Abstract: Aspects of the present invention relate to systems and methods of a vane design utilizing welding techniques. The present invention concerns a method for preventing cracking within a vane assembly utilizing full penetration welding. Additional embodiments concern a vane design that, when assembled with another vane, comprises an axial slot that prevents cracking within a vane assembly.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length. The increased surface area allows for a greater amount of air to be taken in by the airfoil, thus increasing the air flow through the gas turbine engine.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.

Abstract: A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length. The increased surface area allows for a greater amount of air to be taken in by the airfoil, thus increasing the air flow through the gas turbine engine.

Abstract: Aspects of the present invention relate to systems and methods of a vane design utilizing welding techniques. The present invention concerns a method for preventing cracking within a vane assembly utilizing full penetration welding. Additional embodiments concern a vane design that, when assembled with another vane, comprises an axial slot that prevents cracking within a vane assembly.

Abstract: A compressor component having an improved airfoil profile so as to eliminate previously known vibratory issues in the blade tip is disclosed. By altering the airfoil profile throughout its span, the natural frequency of the airfoil is altered so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.

Abstract: Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is disclosed. The vane platforms are configured so the joint between adjacent vanes is repositioned a sufficient distance away from the leading edge of the vane airfoil and the associated bow wave generated by the hot combustion gases passing over the airfoil leading edge.

Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.

Abstract: Disclosed are methods, compositions of matter, and kits useful for augmentation of homing and engraftment of stem, progenitor and mature cells through modification of cellular membrane properties following ex vivo treatment. The methods, compositions, and cells may be used for the treatment of a wide variety of disorders in which augmentation of cell trafficking, homing and engraftment is desired.

Abstract: A system for automatically planning, booking and calendaring travel arrangements includes a data storage device, a booking engine, an output device and a processor. Maintained in the storage device is a database of user profile information. The processor receives a travel request input including travel request data gathered from a user's calendar application. The stored user profile information and the travel request data is used to automatically formulate a travel request in response to the travel request input. The travel request includes airline, hotel and rental car reservation information. A travel query file is automatically created from the travel request.

Abstract: The invention relates to an actuating apparatus (12) with automatic clearance adjustment for a vehicle hydraulic disk brake and includes a housing (14) having a base (16) and a shell (18) in which an open cylinder bore (20) is provided. For actuating the brake, a piston (24) is hydraulically displaceable in the bore. A mechanical actuating device for displacing the piston in the bore and for compensating lining wear comprises an expanding device (34) acting axially in a brake actuating direction and a length adjustable strut between the expanding device and the piston. The strut is formed by a first strut part (52) having a bolt shaped end, which is screwed into a second, substantially sleeve shaped strut part (54), which rests with a conical flange (68) against the piston. Between the bolt shaped end of the first strut part and the second strut part there is a cavity (90) which is to be filled with brake fluid and closed off in a fluid tight manner at one end.

Abstract: The invention relates to an actuating apparatus (12) with automatic clearance adjustment for a vehicle hydraulic disk brake and includes a housing (14) having a base (16) and a shell (18) in which an open cylinder bore (20) is provided. For actuating the brake, a piston (24) is hydraulically displaceable in the bore. A mechanical actuating device for displacing the piston in the bore and for compensating lining wear comprises an expanding device (34) acting axially in a brake actuating direction and a length adjustable strut between the expanding device and the piston. The strut is formed by a first strut part (52) having a bolt shaped end, which is screwed into a second, substantially sleeve shaped strut part (54), which rests with a conical flange (68) against the piston. Between the bolt shaped end of the first strut part and the second strut part there is a cavity (90) which is to be filled with brake fluid and closed off in a fluid tight manner at one end.