Patent ID: 8220276
Filing Date: 2012-07-17
Classification: F02C,F04D,F05D,Y02T

Abstract:
1. A gas turbine axial flow compressor, comprising: a casing; a rotor hub rotatably borne in the casing; an axial flow compressor duct disposed between the casing and the rotor hub; at least one rotor, which is rotatable about a machine axis; at least one stator, the at least one rotor and at least one stator being positioned axially spaced from one another within the axial flow compressor duct; a bleed air tapping device having a plurality of recesses axially positioned in the casing both: outside of a bladed space of the at least one stator, and at least one of: before or behind a blade row of the at least one rotor or between two blade rows of two rotors; which recesses, in at least one circumferential area, are arranged circumferentially to each other, wherein each recess includes, in a circumferential direction, a circumferential leading edge and a circumferential trailing edge, each of which is situated at an identical angle (β where (ξ) is a dimensionless air quantity to be tapped, which derives from an extraction air flow m (r (r (ν) is a hub ratio at the circumferential leading edge, with (ν)=r (A (BOA) is an identical angle of the circumferential leading edge and the circumferential trailing edge, relative to a straight line located parallel to the machine axis, with the angle (BOA) satisfying one of the following rules: