GAS TURBINE REHEAT USING IN SITU COMBUSTION

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Description

In situ reheat is an alternative to traditional gas turbine reheat design in which fuel is fed through airfoils rather than in a bulky discrete combustor separating HP and LP turbines. The goals are to achieve increased power output and/or efficiency without higher emissions. In this program the scientific basis for achieving burnout with low emissions has been explored. In Task 1, Blade Path Aerodynamics, design options were evaluated using CFD in terms of burnout, increase of power output, and possible hot streaking. It was concluded that Vane 1 injection in a conventional 4-stage turbine was preferred. Vane 2 injection ... continued below

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112 pages

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Bachovchin, D.M.; Lippert, T.E. & Cizmas, R.A. Newby P.G.A. May 17, 2004.

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Description

In situ reheat is an alternative to traditional gas turbine reheat design in which fuel is fed through airfoils rather than in a bulky discrete combustor separating HP and LP turbines. The goals are to achieve increased power output and/or efficiency without higher emissions. In this program the scientific basis for achieving burnout with low emissions has been explored. In Task 1, Blade Path Aerodynamics, design options were evaluated using CFD in terms of burnout, increase of power output, and possible hot streaking. It was concluded that Vane 1 injection in a conventional 4-stage turbine was preferred. Vane 2 injection after vane 1 injection was possible, but of marginal benefit. In Task 2, Combustion and Emissions, detailed chemical kinetics modeling, validated by Task 3, Sub-Scale Testing, experiments, resulted in the same conclusions, with the added conclusion that some increase in emissions was expected. In Task 4, Conceptual Design and Development Plan, Siemens Westinghouse power cycle analysis software was used to evaluate alternative in situ reheat design options. Only single stage reheat, via vane 1, was found to have merit, consistent with prior Tasks. Unifying the results of all the tasks, a conceptual design for single stage reheat utilizing 24 holes, 1.8 mm diameter, at the trailing edge of vane 1 is presented. A development plan is presented.

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112 pages

Notes

OSTI as DE00827534

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  • Other Information: PBD: 17 May 2004

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  • Report No.: NONE
  • Grant Number: FC26-00NT40913
  • DOI: 10.2172/827534 | External Link
  • Office of Scientific & Technical Information Report Number: 827534
  • Archival Resource Key: ark:/67531/metadc783411

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Office of Scientific & Technical Information Technical Reports

Reports, articles and other documents harvested from the Office of Scientific and Technical Information.

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  • May 17, 2004

Added to The UNT Digital Library

  • Dec. 3, 2015, 9:30 a.m.

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  • Jan. 3, 2017, 12:37 p.m.

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Bachovchin, D.M.; Lippert, T.E. & Cizmas, R.A. Newby P.G.A. GAS TURBINE REHEAT USING IN SITU COMBUSTION, report, May 17, 2004; United States. (digital.library.unt.edu/ark:/67531/metadc783411/: accessed November 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.