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1963 to 2004

NASA Langley

Hypersonic Airbreathing Propulsion

Senior Combustion Engineer

He is responsible for : Originate, plan, and report the results of research required to demonstrate the Feasibility of high-energy facility designs. Provide new and unique designs and Solutions to operational problems. Provide new and unique concepts for Hypersonic vehicles both air breathing and rocket powered or combinations. Design and develop facilities to test such hypersonic vehicles

1983 to

(Undisclosed)

Engineering Design

Designer

He is a senior engineer providing engineering expertise and project management services required for the development of specialized research systems. His engineering expertise is in the design and analysis of structural and mechanical systems, the use of numerous design codes, developing new criteria for specialized systems, using and mentoring others in the use of design and analysis software, and developing unique closed form solutions to problems. He is a project manager, leading a multi-disciplined team of engineers, technicians, administration personnel, and contractors through all aspects of a project including: defining requirements and project scope, cost estimating, schedule development and control, conceptual design through final design, analysis, drawings, documentation, specifications, procurement methods, construction management, testing, project close-out, and reporting at various reviews and status meetings. Supervision is limited to defining the broad objective, negotiating for personnel to work on the project, and status meetings.

1989 to 2003

NASA-Langley

Engineering

Project Engineer

He is consulting and solving problems analytically supported by CFD codes on • Subsonic combustors, rocket, and scramjet design. • Heat flux levels in combustors and ramjets-scramjets. Cooling of the combustors for these devices

• He has developed effective acoustic damping techniques ( reduced noise in 8-FT HTT from 70 psi at 30 HZ to 0.5 psia at 360 Hz.- now the quietest combustor in the world for its size
• He has designed and tested , and now in service, Super Ignitor for 8-FT HTT . Uses rich pilot flame ( REQ=3) to stabilize and ignite large jet of methane at near sonic conditions
• He has designed a development facility. In this facility, he designed a number of unique designs and tested : i. The modified Lewis design for use as ignitor ii. The mini-max SUE annular combustor iii. A swirl stabilized combustor iv. A ring type fuel injector v. A modified ring type injector vi. A lifted flame ring injector ( no cooling needed) vii. A lifted flame paired airfoil injector able to operate at 5000 R and 2000 psia without cooling.
• He lead the installion of 84 SUE combustors ( 52 foot diameter plenum ) in the 9 X6 Wind Tunnel . Temperature =2500 R and Poc=200 psia . Used to test Army and Air Force tactical missiles at q of up to 5000 psf . Flow rates of up to 5000 lb./s of which 60% went through combustors. The SAM-D ( now the Patriot was developed here ) ; the improved Hawk ;the use of fused silica as radomes ; radomes for rain and ice also developed here
• He was responsible ( with team) for the redesign of the Mixer for Aerojet for the Hypersonic Test facility

• Impeller expert for consulting on combustor design in a 5 in. dia centrifuge jet engine.