US 12,173,651 B2
Pressure control for bifurcated flow of a turbine engine
Neil J. Terwilliger, Cheshire, CT (US); and Simon W. Evans, Farmington, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on May 15, 2023, as Appl. No. 18/197,558.
Prior Publication US 2024/0384684 A1, Nov. 21, 2024
Int. Cl. F02C 7/042 (2006.01); F02C 7/141 (2006.01); F02C 7/18 (2006.01); F02K 1/06 (2006.01); F02K 3/077 (2006.01); F02C 7/04 (2006.01); F02K 3/06 (2006.01)
CPC F02C 7/042 (2013.01) [F02C 7/141 (2013.01); F02C 7/185 (2013.01); F02K 1/06 (2013.01); F02K 3/077 (2013.01); F02C 7/04 (2013.01); F02K 3/06 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A propulsion system for an aircraft, comprising:
a turbine engine including a propulsor rotor, an engine core and a heat exchanger;
the propulsor rotor configured to rotate about an axis and direct a first air stream along a primary flowpath that bypasses the engine core, and the propulsor rotor configured to direct a second air stream along a secondary flowpath with a geometry extending at least eighty degrees about the axis, the secondary flowpath disposed radially outboard of the primary flowpath and extending circumferentially about the primary flowpath, wherein the turbine engine is configured such that the first air stream enters the primary flowpath at a first pressure and the second air stream enters the secondary flowpath at a second pressure that is greater than the first pressure;
the engine core configured to drive rotation of the propulsor rotor; and
the heat exchanger disposed within the secondary flowpath,
wherein the turbine engine further includes one or both of a variable area nozzle and/or a plurality of guide vanes arranged circumferentially about the axis in an array and located upstream of a splitter between the primary flowpath and the secondary flowpath, the plurality of guide vanes radially overlapping the splitter.