Gas turbine arrangement

Abstract

A gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions, wherein the neck exit of the collector includes a partition device whereby the opposed direction flows at the neck exit are kept substantially separate.

1 - 7 . (canceled) 
   
   
       8 . A gas turbine arrangement, comprising:
 an annular passage, configured to convey combustion gases;   a plurality of turbine blading operatively rotatable about a centre line of the gas turbine and arranged in the passage and further operatively driven by the combustion gases;   an annular diffuser configured and arranged to diffuse the combustion gases downstream of the turbine blading, the diffuser comprising a mouth where combustion gases leave the diffuser; and   a collector comprising an annular main part, and a neck exit arranged at a position around the annular main part, the collector configured to collect the combustion gases diffused by the diffuser at the diffuser mouth such that the combustion gases collected by the collector are operatively conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions,
 wherein the neck exit of the collector comprises a partition device that runs parallel to the centre line and extends radially from the centre line and is configured to keep the opposed direction flows substantially separate at the neck exit, the partition device comprising
 a first portion that extends over the collector mouth, and 
 a second portion that extends to one side of the mouth and radially inward 
 
 to a position closer to the centre line than the mouth. 
   
   
   
       9 . The arrangement according to  claim 8 , wherein a side of the first portion that faces radially inwardly increases in distance from the centre line as the distance from the second portion increases. 
   
   
       10 . The arrangement according to  claim 9 , wherein the partition device comprises a flat plate. 
   
   
       11 . The arrangement according to  claim 10 , wherein the diffuser comprises a curved shroud rim where combustion gases leave the diffuser and enter the collector, the shroud rim comprising an extension configured to operatively increase pressure recovery in the gas turbine arrangement and the extension comprises a flat rim extension that is essentially planar in form and forms a discontinuity with the curved shroud rim. 
   
   
       12 . The arrangement according to  claim 10 , wherein the diffuser comprises a curved shroud rim where combustion gases leave the diffuser and enter the collector, the shroud rim comprising an extension configured to operatively increase pressure recovery in the gas turbine arrangement and the extension comprises a spiral rim extension that continues or extends the curve of the curved shroud rim so as to form a spiral.