Research Papers: Gas Turbines: Industrial & Cogeneration

Three-Dimensional Modeling for Wet Compression in a Single Stage Compressor Including Liquid Particle Erosion Analysis

[+] Author and Article Information
Jobaidur R. Khan, Ting Wang

Energy Conversion and Conservation Center, University of New Orleans, New Orleans, LA 70148-2220

J. Eng. Gas Turbines Power 133(1), 012001 (Sep 27, 2010) (13 pages) doi:10.1115/1.4001828 History: Received April 09, 2010; Revised April 27, 2010; Published September 27, 2010; Online September 27, 2010

Gas turbine inlet fog/overspray cooling is considered as a simple and effective method to increase power output. To help understand the water mist transport in the compressor flow passage, this study conducts a 3D computational simulation of wet compression in a single rotor-stator compressor stage using the commercial code FLUENT . A sliding mesh scheme is used to simulate the stator-rotor interaction in a rotating frame. Eulerian–Lagrangian method is used to calculate the continuous phase and track the discrete (droplet) phase. Models to simulate droplet breakup and coalescence are incorporated to take into consideration the effect of local acceleration and deceleration on water droplet dynamics. Analysis on the droplet history (trajectory and size) with stochastic tracking is employed to interpret the mechanism of droplet dynamics under the influence of local turbulence, acceleration, diffusion, and body forces. A liquid-droplet erosion model is included. The sensitivity of the turbulence models on the results is conducted by employing six different turbulence models and four different time constants. The result shows that the local thermal equilibrium is not always achieved due to short residence time and high value of latent heat of water. Local pressure gradients in both the rotor and stator flow passages drive up the droplet slip velocity during compression. The erosion model predicts that the most eroded area occurs in the leading edge and one spot of the trailing edge of the rotor suction side.

Copyright © 2011 by American Society of Mechanical Engineers
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Figure 1

Meshes for the rotor and stator (the mesh number is reduced for visual clarity)

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Figure 2

(a) Periodic meshes; (b) close-up view of one pitch of the inlet, rotor, and stator

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Figure 3

Selected surfaces for analysis (three radial, three axial, and one circumferential plane). The cross marks show the water injection locations

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Figure 4

Flow and blade angles and the velocity diagrams at the mean diameter

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Figure 5

(a) Static pressure distribution for baseline case in different radial planes; (b) stagnation pressure distribution on the rotor surface for baseline on the suction surface, leading edge, and pressure surface; (c) static pressure distribution for fogging case on different radial planes and over the hub; and (d) stagnation pressure distribution for fogging case across the rotor surface

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Figure 6

(a) Static temperature distribution for baseline case (no fogging) on three radial planes; 6 (b) temperature distribution for fogging case on different radial planes and hub surface

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Figure 7

(a) Secondary flow moving towards the suction surface at 20% chord length from the stator leading edge Data points are reduced for clarity. The main flow is moving into the paper. The plane of projection in this figure is the red (third) plane shown in Fig. 3; (b) Secondary flow near the stator exit. Data points are reduced for clarity. The main flow is moving into the paper. The plane of projection in this figure is the black (rightmost) plane shown in Fig. 3.

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Figure 8

Water droplet trace with droplets’ relative Reynolds number (one in every five droplets have been shown)

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Figure 9

(a) Contour of the pressure coefficient on the rotor and stator surfaces on three radial planes for the fogging case; variation in the pressure coefficient across the rotor and stator surfaces (b) for the baseline case and (c) for the fogging case

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Figure 10

Water droplet trace with diameter. Red dots shows coalescence

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Figure 11

Liquid concentration (a) on four different axial planes and (b) on three different radial planes

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Figure 12

(a) Blade erosion on the suction side of the rotor and pressure side of the stator. (b) Blade erosion on the pressure side of the rotor and suction side of the stator. Arrows show the flow direction.




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