United Technologies Corporation

The United States of America As Represented by the Administrator of the

John J Marra

Gregory E Chetta

Donna R Dickerson

A method and system for designing a low pressure turbine shaft comprising the steps of creating a low pressure turbine shaft knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of a low pressure turbine shaft, wherein the knowledge base comprises at least one data value signal for each one of the plurality of design rule signals. The steps also include entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the low pressure turbine shaft and comparing the entered desired data value signal for the selected one of the plurality of parameters with the corresponding at least one data value signal in the knowledge base for the corresponding one of the plurality of design rule signals. If the result of the step of comparing is such that the entered desired data value signal for the selected one of the plurality of parameter signals is determined to have a first predetermined relationship with respect to the corresponding at least one data value signal in the knowledge base for the selected one of the plurality of design rule signals, create signals representative of a geometric representation of the selected one of the plurality of parameter signals of the associated element of the low pressure turbine shaft.

Method and system for designing a low pressure turbine shaft

A method and a system for designing a spline coupling, comprising the steps of creating signals representing a spline coupling knowledge base of information having a plurality of rule signals with respect to a corresponding plurality of parameter signals of associated elements of the spline coupling, wherein the spline coupling knowledge base comprises at least one data value signal for each one of the plurality of rule signals. Included are the steps of entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the spline coupling, and comparing the entered desired data value signal for the selected one of the plurality of parameter signals with the corresponding at least one data value signal in the spline coupling knowledge base for the corresponding one of the plurality of rule signals. The steps also include creating signals representative of a geometric representation of the selected one of the plurality of parameter signals of the associated element of the spline coupling if the result of the step of comparing is such that the entered desired data value signal for the selected one of the plurality of parameter signals is determined to have a first predetermined relationship with respect to the corresponding at least one data value signal in the spline coupling knowledge base for the selected one of the plurality of rule signals.

Method and system for designing a spline coupling

The invention is directed to a damper ring for damping the natural vibration of the rotor blades of an integrally bladed rocket turbine rotor. The invention consists of an integral damper ring which is fixed to the underside of the rotor blade platform of a turbine rotor. The damper ring includes integral supports which extend radially outwardly therefrom. The supports are located adjacent the base portion and directly under each blade of the rotor. Vibration damping is accomplished by action of tuned mass damper beams attached at each end to the supports. These beams vibrate at a predetermined frequency during operation. The vibration of the beams enforce a local node of zero vibratory amplitude at the interface between the supports and the beam. The vibration of the beams create forces upon the supports which forces are transmitted through the rotor blade mounting platform to the base of each rotor blade. When these forces attain a predetermined design frequency and magnitude and are directed to the base of the rotor blades, vibration of the rotor blades is effectively counteracted.

Tuned mass damper for integrally bladed turbine rotor

A casing around a turbine and a casing around discharge nozzles have a concentrically arranged shell portion. The seal contains internal pressure while accommodating eccentric, expansion and axial travel. Arcuate seal segments have one leg sealing against a radial surface extending from the inner shell and the other leg against the outer shell. A linkage guides travel of the segments.

Seal accommodating thermal expansion between adjacent casings in gas

A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the assembly balance of the rotor. A snap ring (44) retains the weights within the openings. An eccentric inwardly extending raised area 26 throughout a substantial minority of the circumference provides for initial gross unbalance correction upon installation.

Method of balancing a rotor

A balance ring (18) which is shrunk fit within each disk (12) of a rotor is selectively ground for detail balance. A plurality of openings (20) through the outer edge of the balance ring receive weights during the assembly balance of the rotor. A snap ring (44) retains the weights within the openings. An eccentric inwardly extending raised area (26) throughout a substantial minority of the circumference provides for initial gross unbalance correction upon installation.

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Jupiter, FL, United States of America

John J Marra