Daniel C Eylon

48327603, May 23, 1989

Dec 4, 1987

7/128842

Daniel Eylon - Dayton OH
Francis H. Froes - Xenia OH

The United States of America as represented by the Secretary of the Air
Force - Washington DC

C22F 118

148 203

A method for improving the microstructure of prealloyed titanium alloy compacted articles which comprises the steps of hydrogenating the article at a temperature of about 780. degree. to 1020. degree. C. to a hydrogen level of about 0. 50 to 1. 50 weight percent, cooling the thus-hydrogenated article to room temperature at a controlled rate, heating the thus-cooled, hydrogenated article to a temperature of about 650. degree. to 750. degree. C. and applying a vacuum to dehydrogenate the article.

51044609, Apr 14, 1992

Dec 17, 1990

7/628955

Paul R. Smith - Miamisburg OH
Daniel Eylon - Dayton OH
William C. Revelos - Kettering OH

The United States of America as represented by the Secretary of the Air
Force - Washington DC

C22C 1400

148 115F

A method for fabricating a composite structure consisting of a filamentary material selected from the group consisting of silicon carbide, silicon carbide-coated boron, boron carbide-coated boron, titanium boride-coated silicon carbide and silicon-coated silicon carbide, embedded in an alpha-2 titanium aluminide metal matrix, which comprises the steps of modifying the desired filamentary material with at least one beta stabilizer, providing a beta-stabilized Ti. sub. 3 Al foil, fabricating a preform consisting of alternating layers of foil and a plurality of at least one of the beta stabilizer-coated filamentary materials, and applying heat and pressure to consolidate the preform. The composite structure fabricated using the method of this invention is characterized by its lack of a denuded zone and absence of fabrication cracking.

50321897, Jul 16, 1991

Mar 26, 1990

7/498881

Daniel Eylon - Dayton OH
Francis H. Froes - Moscow ID

The United States of America as represented by the Secretary of the Air
Force - Washington DC

C22F 118

148 115F

Near-alpha and alpha+beta titanium alloy components are produced by a process which comprises the steps of forging an alloy billet to a desired shape at a temperature at or above the beta-transus temperature of the alloy to provide a forged component, heat treating the forged component at a temperature approximately equal to the beta-transus temperature of the alloy, cooling the component at a rate in excess of air cooling to room temperature, annealing the component at a temperature in the approximate range of 10 to 20% below said beta-transus temperature for about 4 to 36 hours, and air cooling the component to room temperature.

48099031, Mar 7, 1989

Nov 26, 1986

6/935363

Daniel Eylon - Dayton OH
Francis H. Froes - Xenia OH

United States of America as represented by the Secretary of the Air Force - Washington DC

B23K 2900

228194

A method for fabricating an improved titanium alloy composite consisting of at least one high strength/high stiffness filament or fiber embedded in an alpha-beta titanium alloy matrix which comprises the steps of providing a rapidly-solidified foil made of a rich metastable beta titanium alloy, fabricating a preform consisting of alternating layers of the rapidly-solidified foil and the filamentary material, and applying heat and pressure to consolidate the preform, wherein consolidation is carried out at a temperature below the beta-transus temperature of the alloy.

48510530, Jul 25, 1989

May 6, 1988

7/198801

Francis H. Froes - Xenia OH
Daniel Eylon - Dayton OH

The United States of America as represented by the Secretary of the Air
Force - Washington DC

C21D 100
C22F 118

148 115F

A method to produce titanium alloy articles having high creep resistance which comprises the steps of: (a) providing a titanium alloy material containing at least one dispersoid forming alloy addition: (b) hydrogenating the alloy material to a level of about 0. 1 to 4. 0 weight percent hydrogen; (c) introducing the resulting hydrogenated material into a mold; (d) hot compacting the alloy material in the mold to produce a substantially fully dense article; (e) beta heat treating the compacted article; and, (f) dehydrogenating the article. Following heat treatment, the microstructure in the article will be lenticular transformed beta which is highly creep resistant, while size of the dispersoid will be approximately the same as before the heat treatment, due to the relatively low beta treatment temperature.

48203602, Apr 11, 1989

Dec 4, 1987

7/128839

Daniel Eylon - Dayton OH
Francis H. Froes - Xenia OH
Charles F. Yolton - Coraopolis PA

The United States of America as represented by the Secretary of the Air
Force - Washington DC

C22F 118

148133

A method for improving the microstructure of cast titanium alloy articles which comprises the steps of hydrogenating the cast article at a temperature near or above the titanium-hydrogen eutectoid of 815. degree. C. (of about 780. degree. to 1020. degree. C. ) to a hydrogen level of about 0. 50 to 1. 50 weight percent, cooling the thus-hydrogenated article to room temperature at a controlled rate, heating the thus-cooled, hydrogenated article to a temperature of about 650. degree. to 750. degree. C. , applying a vacuum to dehydrogenate the article, and cooling the thus-dehydrogenated article at a controlled rate.

48077984, Feb 28, 1989

Nov 26, 1986

6/935362

Daniel Eylon - Dayton OH
Francis H. Froes - Xenia OH

The United States of America as represented by the Secretary of the Air
Force - Washington DC

B23K 2022
B23K 3100

228190

A method for fabricating an improved titanium alloy composite consisting of at least one high strength/high stiffness filament or fiber embedded in an alpha-beta titanium alloy matrix which comprises the steps of providing a rapidly-solidified foil made of a lean metastable beta titanium alloy, fabricating a preform consisting of alternating layers of the rapidly-solidified foil and the filamentary material, and applying heat and pressure to consolidate the preform, wherein consolidation is carried out at a temperature below the beta-transus temperature of the alloy.

49178580, Apr 17, 1990

Aug 1, 1989

7/387925

Daniel Eylon - Dayton OH
Francis H. Froes - Xenia OH

The United States of America as represented by the Secretary of the Air
Force - Washington DC

B22F 324

419 28

A method for producing foil of titanium aluminide is described which comprises providing a preselected quantity of blended powder of chloride free commercially pure elemental titanium, aluminum and other alloying metal(s) in preselected proportions, rolling the blended powder into a green foil, sintering the green foil, and thereafter pressing the sintered foil to full density.