US 11,053,797 B2
Rotor thrust balanced turbine engine
Thomas Ory Moniz, Loveland, OH (US); and Jeffrey Donald Clements, Mason, OH (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 23, 2017, as Appl. No. 15/412,216.
Prior Publication US 2018/0209273 A1, Jul. 26, 2018
Int. Cl. F01D 3/00 (2006.01); F01D 5/02 (2006.01); F01D 25/16 (2006.01); F02C 7/28 (2006.01); F01D 11/00 (2006.01); F01D 11/08 (2006.01); F01D 25/24 (2006.01); F04D 25/04 (2006.01); F04D 29/053 (2006.01); F04D 29/32 (2006.01)
CPC F01D 5/027 (2013.01) [F01D 3/00 (2013.01); F01D 11/005 (2013.01); F01D 11/08 (2013.01); F01D 25/16 (2013.01); F01D 25/24 (2013.01); F02C 7/28 (2013.01); F04D 25/045 (2013.01); F04D 29/053 (2013.01); F04D 29/325 (2013.01); F05D 2220/32 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, and an axial centerline extended along the longitudinal direction, the gas turbine engine comprising:
a low pressure spool comprising a fan assembly and a turbine rotor assembly, wherein the low pressure spool is connected to a bearing assembly, and wherein the turbine rotor assembly defines a first flowpath radius and a second flowpath radius each extended from the axial centerline, wherein the first flowpath radius is disposed at an upstream end of the turbine rotor assembly, wherein the upstream end is at a forward edge of a blade of a first rotating stage of the turbine rotor assembly, and wherein the second flowpath radius is disposed at a downstream end of the turbine rotor assembly; and
a turbine frame, wherein the turbine frame and the turbine rotor assembly together define a seal interface, the seal interface positioned forward of or aligned along the radial direction with the upstream end of the turbine rotor assembly, and the seal interface having a seal interface radius inward of the turbine rotor assembly along the radial direction and concentric to the axial centerline, and wherein the turbine rotor assembly defines a ratio of the first flowpath radius to the seal interface radius, the ratio of the first flowpath radius to the seal interface radius defining at least in part a thrust balance at the bearing assembly at the low pressure spool, wherein the ratio of the first flowpath radius to the seal interface radius is less than or equal to 1.79.