Research Papers

A Study of Fan-Distortion Interaction Within the NASA Rotor 67 Transonic Stage

[+] Author and Article Information
V. Jerez Fidalgo1

Whittle Laboratory,  University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, United Kingdom

C. A. Hall, Y. Colin

Whittle Laboratory,  University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, United Kingdom


Corresponding author, e-mail: vj229@cam.ac.uk

J. Turbomach 134(5), 051011 (May 08, 2012) (12 pages) doi:10.1115/1.4003850 History: Received January 14, 2011; Accepted January 29, 2011; Published May 08, 2012; Online May 08, 2012

The performance of a transonic fan operating within nonuniform inlet flow remains a key concern for the design and operability of a turbofan engine. This paper applies computational methods to improve the understanding of the interaction between a transonic fan and an inlet total pressure distortion. The test case studied is the NASA rotor 67 stage operating with a total pressure distortion covering a 120-deg sector of the inlet flow field. Full-annulus, unsteady, three-dimensional CFD has been used to simulate the test rig installation and the full fan assembly operating with inlet distortion. Novel post-processing methods have been applied to extract the fan performance and features of the interaction between the fan and the nonuniform inflow. The results of the unsteady computations agree well with the measurement data. The local operating condition of the fan at different positions around the annulus has been tracked and analyzed, and this is shown to be highly dependent on the swirl and mass flow redistribution that the rotor induces ahead of it due to the incoming distortion. The upstream flow effects lead to a variation in work input that determines the distortion pattern seen downstream of the fan stage. In addition, the unsteady computations also reveal more complex flow features downstream of the fan stage, which arise due to the three dimensionality of the flow and unsteadiness.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

NASA R67 fan-stage meridional view with distortion screen position (station 0), measurement planes (stations 1, 2, 3, and 4), and leading edge station (LE)

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Figure 2

Representative rotor and stator blade sections at three spanwise locations: hub (black), midheight (blue), and casing (blue)

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Figure 3

Isometric view of the computational domain

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Figure 4

Time-averaged, total pressure circumferential traverses at midspan, at measurement station 1

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Figure 5

Rotor and stator grids at midspan

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Figure 6

Clean flow total pressure ratio and efficiency characteristics for rotor alone configuration

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Figure 7

Time-averaged, circumferential distributions of static pressure (top) and mass flux (bottom) for three axial locations ahead of the rotor

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Figure 8

Time-averaged, circumferential distributions of absolute whirl angle ahead of the stage at midspan

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Figure 9

Time-averaged flow in the upstream duct. Contours of stagnation pressure stations 0 and 1, contours of static pressure on spinner, and duct streamlines

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Figure 10

Time-averaged radial traverses of stagnation pressure at station 1 in the distorted (left) and clean (right) sectors of the inlet flow field

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Figure 11

Contours of time-averaged absolute whirl and radial angles at station 1

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Figure 12

Inlet (right) and exit (left) sectors used for calculating the rotor local operating condition: the “orbit” around the mean point

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Figure 13

The variation in local rotor operating conditions when operating in distortion

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Figure 14

Time-averaged total pressure (left) and temperature (right) at station 2

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Figure 15

Snapshots of mass flux and absolute whirl angle at rotor’s LE

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Figure 16

Time-averaged particle displacements between the rotor’s LE and TE: circumferential and radial

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Figure 22

Unwrapped blade-to-blade snapshots at 90% span of stagnation pressure and temperature and static pressure

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Figure 21

Time-averaged radial traverses downstream of the OGV for θ = 177 deg (top) and θ = 327 deg (bottom)

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Figure 20

Time-averaged circumferential traverses downstream of the OGV at midspan

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Figure 19

Time-averaged radial traverses downstream of the rotor at circumferential position θ = 73 deg

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Figure 18

Time-averaged circumferential traverses downstream of the rotor at midspan

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Figure 17

Time-averaged mass flux and radial angle at station 2



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