Neal D Domel

8316631, Nov 27, 2012

Sep 30, 2010

12/894415

Daniel N. Miller - Bainbridge Island WA, US
Neal D. Domel - Aledo TX, US
Cole W. Schemm - Willow Park TX, US

Lockheed Martin Corporation - Bethesda MD

B64G 1/40

60204, 60231

An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be occupied by an exhaust plume when the engine is running. A flow generator transmits fluid flow into such an exhaust plume through the injectors. Each injector emits fluid in at least two divergent directions to increase the cross-sectional area of the exhaust plume by forming fluidic lobes in the exhaust plume.

8403271, Mar 26, 2013

Aug 24, 2010

12/862436

Neal D. Domel - Fort Worth TX, US
Dan J. Baruzzini - Keller TX, US
Daniel N. Miller - Bainbridge Island WA, US

Lockheed Martin Corporation - Bethesda MD

B64C 21/00

244200, 244198, 2442001

A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.

20110293421, Dec 1, 2011

May 28, 2010

12/790091

Brett W. Denner - Fort Worth TX, US
Neal D. Domel - Aledo TX, US

Lockheed Martin Corporation - Bethesda MD

F01D 5/18

416 92

A rotor blade includes a bleed path opening to a suction surface, extending through the blade, exiting to at least one of the suction or a trailing surface, and through which working fluid flows under centrifugal pumping forces when the blade rotates, to passively bleed working fluid from the suction surface.

20130133857, May 30, 2013

Nov 30, 2011

13/307741

Daniel N. Miller - Bainbridge Island WA, US
Neal D. Domel - Aledo TX, US
Dan J. Baruzzini - Keller TX, US

Lockheed Martin Corporation - Bethesda MD

F28F 7/00

165 47

An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.

20130146715, Jun 13, 2013

Dec 13, 2011

13/324537

Neal D. Domel - Aledo TX, US
Eric F. Charlton - Grapevine TX, US
Daniel N. Miller - Bainbridge Island WA, US

Lockheed Martin Corroration - Bethesda MD

B64C 23/06

2441994, 2441992

An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil.

20130318944, Dec 5, 2013

May 29, 2012

13/482131

Neal D. Domel - Fort Worth TX, US
Daniel N. Miller - Bainbridge Island WA, US

Lockheed Martin Corporation - Bethesda MD

F02K 1/78
F02K 1/00

60204, 60770

Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.

20170096965, Apr 6, 2017

Dec 1, 2016

15/366876

- Bethesda MD, US
Neal David Domel - Fort Worth TX, US
Daniel N. Miller - Bainbridge Island WA, US

F02K 1/82
F02K 1/38
F02K 1/46
B64D 33/04
B64D 41/00

An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.

20150143812, May 28, 2015

Nov 27, 2013

14/092147

- Bethesda MD, US
Neal David Domel - Fort Worth TX, US
Daniel N. Miller - Bainbridge Island WA, US

Lockheed Martin Corporation - Bethesda MD

F02K 1/82

60772, 60 395

An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases.