Jay T Lane, 624175 S Lake Orlando Pkwy, Orlando, FL 32808

6514046, Feb 4, 2003

Sep 29, 2000

09/677044

Jay A. Morrison - Oviedo FL
Gary B. Merrill - Monroeville PA
Jay E. Lane - Murrysville PA
Christian X. Campbell - Orlando FL
Daniel G. Thompson - Pittsburgh PA
Eric V. Carelli - Greensburg PA
Christine Taut - Essen, DE

Siemens Westinghouse Power Corporation - Orlando FL

F01D 518

416229A, 416241 B

A vane assembly for a turbine assembly includes an inner endcap, an outer endcap, and a body. The body includes a metallic core assembly, a ceramic shell assembly and a support assembly. The metallic core assembly is coupled to the inner and outer endcaps and bears most of the mechanical loads, including aerodynamic loads. The ceramic shell bears substantially all of the thermal stress placed on the vane assembly. The support assembly is disposed between the metallic core assembly and said ceramic shell assembly and is coupled to the metallic core assembly.

6528190, Mar 4, 2003

Aug 2, 2000

09/631097

Christian X. Campbell - Orlando FL
Jay E. Lane - Murrysville PA

Siemens Westinghouse Power Corporation - Orlando FL

B32B 900

428701, 428702, 4282934, 4282941, 428332

A composite ( ) has a matrix ( ), preferably of ceramic, interspersed with reinforcement structures ( ), preferably ceramic fibers, coated with a material ( ) selected from ZrGeO , HfGeO and CeGeO , where the composite can be used as a component in high temperature turbines.

6709230, Mar 23, 2004

May 31, 2002

10/158946

Jay A. Morrison - Ovledo FL
Chris Campbell - Orlando FL
Gary Brian Merrill - Orlando FL
Jay Edgar Lane - Murrysville PA
Daniel George Thompson - Pittsburgh PA
Harry A. Albrecht - Hobe Sound FL
Yevgeniy P. Shteyman - West Palm Beach FL

Siemens Westinghouse Power Corporation - Orlando FL

F01D 904

415115, 415200, 416 97 R, 416 97 A, 416229 A, 416224, 416241 B

A hybrid vane ( ) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member ( ) bonded to a substantially solid core member ( ). The airfoil member and core member are cooled by a cooling fluid ( ) passing through cooling passages ( ) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond (( ) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation ( ) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.

6733907, May 11, 2004

Sep 26, 2001

09/963278

Jay A. Morrison - Oviedo FL
Michael A. Burke - Pittsburgh PA
Gary B. Merrill - Orlando FL
Jay E. Lane - Murrysville PA

Siemens Westinghouse Power Corporation - Orlando FL

B32B 900

428699, 428213, 428698, 428701, 428702, 428704, 428408, 416241 B

A hybrid ceramic structure ( ), for use in high temperature environments such as in gas turbines, is made from an insulating layer ( ) of porous ceramic that is thermally stable at temperatures up to 1700Â C. bonded to a high mechanical strength structural layer ( ) of denser ceramic that is thermally stable at temperatures up to 1200Â C. , where optional high temperature resistant adhesive ( ) can bond the layers together, where optional cooling ducts ( ) can be present in the structural layer and where hot gas ( ) can contact the insulating layer ( ) and cold gas ( ) can contact the structural layer ( ).

6884384, Apr 26, 2005

Sep 27, 2001

09/965558

Gary Brian Merrill - Orlando FL, US
Jay Edgar Lane - Murrysville PA, US
Curtis Gosik - Irwin PA, US

Siemens Westinghouse Power Corporation - Orlando FL

B28B001/26

264642, 264651, 264660

A method for making a thermal insulating material includes the steps of: providing a chamber, placing hollow geometric shapes in the chamber, closing the chamber, evacuating air from the chamber, feeding a slurry into an adjacent slurry chamber, pressurizing the slurry chamber and forcing the slurry in to the sphere chamber around the spheres against a fibrous material adjacent a side wall of the sphere chamber. The fibrous material allows capillary wicking of the liquid from the slurry around the spheres. Due to this pressure the spheres and slurry are semi dried into a green state. The material in its green state green is subsequently dried and fired to form the insulating material.

