Multistage axial compressor and gas turbine
AssigneeMitsubishi Heavy Industries, Ltd.
InventorDaisuke MORITA
Life of this patent
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Abstract
A multistage axial compressor includes: a rotational shaft to which a plurality of rotor blades are mounted; a casing surrounding the rotational shaft, the casing forming a flow passage of a working fluid between the rotational shaft and the casing; a wall portion having an annular shape and extending in a circumferential direction of the rotational shaft so as to surround the casing, the wall portion forming an bleed chamber having an annular shape and being in communication with the flow passage; a plurality of port portions connected to an outer peripheral surface of the wall portion, the port portions forming respective outlet flow passages which are in communication with the bleed chamber; and a plurality of bleed pipes connected to the respective port portions.
Claims11
A multistage axial compressor, comprising:
- a rotational shaft to which a plurality of rotor blades are mounted;
- a casing surrounding the rotational shaft, the casing forming a flow passage of a working fluid between the rotational shaft and the casing;
- a wall portion having an annular shape and extending in a circumferential direction of the rotational shaft so as to surround the casing, the wall portion forming an bleed chamber having an annular shape and being in communication with the flow passage;
- a plurality of port portions connected to an outer peripheral surface of the wall portion, the port portions forming respective outlet flow passages which are in communication with the bleed chamber;
- and
- a plurality of bleed pipes connected to the respective port portions,
- wherein, in a cross-sectional view orthogonal to the rotational shaft, of two corner regions where an inner surface of each of the port portions and an inner surface of the wall portion intersect with each other, at the corner region positioned on a back side in a rotational direction of the working fluid in the bleed chamber, when θ1 is defined as an angle formed between the inner surface of the port portion and the inner surface of the wall portion,
- the angle θ1 is not greater than 225°.
A gas turbine, comprising:
- a multistage axial compressor;
- a combustor capable of producing combustion gas by combusting fuel by utilizing air compressed by the multistage axial compressor;
- and
- a turbine capable of outputting power by utilizing combustion gas produced in the combustor,
- wherein the multistage axial compressor includes:
- a rotational shaft to which a plurality of rotor blades are mounted;
- a casing surrounding the rotational shaft, the casing forming a flow passage of the air serving as a working fluid between the rotational shaft and the casing;
- a wall portion having an annular shape and extending in a circumferential direction of the rotational shaft so as to surround the casing, the wall portion forming an bleed chamber having an annular shape and being in communication with the flow passage;
- a plurality of port portions connected to an outer peripheral surface of the wall portion, the port portions forming respective outlet flow passages which are in communication with the bleed chamber;
- and
- a plurality of bleed pipes connected to the respective port portions,
- wherein, in a cross-sectional view orthogonal to the rotational shaft, of two corner regions where an inner surface of each of the port portions and an inner surface of the wall portion intersect with each other, at the corner region positioned on a back side in a rotational direction of the working fluid in the bleed chamber, when 01 is defined as an angle formed between the inner surface of the port portion and the inner surface of the wall portion,
- the angle θ1 is not greater than 225°.
Dependencies are inferred from the claim text.