Patent ID: 6099244
Filing Date: 2000-08-08
Classification: F01D,F02D,F05D,Y02T

Abstract:
A cooled stationary blade assembly for a gas turbine, comprising:a blade having a leading edge, a trailing edge, an outer end and an inner end, and the blade defining an internal first blade cooling passage and an internal second blade cooling passage, wherein the first blade cooling passage is arranged for directing a first flow of air through the blade and discharging the first flow from the trailing edge of the blade;an inside shroud connected to the inner end of the blade and comprising a leading side and a trailing side, wherein the inside shroud defines a shroud cooling passage therein, the second blade cooling passage is arranged for directing a cooling second flow of air through the blade to the shroud cooling passage, and the shroud cooling passage is arranged for discharging the second flow from the trailing side of the inside shroud; andan outside shroud connected to the outer end of the blade and operative to supply the first flow to the first passage and a further operative to supply the second flow to the second passage, wherein the first passage, the second passage and the shroud passage are arranged so that the portion of the first flow that is downstream from the outside shroud and upstream from the trailing edge of the blade is isolated from the portion of the second flow that is downstream from the outside shroud and upstream from the trailing side of the inside shroud, whereby the blade and the outside shroud may be optimally cooled.