Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.

Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Abstract: A gas turbine engine exhaust system comprises an instrumented exhaust duct including a set of exhaust temperature probes installed at the exhaust end of the duct in an air space between the engine outer case and a surrounding engine nacelle. A shield is removably installed at the end of the exhaust duct to protect the probes and associated wiring in the air space.

Abstract: A gas turbine engine exhaust system comprises an instrumented exhaust duct including a set of exhaust temperature probes installed at the exhaust end of the duct in an air space between the engine outer case and a surrounding engine nacelle. A shield is removably installed at the end of the exhaust duct to protect the probes and associated wiring in the air space.

Abstract: An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.

Abstract: This invention encompasses near-real-time processing of astronomical images for viewing on a computer. This image processing method is preferably integrated with the control of an astronomical observatory. The subject invention thus includes an Internet-based system that provides a virtual experience of an astronomical observatory. The subject invention preferably uses an unmanned astronomical observatory to observe galaxies, nebulae, stars, etc. The observatory produces color images suitable for viewing on a computer monitor. These images are delivered to users across the Internet using web browser-based software.

Abstract: A method and an apparatus for playing a ball game are disclosed. The game involves a customized bat and a ball. The ball is uniquely designed to overcome typical obstacles of bat and ball games, allowing players to hit and pitch the ball in a variety of new ways. The object of the game is to score more points than the opposition by using the bat to hit the ball past a set of designated landmarks on a field in order to score.

Abstract: This invention encompasses near-real-time processing of astronomical images for viewing on a computer. This image processing method is preferably integrated with the control of an astronomical observatory. The subject invention thus includes an Internet-based system that provides a virtual experience of an astronomical observatory. The subject invention preferably uses an unmanned astronomical observatory to observe galaxies, nebulae, stars, etc. The observatory produces color images suitable for viewing on a computer monitor. These images are delivered to users across the Internet using web browser-based software.