The present invention relates to a high pressure process for Pre-Combustion and Post-Combustion CO.sub.2 capture (HP/MP/LP gasification) from a CO.sub.2 gas stream (CO2-Stream) by way of CO.sub.2 total subcritical condensation (CO2-CC), separation of liquid CO.sub.2, higher pressure elevation of obtained liquid CO.sub.2 via HP pump, superheating of CO.sub.2 up to high temperature for driving of a set of CO.sub.2 expander turbines for additional power generation (CO2-PG), EOR or sequestration (First new Thermodynamic Cycle). The obtained liquid CO.sub.2 above, will be pressurized at a higher pressure and blended with HP water obtaining high concentrated electrolyte, that is fed into HP low temperature electrochemical reactor (HPLTE-Syngas Generator) wherefrom the cathodic syngas and anodic oxygen will be performed. In particular the generated HP oxygen/syngas will be utilized for sequential combustion (“H.sub.2/O.sub.2-torches”) for super-efficient hydrogen based fossil power generation (Second new Thermodynamic Cycle).

The present invention relates to a high pressure process for Pre-Combustion and Post-Combustion CO.sub.2 capture (HP/MP/LP gasification) from a CO.sub.2 gas stream (CO2-Stream) by way of CO.sub.2 total subcritical condensation (CO2-CC), separation of liquid CO.sub.2, higher pressure elevation of obtained liquid CO.sub.2 via HP pump, superheating of CO.sub.2 up to high temperature for driving of a set of CO.sub.2 expander turbines for additional power generation (CO2-PG), EOR or sequestration (First new Thermodynamic Cycle). The obtained liquid CO.sub.2 above, will be pressurized at a higher pressure and blended with HP water obtaining high concentrated electrolyte, that is fed into HP low temperature electrochemical reactor (HPLTE-Syngas Generator) wherefrom the cathodic syngas and anodic oxygen will be performed. In particular the generated HP oxygen/syngas will be utilized for sequential combustion (“H.sub.2/O.sub.2-torches”) for super-efficient hydrogen based fossil power generation (Second new Thermodynamic Cycle).

An apparatus for detecting a transient event in an operating machine, the apparatus comprising: a controller configured to control performance of the following steps: a measurement step comprising measuring a periodic signal from a machine; a processing step comprising synchronously processing the periodic signal to track the primary frequency; a filtering step comprising removing the primary periodic component and its harmonics from the periodic signal to yield a filtered dataset; an integration step comprising integrating the filtered dataset over the remaining frequencies to yield an integrated dataset representing the periodic energy at frequencies other than the primary frequency and its harmonics; an analysis step comprising identifying a short-term transient in the integrated dataset to identify a transient disruption in the operation of the machine.

An apparatus for detecting a transient event in an operating machine, the apparatus comprising: a controller configured to control performance of the following steps: a measurement step comprising measuring a periodic signal from a machine; a processing step comprising synchronously processing the periodic signal to track the primary frequency; a filtering step comprising removing the primary periodic component and its harmonics from the periodic signal to yield a filtered dataset; an integration step comprising integrating the filtered dataset over the remaining frequencies to yield an integrated dataset representing the periodic energy at frequencies other than the primary frequency and its harmonics; an analysis step comprising identifying a short-term transient in the integrated dataset to identify a transient disruption in the operation of the machine.

An airfoil includes an airfoil section that is formed of a fiber-reinforced composite that has fiber plies. The fiber plies include at least one overwrap fiber ply, first and second support fiber plies, and a serpentine fiber ply. The overwrap fiber ply circumscribes an internal cavity and defines first and second sides and leading and trailing ends of the airfoil section. The first and second support fiber plies define respective first and second radial tubes in the internal cavity. The serpentine fiber ply winds from the first side and around the first radial tube to the second side, then from the second side back to the first side, and then from the first side and around the second radial tube back to the second side.

An airfoil includes an airfoil section that is formed of a fiber-reinforced composite that has fiber plies. The fiber plies include at least one overwrap fiber ply, first and second support fiber plies, and a serpentine fiber ply. The overwrap fiber ply circumscribes an internal cavity and defines first and second sides and leading and trailing ends of the airfoil section. The first and second support fiber plies define respective first and second radial tubes in the internal cavity. The serpentine fiber ply winds from the first side and around the first radial tube to the second side, then from the second side back to the first side, and then from the first side and around the second radial tube back to the second side.

A combustor for a gas turbine engine. The combustor has a combustor liner that includes a vortex turbulence generator. The vortex turbulence generator has a flow passage extending therethrough, the flow passage being defined by a wall about a periphery of the flow passage, and a plurality of vortex generating turbulators disposed on the wall, each of the plurality of vortex generating turbulators a projection portion extending from a surface of the wall into the flow passage and generating a vortex turbulent flow of an oxidizer passing through the flow passage from a cold surface side of the combustor liner to a hot surface side of the combustor liner.

A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

A gas turbine engine has a compression system radius ratio defined as the ratio of the radius of the tip of a fan blade to the radius of the tip of the most downstream compressor blade in the range of from 5 to 9. This results in an optimum balance between installation benefits, operability, maintenance requirements and engine efficiency when the gas turbine engine is installed on an aircraft.

A shaft for a gas turbine engine includes an inner contour with a stiffening rib that defines a stiffened wall thickness related to a nominal wall thickness according to a ratio between about 1.125-2.1.