US 12,392,295 B2
Aircraft propulsion system
Jeffrey D. Rambo, Mason, OH (US); Brandon W. Miller, Middletown, OH (US); and Scott G. Edens, Milford, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jan. 11, 2023, as Appl. No. 18/152,903.
Prior Publication US 2024/0229726 A1, Jul. 11, 2024
Int. Cl. F02C 9/00 (2006.01); F02C 3/04 (2006.01); F02C 7/057 (2006.01); F02C 9/18 (2006.01)
CPC F02C 9/18 (2013.01) [F02C 3/04 (2013.01); F02C 7/057 (2013.01); F05D 2220/10 (2013.01); F05D 2220/3217 (2013.01); F05D 2220/323 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A propulsion system comprising:
a turbine engine including a compressor section, a combustor, and a turbine section;
a ramjet engine;
an inlet section including a turbine engine inlet portion and a ramjet inlet portion, the inlet section providing an inlet airflow to the turbine engine and to the ramjet engine, wherein the turbine engine inlet portion includes a converging/diverging inlet having a throat portion, the converging/diverging inlet converges from a forward end of the converging/diverging inlet to the throat portion and then diverges from the throat portion to an aft end of the converging/diverging inlet;
an expansion turbine arranged in the turbine engine inlet portion upstream of the turbine engine; and
a translating spike disposed within the turbine engine inlet portion upstream of the expansion turbine, wherein the translating spike engages the throat portion of the converging/diverging inlet, in a first operating state of the propulsion system, to restrict the inlet airflow to the expansion turbine such that the inlet airflow bypasses the expansion turbine, and the translating spike disengages the throat portion of the converging/diverging inlet, in a second operating state of the propulsion system, and to permit the inlet airflow through the expansion turbine to the turbine engine.