Gas turbine engine
AssigneeVolvo Aero Corporation
InventorAnders Lundbladh
Life of this patent
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Abstract
A gas turbine engine includes in serial flow relationship: a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor; a combustion chamber; and a first turbine provided with at least one row of turbine blades distributed circumferentially around the first turbine, wherein the first compressor and the first turbine are rotationally rigidly connected by a first shaft. The first turbine is adapted to influence a gas flow rate through the gas turbine engine depending on a rotational speed of the first turbine, wherein the gas turbine engine further includes an arrangement for controlling the rotational speed of the first turbine. A method for controlling a gas flow rate in an axial flow gas turbine engine is also provided.
Claims33
Gas turbine engine comprising in serial flow relationship:
- a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor;
- a combustion chamber;
- and
- a first turbine provided with at least one row of turbine blades distributed circumferentially around the first turbine, wherein the first compressor and the first turbine are rotationally rigidly connected by a first shaft,
- wherein the first turbine is adapted to influence a normalized gas flow rate through the gas turbine engine depending on a rotational speed of the first turbine, a turbine rotor of the first turbine is arranged directly downstream of the combustion chamber so that no stator vanes or similar gas deflecting components are arranged in a region downstream of the combustion chamber and upstream of the first turbine rotor, and the gas turbine engine further comprises means for controlling the rotational speed of the first turbine.
Method for controlling a gas flow rate in an axial flow gas turbine engine, wherein the method comprises the step of:
- controlling a rotational speed of a turbine, wherein the turbine is adapted to influence the normalized gas flow rate through the gas turbine engine depending on the rotational speed of the turbine.
Axial flow gas turbine engine comprising
- a first rotor arrangement comprising a first compressor, and
- a second rotor arrangement comprising a second compressor, wherein the first and second rotor arrangements are positioned concentrically and are arranged to rotate in opposite directions, and wherein the first compressor comprises a case arranged to rotate around the second compressor, which case is provided with a plurality of rows of compressor blades protruding in an inward direction towards the second compressor, wherein the first compressor and the second compressor overlap, wherein the second compressor extends in an axial direction of the gas turbine engine over a longer distance than the first compressor such that the first and second compressors overlap only partly.
Dependencies are inferred from the claim text.