CPC F02K 7/10 (2013.01) [B64D 33/02 (2013.01); B64D 2033/026 (2013.01); F02C 7/04 (2013.01)] | 20 Claims |
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.
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