US 12,017,751 B2
Inlet for unducted propulsion system
Brandon Wayne Miller, Liberty Township, OH (US); David Marion Ostdiek, Liberty Township, OH (US); and Darek Tomasz Zatorski, Fort Wright, KY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Sep. 15, 2021, as Appl. No. 17/475,744.
Prior Publication US 2023/0085244 A1, Mar. 16, 2023
Int. Cl. B64C 11/00 (2006.01); B64C 11/18 (2006.01); B64C 11/48 (2006.01); F01D 9/04 (2006.01); F01D 17/16 (2006.01); F02C 6/20 (2006.01); F02K 1/46 (2006.01); F02K 3/02 (2006.01); B64D 27/00 (2006.01)
CPC B64C 11/001 (2013.01) [B64C 11/18 (2013.01); B64C 11/48 (2013.01); F01D 9/041 (2013.01); F01D 17/16 (2013.01); F02C 6/206 (2013.01); F02K 1/46 (2013.01); F02K 3/025 (2013.01); B64D 2027/005 (2013.01); F05B 2240/12 (2013.01); F05B 2260/96 (2013.01); F05D 2220/324 (2013.01); F05D 2220/325 (2013.01); F05D 2220/36 (2013.01); F05D 2250/30 (2013.01); F05D 2250/51 (2013.01); F05D 2250/52 (2013.01); F05D 2260/14 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A propulsion system comprising:
an unducted rotating fan defining a fan axis; and
a turbomachine disposed downstream from the unducted rotating fan, wherein the turbomachine defines a working gas flowpath flowing therethrough;
wherein the propulsion system defines a third stream flowpath and an inlet passage having an inlet that is offset from the fan axis, wherein the inlet passage is configured to provide an inlet airflow to the working gas flowpath, and wherein the third stream flowpath bypasses at least a portion of the turbomachine, and
wherein the turbomachine comprises a mid-fan, wherein the third stream flowpath defines a third stream inlet having a radial height, wherein the mid-fan defines a blade span, and wherein the radial height of the third stream inlet is at least 5% of the blade span of the mid-fan and up to 50% of the blade span of the mid-fan.