Abstract: The gas turbine engine comprises a gas generator (66), comprised of a compressor section (11), and a power turbine section (65). The power turbine section (65) comprises a power turbine rotor (81) supported by a power turbine shaft (93), which is mechanically uncoupled from the gas generator (66). The power turbine shaft (93) has an axial cavity (511) therein, fluidly coupled to a bearing sump (521) fluidly coupled to the compressor section (11) and housing at least one bearing (106) supporting a shaft of the gas generator (66). An air venting path (527) extends from said axial cavity (511) and leads in a combustion gas flow path (515) downstream of the power turbine rotor (81).

Abstract: The gas turbine engine comprises a gas generator (66), comprised of a compressor section (11), and a power turbine section (65). The power turbine section (65) comprises a power turbine rotor (81) supported by a power turbine shaft (93), which is mechanically uncoupled from the gas generator (66). The power turbine shaft (93) has an axial cavity (511) therein, fluidly coupled to a bearing sump (521) fluidly coupled to the compressor section (11) and housing at least one bearing (106) supporting a shaft of the gas generator (66). An air venting path (527) extends from said axial cavity (511) and leads in a combustion gas flow path (515) downstream of the power turbine rotor (81).

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: A turbine comprising a rotatable rotor and a pressure chamber; a wall of the pressure chamber is arranged to act on the rotor so that to balance thrust exerted by the rotor when it rotates; a conduit connects the pressure chamber and arranged to a pressure source; a valve associated to the conduit may open and close the conduit; the valve is arranged to open automatically when the pressure upstream of the valve exceeds a first predetermined threshold value; in this way, when the load of the turbine is high excessive thrust is balanced because of the higher pressure in the pressure chamber.

Abstract: A system and computer-implemented method for monitoring and diagnosing anomalies in a wheel-space of a gas turbine is implemented using a computer device coupled to a user interface and a memory device and includes storing a plurality rule sets in the memory device, the rule sets relative to the wheel-space, the rule sets including at least one rule expressed as a relational expression of a real-time data output relative to a real-time data input, the relational expression being specific to a temperature of the wheel-space. The method also includes receiving real-time and historical data inputs from a condition monitoring system associated with the gas turbine, the data inputs relating to sources providing heat to the wheel-space and estimating a wheel-space temperature value using the inputs relating to a temperature of the wheel-space.