US 12,319,417 B2
Reverse flow gas turbine engine having electric machine
Arthur William Sibbach, Boxford, MA (US); and Adam Tomasz Pazinski, Warsaw (PL)
Assigned to General Electric Company, Evendale, OH (US); and General Electric Company Polska Sp. z o.o., Warsaw (PL)
Filed by General Electric Company, Evendale, OH (US); and General Electric Company Polska Sp. z o.o., Warsaw (PL)
Filed on Dec. 20, 2024, as Appl. No. 18/990,417.
Application 18/990,417 is a continuation in part of application No. 18/307,938, filed on Apr. 27, 2023, granted, now 12,188,414.
Claims priority of application No. 443814 (PL), filed on Feb. 17, 2023.
Prior Publication US 2025/0121945 A1, Apr. 17, 2025
Int. Cl. B64D 27/33 (2024.01); B64D 27/10 (2006.01); F01D 11/00 (2006.01); F02C 3/14 (2006.01); F02C 7/18 (2006.01); F02C 7/28 (2006.01); F02C 7/32 (2006.01)
CPC B64D 27/33 (2024.01) [B64D 27/10 (2013.01); F01D 11/003 (2013.01); F02C 3/145 (2013.01); F02C 7/18 (2013.01); F02C 7/28 (2013.01); F02C 7/32 (2013.01); F05D 2220/76 (2013.01); F05D 2240/55 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft engine assembly comprising:
a gas turbine engine having a high pressure compressor, a high pressure turbine, a high pressure shaft coupling the high pressure compressor with the high pressure turbine, a low pressure turbine, and a low pressure shaft coupled to the low pressure turbine, the high pressure turbine located forward of the high pressure compressor, and the low pressure turbine located on a forward end of the gas turbine engine;
a propeller located on the forward end of the gas turbine engine and coupled via the low pressure shaft with the low pressure turbine;
an intake channel of the gas turbine engine configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction; and
an electric machine coupled with the low pressure shaft and located on a side of the high pressure compressor opposite of the high pressure turbine and proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated,
wherein at least one of the gas turbine engine, the propeller, the intake channel, or the electric machine includes an engine structure comprising:
an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall; and
an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner wall and the outer wall.