Eric D Taylor

US Patent:

6497091, Dec 24, 2002

Filed:

Jun 6, 2001

Appl. No.:

09/877800

Inventors:

Eric S. Taylor - Huntsville AL
W. Neill Myers - Huntsville AL
Michael A. Martin - Huntsville AL

Assignee:

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

F02C 724

US Classification:

60 39824

Abstract:

An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture to rupture and hypergolic fluid contained within the cartridge is discharged out the outlet. Once the piston assembly reaches the discharge end of the cartridge, purge grooves allow for fuel and remaining hypergolic fluid, to be discharged out the ignitor outlet into the combustion chamber to purge the ignitor of any remaining hypergolic fluid.

US Patent:

6845605, Jan 25, 2005

Filed:

Nov 4, 2002

Appl. No.:

10/288800

Inventors:

Eric S. Taylor - Huntsville AL, US
W. Neill Myers - Huntsville AL, US
Michael A. Martin - Huntsville AL, US

Assignee:

The United States of America as represented by the Administrator National Aeronautics and Space Administration - Washington DC

International Classification:

F02C 7264

US Classification:

60 39824

Abstract:

An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture disc to rupture and hypergolic fluid contained within the cartridge is discharged out the ignitor outlet.

US Patent:

61893153, Feb 20, 2001

Filed:

Jun 18, 1999

Appl. No.:

9/350412

Inventors:

Henry J. Dennis - Madison AL
D. Andy Hissam - Madison AL
W. Neill Myers - Huntsville AL
Eric S. Taylor - Huntsville AL

Assignee:

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

International Classification:

F02K 942

US Classification:

60259

Abstract:

A gas generator and ignitor assembly for powering a turbine of a turbopump assembly for a rocket engine comprises an injector and a combustion chamber, the injector having a body member including a fuel inlet and an oxidizer inlet spaced one from the other and communicating with respective radially spaced apart annular members in the body member. Three annuli communicate with the fuel inlet and two annuli communicate with the oxidizer inlet, the annuli which communicates with the oxidizer being positioned between pairs of the other annuli. The body member is enclosed by a plate having an array of bores arranged in two series with three radially spaced apart groups of circular rows in each series. The outer series has 28 groups of triplet bores while the inner series has 14 groups of triplet bores. The annuli which communicate with oxidizer feed bores of each series that are between the other bores of a triplet, the latter bores communicating with annuli that communicate with fuel.