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Research Papers

High-Fidelity Numerical Analysis of Per-Rev-Type Inlet Distortion Transfer in Multistage Fans—Part I: Simulations With Selected Blade Rows

[+] Author and Article Information
Jixian Yao

 GE Global Research, One Research Circle, Niskayuna, NY 12309

Steven E. Gorrell

Department of Mechanical Engineering, Brigham Young University, 435 CTB, Provo, UT 84602

Aspi R. Wadia

 GE Aviation, 30 Merchant Street, P20, Cincinnati, OH 45215

J. Turbomach 132(4), 041014 (May 06, 2010) (10 pages) doi:10.1115/1.3148478 History: Received September 09, 2008; Revised January 16, 2009; Published May 06, 2010; Online May 06, 2010

Demands for improved performance and operability of advanced propulsion systems require an understanding of the physics of inlet flow distortion transfer and generation and the subsequent engine response. This also includes developing a high-fidelity characterization capability and suitable tools/rules for the design of distortion tolerant engines. This paper describes efforts to establish a high-fidelity prediction capability of distortion transfer and fan response via high-performance computing. The current CFD capability was evaluated with a focus of predicting the transfer of prescribed inlet flow distortions. Numerical simulations, comparison to experimental data, and analysis of two selected three-stage fans are presented. The unsteady Reynolds-Averaged Navier-Stokes (RANS) code PTURBO demonstrated remarkable agreement with data, accurately capturing both the magnitude and profile of total pressure and total temperature measurements. Part I of this paper describes the establishment of the required numerical simulation procedures. The computational domains are limited to the first three blade rows for the first multistage fan and the last three blade rows for the second fan. This paper presents initial validation and analysis of the total pressure distortion transfer and the total temperature distortion generation. Based on the established ground work of Part I, the entire two multistage fans were simulated with inlet distortion at normal operating condition and near stall condition, which is Part II of this paper. Part II presents the full range validation against engine test data and in-depth analysis of distortion transfer and generation mechanisms throughout the two fans.

Copyright © 2010 by American Society of Mechanical Engineers
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Figures

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Figure 1

Computational domain of Fan Model 1

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Figure 2

Boundary conditions for Fan Model 1. 1/rev total pressure distortion at inlet (a), and the static pressure distribution at Stator-1 exit (b). [(Pt−P¯t)/P¯t]% is plotted in (a), and [(Ps−P¯s)/P¯s]% is plotted in (b).

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Figure 3

Inlet boundary conditions for Fan Model 2. 1/rev total pressure distortion at inlet to Stator-2 (a), and the total temperature distortion at inlet to Stator-2 (b). [(Pt−P¯t)/P¯t]% is plotted in (a), and [(Tt−T¯t)/T¯t]% is plotted in (b).

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Figure 4

Time-accurate solution of absolute total pressure and total temperature distribution at midspan on unwrapped surface

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Figure 5

Comparison of absolute total pressure (PTA) and total temperature (TTA) at midspan, Stator-1 inlet

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Figure 6

Comparison of absolute total pressure and total temperature at Stator-1 inlet, about 10% immersion

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Figure 7

Comparison of absolute total pressure and total temperature at Stator-1 inlet, about 30% immersion

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Figure 8

Comparison of absolute total pressure and total temperature at Stator-1 inlet, about 70% immersion

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Figure 9

Comparison of absolute total pressure and total temperature at Stator-1 inlet, about 90% immersion

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Figure 10

Comparison of casing static pressure at upstream and downstream of the Rotor-1. Reference pressure (used for nondimensionalization) location is Rotor-1 inlet on casing.

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Figure 11

Absolute total pressure distribution, snapshot of time-accurate solution at about 50% immersion

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Figure 12

Absolute total temperature distribution, snapshot of time-accurate solution at about 50% immersion

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Figure 13

Comparison of calculated Pt and Tt profiles with data at 91% immersion

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Figure 14

Comparison of calculated Pt and Tt profiles with data at 55% immersion

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Figure 15

Comparison of calculated Pt and Tt profiles with data at 7.3% immersion

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Figure 16

Circumferential profiles of static temperature (top) and absolute velocity (bottom) at an upstream and downstream location of Rotor-1 at midspan. Reference location is Rotor-1 inlet at midspan.

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Figure 17

Circumferential profiles of static pressure (top) and density (bottom) at an upstream and downstream location of Rotor-1 at midspan. Reference location is Rotor-1 inlet at midspan.

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