Abstract: The arcuate vane support segments (26) each carry a plurality of vanes (28) and have a pair of axially extending feet (38). These feet do not slide axially into a groove, but move radially against an arm (22) of the "T" shaped air seal. The casing ring 62 is translated axially in place entrapping the feet (38).

Abstract: A stator vane assembly 30 for a rotary machine is disclosed. The stator vane assembly includes an array of stator vanes 44 and an inner air seal 46. Various construction details which damp vibrational stresses in the vanes are developed. In one embodiment, the stator vanes slidably engage the inner air seal. The inner air seal is urged radially into sliding contact with the vanes at the inner ends 52 of the vanes by a resilient device such as a radial spring member 70. In one detailed embodiment, the stator vane has at least two airfoils 55b,c which are circumferentially spaced at their inner ends leaving a circumferential gap therebetween.

Abstract: A pressure and temperature measuring probe with a low drag, airfoil shaped cross section includes a longitudinally extending pressure cavity adjacent the leading edge and a separate longitudinally extending temperature cavity immediately downstream thereof. Longitudinally spaced apart passages extend downstream from their inlets at pressure measuring stations along the leading edge and intersect the pressure cavity. At temperature measuring stations along the leading edge passages extend downstream adjacent the pressure cavity to intersect the temperature cavity and direct a high velocity flow of gases over a thermocouple junction disposed within the temperature cavity. Stagnation devices at the leading edge reduce gas velocity to zero at the passage inlets.

Abstract: A flow directing apparatus for use in an axial flow turbomachine is disclosed. Techniques for reducing aerodynamic drag along the walls of the flow directing apparatus are developed. In one embodiment, rotor blades have multiplanar platform surfaces which reduce aerodynamic drag pressure losses at the interface between each blade platform and the adjacent structure.