US 11,988,146 B2
Thermal management of a gas turbine engine shaft
Gary D. Roberge, Tolland, CT (US); and Jorn Axel Glahn, Manchester, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jul. 15, 2021, as Appl. No. 17/376,482.
Application 17/376,482 is a continuation of application No. 15/993,675, filed on May 31, 2018, granted, now 11,078,843.
Prior Publication US 2021/0340911 A1, Nov. 4, 2021
Int. Cl. F02C 7/18 (2006.01); F01D 5/08 (2006.01); F01D 25/12 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/18 (2013.01) [F01D 5/085 (2013.01); F01D 25/125 (2013.01); F02K 3/06 (2013.01); F05D 2240/50 (2013.01); F05D 2240/55 (2013.01); F05D 2240/61 (2013.01); F05D 2260/20 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan rotor, a compressor section, a combustor section, and a turbine section, said turbine section being positioned downstream of said combustor section;
a fan drive turbine in said turbine section, and a shaft connecting said fan drive turbine to said fan rotor;
an inlet duct connected to a cooling air source and connected to a cooling compressor downstream of said fan drive turbine, and said cooling compressor fluidly connected to the cooling air source and connected to a turning duct for passing compressed air in an upstream direction through said shaft;
wherein said cooling compressor is supported by a bearing which also supports said shaft; and
wherein there being connection passages in said shaft providing communication between an inner passage and an outer passage in said shaft, the inner passage and the outer passage both radially inward of the fan drive turbine, such that the compressed air, having passed in said upstream direction through said shaft in one of the inner passage and the outer passage is returned in the other of the inner passage and the outer passage in a downstream direction to provide cooling to said shaft.