US 11,852,024 B2
Electrical strut for a turbine engine
Pawel Piotr Hanczewski, Warsaw (PL); Mohamed Osama, Garching (DE); and Pawel Pawlowski, Zyrardów (PL)
Assigned to GE Aviation Systems LLC, Grand Rapids, MI (US)
Filed by GE Aviation Systems LLC, Grand Rapids, MI (US)
Filed on Dec. 2, 2021, as Appl. No. 17/540,779.
Claims priority of application No. 436397 (PL), filed on Dec. 18, 2020.
Prior Publication US 2022/0195887 A1, Jun. 23, 2022
Int. Cl. F01D 25/12 (2006.01); F01D 9/02 (2006.01); F01D 5/18 (2006.01); F01D 15/10 (2006.01); F01D 25/16 (2006.01); F01D 25/30 (2006.01); F01D 9/06 (2006.01); F01D 9/04 (2006.01); F01D 25/00 (2006.01); H02G 5/10 (2006.01); H05K 9/00 (2006.01)
CPC F01D 25/12 (2013.01) [F01D 9/02 (2013.01); H02G 5/10 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2260/20 (2013.01); H05K 9/0081 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil for a turbine engine, the airfoil comprising:
an outer wall having a pressure side, a suction side, a leading edge, and a trailing edge, the outer wall defining an interior and separating the interior from an exterior, wherein the outer wall extends between the pressure side and the suction side to define a lateral direction, between the leading edge and the trailing edge to define a chord-wise direction, and between a root and a tip to define a span-wise direction; and
multiple electrical conduits extending from the exterior into the interior along the span-wise direction, at least one electrical conduit of the multiple electrical conduits comprising:
at least one conductor forming a cooling conduit with a hollow interior having a central axis along which at least a portion of a cooling flow path extends;
wherein the at least one conductor surrounds the cooling flow path; and
wherein the multiple electrical conduits are spaced from each other a first distance in the exterior and a second distance less than the first distance within the interior.