Abstract: An improved system and methodology for starting up a gas-turbine driven multi-stage compressor. The improvement involves isolating individual compression stages and creating positive pressure in each stage prior to initiating rotation of the compressor/driver system. The isolation of individual compression stages allows the turbine to reach normal operating speeds with substantially no supplemental power from an auxiliary source.

Abstract: A control method and apparatus for simultaneously protecting a compression system from driver overpowering and turbocompressor surge. When overpowering is detected, flow rate through the each compressor in the turbocompressor train is reduced by closing an inlet throttling valve at the inlet of each respective compressor stage unless a compressor operating point is sufficiently near surge. In this latter case, the inlet throttling valve is not closed. In this way, overall flow rate through the compressor train is reduced while maintaining adequate flow through compromised stages to avoid surge.

Abstract: An anti-bogdown control system monitors and regulates operation of a turbine and a compressor to prevent underspeed trip of the turbine while avoiding surge of the compressor. A turbine speed controller receives a turbine speed signal and a turbine temperature signal, generates a surge margin setpoint, and regulates overfiring of the turbine. A surge margin controller associated with the compressor receives the surge margin setpoint from the turbine speed controller and receives a load signal from one or more sensors and modulates a compressor throttle valve so that the compressor operates at a surge margin that is approximately equal to the surge margin setpoint. In a system with multiple compressors driven by a single turbine, a surge margin controller is associated with each compressor.

Abstract: A control method and apparatus for simultaneously protecting a compression system from driver overpowering and turbocompressor surge. When overpowering is detected, flow rate through the each compressor in the turbocompressor train is reduced by closing an inlet throttling valve at the inlet of each respective compressor stage unless a compressor operating point is sufficiently near surge. In this latter case, the inlet throttling valve is not closed. In this way, overall flow rate through the compressor train is reduced while maintaining adequate flow through compromised stages to avoid surge.

Abstract: An improved system and methodology for starting up a gas-turbine driven multi-stage compressor. The improvement involves isolating individual compression stages and creating positive pressure in each stage prior to initiating rotation of the compressor/driver system. The isolation of individual compression stages allows the turbine to reach normal operating speeds with substantially no supplemental power from an auxiliary source.

Abstract: An anti-bogdown control system monitors and regulates operation of a turbine and a compressor to prevent underspeed trip of the turbine while avoiding surge of the compressor. A turbine speed controller receives a turbine speed signal and a turbine temperature signal, generates a surge margin setpoint, and regulates overfiring of the turbine. A surge margin controller associated with the compressor receives the surge margin setpoint from the turbine speed controller and receives a load signal from one or more sensors and modulates a compressor throttle valve so that the compressor operates at a surge margin that is approximately equal to the surge margin setpoint. In a system with multiple compressors driven by a single turbine, a surge margin controller is associated with each compressor.

Abstract: A process for converting a hydrocarbon gas (e.g. natural gas) to syngas which, in turn, is converted into a liquid hydrocarbon product wherein a substantial amount of the heat generated in the process is recovered for use in generating steam needed in the process or for conversion into mechanical energy. Further, tail gas produced by the process is used to fuel the gas turbine which, in turn, is used power the compressors needed for compressing the air used in the process. By using tail gas to fuel the gas turbine, less of the compressed combustion-air is needed to cool the combustion gases in the turbine and, instead, can be used to provide a portion of the process-air required in the process; thereby possibly saving up to 20 to 30 percent of the horsepower otherwise needed to compress the required volume of process-air.

Abstract: An improved process for the compression and heating of air or oxygen-enriched air for charging to an autothermal reactor by using a single high compression ratio compressor to produce a high-pressure, high-temperature air or oxygen-enriched air stream for mixture with a hydrocarbon gas stream to produce a charge stream to an autothermal reactor at an elevated pressure above about 350 psig and at an elevated temperature from about 700 to about 900.degree. F.

Abstract: A system and a method for producing increased quantities of oil from an oil well producing a mixture of oil and gas through a well bore penetrating an oil bearing formation containing a gas cap zone and an oil bearing zone by separating at least a portion of the gas from the mixture of oil and gas downhole in an auger separator to produce a separated gas and an oil enriched mixture; compressing at least a portion of the separated gas downhole to a pressure greater than the pressure in the gas cap zone to produce a compressed gas; and, injecting the compressed gas into the gas cap and, recovering at least a major portion of the oil enriched mixture.

Abstract: Gas compression and chilling systems, particularly adapted for compressing and chilling gas for transmission through arctic pipelines are provided with a cross heat exchanger for transferring heat from gas compressed to the inlet gas to the compressor. The heat exchanger is disposed upstream of an expander which may comprise a mechanical expander or a throttling valve, or both, to achieve a predetermined final output pressure and temperature. An aerial heat exchanger is interposed between the compression and expansion stages upstream of the inlet gas heat exchanger. One embodiment of the system uses two stages of compression, aerial cooling and expansion to the final temperature and pressure.