High pressure compressor for an engine
AssigneeMTU Aero Engines AG
InventorsHarsimar Sahota, Alexander Halcoussis, Sergio Elorza Gomez
Life of this patent
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Abstract
An engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.
Claims15
A high pressure compressor for an engine, comprising a first, second, third and fourth quasi-stage, each quasi-stage having a stator and a downstream rotor, wherein a blade/vane solidity in a respective center section of each quasi-stage is:
- in the first quasi-stage, at least 1.04 and at most 1.18 for the stator and at least 1.46 and at most 1.67 for the rotor;
- in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor;
- in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor;
- in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.
Dependencies are inferred from the claim text.