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Research Papers

A Model for Stall and Surge in Low-Speed Contra-Rotating Fans

[+] Author and Article Information
Mohammad Javad Shahriyari

Department of Aerospace Engineering,
Center of Excellence in Computational
Aerospace Engineering,
Amirkabir University of Technology,
Tehran 15875-4413, Iran
e-mail: grifin@aut.ac.ir

Hossein Khaleghi

Department of Aerospace Engineering,
Center of Excellence in Computational
Aerospace Engineering,
Amirkabir University of Technology,
Tehran 15875-4413, Iran
e-mail: khaleghi@aut.ac.ir

Martin Heinrich

Institute for Mechanics and Fluid Dynamics,
Technical University Bergakademie,
Freiberg 09596, Germany
e-mail: martin.heinrich@imfd.tu-freiberg.de

Manuscript received November 21, 2018; final manuscript received March 17, 2019; published online April 8, 2019. Assoc. Editor: Tim Allison.

J. Eng. Gas Turbines Power 141(8), 081009 (Apr 08, 2019) (11 pages) Paper No: GTP-18-1693; doi: 10.1115/1.4043251 History: Received November 21, 2018; Revised March 17, 2019

This paper reports on a theory for poststall transients in contra-rotating fans, which is developed from the basic Moore–Greitzer theory. A second-order hysteresis term is assumed for the fan pressure rise, which gives the theory more capabilities in predicting the fan instabilities. The effect of the rotational speed ratio of the two counter rotating rotors on the fan performance during the occurrence of surge and rotating stall are studied (the rotational speed of the front rotor is assumed to be kept constant whereas the speed of the rear rotor is variable). One of the new capabilities of the current model is the possibility of investigating the effect of the initial slope on the fan characteristic. Results reveal that unlike the conventional fans and compressors, in the current contra-rotating fan stall cannot be initiated from the negative slope portion of the fan pressure rise characteristic curve. One of the important advantages of the developed model is that it enables investigation of the effect of the rate of throttling on the instabilities. Results show that more the rotational speed of the rear rotor, the more robust to surge (caused by throttling) the fan is.

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References

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Figures

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Fig. 1

Compression system

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Fig. 2

Typical stage pressure rise characteristic

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Fig. 3

Pressure ratio characteristic of a contra-rotating fan [17]

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Fig. 4

Fan pressure rise characteristic for different speed ratios

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Fig. 5

Transient stall cell speed

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Fig. 6

Stall cell amplitude (initial slope = −0.1): (a) contra-rotating fan, A(0)=1 and (b) conventional stage (b=∞),A(0)=0.01

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Fig. 7

Stall cell amplitude (initial slope = 0.1)

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Fig. 8

Stall cell amplitude and its time derivative (initial Φ=0.43): (a) stall cell amplitude and (b) growth rate of the stall cell amplitude

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Fig. 9

Time histories of the mean axial flow and pressure rise coefficients (initial slope = 0.1): (a) flow coefficient and (b) pressure rise

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Fig. 10

Time histories of the mean axial flow and pressure rise coefficients (initial Φ=0.43): (a) flow coefficient and (b) pressure rise

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Fig. 11

Time histories of the mean axial flow coefficient: (a) initial slope = 0.1 and (b) initial Φ=0.43

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Fig. 12

Time history of the annulus averaged flow coefficient (b = 2/3, initial slope = 0.1): (a) Initial dΦ/dξ = 0.8 and (b) initial dΦ/dξ=1.65

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Fig. 13

Time history of the annulus averaged flow coefficient (b = 1.5, initial slope = 0.1): (a) initial dΦ/dξ = 0.03 and (b) initial dΦ/dξ=0.06

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Fig. 14

Time history of the annulus averaged flow coefficient (b = 2/3, initial Φ=0.43): (a) initial dΦ/dξ= 0.03 and (b) initial dΦ/dξ=0.06

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Fig. 15

Time history of the annulus averaged flow coefficient (b = 1.5, initial Φ=0.43): (a) initial dΦ/dξ=0.02 and (b) initial dΦ/dξ=0.03

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Fig. 16

Minimum rate of throttling which changes the type of instability from rotating stall to surge

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