Abstract: Mechanical overloads in a reciprocating gas compressor can cause irreparable damage to compressor components if the source of the overloads is not repaired. A method of detecting mechanical overloads includes applying an overload indicator across an interface between components in the compressor, and observing a mechanical condition of the overload indicator. The mechanical condition of the overload indicator is indicative of whether the compressor experienced a mechanical overload. By placing the indicator in an appropriate location in the compressor, overload conditions can be checked during routine inspections and maintenance checks.

Abstract: Mechanical overloads in a reciprocating gas compressor can cause irreparable damage to compressor components if the source of the overloads is not repaired. A method of detecting mechanical overloads includes applying an overload indicator across an interface between components in the compressor, and observing a mechanical condition of the overload indicator. The mechanical condition of the overload indicator is indicative of whether the compressor experienced a mechanical overload. By placing the indicator in an appropriate location in the compressor, overload conditions can be checked during routine inspections and maintenance checks.

Abstract: Mechanical overloads in a reciprocating gas compressor can cause irreparable damage to compressor components if the source of the overloads is not repaired. A method of detecting mechanical overloads includes forming a mechanical fuse that is configured to strain under overload conditions, and observing a condition of the mechanical fuse. The condition of the mechanical fuse is indicative of whether the compressor experienced a mechanical overload. By simply observing the mechanical fuse, overload conditions can be checked during routine inspections and maintenance checks.

Abstract: Mechanical overloads in a reciprocating gas compressor can cause irreparable damage to compressor components if the source of the overloads is not repaired. A method of detecting mechanical overloads includes forming a mechanical fuse that is configured to strain under overload conditions, and observing a condition of the mechanical fuse. The condition of the mechanical fuse is indicative of whether the compressor experienced a mechanical overload. By simply observing the mechanical fuse, overload conditions can be checked during routine inspections and maintenance checks.

Abstract: A method of determining fuse parameters in a reciprocating gas compressor ensures a safe failure upon exceeding an overload limit. Stresses and bolted joint behavior for critical components in compressor running gear are evaluated using a finite element analysis. Capabilities of the critical components during an overload event are evaluated using a propagation and variances tool. The capabilities of the critical components are compared against overload conditions. At least one of an optimal fuse location and a fuse geometry are determined according to the comparison to establish a safe failure point upon exceeding the overload limit. With a mechanical fuse defining a failure point, critical compressor components can be protected from damage, and personnel can be protected from risk of a gas leakage.

Abstract: A method comprises storing data relating to the wear of a component of at least one turbine system in a database of a system for processing wear related information, generating a displayable menu containing a plurality of user-selectable links respectively associated with software modules of the system, and receiving an on-line selection of one of the user-selectable links to enable the associated software module of the system to generate displayable content including information relating to the wear of the component of the turbine system. The selected module may enable a quantitative amount of the wear of the component or qualitative wear range characterizing the amount of the wear of the component to be input and received on-line. Alternatively, the selected module may enable a component type to be input and received on-line and display a component fleet leader.

Abstract: An apparatus for providing active clearance control between blade tips and seals in a turbomachine comprising: a first stator carrier segment, with stator seals centripetally disposed on it; a second stator carrier segment located along a same circumference as the first stator carrier segment, also with stator seals centripetally disposed on it; a shell that adjustably houses the first stator carrier segment and the second carrier segment; at least one displacement apparatus in operable communication with at least one stator carrier segment and configured to position the at least one stator carrier segment to provide active clearance control to the stator seals disposed on the at least one stator carrier segment.

Abstract: A seal assembly includes an annular hanger having a supporting ledge. An arcuate seal segment includes an outer rail mounted on the ledge and supporting an inner seal. An arcuate carrier is mounted between the hanger and the rail, and includes a piston mounted in a bore. The bore is selectively pressurized to deploy the piston between the hanger and rail for temporarily retracting the seal segment from an adjacent rotor component.

Abstract: Multistage brush seals are made by initially specifying designs thereof for collectively sharing a differential pressure along an adjacent land subject to relative rotation with the seals. The seals are modified to share the loading without blowdown therefrom. The seals are further modified to ensure rotational stability with the land. The seals are built and tested under pressure to determine pressure blowdown thereof. And then, the seals are again modified to share the pressure loading under blowdown. In this way, the seals share the load in situ under the effects of blowdown.

