1
Craig Allen
Massimiliano Mariotti, Craig Allen Bielek, Michele D Ercole, Luciano Mei: Turbine inlet guide vane with scalloped platform and related method. Nuovo Pignone S p A, GE Global Patent Operation, November 20, 2012: US08313291 (1 worldwide citation)

A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engin ...


2
Craig Allen
Massimiliano Mariotti, Craig Allen Bielek, Michele D Ercole, Luciano Mei: Turbine inlet guide vane with scalloped platform and related method. General Electric Company, GE Global Patent Operation, June 25, 2009: US20090162193-A1

A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engin ...


3
George L Minott, Jonathan C Plimpton: Fiber optic linked flame sensor. Meggitt Avionics, Lorusso & Loud, October 27, 1998: US05828797 (191 worldwide citation)

A fiber optic linked flame sensor for continuous optical monitoring of the combustion process within the combustion chamber of a gas turbine engine. The system includes a high temperature optical probe, a fiber optic cable, and electro-optics module. The high temperature probe is mounted on the engi ...


4
Jorge F Seda, Lawrence W Dunbar, Philip R Gliebe, Peter N Szucs, John C Brauer, James E Johnson, Thomas Moniz, Gregory T Steinmetz: Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors. General Electric Company, Nathan D Herkamp, Steven J Rosen, September 16, 2003: US06619030 (190 worldwide citation)

An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axia ...


5
Paul W Duesler, Constantino V Loffredo, Harold T Prosser Jr, Christopher W Jones: Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems. United Technologies Corporation, Kenneth C Baran, July 14, 1998: US05778659 (178 worldwide citation)

A gas turbine engine (10) includes a translating sleeve (38) disposed within a downstream portion of an outer nacelle (20). A variable area fan exhaust nozzle (30) is defined between the trailing edge (32) of the translating sleeve (38) and a conical core cowl (26) disposed radially inwardly of the ...


6
Gaudencio A Labrador: Scavenger energy converter system its new applications and its control systems. December 11, 2001: US06327994 (149 worldwide citation)

What has been invented is a series of scientific applications of the wideface energy converter device, be it in the form of a wideface solar heat receiver or a wideface fluid impeder device. The wider is the solar heat receiver, the more solar power is available for conversion. The wider is the sail ...


7
Edmund Emil Striebel, Theodore Richard Koblish, Thomas Joseph Madden, Roger Halsted James: Premix combustor. United Technologies Corporation, Robert C Walker, July 18, 1978: US04100733 (143 worldwide citation)

Apparatus for supplying fuel to the combustion chamber of a gas turbine engine is disclosed. Techniques for increasing combustion efficiency and for decreasing the percentage of noxious emissions in the effluent from the chamber are developed. Axially extending tubes are used extensively in the disc ...


8
Alexander A Belokon, George L Touchton: Recuperated gas turbine engine system and method employing catalytic combustion. MES International, Alston & Bird, March 7, 2006: US07007487 (137 worldwide citation)

A recuperated gas turbine engine system and associated method employing catalytic combustion, wherein the combustor inlet temperature can be controlled to remain above the minimum required catalyst operating temperature at a wide range of operating conditions from full-load to part-load and from hot ...


9
Joseph L Bernier, Peter W Kamber: Real time performance monitoring of gas turbine engines. The Boeing Company, Christensen O Connor Johnson & Kindness, July 29, 1980: US04215412 (136 worldwide citation)

A real-time gas turbine engine monitoring system is disclosed which includes a digital processor that utilizes a set of scalar coefficients and the current value of various engine operating parameters to predict the current value of a set of engine performance parameters. The actual values of these ...


10
Alan R Stuart: High bypass ratio counterrotating turbofan engine. General Electric Company, Derek P Lawrence, December 13, 1988: US04790133 (134 worldwide citation)

A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and ...