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US 8,616,834 B2Granted
Gas turbine engine airfoil integrated heat exchanger
AssigneeGeneral Electric Company
InventorsGlenn Knight, III, Bojan Lukovic, Daniel Laborie, Kenneth S. Scheffel
Life of this patent
Estimating the term…
Abstract
A heat exchanger apparatus includes: (a) an airfoil having opposed pressure and suction sides, a root, a tip, and spaced-apart leading and trailing edges; and (b) a plenum integrally formed within the airfoil which is configured to receive a flow of circulating working fluid; and (c) inlet and outlet ports communicating with the plenum and an exterior of the airfoil.
Claims4
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.
7 more elements
Dependencies are inferred from the claim text.