Abstract: One embodiment of the present invention comprises an actuating mechanism for a turbine comprising a compliant member (meaning at least one compliant member) comprising a series of serpentine folds forming a plurality of fold sections and a central cavity (meaning at least one central cavity) interposed between the adjacent fold sections wherein the compliant member is movable between a first retracted position and a second extended position upon introduction of a pressurized medium into the central cavity and dispersion of the pressurized medium within the serpentine folds.

Abstract: A steam gland includes a steam inlet scroll and an extraction scroll axially spaced from one another defining high and low pressure regions. A seal body is disposed between the regions and includes a pair of brush seals axially spaced from one another. Intermediate the brush seals is a honeycomb seal. The hybrid brush seal/honeycomb seal combination minimizes steam leakage between the high and low pressure regions and eliminates the possibility of heat induced damage to the rotor while optimizing seal leakage performance.

Abstract: An actuated seal assembly for controlling flow in a fluid path in turbomachinery comprising a seal and a seal carrier coupled to the seal is provided. A displacement apparatus is coupled to the seal carrier for positioning the seal so as to control the flow in the fluid path. In addition, a drive system is provided for powering the displacement apparatus.

Abstract: A seal assembly includes an annular hanger having a supporting ledge. An arcuate seal segment includes an outer rail mounted on the ledge and supporting an inner seal. An arcuate carrier is mounted between the hanger and the rail, and includes a piston mounted in a bore. The bore is selectively pressurized to deploy the piston between the hanger and rail for temporarily retracting the seal segment from an adjacent rotor component.

Abstract: A steam gland includes a steam inlet scroll and an extraction scroll axially spaced from one another defining high and low pressure regions. A seal body is disposed between the regions and includes a pair of brush seals axially spaced from one another. Intermediate the brush seals is a honeycomb seal. The hybrid brush seal/honeycomb seal combination minimizes steam leakage between the high and low pressure regions and eliminates the possibility of heat induced damage to the rotor while optimizing seal leakage performance.

Abstract: Multistage brush seals are made by initially specifying designs thereof for collectively sharing a differential pressure along an adjacent land subject to relative rotation with the seals. The seals are modified to share the loading without blowdown therefrom. The seals are further modified to ensure rotational stability with the land. The seals are built and tested under pressure to determine pressure blowdown thereof. And then, the seals are again modified to share the pressure loading under blowdown. In this way, the seals share the load in situ under the effects of blowdown.

Abstract: A seal carrier is provided for a rotary machine wherein the seal carrier comprises a packing ring coupled to a seal and wherein the packing ring comprises a channel disposed therein. In addition, a displacement apparatus is disposed in the channel for radially positioning the seal to control a flow of a fluid in a fluid path.

Abstract: The present invention provides an actuated seal assembly for controlling flow in a fluid path in turbomachinery comprising a seal and a seal carrier coupled to the seal. A displacement apparatus is coupled to the seal carrier for positioning the seal so as to control the flow in the fluid path. In addition, a drive system is provided for powering the displacement apparatus.

Abstract: A seal assembly is provided for a rotary machine wherein the rotary machine comprises a rotor and a casing. The rotor comprises a generally longitudinally-extending axis. The casing is generally coaxially aligned with the axis. The casing circumferentially surrounds, is radially spaced apart from the rotor, and comprises an inner circumferential channel generally coaxially aligned with the rotor. The seal assembly comprises a plurality of seal carrier segments fixedly disposed in a circumferential array in the inner circumferential channel. Each of the seal carrier segments comprises a seal carrier channel. At least one of the seal carrier segments comprises at least one fluid inlet disposed therein. In addition, the seal assembly comprises a (meaning at least one) seal disposed in the seal carrier channel and is movable between radially inward and radially outward positions upon introduction of fluid medium in the fluid inlet.

Abstract: One embodiment of the present invention comprises an actuating mechanism for a turbine comprising a compliant member (meaning at least one compliant member) comprising a series of serpentine folds forming a plurality of fold sections and a central cavity (meaning at least one central cavity) interposed between the adjacent fold sections wherein the compliant member is movable between a first retracted position and a second extended position upon introduction of a pressurized medium into the central cavity and dispersion of the pressurized medium within the serpentine folds.

Abstract: A brush seal segment is mounted within a pressure vessel and against an arcuate surface of an element to provide a seal between regions on opposite sides of the seal at different pressures. By vibrating the vessel through a range of frequencies, natural frequencies of the brush seal under pressure loading can be ascertained. Additionally, by adjusting interference between the arcuate surface and the bristle tips, natural frequencies of the brush seal under various interference loadings can likewise be ascertained. The pressure vessel has mounts for attaching the vessel to a shaker table to facilitate vibrating the vessel through the range of frequencies.