US 12,416,262 B2
Reverse flow gas turbine engine having electric machine
Arthur William Sibbach, Boxford, MA (US); and Adam Tomasz Paziński, 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 Oct. 24, 2024, as Appl. No. 18/925,935.
Application 18/925,935 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 2025/0052194 A1, Feb. 13, 2025
Int. Cl. F02C 6/20 (2006.01); F01D 15/10 (2006.01); F01D 25/12 (2006.01); F02C 7/04 (2006.01); F02C 7/08 (2006.01)
CPC F02C 6/20 (2013.01) [F01D 15/10 (2013.01); F01D 25/12 (2013.01); F02C 7/04 (2013.01); F02C 7/08 (2013.01); F05D 2220/323 (2013.01); F05D 2220/70 (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 a 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 the high pressure compressor includes:
a shaft comprising a forward end portion, wherein the forward end portion defines an outer surface and rotates with the shaft;
a first row of compressor rotor blades coupled to the shaft downstream from the forward end portion;
an outer casing at least partially surrounding the first row of compressor rotor blades and the outer surface of the forward end portion of the shaft, the outer casing at least partially defining an inlet to the high pressure compressor; and
an inlet guide vane comprising a mounting portion, a tip portion, a leading-edge portion, and a trailing-edge portion, wherein the mounting portion is coupled to the outer casing upstream from the first row of compressor rotor blades, wherein the tip portion extends towards the outer surface of the forward end portion of the shaft, and wherein a radial gap is defined between the tip portion and the outer surface.