Turbine blade that is cooled by automatically variable internal circulation of coolant.

A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors.

The inventive turbine comprises a cooled turbine wheel.

Turbine blade that is cooled by automatically variable internal circulation of coolant.

A passively cooled blade platform (16) for a gas turbine rotor adapted for rotation about an axis within a stationary coolant fluid.

By this, the turbine nozzle (2) is cooled and the compressed air used to cool the turbine nozzle is made to flow toward the turbine impeller (3).

A turbine nozzle (2) that, among components constructing a turbine, reaches particularly high temperature is efficiently cooled with a relatively simple structure.

The large part of the gas turbine blade (1) is steam cooled to save compressor air.

Steam used to cool the intermediate and low pressure vanes and blades of the high pressure turbine is directed to an intermediate pressure turbine for cooling and expansion.

The heated solution is optionally cooled to form a cooled solution.

Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components.

The secondary loop brings the steam to the turbines and returns cooled water from the condenser back to the boiler.

The enclosure provides a cooled interior section and a noncooled interior section.

The invention relates to a gas turbine blade (1), cooled in separate cavities (16, 17, 18) by air and steam.

The water vapor drives the low-pressure steam turbine I to serve as the power source for a cooling machine, and cooled water is obtained.