CPC F01D 9/06 (2013.01) [F01D 25/12 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2260/20 (2013.01)] | 20 Claims |
1. A turbine vane in a gas turbine engine, the turbine vane comprising:
an inner platform having an aperture;
an outer platform;
a vane airfoil positioned between the inner platform and the outer platform, the vane airfoil comprising:
a first cooling passage extending between the outer platform and the inner platform;
a second cooling passage extending between the outer platform and the inner platform, the second cooling passage arranged downstream of the first cooling passage with respect to a flow direction;
a jumper tube disposed between the second cooling passage and the inner platform, the jumper tube comprising an inlet, an outlet, and a tube wall enclosing a hollow interior, the inlet positioned a distance within the second cooling passage, and the outlet positioned at least partially through the aperture of the inner platform; and
a cover plate attached to the jumper tube and the inner platform,
wherein the inlet is positioned at a portion of a span length of the second cooling passage such that a gap is defined between the inlet and the outer platform within the second cooling passage.
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