1
James A Martus, Paul P Mehta, Seetharamaiah Mannava: Method for making or repairing a gas turbine engine component. General Electric Company, Charles L Moore Jr, Jerome C Squillaro, June 8, 1993: US05216808 (62 worldwide citation)

A method for making or repairing a gas turbine engine component includes the step of directing a pulsed ultra-violet laser beam on a location of a film cooling hole after application of a thermal barrier coating to athermally remove any coating material which may be obstructing the cooling hole with ...


2
Christopher C Glynn, Paul S Wilson, James A Martus, Clay K Carlson: Low cost airfoil cooling circuit with sidewall impingement cooling chambers. General Electric Company, Andrew C Hess, Rodney M Young, March 27, 2001: US06206638 (58 worldwide citation)

A gas turbine engine airfoil includes an airfoil outer wall having widthwise spaced apart pressure and suction sidewall sections extending chordally between leading and trailing edges of the airfoil and extending longitudinally from a base to a tip. Inside the airfoil is at least one internal coolin ...


3
Joseph W Savage, Ely E Halila, Robert J Orlando, Valentine R Boehm Jr, James A Martus, Thomas T Wallace, Monty L Shelton: Variable area turbine nozzle. General Electric Company, Andrew C Hess, David L Narciso, August 3, 1999: US05931636 (35 worldwide citation)

A variable area turbine nozzle includes a plurality of circumferentially adjoining nozzle segments. Each nozzle segment includes outer and inner bands, with a plurality of first vane segments fixedly joined therebetween. A plurality of second vane segments adjoin respective ones of the first vane se ...


4
Nicholas Damlis, James A Martus, Edward H Goldman: Impingement cooled airfoil with bonding foil insert. General Electric Company, Jerome C Squillaro, November 9, 1993: US05259730 (29 worldwide citation)

An impinqement cooled airfoil is fabricated by diffusion bonding a pair of airfoil half-sections together using an insert which is prefabricated from diffusion bonding foil. The insert is perforated so as to act as an impingement baffle. Axially-extending ribs may be formed on the internal walls of ...


5
Nicholas Damlis, James A Martus, Edward H Goldman: Photoetched cooling slots for diffusion bonded airfoils. General Electric Company, Jerome C Squillaro, January 5, 1993: US05176499 (26 worldwide citation)

Cooling passages are accurately formed along the faying surfaces of a pair of diffusion bonded members such as a pair of half sections used to fabricate an airfoil. A particularly advantageous application of the invention is the photoetching of cooling air grooves into the opposed surfaces of a diff ...


6
Nicholas Damlis, Anne M Isburgh, James A Martus, Edward H Goldman: Bonded turbine airfuel with floating wall cooling insert. General Electric Company, Andrew C Hess, Patrick R Scanlon, May 14, 1996: US05516260 (25 worldwide citation)

A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with a radially extending airfoil having an outer wall surrounding at least one radially extending cavity and extending chordwise through at least a portion of the airfoil. The outer wall has ribs ...


7
Ely E Halila, Michael Anderson, James A Martus: Method for providing concentricity of pilot fuel assembly in a combustor. General Electric Company, William Scott Andes, Patrick R Scanlon, Pierce Atwood, April 29, 2003: US06553769 (2 worldwide citation)

Concentric installation of a pilot fuel assembly in an opening in a gas turbine combustor casing is achieved by providing a boss having at least two flat surfaces which are perpendicular to each other on the combustor casing surrounding the opening and a mounting flange having at least two flat surf ...


8
Ely E Halila, Michael Anderson, James A Martus: Method for providing concentricity of pilot fuel assembly in a combustor. General Electric Company, General Electric Company, Andrew C Hess, October 17, 2002: US20020148230-A1

Concentric installation of a pilot fuel assembly in an opening in a gas turbine combustor casing is achieved by providing a boss having at least two flat surfaces which are perpendicular to each other on the combustor casing surrounding the opening and a mounting flange having at least two flat surf ...