Bradley Clarke Leland

7568347, Aug 4, 2009

Jul 22, 2005

11/187577

Bradley C. Leland - Burleson TX, US
John D. Klinge - Fort Worth TX, US
Brian F. Lundy - Arlington TX, US

Lockheed Martin Corporation - Bethesda MD

F02C 7/00
B64D 33/02

60768, 137 151, 244 53 B, 703 1

A diverterless hypersonic inlet (DHI) for a high speed, air-breathing propulsion system reduces the ingested boundary layer flow, drag, and weight, and maintains a high capture area for hypersonic applications. The design enables high vehicle fineness ratios, low-observable features, and enhances ramjet operability limits. The DHI is optimized for a particular design flight Mach number. A forebody segment generates and focuses a system of multiple upstream shock waves at desired strengths and angles to facilitate required inlet and engine airflow conditions. The forebody contour diverts boundary layer flow to the inlet sides, effectively reducing the thickness of the boundary layer that is ingested by the inlet, while maintaining the capture area required by the hypersonic propulsion system. The cowl assembly is shaped to integrate with the forebody shock system and the thinned boundary layer region.

7690595, Apr 6, 2010

Dec 12, 2006

11/637644

Bradley C. Leland - Burleson TX, US
Brian F. Lundy - Arlington TX, US
John D. Klinge - Palmdale CA, US

Lockheed Martin Corporation - Bethesda MD

B64D 33/02

244 53B, 137 151

A system, method, and apparatus for throat corner scoop offtake for mixed compression inlets for high speed aircraft engine applications is disclosed. The throat corner scoops are small air intakes located inside the large mixed compression inlet. They are positioned in a region otherwise prone to generate low pressure airflow. The throat corner scoops capture and remove the low pressure airflow from the bulk stream that is passed on to the engine. This location also provides inlet stability enhancement, and the airflow is used on the auxiliary systems.

8297058, Oct 30, 2012

Dec 16, 2008

12/336389

Bradley C. Leland - Burleson TX, US
John D. Klinge - Fort Worth TX, US
Brian F. Lundy - Arlington TX, US

Lockheed Martin Corporation - Bethesda MD

F02K 7/10

60768, 137 151, 244 53 B

A diverterless hypersonic inlet (DHI) for a high speed, air-breathing propulsion system reduces the ingested boundary layer flow, drag, and weight, and maintains a high capture area for hypersonic applications. The design enables high vehicle fineness ratios, low-observable features, and enhances ramjet operability limits. The DHI is optimized for a particular design flight Mach number. A forebody segment generates and focuses a system of multiple upstream shock waves at desired strengths and angles to facilitate required inlet and engine airflow conditions. The forebody contour diverts boundary layer flow to the inlet sides, effectively reducing the thickness of the boundary layer that is ingested by the inlet, while maintaining the capture area required by the hypersonic propulsion system. The cowl assembly is shaped to integrate with the forebody shock system and the thinned boundary layer region.

8484976, Jul 16, 2013

Jun 12, 2008

12/137603

Bradley C. Leland - Burleson TX, US
David M. Wells - Fort Worth TX, US

Lockheed Martin Corporation - Bethesda MD

F02C 7/24
B64C 1/40
B64C 23/00

60725, 244 1 N

A fluidic effector provides enhanced plume mixing for an aircraft engine. Air jet injectors are located on both the external and internal cowl surfaces and angled in opposite directions to induce large scale vortices in the exhaust plume. The vortices mix actuation air with the exhaust plume to produce ejector action. The plume mixes out quickly, thereby lowering jet noise and jet exhaust temperature. The injectors have orientations and injection rates that are adjustable to allow variable mixing rates for use at different flight and engine conditions.

20060266412, Nov 30, 2006

May 31, 2005

11/140800

Brian Lundy - Arlington TX, US
John Klinge - Fort Worth TX, US
Bradley Leland - Burleson TX, US

F02K 11/00
B64D 33/02

137015200, 24405300B

An advanced aperture inlet (AAI) uses a three-dimensional, mixed compression inlet design derived from computational fluid dynamics (CFD) by streamline tracing a supersonic section from an axisymmetric mixed compression inlet solution. The axisymmetric design is used to obtain a CFD solution with slip wall boundaries at the inlet design point and serves as a flow field generator for the AAI. The AAI geometry is obtained by projecting a desired aperture shape onto a surface model of the external oblique shock. Streamline seeds are located on the projected aperture segments and transferred into the CFD solution space. The streamlines generated by these seeds inside the CFD solution space are then used as a wireframe to define the supersonic diffuser back to the throat location. Traditional design techniques are then used to define the subsonic diffuser from the inlet throat to the engine face.