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Numerical Simulation of TOBI Flow: Analysis of the Cavity Between a Seal-Plate and HPT Disc With Pumping Vanes

[+] Author Affiliations
Anish Kumar Gupta, Dhinagaran Ramachandran

Honeywell Technology Solutions Lab, Bangalore, India

Douglas Ramerth

Honeywell Engines Systems & Services, Phoenix, AZ

Paper No. GT2008-50739, pp. 1571-1578; 8 pages
doi:10.1115/GT2008-50739
From:
  • ASME Turbo Expo 2008: Power for Land, Sea, and Air
  • Volume 4: Heat Transfer, Parts A and B
  • Berlin, Germany, June 9–13, 2008
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4314-7 | eISBN: 0-7918-3824-2
  • Copyright © 2008 by ASME

abstract

HP turbine cooling systems utilize a TOBI (tangential on-board injector) nozzle and seal-plate to deliver cooling air to the airfoils with minimal loss in pressure and a benefit in relative total temperature. It was necessary to have a low TOBI exit pressure to control excess leakage across adjacent labyrinth seals with a trade-off of maintaining adequate pressure to supply blade cooling. Consequently, pumping vanes were needed on the seal-plate to restore pressure, which adds parasitic work to the turbine and a corresponding loss of engine efficiency. Engine testing revealed recirculation zones attached to the radial pumping vanes. Subsequent numerical simulation corroborated the recirculation and resulting circumferential asymmetry in flow distribution to the cooled airfoils. As a consequence, excess cooling air is supplied to the HP rotor with some airfoils receiving the minimum amount of cooling air. This study seeks to improve the flow distribution and pumping effectiveness by means of contouring the pumping vanes, increasing pumping vane solidity and/or controlling diffusion by re-contouring the seal-plate surface. Design features that increase total through flow when overall pressure ratio is fixed are also explored.

Copyright © 2008 by ASME

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