INTERMEDIATE TRANSITION ANNULUS FOR A TWO SHAFT GAS TURBINE ENGINE

INTERMEDIATE TRANSITION ANNULUS FOR A TWO SHAFT GAS TURBINE ENGINE A two shaft gas turbine engine is shown wherein the power turbine comprises a single stage which is closely coupled to the compressor turbine through an annular transition portion having radially diverging side walls forming an inner and outer shroud. The relatively high velocity of the working fluid is maintained through the transition portion by an array of non-rotating stationary struts. Each strut defines a camber line which at the entry of the strut is angled to receive the working fluid, having a swirl component therein, at a 0.degree. angle of incidence. Further, each strut has a configuration which, in cooperation with the increasing angle of the camber line compensates for the divergence of the shrouds to maintain the flow of the working fluid at a generally undiminished velocity therethrough An array of non-rotating variable vanes is disposed intermediate the downstream end of the struts to direct the working fluid into the power turbine at an optimum angular discharge depending upon the desired output of the power turbine shaft.