US 11,788,493 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. 8, 2022, as Appl. No. 17/860,157.
Application 17/860,157 is a continuation of application No. 16/762,972, granted, now 11,466,644, 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 2023/0091268 A1, Mar. 23, 2023
This patent is subject to a terminal disclaimer.
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)] 20 Claims
OG exemplary drawing
 
1. A method for supersonic flight via a turbine engine with a mixed-compression inlet duct comprising the steps of:
(a) passing an airflow over at least two spikes disposed along an interior surface of a duct structure of said mixed-compression inlet duct, each said spike sealingly contacts said interior surface, each said spike includes a longitudinal ridge and a lateral ridge which intersect at an apex, said longitudinal ridge intersects a base at an upstream end and a downstream end to define a height wherein said height between said longitudinal ridge and said base increases along said longitudinal ridge in direction toward said apex, said lateral ridge intersects said base at a pair of lateral ends to define a width wherein said width decreases along said longitudinal ridge with distance from said apex, said mixed-compression inlet duct having an opening at an upstream side to permit said airflow to enter said mixed-compression inlet duct, said upstream end of said longitudinal ridge located at or downstream from said opening;
(b) compressing said airflow along a first diffuser section of said spikes upstream of an inlet throat, said inlet throat formed at said apexes;
(c) forming a normal shock after said compressing step and downstream from said inlet throat, said airflow more supersonic at said normal shock than at said inlet throat; and
(d) expanding said airflow along a second diffuser section of said spikes downstream of said inlet throat, said normal shock decelerates said airflow which enters said opening to less than supersonic and at a pressure permitting said supersonic flight.