Disclosed is a turbine dental drill mechanism, comprising a turbine (1) and a turbine shaft (2).

The invention additionally describes a turbine which contains a corresponding turbine oil as lubricant.

A turbine nozzle support device of a steam turbine, comprising a plurality of turbine stages and a cylindrical body.

Provided is an integral axial flow turbine compressor used in a gas turbine engine.

A power generator for a hydro turbine is axially coupled to the hydro turbine.

The present invention is directed to a turbine seal system.

The present invention relates to a regulating stage (100) for a turbine.

The invention relates to a rotor for a gas turbine, in particular for an aircraft engine.

An air turbine flow restrictor comprises a sensor for determining the rotational velocity of the turbine wheel.

Hollow fan blades for gas turbine engines are disclosed.

The Ti-Al alloy thus treated can be advantageously used as, e.g., a turbine wheel for superchargers, engine bulb, or turbine blade for gas turbines.

A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount.

The invention concerns a turbine shaft (1), in particular for a combined high-pressure/medium-pressure steam turbine installed in a common housing (22).

The containment system utilizes a catcher (60, 62) extending from the shroud back plate (34) adjacent the impeller, which engages the snagger (50, 52) formed as a unitary part of the impeller.

Embodiments include an inlet particle separator system for a gas turbine engine.