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Research Papers: Gas Turbines: Industrial & Cogeneration

Three-Dimensional Calculations of Evaporative Flow in Compressor Blade Rows

[+] Author and Article Information
R. C. Payne

Hopkinson Laboratory, Cambridge University, Engineering Department, Trumpington Street, Cambridge CB2 1PZ, UKrcp27@cam.ac.uk

A. J. White

Hopkinson Laboratory, Cambridge University, Engineering Department, Trumpington Street, Cambridge CB2 1PZ, UK

J. Eng. Gas Turbines Power 130(3), 032001 (Apr 02, 2008) (6 pages) doi:10.1115/1.2836742 History: Received May 07, 2007; Revised January 02, 2008; Published April 02, 2008

The present paper describes a three-dimensional computational method developed to solve the flow of a two-phase air-water mixture, including the effects of evaporation for a monodispersion of liquid droplets. The calculations employ a fully Eulerian method for the conservation of droplet number and liquid mass and are applicable to multiple blade rows, both stationary and rotating. The method is first tested to ensure that it computes the correct droplet evaporation rate and the correct physical behavior for evaporation within a 1D duct. Results are then presented for flow within a single compressor stage, i.e., a rotor-stator combination.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Comparison of the thermodynamic performance of wet and dry cycles. All turbomachinery is 90% efficient, heat exchangers have 75% effectiveness, combustion chambers and heat exchangers 5% pressure drop.

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Figure 2

Comparison between the computed evaporation rates and the experimentally measured rates from (15)

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Figure 3

Condensing flow at high Mach number. Inlet stagnation conditions are 325.5K, 1bar, and 75% relative humidity with 5% by mass of 5μm diameter droplets.

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Figure 4

Streamwise variations of liquid mass fraction and relative humidity. 4μm droplets at 2% and 5% liquid mass fractions. T01=350K, p01=1bar, and ϕ=10%.

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Figure 5

Compressor map for a single stage compressor with 4μm droplets at 2% and 5% liquid mass fractions

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Figure 6

Blade surface pressure distributions at midspan for Cases A, B, and C

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Figure 7

Velocity triangle at rotor exit for dry and 5% evaporative flows at midspan. Axial velocity at inlet is the same in each case.

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Figure 8

Absolute flow angle downstream of the rotor for dry and 5% evaporative flows at midspan. Axial velocity at inlet is the same in each case.

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