Axial flow compressor, gas turbine including the same, and stator blade of axial flow compressor
An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion. Each blade of the blade row located at the protruding portion of the wall surface is configured such that an increase rate in a wall surface direction of a blade outlet angle in a blade end portion on the side of the wall surface having the protruding portion is greater than an increase rate in the wall surface direction of a blade outlet angle in a blade height intermediate portion.
1. An axial flow compressor comprising:
multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged inside an annular channel through which a working fluid flows,
wherein a first portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel has a protruding portion such that downstream side part of the first portion is curved so as to further protrude to the annular channel than upstream side part of the first portion, where the first portion is disposed in a place where at least one of the rotor blade rows and the stator blade rows is located, and
wherein each of the multiple rotor and stator blades located at the protruding portion of the wall surface is configured such that a blade outlet angle in a blade height portion monotonously changes toward the wall surface having the protruding portion and an increase rate of a blade outlet angle at a blade end on a side of the wall surface having the protruding portion is greater than an increase rate of the blade outlet angle in the blade height portion.
2. The axial flow compressor according to claim 1 ,
wherein the protruding portion is formed in a circumferential direction of the annular channel.
3. The axial flow compressor according to claim 1 ,
wherein the protruding portion is formed only in a region on a suction surface side of the each of the multiple rotor and stator blades.
4. The axial flow compressor according to claim 2 ,
wherein the first portion of the wall surface having the protruding portion includes:
a first curved surface,
a second curved surface located on a downstream side of the first curved surface, the second curved surface having a shape convex to an inside of the annular channel, and
a first inflection point between the first curved surface and the second curved surface.
5. The axial flow compressor according to claim 4 ,
wherein the first inflection point is located in any range from 40% to 60% of an axial chord length of the blade end and is located on the side of the wall surface having the protruding portion from a leading edge of the blade, where the axial chord length is a length in an axial direction of a chord line.
6. The axial flow compressor according to claim 4 ,
wherein a portion on the downstream side from the blade row on the wall surface having the protruding portion includes:
a third curved surface connected to the second curved surface, the third curved surface having a shape convex to the inside of the annular channel,
a fourth curved surface located on the downstream side of the third curved surface, and
a second inflection point between the third curved surface and the fourth curved surface.
7. The axial flow compressor according to claim 1 ,
wherein the blade is configured such that an axial chord length of the blade end is longer than an axial chord length of the blade height portion, where the axial chord length is a length in an axial direction of a chord line.
8. The axial flow compressor according to claim 1 ,
wherein at least one of the multiple stator blades comprises:
a blade section having an airfoil-shaped cross section, and
a blade tip shroud disposed on an inner peripheral end of the blade section,
wherein an outer peripheral surface of the blade tip shroud configures the wall surface having the protruding portion on the inner peripheral side of the annular channel, and
wherein a stationary member or a rotary member is arranged on an inner peripheral side of the blade tip shroud.
9. A gas turbine comprising the axial flow compressor according to claim 1 .
10. A stator blade which configures a part of a stator blade row of an axial flow compressor, the stator blade comprising:
a blade section having an airfoil-shaped cross section; and
a blade tip shroud disposed on an inner peripheral end of the blade section,
wherein an outer peripheral surface of the blade tip shroud has a protruding portion such that downstream side part of the outer peripheral surface is curved so as to further protrude to a blade section side than upstream side part of the outer peripheral surface, and
wherein the blade section is configured such that a blade outlet angle in a blade height portion monotonously changes toward the wall surface having the protruding portion and an increase rate of a blade outlet angle in an inner peripheral end direction in an inner peripheral side end portion is greater than an increase rate of the blade outlet angle in the inner peripheral end direction in the blade height portion.