Gas turbine with at least one multi-stage compressor unit including several compressor modules
AssigneeRolls-Royce Deutchland Ltd Co KG
InventorMetin Talan
Life of this patent
Estimating the term…
Abstract
A gas turbine includes at least one multi-stage compressor unit 2, with the compressor unit 2 including several, independent compressor modules 3-5, which, independently of each other, are rotatably borne on a drive shaft 1 and are each engageable with the drive shaft 1 by at least one clutch unit 9-11.
Claims17
A gas turbine, comprising:
- a drive shaft having an axis about which it is rotatable;
- at least one multi-stage compressor unit having a plurality of independent compressor modules, which, independently of each other, are rotatably borne on the drive shaft, each independent compressor module including a compressor stage having a rotor with a plurality of rotor blades disposed circumferentially around the axis of the drive shaft;
- a respective clutch unit for each of the plurality of independent compressor modules by which each independent compressor module is engageable with the drive shaft such that the plurality of rotor blades of that independent compressor module is rotationally fixed to the drive shaft around the axis of the drive shaft and disengageable from the drive shaft such that the plurality of rotor blades of that independent compressor module is rotatable with respect to the drive shaft around the axis of the drive shaft.
A method for starting a gas turbine having a plurality of independent compressor modules rotatably borne on a drive shaft of the gas turbine, comprising:
- providing a respective clutch unit for each of the plurality of independent compressor modules by which each independent compressor module is engageable with and disengageable from the drive shaft;
- disengaging at least one of the plurality of independent compressor modules from the drive shaft to reduce a load on the drive shaft and allow the drive shaft to be accelerated at a faster rate;
- accelerating the drive shaft to a rotational speed sufficient for starting the gas turbine while the at least one of the plurality of independent compressor modules is disengaged from the drive shaft;
- and
- after the gas turbine has been started, engaging the at least one of the plurality of independent compressor modules with the drive shaft when operating conditions require the gas turbine to operate at a higher load.
A method for operating a gas turbine having a plurality of independent compressor modules rotatably borne on a drive shaft of the gas turbine, comprising:
- providing a respective clutch unit for each of the plurality of independent compressor modules by which each independent compressor module is engageable with and disengageable from the drive shaft;
- disengaging at least one of the plurality of independent compressor modules from the drive shaft during partial load operation of the gas turbine;
- and
- engaging the at least one of the plurality of independent compressor modules with the drive shaft when operating conditions require the gas turbine to operate at a higher load.
Dependencies are inferred from the claim text.