Research Papers: Gas Turbines: Turbomachinery

The Influence of Roughness on a High-Pressure Steam Turbine Stage: An Experimental and Numerical Study

[+] Author and Article Information
Juri Bellucci

Department of Industrial Engineering,
University of Florence,
via di Santa Marta, 3,
Florence 50139, Italy
e-mail: juri.bellucci@arnone.de.unifi.it

Filippo Rubechini, Michele Marconcini, Andrea Arnone

Department of Industrial Engineering,
University of Florence,
via di Santa Marta, 3,
Florence 50139, Italy

Lorenzo Arcangeli, Nicola Maceli

GE Oil & Gas,
via Felice Matteucci, 2,
Florence 50127, Italy

Vincenzo Dossena

Dipartimento di Energia,
Politecnico di Milano,
via Lambruschini, 4,
Milan 20158, Italy

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received May 9, 2014; final manuscript received July 7, 2014; published online August 26, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(1), 012602 (Aug 26, 2014) (9 pages) Paper No: GTP-14-1228; doi: 10.1115/1.4028205 History: Received May 09, 2014; Revised July 07, 2014

This work deals with the influence of roughness on high-pressure steam turbine stages. It is divided in three parts. In the first one, an experimental campaign on a linear cascade is described, in which blade losses are measured for different values of surface roughness and in a range of Reynolds numbers of practical interest. The second part is devoted to the basic aspects of the numerical approach and consists of a detailed discussion of the roughness models used for computations. The fidelity of such models is then tested against measurements, thus allowing their fine-tuning and proving their reliability. Finally, comprehensive computational fluid dynamics (CFD) analysis is carried out on a high-pressure stage, in order to investigate the influence of roughness on the losses over the entire stage operating envelope. Unsteady effects that may affect the influence of the roughness, such as the upcoming wakes on the rotor blade, are taken into account, and the impact of transition-related aspects on the losses is discussed.

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Fig. 1

Experimental test section scheme

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Fig. 2

Experimental total pressure loss coefficient

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Fig. 3

Experimental total pressure loss coefficient as a function of ksC for several Reynolds numbers

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Fig. 4

Experimental total pressure loss coefficient as a function of Re2,ks for several Reynolds numbers

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Fig. 5

Flat-plate near-wall behavior of the turbulent kinetic energy in wall units k+=k/v*2,(klog,theory+=1/β*,β*=0.09)

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Fig. 6

Flat-plate environment: convergence of the skin friction and drag coefficients (ksL = 5 × 10−4)

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Fig. 7

Flat-plate environment: computed skin friction coefficients compared with the correlation of Mills and Hang [36]

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Fig. 8

Cascade two-dimensional O-type grid

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Fig. 9

Smooth blade experimental and computational isentropic Mach distribution

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Fig. 10

Total pressure loss coefficient: experimental (open symbol) and CFD (filled symbol and solid line) results

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Fig. 11

Stage meridional view

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Fig. 12

Time-averaged CFD (filled symbols) and Craig and Cox correlation (open symbols) loss coefficient as a function of Re2 (rotor row)

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Fig. 13

Time-averaged CFD (filled symbols) and Craig and Cox correlation (open symbols) loss coefficient as a function of ksC (rotor row)




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