| 摘要 |
1,135,879. Gas turbine engines. GENERAL ELECTRIC CO. April 5, 1967 [Aug. 24, 1966], No. 15519/67. Headings F1G and FIT. In an axial flow rotary machine, such as the turbine of a gas turbine engine, the stator assembly comprises a segmented ring of blade support platforms, there being at least one blade mounted on each platform and formed with a cooling fluid passageway therein. Each of the platforms includes a chamber having an inlet for receiving cooling fluid and an outlet connected to the passageway in the associated blade. A wall member is provided between the segmented ring and an annular manifold from which cooling fluid passes to the closed chambers of the ring, the wall member serving to restrict leakage of cooling fluid from the manifold through gaps between adjacent blade support platforms, there being a conduit which passes through the wall member to the inlet of each chamber for supplying cooling fluid directly from the manifold to the chamber, the conduits being so disposed as to allow thermal expansion of the stator assembly. In the embodiment shown the invention is applied to the second stage nozzle guide vanes 19 of the gas turbine of a gas turbine engine, the turbine assembly comprising rotor discs 11, 12 carrying rotor blades 10, 13 respectively. The inlet nozzle assembly comprises guide vanes 18 and the second stage nozzle assembly comprises guide vanes 19. The turbine stator casing comprises outer wall members 4, the upstream wall member being formed with inner and radial portions 20 so as to define an annular manifold 14 to which cooling fluid such as air tapped from the engine compressor is supplied through duct 16. The second stage nozzle guide vane assembly comprises vanes 19 mounted on arcuate support members 24 as shown in Fig. 2, the support members comprising walls 17, 26, 27, 28 which together define chambers 29 to which cooling air passes from the manifold 14 through ducts 30 and from which it passes to cooling passages 40 in the vanes 19 through bores 39, the air finally discharging through outlets 42 at the trailing edges of the vanes. The duct 30 is a close fit in the upstream wall 27 of the chamber 29 but is a loose fit in the radial wall 20 of the manifold 14, there being a clearance 44 between the duct and the wall. Some cooling air passes through the clearance 44 to the space 38, the air finally passing into the working fluid passage through the gaps between the ends of adjacent vane support segments. The radial wall 20 serves to prevent excessive flow of cooling air to the space 38 and so to the working fluid passage. Each vane support segment may support a single vane only. The duct 30 may be mounted in the bore in the radial wall 27 in such a manner that pivotal movement of the duct may occur. |
