US 11,927,151 B2
Mixed-compression inlet duct for turbine engines facilitating supersonic flight
Neeraj Sinha, Ivyland, PA (US); Stephen M. Barr, Hellertown, PA (US); and Michael R. O'Gara, Sellersville, PA (US)
Assigned to Combustion Research and Flow Technology, Inc., Pipersville, PA (US)
Filed by Combustion Research and Flow Technology, Inc., Pipersville, PA (US)
Filed on Jul. 10, 2023, as Appl. No. 18/349,410.
Application 18/349,410 is a continuation of application No. 17/860,157, filed on Jul. 8, 2022, granted, now 11,788,493.
Application 17/860,157 is a continuation of application No. 16/762,972, granted, now 11,466,644, issued on Oct. 11, 2022, previously published as PCT/US2018/064665, filed on Dec. 10, 2018.
Claims priority of provisional application 62/764,891, filed on Aug. 16, 2018.
Prior Publication US 2023/0349344 A1, Nov. 2, 2023
Int. Cl. F02K 7/10 (2006.01); B64D 33/02 (2006.01); F02C 7/04 (2006.01)
CPC F02K 7/10 (2013.01) [B64D 33/02 (2013.01); B64D 2033/026 (2013.01); F02C 7/04 (2013.01)] 28 Claims
OG exemplary drawing
 
1. An inlet duct for use with a turbine engine comprising:
(a) a duct structure having an interior surface;
(b) at least two spikes disposed along said interior surface so said spikes interact in use with an airflow, each said spike includes a longitudinal ridge and a lateral ridge which intersect at an apex, said longitudinal ridge intersects said interior surface at an upstream end and a downstream end to define a height between said longitudinal ridge and said interior surface wherein said height increases along said longitudinal ridge in direction toward said apex, said lateral ridge intersects said interior surface at a pair of lateral ends to define a width between said lateral ends wherein said width decreases along said longitudinal ridge with distance from said apex, said duct structure having an opening at an upstream side to permit said airflow to enter said duct structure, said upstream end of said longitudinal ridge located at or downstream from said opening; and
(c) an inlet throat formed at said apexes, a normal shock formed in use downstream from said inlet throat, said normal shock decelerates said airflow to less than supersonic and at a pressure permitting supersonic flight.