US 12,116,906 B2
Turbine vane in gas turbine engine
Daniel Joo, Oviedo, FL (US); Ching-Pang Lee, Cincinnati, OH (US); Gm Salam Azad, Oviedo, FL (US); and Sin Chien Siw, Simsbury, CT (US)
Assigned to Siemens Energy Global GmbH & Co. KG, Munich (DE)
Appl. No. 18/269,037
Filed by SIEMENS ENERGY GLOBAL GMBH & CO. KG, Munich (DE)
PCT Filed Jan. 6, 2021, PCT No. PCT/US2021/012336
§ 371(c)(1), (2) Date Jun. 22, 2023,
PCT Pub. No. WO2022/150036, PCT Pub. Date Jul. 14, 2022.
Prior Publication US 2024/0076993 A1, Mar. 7, 2024
Int. Cl. F01D 9/06 (2006.01); F01D 25/12 (2006.01)
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
OG exemplary drawing
 
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.