Patent ID: 8616834

Claim:
A guide vane apparatus for a gas turbine engine comprising: (a) an annular array of stationary airfoils, each stationary airfoil comprising: (i) opposed pressure and suction sides, a root, a tip, and spaced-apart leading and trailing edges; (ii) a plenum integrally formed within the airfoil which is configured to receive a flow of circulating working fluid; (iii) inlet and outlet ports disposed at the tip of the airfoil, each port communicating with the plenum and an exterior of the airfoil; (b) an annular casing surrounding the array of stationary airfoils, wherein the tip of each stationary airfoil is connected to the casing; and (c) a jumper tube assembly coupled to each of the inlet and outlet ports, each jumper tube assembly comprising: (i) a jumper tube having a first end received within the respective port, the jumper tube spanning a radial gap between the tip of the airfoil and the casing and passing through an opening in the casing; and (ii) a retainer attached to the casing which receives a second end of the jumper tube and retains the jumper tube in position, the retainer including a fluid fitting in fluid communication with the jumper tube, wherein the retainer includes an internal surface that blocks the jumper tube from radially outward movement relative to the casing.