DR. JOHN D MILLER, D.D.S, P.A
Dentist at Tequesta Dr, Jupiter, FL

4479293, Oct 30, 1984

Nov 27, 1981

6/325149

John A. Miller - Jupiter FL
Ralph E. Anderson - Palm Beach Gardens FL
Marvin M. Allen - Lake Worth FL

United Technologies Corporation - Hartford CT

B21K 300

291568R

An integrally bladed bimetallic rotor for high temperature operation having airfoils with good stress rupture and creep strength and a hub with high tensile strength and good low cycle fatigue resistance is made from a preform of two concentric cylinders of different superalloy metals metallurgically bonded to each other at their interface, both materials being in such a condition that they exhibit superplastic behavior at a certain, controlled strain rate and temperature without incurring substantial grain growth. The metal of the outer cylinder is selected such that it has a lower gamma prime solvus temperature than the metal of the inner cylinder. The preform is isothermally forged at the controlled strain rate and temperature to form the airfoils from the alloy of the outer cylinder and to form the hub from the alloy of the inner cylinder. A sharp, reproducible interface is created between the two alloys. After forging, the rotor is heated to a temperature between the gamma prime solvus temperatures of the alloys and under conditions which cause full gamma prime solutioning of the airfoils up to the interface but only partial gamma prime solutioning of the rotor hub.

5074925, Dec 24, 1991

Jun 25, 1990

7/543285

William J. Gostic - Tequesta FL
John A. Miller - Jupiter FL

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

C22F 110

148 115R

A thermomechanical method for fabricating net shape single crystal airfoils is disclosed. A cast single crystal superalloy workpiece is solution heat treated to provide a homogeneous gamma prime distrubition. The single crystal sheet stock is then warm worked, generally forged or rolled, at a working temperature of gamma prime solvus minus about 50. degree. -300. degree. F. with a maximum six percent deformation per pass. Following the first warm working, the single crystal sheet stock is cyclic annealed in a temperature range of gamma prime solvus minus about 50. degree. -125. degree. F. to prevent recrystallization of the single crystal sheet stock. The cyclic annealing is preferably cycled three to ten times between the low and high ends of the temperature range at a rate of change of temperature between about 1. degree. F. per minute to about 10. degree. F. per minute.

5693159, Dec 2, 1997

Jan 10, 1994

8/180755

Roy L. Athey - North Palm Beach FL
John A. Miller - Jupiter FL
William J. Gostic - Tequesta FL
Paul D. Genereux - Cromwell CT
Timothy P. Fuesting - Lynchburg VA

United Technologies Corporation - Hartford CT

C22F 110

148677

A process for producing a fine grain forged superalloy article having a high yield strength at intermediate temperatures. A preferred starting composition comprises, by weight, 15% Cr, 13. 6% Co, 4. 1% Mo, 4. 6% Ti, 2. 2% Al, 0. 01% C, 0. 007% B, 0. 07% Zr, balance Ni. This material is forged at a temperature above the gamma prime solvus and at a true strain of at least 0. 5. Alternately, the material may be forged below the gamma prime solvus temperature with intermediate super solvus anneals. The overaged material is then worked at a temperature below the gamma prime solvus. The resultant fine grain material is then heat treated or can be further isothermally forged prior to heat treatment to produce complex shapes.

5223053, Jun 29, 1993

Jan 27, 1992

7/828542

Fred P. Cone - Jupiter FL
John A. Miller - Jupiter FL
Brendan J. Cryns - Shorewood WI
Robert Zanoni - Milwaukee WI

United Technologies Corporation - Hartford CT

C21D 800

148624

A process for strengthening heavy, thick-section forgings of precipitation age hardenable iron base superalloys. The process includes initial recrystallization to achieve a uniform grain size, intermediate temperature warm working at controlled strain rates and for limited amounts of deformation, and precipitation heat treating. The controlled warm working conditions avoid further recrystallization, thus preserving the strain hardening which improves the mechanical properties.

5527403, Jun 18, 1996

Jul 27, 1995

8/507875

John J. Schirra - Guilford CT
John A. Miller - Jupiter FL
Robert W. Hatala - South Windsor CT

United Technologies Corporation - Hartford CT

C22F 110

148675

A method of heat treating articles cast of a superalloy, comprising a nickel-base alloy capable of forming a chromium carbide precipitate, such as INCONEL 939. TM. The method includes selective heating of the article to cause chromium and carbon nuclei in the lattice of the crystals in the superalloy to go into solution, and selective cooling of the article to cause the formation of discrete chromium carbide nuclei along the grain boundary of the crystals. Additional heating steps may be performed to enhance the size of the chromium carbide nuclei. Articles so treated have improved mechanical properties.

4608094, Aug 26, 1986

Dec 18, 1984

6/682968

John A. Miller - Jupiter FL
Roy L. Athey - North Palm Beach FL

United Technologies Corporation - Hartford CT

C22F 110

148 115N

A method is described for producing metallic articles, especially turbine disks, which have a hot-worked structure in one region and a warmworked structure in another region and thereby have properties which differ in different regions. The method comprises an initial hot-working step, an intermediate heat treatment step and a final warm-working step.

5120373, Jun 9, 1992

Apr 15, 1991

7/685580

John A. Miller - Jupiter FL
Daniel F. Paulonis - Higganum CT
Paul D. Genereux - Cromwell CT
Jeffery W. Samuelson - Jupiter FL
Laurence A. Jackman - Monroe NC
Frederick P. Vaccaro - Waxhaw NC
William M. Thomas - Monroe NC

United Technologies Corporation - Hartford CT
Teledyne Industries, Inc. - Los Angeles CA

C22F 110

148564

A process for producing a fine grain forged superalloy article having a high yield strength at intermediate temperatures. A preferred starting composition comprises, by weight, 15% Cr, 13. 6% Co, 4. 1% Mo, 4. 6% Ti, 2. 2% Al, 0. 01% C, 0. 007% B, 0. 07% Zr, balance Ni. This material is forged at a temperature above the gamma prime solvus and at a true strain of at least 0. 5. Alternately, the material may be forged below the gamma prime solvus temperature with intermediate super solvus anneals. The overaged material is then worked at a temperature below the gamma prime solvus. The resultant fine grain material is then heat treated or can be further isothermally forged prior to heat treatment to produce complex shapes.