MARTIN C HEMSWORTH
Engineering in Cincinnati, OH

6464461, Oct 15, 2002

Dec 8, 2000

09/731982

Ian David Wilson - Mauldin SC
Kevin Joseph Barb - Halfmoon NY
Ming Cheng Li - Cincinnati OH
Susan Marie Hyde - Schenectady NY
Thomas Charles Mashey - Coxsackie NY
Ronald Richard Wesorick - Albany NY
Christopher Charles Glynn - Hamilton OH
Martin C. Hemsworth - Cincinnati OH

General Electric Company - Schenectady NY

F01D 508

416 96R, 415116, 415134, 285205

The steam cooling circuit for a gas turbine includes a bore tube assembly supplying steam to circumferentially spaced radial tubes coupled to supply elbows for transitioning the radial steam flow in an axial direction along steam supply tubes adjacent the rim of the rotor. The supply tubes supply steam to circumferentially spaced manifold segments located on the aft side of the - spacer for supplying steam to the buckets of the first and second stages. Spent return steam from these buckets flows to a plurality of circumferentially spaced return manifold segments disposed on the forward face of the - spacer. Crossover tubes couple the steam supply from the steam supply manifold segments through the - spacer to the buckets of the first stage. Crossover tubes through the - spacer also return steam from the buckets of the second stage to the return manifold segments. Axially extending return tubes convey spent cooling steam from the return manifold segments to radial tubes via return elbows.

4087199, May 2, 1978

Nov 22, 1976

5/743616

Martin C. Hemsworth - Cincinnati OH
Robert J. Corsmeier - Cincinnati OH
Ambrose A. Hauser - Wyoming OH

General Electric Company - Cincinnati OH

F01D 1108

415174

A high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring. The blocks are supported by a pair of annular support members which retain the blocks in the assembly. Spring-like fingers associated with the support members apply a preloaded force against a pair of slanted dovetail surfaces on the blocks to force the blocks against rigid stops formed upon the annular support members, thereby establishing their proper radial position within the assembly. The preload applied by the fingers accommodates the thermal expansion differences between the ceramic blocks and the metallic support members. In an alternative embodiment, the blocks are retained between cooperating rigid legs extending from the annular support members and wedged radially inwardly into position by a preloaded spring contacting the back side of the blocks. Heat transfer between the blocks and metallic support members is minimized by providing point or line contact between components, thus reducing the contact area available for heat conduction.

4289447, Sep 15, 1981

Oct 12, 1979

6/084244

Albert P. Sterman - Cincinnati OH
Charles H. Gay - Loveland OH
Frederick W. Tegarden - Cincinnati OH
Dean T. Lenahan - Cincinnati OH
Martin C. Hemsworth - Cincinnati OH

General Electric Company - Cincinnati OH

F01D 2524, B32B 300

415200

A turbine shroud includes a ceramic sealing layer secured to a metal substrate. In one form, the metal substrate includes a plurality of pegs extending therefrom. Intermediate bonding layers are disposed on the peg-metal substrate structure. A ceramic sealing layer of zirconium oxide with about 20 weight percentage magnesium oxide is disposed, e. g. , plasma sprayed, on the intermediate bonding layers. The ceramic sealing layer includes an ordered pattern of very fine cracks therein which reduce the thermal stress in the ceramic sealing layer. A method of constructing a turbine shroud structure is also disclosed.

RE34207, Mar 30, 1993

Feb 26, 1991

7/660459

Joey L. Nelson - Cincinnati OH
Sidney B. Elston - Cincinnati OH
Wu-Yang Tseng - West Chester OH
Martin C. Hemsworth - Cincinnati OH

General Electric Company - Cincinnati OH

F01D 514

416226

A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.

