A hydrocarbon production system includes a well at a remote location. The well is configured to produce hydrocarbon production fluids comprising natural gas. The system also includes a turbo-generator coupled to the well and configured to receive the natural gas and produce electricity from the natural gas. In addition, the system includes a high performance computing (HPC) data center coupled to the turbo-generator and configured to be powered by the electricity from the turbo-generator.

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.

A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.

A method of motoring a gas turbine engine is provided. The method comprises: determining a first speed to motor a gas turbine engine for cooling; motoring a gas turbine engine at the first speed; detecting a gap parameter of a gas turbine engine; detecting a speed parameter of the gas turbine engine; detecting a vibration parameter of the gas turbine engine; and motoring the gas turbine at a second speed in response to at least one gap parameter, speed parameter, and vibration parameter.

A centrifugal compressor assembly for use in a turbine engine is provided. The assembly includes an impeller that includes a plurality of rotor blades. The assembly also includes a stationary assembly circumscribing the impeller such that a clearance is defined therebetween. The stationary assembly includes at least one articulating seal member positioned adjacent the plurality of rotor blades, and a biasing mechanism configured to cause the at least one articulating seal member to selectively translate relative to the plurality of rotor blades based on an operating condition of the turbine engine.

A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42) therebetween, resulting in blade tip gaps that are dynamically adjusted operation.

A high-efficiency compressor section (10) for a gas turbine engine is disclosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip-facing, elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing, elements have thermal properties sufficiently different to allow relative growth and geometric properties strategically selected to strategically form an interface gap therebetween (42) resulting in blade tip gaps that are dynamically adjusted operation.