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Cooling of a gas turbine engine downstream of combustion chamber

  • US 8,132,417 B2
  • Filed: 02/04/2010
  • Issued: 03/13/2012
  • Est. Priority Date: 08/06/2007
  • Status: Active Grant
First Claim
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1. A gas turbine system for a utility power plant, the system comprising:

  • a combustion chamber comprising an inner chamber wall and an outer chamber wall which define an annular outlet region and radially delimit a combustion chamber gas path;

    a turbine comprising a turbine inner wall and a turbine outer wall which define a stationary annular inlet region and radially delimit a turbine gas path;

    a radially inward, radially outward, or both, axial gap between the combustion chamber and the turbine, at which axial gap the inner chamber wall, the outer chamber wall, or both, and the turbine inner wall, the turbine outer wall, or both, end;

    a cooling gas supply, which via the axial gap can introduce a cooling gas into the turbine gas path, into the combustion chamber gas path, or into both;

    wherein an end section of a respective turbine wall, of a respective chamber wall, or of both, adjoining the gap is radially inwardly, radially outwardly, or both, formed so that, in the circumferential direction at the gap, positive stages and negative stages alternate;

    wherein a positive stage comprises a respective wall situated downstream of the axial gap radially projecting into the respective gas path relative to a respective wall situated upstream of the axial gap;

    wherein a negative stage comprises a respective wall situated upstream of the axial gap radially projecting into the respective gas path relative to a respective wall situated downstream of the axial gap; and

    wherein a configuration of said circumferentially alternating positive and negative stages is a function of a cooling demand which circumferentially varies and which results at the axial gap during operation of the gas turbine system.

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