0

Full Content is available to subscribers

Subscribe/Learn More  >

Prediction of Clearance in Industrial Gas Turbine Validated by Field Operation Data

[+] Author Affiliations
Luca Bordo, Silvia Bruzzone, Andrea Perrone, Laura Traversone

Ansaldo Energia SpA, Genoa, Italy

Paper No. GT2012-69617, pp. 675-683; 9 pages
doi:10.1115/GT2012-69617
From:
  • ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
  • Volume 7: Structures and Dynamics, Parts A and B
  • Copenhagen, Denmark, June 11–15, 2012
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4473-1
  • Copyright © 2012 by ASME

abstract

During load operations the gas turbine is characterized by cyclic transients and long dwell times, resulting clearance variation occurs.

Tight clearances in both the compressor and the turbine section is one key to high component efficiencies. However, under any operating condition, some clearance must be maintained in order to avoid contact between rotating and stationary parts.

The optimization of the clearances during the running is one of the most relevant key to improve the engine performance, a Hydraulic Clearance Optimization (HCO) system is installed on the Ansaldo Energia gas-turbine models fleet in order to control turbine blade-tip clearances by appropriate shifting of the rotor against the flow direction and consequently reducing the radial gaps above the turbine blade tips.

In particular the proposed procedure takes into account the HCO effect on the blade clearances and their optimizing during the operation conditions.

The proposed procedure is based on a combination of 2D/3D FEM model of complete rotor-casing assembly and field operation data.

The computational approach is based on a 2D axi-symmetric finite element model of the engine rotor, including the stacked rotor discs and the connecting tie-rod. Particular care has been put in the definition of the boundary conditions which are: the centrifugal loads, the tierod pre-tightening, the thermal transient conditions. To take into account 3D effect of airfoil twisting and bending, the 3D models of the assembly blade-disk are built. The 3D FE displacements of the tip blades are combined with the 2D FE displacements of the complete rotor in the evaluation process. 3D casing FEM model are built to calculate the casing distortion due to temperature difference between cylindrical shell and horizontal flange. The procedure evaluates the axial and radial clearance combining the rotor/stator displacements.

The clearance and temperature values are measured and filed thanks to tip timing capacitive sensors and thermocouples sensors installed on same stages.

The proposed procedure gives results in good agreement with the measured clearances in all the transient operation conditions.

Copyright © 2012 by ASME

Figures

Tables

Interactive Graphics

Video

Country-Specific Mortality and Growth Failure in Infancy and Yound Children and Association With Material Stature

Use interactive graphics and maps to view and sort country-specific infant and early dhildhood mortality and growth failure data and their association with maternal

NOTE:
Citing articles are presented as examples only. In non-demo SCM6 implementation, integration with CrossRef’s "Cited By" API will populate this tab (http://www.crossref.org/citedby.html).

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In