| 摘要 |
PURPOSE: A platform arrangement in an axial-throughflow gas turbine with improved cooling of the wall segments and a method for reducing gap losses are provided to reduce losses of a guide vane platform forming an inner contour of a flow channel in the axial gas turbine and the gap, and to improve the cooling of wall segments. CONSTITUTION: A platform arrangement in an axial-throughflow gas turbine with improved cooling of the wall segments and a method for reducing gap losses are composed of forming an inner contour of a flow channel(13) at least predominantly by guide vane platforms(9,10) and arranging transitional regions(16) between the platforms within a cavity(12) formed by continuous sealing ribs(3,4) of a shroud(2). The guide vane platforms possess prolongations(9',10') on both sides in the direction of a respectively adjacent moving blade row(1) and extend into a region delimited by the sealing ribs. Guide vane carriers(14,15) are designed as a hollow profile, and cooling air acts at least partially on wall voids(17,18,19) formed between a stator housing(5) and platforms. The cooling air is introduced at least from the wall void into the cavity of the shroud under a pressure in the surrounding flow channel.
|
