JACK R MARTIN
Engineering in Bedford, MA

5182855, Feb 2, 1993

Dec 13, 1990

7/627161

Jack R. Martin - Bedford MA

General Electric Company - Cincinnati OH

B23P 1502

2988922

A method of manufacturing a turbine nozzle for obtaining a predetermined value of throat area between adjacent ones of nozzle vanes includes providing a first vane, providing a datum for locating the first vane relative to an adjacent vane in the turbine nozzle, and fixturing the first vane relative to the datum for providing a trailing edge nest having six supports for predeterminedly locating the first vane relative to the adjacent vane. The trailing edge nest includes four trailing edge supports for locating the vane trailing edge to define a hinge axis extending along the trailing edge about which the vane is rotatable. A radial support radially locates the vane, and a throat support predeterminedly locates the vane about the hinge axis for obtaining the predetermined value of the throat area.

4363602, Dec 14, 1982

Feb 27, 1980

6/125063

Jack R. Martin - Bedford MA

General Electric Company - Lynn MA

F01D 534

416230

An integral composite airfoil and disc assembly for use in a turbomachine is provided wherein the assembly includes an airfoil portion having a plurality of axially adjacent first filaments extending in a first direction. The assembly further includes a hub portion having at least one second filament extending in a second direction and a matrix material dispersed between filaments of the first plurality and the second filament. The first and second filaments are disposed so as to extend in the direction of principal stress in the airfoil and disc portions respectively.

4088422, May 9, 1978

Oct 1, 1976

5/728525

Jack R. Martin - Bedford MA

General Electric Company - Lynn MA

F01D 506

416198A

An interstage spacer for the turbine section of a gas turbine engine is provided with a flexible bellows which absorbs axial growth of the adjacent turbine stages to prevent seizing and binding.

5174715, Dec 29, 1992

Oct 31, 1991

7/785677

Jack R. Martin - Bedford MA

General Electric Company - Cincinnati OH

F01D 102

4152094

A method of manufacturing a turbine nozzle for obtaining a predetermined value of throat area between adjacent ones of nozzle vanes is disclosed. The method includes providing a first vane, providing a datum for locating the first vane relative to an adjacent vane in the turbine nozzle, and fixturing the first vane relative to the datum for providing a trailing edge nest having six supports for predeterminedly locating the first vane relative to the adjacent vane. The trailing edge nest includes four trailing edge supports for locating the vane trailing edge to define a hinge axis extending along the trailing edge about which the vane is rotatable. A radial support radially locates the vane, and a throat support predeterminedly locates the vane about the hinge axis for obtaining the predetermined value of the throat area.

4682935, Jul 28, 1987

Dec 12, 1983

6/560718

Jack R. Martin - Bedford MA

General Electric Company - Lynn MA

F01D 512

416223A

The invention comprises a blade for a gas turbine engine including an airfoil portion having a non-linear stacking axis which is effective for generating a compressive component of bending stress due to centrifugal force acting on the blade. The compressive component of bending stress is provided in a life-limiting section of the blade, which, for example, includes trailing and leading edges of the blade. Inasmuch as the stacking axis, which represents the locus of centers of gravity of transverse sections of an airfoil portion of the blade, is non-linear, an increased amount of a compressive component of bending stress can be generated at a life-limiting section between root and tip sections of the blade without substantially increasing bending stress at the root of the blade.