4971641, Nov 20, 1990

Mar 1, 1990

7/490506

Joey L. Nelson - Cincinnati OH
Sidney B. Elston - Marblehead MA
Wu-Yang Tseng - West Chester OH
Martin C. Hemsworth - Cincinnati OH

General Electric Company - Cincinnati OH

B32B 3112, B32B 3114

156064

An aircraft propeller blade is constructed by forming two shells of composite material laminates and bonding the two shells to a metallic spar with foam filler pieces interposed between the shells at desired locations. The blade is then balanced radially and chordwise.

4784575, Nov 15, 1988

Feb 12, 1988

7/157179

Joey L. Nelson - Cincinnati OH
Sidney B. Elston - Marbelhead MA
Wu-Yang Tseng - West Chester OH
Martin C. Hemsworth - Cincinnati OH

General Electric Company - Cincinnati OH

F01D 514

416226

A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.

5197857, Mar 30, 1993

Jun 6, 1991

7/710989

Christopher C. Glynn - Hamilton OH
Martin C. Hemsworth - Cincinnati OH

General Electric Company - Cincinnati OH

B63H 120, B63H 500

416204A

A rotor assembly for supporting rotor blades includes a plurality of axially adjoining discrete disks each having a rim, web, and hub. The rims include axial dovetail grooves for collectively supporting a respective blade dovetail therein. Each of the disks includes at least one axially extending annular arm joined integrally with the disk and fixedly joined to an adjacent one of the arms. The disks are fixedly joined together solely by the blade dovetails in the rim dovetail grooves and by the arms so that upon a crack failure of one of the disks, centrifugal load from the failed disk is transferred to an adjacent disk.

5853285, Dec 29, 1998

Jun 11, 1997

8/872840

Frederick Martin Miller - Cincinnati OH
Roger Clayton Walker - Middletown OH
Christopher Charles Glynn - Hamilton OH
Martin C. Hemsworth - Cincinnati OH

General Electric Co. - Schenectady NY

F01D 508, F01D 510

416 96R

In a compressor rotor assembly including a plurality of rotor disks affixed to a rotor body, and wherein at least one radially directed cooling tube is supported from a radially outer end within a rotor shaft, with an opposite, radially inner free end extending toward a longitudinal axis of the rotor, an improvement comprising a ring member loosely secured to the tube at the free end.

4606699, Aug 19, 1986

Feb 6, 1984

6/577397

Martin C. Hemsworth - Cincinnati OH

General Electric Company - Cincinnati OH

F01D 1108

415170R

A means for improving the aerodynamic efficiency of the compressor of an axial flow turbomachine is disclosed. The compressor includes a first airfoil relatively rotatable with respect to a radially disposed surface and a second airfoil, aft of the first airfoil, and fixed with respect to the surface. The surface bounds a flowpath for aft moving fluid. The surface has a circumferentially extending recess radially disposed relative to the airfoils. The recess has a generally aft facing wall, a generally axially directed wall, and a generally forward facing wall. The aft facing wall is oriented so as to provide a barrier to the forward flow of fluid in the clearance between airfoil and surface. The forward facing wall is oriented so as to provide an aerodynamically smooth transition from the recess into the flowpath.

5593274, Jan 14, 1997

Mar 31, 1995

8/414695

Diether E. Carreno - Schenectady NY
Albert Myers - Amsterdam NY
Gene D. Palmer - Clifton Park NY
Philip M. Caruso - Selkirk NY
Ian D. Wilson - Clifton Park NY
Martin C. Hemsworth - Cincinnati OH

General Electric Co. - Schenectady NY

F01D 508, F01D 506

415115

A rotor cooling circuit includes a cooling medium supply reservoir for supplying cooling medium to a plurality of axial passages through the turbine wheel and spacer disc rims. A passageway communicates cooling medium from the reservoir for flow in series and in a serpentine manner in and about the cavities between the wheels and discs. The flows are reunited at a plenum for flowing the cooling medium into first and second stage buckets. Return passages through the rims of the wheels and spacer discs return spent cooling medium from the buckets to a return location external of the rotor. Transition elements between the buckets and spacer plates in the rotor rim accommodate any thermal mismatch between the adjoining buckets and spacer plates to prevent cooling medium leakage at the joints.