Abstract: Methods and systems of balancing a rotatable member are provided. A method includes separately balancing a first portion and a second portion of the rotatable member wherein the second portion mateable to said first portion, coupling the first and second portions to each other, measuring a physical dimension of the coupled first and second portions, and determining a balance weight magnitude and position based on the measured physical dimension.

Abstract: Vibration is monitored in a dual rotor engine. A first total vibration of the engine is measured during operation. Relative phase of the two rotors is then clocked, and a second total vibration of the engine is then measured during operation. First and second total unbalances are then resolved at a common response frequency from the measured total vibrations. First and second rotor unbalances are then resolved for the corresponding rotors from the first and second total unbalances. In a further method, corresponding corrective balance weights may be determined for offsetting the resolved rotor unbalances.

Abstract: Methods and systems for ordering blades in a rotatable machine is provided. The method includes receiving at least one geometric parameter measurement of each blade in a row of blades, determining a root sum squared value of a difference of a selected one of the received geometric parameter measurements between adjacent blades in the row of blades, determining a vector sum of a selected other one of the received geometric parameter measurements, determining a moment weight vector sum of each blade to be positioned on the rotor, and determining, using a computer, a sequence map of each blade using the root sum squared value of the difference of the geometric parameter measurement between adjacent blades in the row of blades, the vector sum of a selected other one of the received geometric parameter measurements, and the moment weight vector sum.

Abstract: A method for fabricating a fan assembly is provided, wherein the method includes providing a rotor having a plurality of rotor blades. At least one rotor blade is fabricated from a frangible material. The method also includes coupling a casing substantially circumferentially about the rotor, and positioning the casing a distance from the plurality of rotor blades. The distance is selected to facilitate increasing an amount of initial resistance created between the casing and the plurality of rotor blades after a bladeout.

Abstract: A method of assembling a gas turbine engine includes providing at least one blade assembly. The method also includes forming at least one blade tip fuse within at least a portion of the at least one blade assembly. The method further includes coupling the at least one blade assembly into the gas turbine engine. The blade assembly includes an airfoil and a metal leading edge (MLE) coupled to at least a portion of the airfoil. The MLE includes the at least one blade tip fuse.

Abstract: Methods and systems of balancing a rotatable member are provided. A method includes separately balancing a first portion and a second portion of the rotatable member wherein the second portion mateable to said first portion, coupling the first and second portions to each other, measuring a physical dimension of the coupled first and second portions, and determining a balance weight magnitude and position based on the measured physical dimension.

Abstract: Embodiments described herein generally relate to a method of measuring the vibration of an aircraft engine. One embodiment herein provides an engine monitoring system either connected to and/or positioned in close proximity to an aircraft engine. Also provided is a clearance measuring device within the engine monitoring system. The clearanceometer collects clearance data that is later converted into vibration data.

Abstract: A vibration measurement system for a gas turbine engine. The vibration measurement system includes a first accelerometer coupled to the gas turbine engine, the first accelerometer configured to transmit a first identifier, a second accelerometer coupled to the gas turbine engine, the second accelerometer configured to transmit a second identifier that is different than the first identifier, and a signal conditioning computer coupled to the first and second accelerometers for receiving the first and second identifiers, the signal conditioning computer configured to determine which of the first and second accelerometers is connected to the signal conditioning computer based on the first and second identifiers.

Abstract: A method facilitates the assembly of a stator assembly for a turbine engine. The method includes providing a cantilevered shell including a first end and a second end, and coupling a second member within the turbine engine. The method also includes coupling the shell to a frame such that the shell extends circumferentially around at least a portion of the second member such that a non-uniform circumferential radial gap is defined radially between the second member and the shell using methods other than directing machining of an inner surface of the shell, and wherein the non-uniform circumferential radial clearance gap becomes substantially uniform during operation of the engine.

Abstract: A method and apparatus for ordering blades in a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a moment weight of each blade in a row of blades, determining a geometric parameter of each blade in the same row of blades, and determining a mapping order of each blade using the moment weight and the geometric parameter. The apparatus includes a computer system that includes a software product code segment for minimizing imbalance in a bladed rotor wherein the segment is configured to receive a moment weight value for each blade to be installed in said rotor, receive a geometric parameter value for each blade to be installed in said rotor, calculate a blade location on the rotor based on the received values, and generate a blade map based on the calculated location.

Abstract: A method and apparatus for assembling a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a moment weight of each blade in a row of blades, determining a geometric parameter of each blade in the same row of blades, and determining a mapping order of each blade using the moment weight and the geometric parameter. The apparatus includes a computer system that includes a software product code segment for minimizing imbalance in a bladed rotor wherein the segment is configured to receive a moment weight value for each blade to be installed in said rotor, receive a geometric parameter value for each blade to be installed in said rotor, calculate a blade location on the rotor based on the received values, and generate a blade map based on the calculated location.

Abstract: A rotor assembly for a gas turbine engine includes a bearing assembly that reduces dynamic loads to a support frame and static bending to the rotor assembly during periods of rotor unbalance. The rotor assembly includes a rotor shaft coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race, a rolling element, and a mounting race. The mounting race includes a spherical face and is secured to the bearing assembly with a retainer that plastically fails at a pre-determined moment load.

Abstract: A squeeze-film damper bearing. Squeeze-film damper bearings contain a fluid film captured between two components, typically (1) a bearing race and (2) a housing which supports the race. The fluid film damps vibration of the two components. However, the fluid film also allows movement of the components with respect to each other, which is not always desired. The invention limits the movement, without significantly diminishing the vibration-damping properties of the fluid.

Abstract: A vibration detector. A machine, such as a gas turbine engine, contains a rotor bearing and a gear. A nearby sensor produces a train of pulses as teeth of the gear travel past. The frequency of the pulse train indicates rotational speed of the rotor. In addition, vibration of the rotor causes the gear to orbit about another center. The orbiting causes amplitude modulation, frequency modulation, or both, in the pulse train. Detection of the modulation indicates the presence of vibration. Thus, a single pulse train, produced by a single sensor, is used to indicate both speed, and the presence of vibration.