Thomas C Joseph

US Patent:

52753573, Jan 4, 1994

Filed:

Jan 16, 1992

Appl. No.:

7/821376

Inventors:

Laurence Seelen - Cincinnati OH
Thomas P. Joseph - West Chester OH
James E. Cencula - Middletown OH
Donald L. Bellia - West Chester OH
Hahn M. Spofford - West Chester OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B64D 2700
F02C 720

US Classification:

244 54

Abstract:

An aircraft engine mount includes a frame fixedly joined in a gas turbine engine and a platform fixedly joined to an aircraft wing or tail pylon. A first beam is pivotally joined to the frame and the platform at first and second joints, respectively. The first beam is additionally joined to the platform at a third joint which allows longitudinal movement between the first beam and the platform at the third joint while preventing rotation of the first beam. A second beam is spaced from the first beam and is pivotally joined to the frame and platform at fourth and fifth joints, respectively, and is additionally joined to the platform at a sixth joint for allowing limited rotation of the second beam during normal operation while preventing rotation of the second beam upon a failure of the first beam to carry load.

US Patent:

53203070, Jun 14, 1994

Filed:

Mar 25, 1992

Appl. No.:

7/857136

Inventors:

Hahn M. Spofford - West Chester OH
Thomas G. Wakeman - Lawrenceburg IN
Donald L. Bellia - West Chester OH
Thomas P. Joseph - West Chester OH
Gregg H. Wilson - Cincinnati OH
James E. Cencula - Middletown OH
Frederick W. Tegarden - Glendale OH
Michael H. Schneider - Loveland OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

F02C 720

US Classification:

244 54

Abstract:

An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart clevises and a center clevis therebetween. The center clevis is pivotally joined to a center of the lever for carrying thrust force from the first frame through both thrust links and to the platform and pylon during normal operation. A pair of pins pivotally join the thrust links to the lever and extend through apertures in the platform first and second clevises to define predetermined gaps therebetween for allowing the lever to rotate relative to the platform center clevis up to a predetermined angular rotation. In a failure mode of operation the pins contact the platform first and second clevises for transmitting thereto either tension or compression thrust loads for providing an alternate failsafe loadpath. In a preferred embodiment, the platform further includes an aft mount joined to an engine second frame spaced aft of the engine first frame.

US Patent:

52773825, Jan 11, 1994

Filed:

Oct 13, 1992

Appl. No.:

7/959885

Inventors:

Laurence Seelen - Cincinnati OH
Thomas P. Joseph - West Chester OH
Hahn M. Spofford - West Chester OH
Charles S. Orkiszewski - Cincinnati OH

Assignee:

General Electric Company - Cincinnati OH

International Classification:

B64D 2700

US Classification:

244 54

Abstract:

An aircraft engine mount includes an annular casing fixedly disposed in the engine, a mounting platform spaced radially outwardly from the casing and fixedly joinable to an aircraft pylon, and a pair of circumferentially spaced apart links pivotally joined to the platform and the casing at respective radially outer and inner joints. The inner joints are circumferentially spaced closer together than the outer joints so that the intersection point of the longitudinal axes of the two links is disposed radially below the two links themselves for reducing lateral deflection of the casing relative to the engine mount.

US Patent:

20210354838, Nov 18, 2021

Filed:

May 15, 2020

Appl. No.:

16/875662

Inventors:

- Schenectady NY, US
Thomas P. Joseph - West Chester OH, US
Jonathan E. Coleman - Mason OH, US
Anthony M. Metz - Harrison OH, US
Stefan K. Fox - Symmes Township OH, US

International Classification:

B64D 27/26
F02K 3/06

Abstract:

Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.

US Patent:

20210324905, Oct 21, 2021

Filed:

Apr 16, 2020

Appl. No.:

16/850865

Inventors:

- Schenectady NY, US
Thomas P. Joseph - West Chester OH, US
Anthony M. Metz - Harrison OH, US
Jonathan E. Coleman - Mason OH, US

International Classification:

F16C 11/06

Abstract:

Bearings with visually distinct wear indicators are disclosed. An example bearing disclosed herein includes a movable portion, a race to receive the movable portion along a first surface to thereby permit movement of the movable portion within the race, and a liner disposed on the first surface of the race, the liner having a first layer and a second layer, the first layer disposed on top of the second layer, the first layer visually distinctive from the second layer.

US Patent:

20210300577, Sep 30, 2021

Filed:

Mar 31, 2020

Appl. No.:

16/836442

Inventors:

- Schenectady NY, US
Timothy L. Schelfaut - Lebanon OH, US
Anthony M. Metz - Harrison OH, US
Thomas P. Joseph - West Chester OH, US
Mahesh Khandeparker - Bengaluru, IN
Kudum Shinde - Bengaluru, IN
Donald L. Gardner - West Chester OH, US

International Classification:

B64D 27/26
F02K 3/06

Abstract:

Methods, apparatus, systems and articles of manufacture are disclosed. A mechanical linkage for mounting a gas turbine engine to a pylon includes: a bending restraint having a first end and a second end; a first joint at the first end of the bending restraint to connect the first end of the bending restraint to a fan section of the gas turbine engine; and a second joint at the second end of the bending restraint to connect the second end of the bending restraint to the pylon.