The United States of America as represented by the Secretary of the Air Force - Washington DC
International Classification:
F02C 3045
US Classification:
60 3943, 415 79
Abstract:
A gas turbine engine structure is described wherein the compressor region and the turbine region of the engine are disposed substantially concentrically of each other between fixed inner and outer casings, with the combustor disposed at one common end of the compressor and turbine, and wherein the rotor components of the engine include one or more rings, bands, housings or casings with the turbine blades and compressor blades mounted respectively on the inner and outer surface thereof, and wherein the compressor and turbine stator components are mounted respectively on the inner surface of the outer casing and the outer surface of the inner casing, or, alternatively, wherein the turbine and compressor stator components are mounted respectively on the inner surface of the outer casing and the outer surface of the inner casing, which structure geometries eliminate much of the weight associated with the disks and interconnecting shafts that characterize conventional engines.
Curved Laser Sheet For Conformal Optical Diagnostics
Jordi Estevadeordal - Saratoga Springs NY, US Christopher Marks - Waynesville OH, US Rolf Sondergaard - Beavercreek OH, US James M. Wolff - Huber Heights OH, US
Assignee:
The United States of America as represented by the Secretary of the Air Force - Washington DC
International Classification:
G01P 3/36
US Classification:
356 28, 356 285
Abstract:
Three-dimensional surface illumination using curved laser sheets is described for optical flow measurements over conformal curved surfaces. The illumination method is applicable to many different optical-based flow visualization and measurement techniques, particularly for particle image velocimetry. An alignment sheet increases the accuracy of determining the position and movement of particles used in optical-base fluid flow techniques.
Christopher G. Murawski - Beavercreek OH Rolf Sondergaard - Fairborn OH
Assignee:
The United States of America as represented by the Secretary of the Air Force - Washington DC
International Classification:
F01D 500
US Classification:
416 23
Abstract:
A turbine blade having an extensible tail is described. The extensible tail is selectively positionable during engine operation, enabling fine-tuning for maximum power and efficiency during engine operation. During periods of operation exhibiting low Reynolds number flows, the extensible tail is projected out from the trailing edge of the turbine blade, into the gas path. As Reynolds number flows increase, the extensible tail is retracted back into the turbine blade, maximizing turbine engine efficiency.
Air Force Research Laboratory Jan 1993 - Jan 2015
Engineer
Air Force Research Laboratory Jan 1993 - Jan 2015
Chief, Turbomachinery Branch, Turbine Engine Division
Wright State University Jan 1993 - Jan 2015
Associate Professor
United States Air Force Jan 1993 - Jan 2015
Research Engineer
Education:
Stanford University 1989 - 1993
Doctorates, Doctor of Philosophy
Stanford University 1987 - 1989
Master of Science, Masters
Caltech 1983 - 1987
Bachelors, Bachelor of Science, Engineering