Abstract: A support system is provided for a gear case of a rope shovel. The gear case supports a gear drive configured to drive rotation of a hoist drum, and the gear case includes a first end, a second end, and a longitudinal axis extending between the first end and the second end. The support system includes: a coupling for securing the gear case against translational movement relative to a rotating frame, the coupling oriented orthogonally to the longitudinal axis and configured to engage the rotating frame and a portion of the gear case; and a support member configured to be coupled to the rotating frame of the rope shovel and supporting the gear case, the support member permitting translational movement of the gear case relative to the rotating frame to accommodate flexing of the rotating frame.

Abstract: A support system is provided for a gear case of a rope shovel. The gear case supports a gear drive configured to drive rotation of a hoist drum, and the gear case includes a first end, a second end, and a longitudinal axis extending between the first end and the second end. The support system includes: a coupling for securing the gear case against translational movement relative to a rotating frame, the coupling oriented orthogonally to the longitudinal axis and configured to engage the rotating frame and a portion of the gear case; and a support member configured to be coupled to the rotating frame of the rope shovel and supporting the gear case, the support member permitting translational movement of the gear case relative to the rotating frame to accommodate flexing of the rotating frame.

Abstract: A support system is provided for a gear case of a rope shovel. The gear case supports a gear drive configured to drive rotation of a hoist drum, and the gear case includes a first end, a second end, and a longitudinal axis extending between the first end and the second end. The support system includes: a coupling for securing the gear case against translational movement relative to a rotating frame, the coupling oriented orthogonally to the longitudinal axis and configured to engage the rotating frame and a portion of the gear case; and a support member configured to be coupled to the rotating frame of the rope shovel and supporting the gear case, the support member permitting translational movement of the gear case relative to the rotating frame to accommodate flexing of the rotating frame.

Abstract: The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for aerodynamic noise reduction. The gas turbine engine components are plasma treated in a high vacuum environment to generally reach a surface roughness (Ra) below 150 nanometers and in some cases below 25 nanometers. Then during the same process the components are coated using either a metallic or ceramic, hard, thin coating ranging from 100 to 3000 nanometers in thickness depending on desired surface smoothness and non-fouling properties. The same treatment combined with a surface relaxation process, which is part of a smoothing process, allows applying even up to 100 micrometers of hard coating without changes to high cycle fatigue properties and overall performance. Improved surface smoothness of the components and enhanced non-adhesiveness of the contaminants advance the quality of the flow through the gas path and compressor aerodynamic noise reduction.

Abstract: The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment to generally reach a surface roughness (Ra) below 150 nanometers and in some cases below 25 nanometers. Then during the same process the components are coated using either a metallic or ceramic, hard, thin coating ranging from 100 to 3000 nanometers in thickness depending on desired surface smoothness and non-fouling properties. The same treatment combined with a surface relaxation process, which is part of a smoothing process, allows applying even up to 100 micrometers of hard coating without changes to high cycle fatigue properties and overall performance. Improved surface smoothness of the components and enhanced non-adhesiveness of the contaminants advance the quality of the flow through the gas path and compressor efficiency.

Abstract: The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for aerodynamic noise reduction. The gas turbine engine components are plasma treated in a high vacuum environment to generally reach a surface roughness (Ra) below 150 nanometers and in some cases below 25 nanometers. Then during the same process the components are coated using either a metallic or ceramic, hard, thin coating ranging from 100 to 3000 nanometers in thickness depending on desired surface smoothness and non-fouling properties. The same treatment combined with a surface relaxation process, which is part of a smoothing process, allows applying even up to 100 micrometers of hard coating without changes to high cycle fatigue properties and overall performance. Improved surface smoothness of the components and enhanced non-adhesiveness of the contaminants advance the quality of the flow through the gas path and compressor aerodynamic noise reduction.

Abstract: The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for increasing fuel efficiency. The gas turbine engine components are plasma treated in a high vacuum environment to generally reach a surface roughness (Ra) below 150 nanometers and in some cases below 25 nanometers. Then during the same process the components are coated using either a metallic or ceramic, hard, thin coating ranging from 100 to 3000 nanometers in thickness depending on desired surface smoothness and non-fouling properties. The same treatment combined with a surface relaxation process, which is part of a smoothing process, allows applying even up to 100 micrometers of hard coating without changes to high cycle fatigue properties and overall performance. Improved surface smoothness of the components and enhanced non-adhesiveness of the contaminants advance the quality of the flow through the gas path and compressor efficiency.

Abstract: The invention relates to a method and an apparatus for applying metallic, ceramic or composite thin film coatings onto parts, components and tools (e.g. gas turbine engine compressor blades or cutting tools) by a cathodic arc deposition technique. The method and the apparatus allows for a continually changing structure of the applied film by nanoimplanting atoms, molecules, compounds or other chemical species and structures of different materials thus coating a substrate during a single process. Furthermore, during the same process it allows for creating a coating with specific parameters as required. For instance: hardness, smoothness, corrosion resistance, erosion resistance.

Abstract: The invention relates to a method and an apparatus for applying metallic, ceramic or composite thin film coatings onto parts, components and tools (e.g. gas turbine engine compressor blades or cutting tools) by a cathodic arc deposition technique. The method and the apparatus allows for a continually changing structure of the applied film by nanoimplanting atoms, molecules, compounds or other chemical species and structures of different materials thus coating a substrate during a single process. Furthermore, during the same process it allows for creating a coating with specific parameters as required. For instance: hardness, smoothness, corrosion resistance, erosion resistance.