7001679, Feb 21, 2006

Aug 8, 2002

10/214785

Christian X. Campbell - Orlando FL, US
Jay E. Lane - Murrysville PA, US

Siemens Westinghouse Power Corporation - Orlando FL

B32B 9/00
C04B 35/51

428698, 4283122, 4283128, 428699, 428702, 428704, 501152

A xenotime phosphate protective overlayer () for protecting a ceramic material () from a high temperature, moisture-containing environment. Yttrium phosphate may be used as a protective overlayer to protect an underlying mullite layer to temperatures in excess of 1,500 C. The coating may have porosity of greater than 15% for improved thermal shock protection. To prevent the ingress of oxygen to an underlying ceramic non-oxide material, such as silicon carbide or silicon nitride, an oxygen barrier layer () is disposed between the xenotime phosphate coating and the non-oxide material. Such a protective overlayer may be used for an article having a ceramic matrix composite substrate.

7093359, Aug 22, 2006

Sep 17, 2002

10/245528

Jay A. Morrison - Oviedo FL, US
Gary Brian Merrill - Orlando FL, US
Jay Edgar Lane - Murrysville PA, US
Steven C. Butner - Poway CA, US
Harry A. Albrecht - Hobe Sound FL, US
Scott M. Widrig - Hobe Sound FL, US
Yevgeniy P. Shteyman - West Palm Beach FL, US

Siemens Westinghouse Power Corporation - Orlando FL

B21K 3/04
B21D 53/78
B23P 15/02

2988971, 2988972, 29889721, 29889722, 4282934, 264 35, 264257, 264259, 264267

A method of manufacturing a composite structure uses a layer of an insulating material () as a mold for forming a substrate of a ceramic matrix composite (CMC) material (). The insulating material may be formed in the shape of a cylinder () with the CMC material wound on an outer surface () of the cylinder to form a gas turbine combustor liner (). Alternatively, the insulating material may be formed in the shape of an airfoil section () with the CMC material formed on an inside surface () of the insulating material. The airfoil section may be formed of a plurality of halves () to facilitate the lay-up of the CMC material onto an easily accessible surface, with the halves then joined together to form the complete composite airfoil. In another embodiment, a box structure () defining a hot gas flow passage () is manufactured by forming insulating material in the shape of opposed airfoil halves () joined at respective opposed ends by platform members (). A layer of CMC material () is then formed on an outside surface of the insulating material.

7179524, Feb 20, 2007

Sep 19, 2003

10/667264

Gary B. Merrill - Orlando FL, US
Jay E. Lane - Murrysville PA, US
Steven C. Butner - San Marcos CA, US
Robert Kreutzer - Poway CA, US
Jay A. Morrison - Oviedo FL, US

Siemens Power Generation, Inc. - Orlando FL

B32B 3/00

4283137

A composite material () formed of a ceramic matrix composite (CMC) material () protected by a ceramic insulating material (). The constituent parts of the insulating material are selected to avoid degradation of the CMC material when the two layers are co-processed. The CMC material is processed to a predetermined state of shrinkage before wet insulating material is applied against the CMC material. The two materials are then co-fired together, with the relative amount of shrinkage between the two materials during the firing step being affected by the amount of pre-shrinkage of the CMC material during the bisque firing step. The shrinkage of the two materials during the co-firing step may be matched to minimize shrinkage stresses, or a predetermined amount of prestress between the materials may be achieved. An aluminum hydroxyl chloride binder material () may be used in the insulating material in order to avoid degradation of the fabric () of the CMC material during the co-firing step.