General Electric Company

Patrick Daniel Noble

Brendon James Leary

Andres Jose Garcia-Crespo

Jeremy Peter Latimer

Joseph Anthony Weber

Michael James Healy

Paul Griffin Delvernois

Donald Earl Floyd

Andrés Jose Garcia-Crespo

Donald Earl Ll Floyd

A vibration-damping system for turbomachine blade(s) in a turbomachine is provided. Each turbomachine blade includes a platform having a radially inner surface. The system includes a spacer axially adjacent the platform of at least one turbomachine blade in the turbomachine, e.g., adjacent a turbomachine blade stage. The spacer includes a body. A damping element coupler is on the body of the spacer, and a vibration-damping element is configured to couple to the damping element coupler. The vibration-damping element and the damping element coupler are disposed to cause the vibration-damping element to engage the radially inner surface of the platform of the turbomachine blade(s) to dampen vibration of the turbomachine blade(s), e.g., during operation of the turbomachine.

Vibration-damping system for turbomachine blade(s) on spacer adjacent blade stage

A system includes a blade segment having a blade and a mounting segment coupled to the blade. Additionally, the mounting segment includes a first contact face and a second contact face, wherein the first and second contact face are concave with respect to a longitudinal axis of the blade segment. To reduce stresses within the mounting segment, the mounting segment further includes a lower face coupling the first contact face and the second contact face, wherein the lower face is convex across the longitudinal axis of the blade segment.

System having blade segment with curved mounting geometry

A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Airfoil shape for first stage compressor rotor blade

A rotor assembly includes a rotor disc including a plurality of circumferentially-spaced diskposts and a plurality of dovetail slots. Each dovetail slot is defined between a pair of circumferentially-adjacent diskposts. A plurality of rotor blades are coupled to the rotor disc. Each rotor blade includes a dovetail portion that is configured to slidably engage a respective dovetail slot. A plurality of platform sections are coupled to the rotor disc such that each platform section is adjacent a respective rotor blade. Each platform section includes a diskpost slot that is configured to receive one of the plurality of diskposts such that each dovetail slot receives a respective dovetail portion and at least a portion of at least one of the platform sections adjacent the rotor blade.

Gas turbine engine rotor assembly and method of assembling the same

A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.

Flowpath boundary and rotor assemblies in gas turbines

A system includes a turbomachine that includes a stator and a rotor. The rotor is configured to rotate about a rotational axis relative to the stator. In addition, the rotor includes a least one rotary blade, and the at least one rotary blade has a patterned structure of beams and cavities.

Turbomachine blade with improved stiffness to weight ratio

An array of rotor blades is provided. The array includes a rotor disk defining a plurality of slots. A first rotor blade that includes a first platform between a first airfoil and a first shank portion is coupled with a first slot of the rotor disk via the first shank portion. The first rotor blade further includes a pair of oppositely disposed flanges positioned between the first platform and the first shank portion and extending beyond a longitudinal side edge defined by the first platform. A second rotor blade, that includes a second platform defining a pair of oppositely disposed overhang lips and positioned between a second airfoil and a second shank portion, is coupled with a second slot of the rotor disk via the second shank portion. The second rotor blade is positioned adjacent to the first rotor blade such that one of the overhang lips of the second platform is positioned over one of the flanges of the first rotor blade. Methods are also generally provided for installing rotor blades onto a rotor disk.

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Greenville, SC, United States of America

Patrick Daniel Noble