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Aerodynamic Analysis and Redesign of an Inlet Segment for a Heavy-Duty Gas Turbine Engine

[+] Author Affiliations
Samer Abdel-Wahab, Gregory Vogel

Alstom Power, West Palm Beach, FL

Paper No. GT2010-22674, pp. 1275-1282; 8 pages
doi:10.1115/GT2010-22674
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by Alstom Technology, Ltd.

abstract

For heavy-duty gas turbines with silo combustors, the transition section between the combustor and the turbine poses unique aerodynamic design challenges due to the non-axis symmetrical shape of the transition from the combustor (pipe), to hot gas casing (torus), to turbine inlet (annulus). The inlet segment is the transition piece located between the hot gas casing and the outer radius of the turbine. The shape of the inlet segment is designed such that it provides minimum pressure loss of the hot gas flowing from the silo combustor to the turbine inlet. Another requirement of the inlet segment shape is to provide as homogeneous as possible flow conditions at the turbine inlet. This paper shows the results from CFD analysis of an inlet segment. The results agree very well with pressure tap measurements in the engine at several discrete circumferential locations. In addition, thermal crystal measurements mounted at several leading edge locations of the vanes at the inlet of the turbine were able to confirm from the CFD the radial and circumferential temperature distribution typically produced in a silo combustor. A new inlet segment profile shape has been designed to produce an equivalent pressure distribution for the turbine inlet but with a reduced surface area, which helps to reduce the cooling requirements for this part.

Copyright © 2010 by Alstom Technology, Ltd.
Topics: Gas turbines

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