An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.

An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.

A metal catalytic converter system employs an engine having an exhaust duct. A multistage metal catalytic converter is mounted in the exhaust duct. A compressor stage is mounted in the exhaust duct, the compressor stage configured to reduce exhaust backpressure created by the converter.

Systems and methods for improving the efficiency of plants that use a gas turbine engine to power a process air compressor are disclosed. Examples of such plants include ammonia production plants, wherein a gas turbine engine is used to power a process air compressor and wherein exhaust gas from the gas turbine engine is provided as combustion gas to a reformer furnace. The increase in efficiency is provided using a booster compressor to enhance the performance of the gas turbine engine. According to some embodiments, the booster compressor may also be used to reduce the power consumption of the process air compressor. According to some embodiments, a side stream from the booster compressor may be provided to the furnace to supplement the combustion gas provided by the gas turbine engine exhaust gas. The disclosed methods and systems increase the efficiency of the plant while maintaining the duty balance between the furnace and the process air compressor-driven process.

A waste heat recovery system including a drive unit, the drive unit having a drive shaft, a compressor, the compressor operably coupled to the drive shaft, wherein operation of the drive unit drives the compressor, and a waste heat recovery cycle, the waste heat recovery cycle coupled to the drive unit and the compressor, wherein a waste heat of the drive unit powers the waste heat recovery cycle, such that the waste heat recovery cycle transmits a mechanical power to the compressor, is provided. Furthermore, an associated method is also provided.

A waste heat recovery system including a drive unit, the drive unit having a drive shaft, a compressor, the compressor operably coupled to the drive shaft, wherein operation of the drive unit drives the compressor, and a waste heat recovery cycle, the waste heat recovery cycle coupled to the drive unit and the compressor, wherein a waste heat of the drive unit powers the waste heat recovery cycle, such that the waste heat recovery cycle transmits a mechanical power to the compressor, is provided. Furthermore, an associated method is also provided.

An expansion turbine configured such that even when pressure of process gas steeply changes, the amount of process gas leaking from a gap between an impeller and a cover is made small. The expansion turbine includes a gas supply passage which is connected to any one of a gas supply passage and a gas discharge passage and through which gas is supplied to a region located between a rotor member and a casing member.

An expansion turbine configured such that even when pressure of process gas steeply changes, the amount of process gas leaking from a gap between an impeller and a cover is made small. The expansion turbine includes a gas supply passage which is connected to any one of a gas supply passage and a gas discharge passage and through which gas is supplied to a region located between a rotor member and a casing member.

An engine system includes a gas generator section and a load compressor. The gas generator section includes a core compressor, a combustion assembly, and a turbine. The core compressor receives and compresses a first flow of air as first compressed air. The combustion assembly receives the first compressed air from the compressor, mixes the first compressed air with fuel, and combusts the first compressed air and fuel mixture to result in combustion gases. The turbine receives the combustion gases from the combustion assembly and extracts energy from the combustion gases. The load compressor is driven by the turbine, and it is further configured to receive and compress a second flow of air as second compressed air. At least a portion of the second compressed air is directed to the gas generator section as cooling air.

An engine system includes a gas generator section and a load compressor. The gas generator section includes a core compressor, a combustion assembly, and a turbine. The core compressor receives and compresses a first flow of air as first compressed air. The combustion assembly receives the first compressed air from the compressor, mixes the first compressed air with fuel, and combusts the first compressed air and fuel mixture to result in combustion gases. The turbine receives the combustion gases from the combustion assembly and extracts energy from the combustion gases. The load compressor is driven by the turbine, and it is further configured to receive and compress a second flow of air as second compressed air. At least a portion of the second compressed air is directed to the gas generator section as cooling air.