Flow coefficient ratio between exit and entrance

κ(r)

Compensation factor

Ωˆ

Reaction degree at design radius

Lˆu

Unit radius work at design radius

References

1. Zeng Y, Wei Y. Analysis of aerodynamic design characteristics of flade fan [J]. Procedia Eng. 2015;99:723–33.10.1016/j.proeng.2014.12.594Suche in Google Scholar

2. Shen SQ, Zhang K. Calculation and analysis on the performance of adjustable ejector[J]. J Petrochem. Univ. 2007;8:57–84.Suche in Google Scholar

3. Standish RR, Laboure B Thrust reverser with adjustable section nozzle for aircraft jet engine: US, US5853148[P]. 1998.Suche in Google Scholar

4. Yonghui Z Numerical analysis on matching between internal and external bypass and fan of aero-engine[D]. Graduate University of Chinese Academy of Sciences (Institute of Engineering Thermal Physics), 2005.Suche in Google Scholar

5. Kurzke J How to get component maps for aircraft gas turbine performance calculations. International Gas Turbine and Aero-engine Congress & Exhibition, Paper 96-GT-164, Birmingham, UK, June 10–13, 1996.10.1115/96-GT-164Suche in Google Scholar

6. Yin J High bypass ratio fan modelling (WP2), performance engineering UTC annual review report. School of Mechanical Engineering, Cranfield University, 1999.Suche in Google Scholar

7. Yin J Proposed calculation procedures for the generation and application of 2-D fan characteristics, performance engineering UTC document PE005. Version 2. School of Mechanical Engineering, Cranfield University, 1999.Suche in Google Scholar

8. Shaw M, Murdoch RW Computer modelling of fan-exit-splitter spacing effects on F100 response to distortion[J]. NASA CR-167879, 1982.Suche in Google Scholar

9. Li MS, Yin JF, Curnock B Low bypass ratio turbofan performance modelling with fan radial flow profiles[J]. Proceedings of the International Gas Turbine Congress 2003 Tokyo, 2003.Suche in Google Scholar

10. Henner M, Kessaci S, Moreau S Latest improvements of CFD models of engine cooling axial fan systems[C]. SAE 2002 Conference, 2002.10.4271/2002-01-1205Suche in Google Scholar

11. Stratford BS The use of boundary layer techniques to calculate the blockage from the annulus boundary layer in a compressor, ASME paper no.67-WA/GT 17, the american society of mechanical engineers. Presented at Winter Annual Meeting, Pittsburg, Pennsylvania, 1967.Suche in Google Scholar

12. Wall RA, Axial flow compressor performance prediction. Compressor Research Department Rolls-Royce Lted Derby. U.K, 1971.Suche in Google Scholar

13. Sutong Z Investigation on different splitter scale characteristic and splitter lip effect for the core and bypass of fan/compressor[D]. Northwestern Polytechnical University, 2007.Suche in Google Scholar

14. Xiaoming D Investigation on design and optimization of fan/compressor splitter[D]. Northwestern Polytechnical University, 2015.Suche in Google Scholar

15. Vallabhaneni NK. Continuously variable rotorcraft propulsion system: modelling and simulation[D]. Knoxville: University of Tennessee, 2011.Suche in Google Scholar

16. Smith LH. The radial-equilibrium equation of turbomachinery[J]. Asme J Eng Power. 1966;88:1.10.1115/1.3678471Suche in Google Scholar

17. Stern AM. Gas turbine engine with variable area fan nozzle bladder system[P]. United Technologies. 2015.Suche in Google Scholar

18. Riegler C, Bauer M, Kurzke J. Some aspects of modelling compressor behavior in gas turbine performance calculations. Transactions of the ASME. J Eng Gas Turbines Power. 2001;123:2001,372–78.10.1115/1.1368123Suche in Google Scholar

19. Meining C, Ying P, Dalei W. Numerical simulation of tandem cascades in an aero-engine fan [J]. J Aeronautics. 2010;25:1117–22.Suche in Google Scholar

20. Allan R General electric company variable cycle engine technology demonstrator programs[C]. Joint Propulsion Conference, 2013.Suche in Google Scholar

Received: 2018-05-13
Accepted: 2018-06-24
Published Online: 2018-08-14
Published in Print: 2021-08-26

© 2018 Walter de Gruyter GmbH, Berlin/Boston

Heruntergeladen am 14.10.2025 von https://www.degruyterbrill.com/document/doi/10.1515/tjj-2018-0015/html?lang=de
Button zum nach oben scrollen