of the midframe portion 313 and both of these angular offsets are combined to determine the total angle of rotation of the air flow 311 while passing from the compressor outlet to the respective combustor head 318 inlet fig4 illustrates the midframe portion 313 within the radial tangential plane in which the air flow 311 passes from the annulus 329 at the compressor outlet not shown in the tangential direction 70 oriented at an angle 373 which is 90 degrees with respect to the radial direction 69 the air flow 311 passes within the diffuser duct 314 that is similarly angled in the radial tangential plane at the angle 373 and enters the combustor head 318 inlet in a mixed flow direction with combined radial and tangential velocity components the air flow 311 emerges from the combustor head 318 inlet in a mixed flow direction with combined radial and tangential velocity components at an angle 375 and passes within the transition 320 that is similarly angled in the radial tangential plane at the angle 375 the air flow 311 subsequently exits the transition 320 at an annulus 331 in a tangential direction 70 that is oriented at the angle 375 which is 90 degrees with respect to the radial direction 69 at the transition 320 exit upon entering the annulus 331 the air flow 311 is directed at the first stage blades of the turbine not shown at the appropriate angle 374 in the longitudinal tangential plane fig5 the angular offset of the air flow 311 in the radial tangential plane is based on.