Turbine static blade, fitting structure, and gas turbine
Provided is a turbine static blade composed of a blade body and shrouds respectively formed on both ends in the blade height direction of the blade body. The shroud includes: a main member having a heat-resistance coat film section which extends from the axial upstream end to the axial downstream end of a gas passing surface; and a protruding section which protrudes from a side end section on the front edge side of the main member toward the axial upstream side. The protruding section comprises a plurality of cooling paths which are disposed in an annular shape at predetermined intervals in the circumferential direction, and connect an inlet opening which is formed in an inner circumferential surface of the protruding section and an inner surface of the main member, and an outlet opening which is formed in an outer circumferential surface of the protruding section.
1 . A turbine static blade comprising:
a blade body; and
shrouds respectively formed at opposite ends in a blade height direction of the blade body,
wherein one of the shrouds includes
a main member having a heat-resistant coating film portion which extends from an axial upstream end to an axial downstream end of a gas path surface, and
a protrusion portion which protrudes from a side end portion on a leading edge side of the main member toward an axial upstream side, the protrusion portion including an inner peripheral surface and an outer peripheral surface, the inner and outer peripheral surfaces both extending along an axial direction,
the protrusion portion is configured to be fittable into a recessed portion which is formed in a seal member arranged adjacent to the turbine static blade and is recessed toward an axially upstream direction, and
the protrusion portion includes a plurality of cooling passages which are annularly disposed at predetermined intervals in a circumferential direction, wherein each cooling passage connects a respective inlet opening formed on an inner peripheral surface of the protrusion portion or on an inner surface of the main member, and a respective outlet opening which is formed on an outer peripheral surface of the protrusion portion and which opens into a gap portion, the gap portion being formed between an inner peripheral surface of the seal member and the outer peripheral surface of the protrusion portion and extending in the circumferential direction on an upstream side with respect to a position of an axial downstream end of the seal member.
2 . The turbine static blade according to claim 1 ,
wherein for each cooling passage, the outlet opening of the cooling passage is formed axially upstream of a position of a coating film portion upstream end, the coating film portion upstream end being at an axial upstream end of the heat-resistant coating film portion formed on the main member.
3 . The turbine static blade according to claim 2 ,
wherein for each cooling passage, the outlet opening of the cooling passage is disposed axially downstream of an axial upstream end of the protrusion portion, and is disposed closer to the position of the coating film portion upstream end than to a position of the axial upstream end of the protrusion portion.
4 . The turbine static blade according to claim 1 ,
wherein for each cooling passage, the inlet opening of the cooling passage formed on the inner peripheral surface of the protrusion portion is formed closer to the side end portion on the leading edge side of the main member than to the outlet opening of the cooling passage.
5 . The turbine static blade according to claim 1 ,
wherein the one of the shrouds includes a cavity formed by a bottom portion forming a bottom surface of the main member and an outer wall portion formed at an outer edge of the one of the shrouds and protruding in the blade height direction, and
for each cooling passage, the inlet opening is formed on the inner surface of the main member and communicates with the cavity.
6 . The turbine static blade according to claim 5 ,
wherein the one of the shrouds includes a collision plate that divides the cavity into an inner cavity formed on a gas path surface side in the blade height direction, and an outer cavity disposed adjacent to the inner cavity in a direction opposite to the gas path surface in the blade height direction, and
for each cooling passage, the inlet opening of the cooling passage is formed on an inner surface of the outer wall portion on a leading edge side of the inner cavity.
7 . A turbine static blade comprising:
a blade body; and
shrouds respectively formed at opposite ends in a blade height direction of the blade body,
wherein one of the shrouds includes
a main member having a heat-resistant coating film portion which extends from an axial upstream end to an axial downstream end of a gas path surface, and
a protrusion portion which protrudes from a side end portion on a leading edge side of the main member toward an axial upstream side,
wherein the protrusion portion includes a plurality of cooling passages which are annularly disposed at predetermined intervals in a circumferential direction, wherein each cooling passage connects a respective inlet opening formed on an inner peripheral surface of the protrusion portion or on an inner surface of the main member, and a respective outlet opening formed on an outer peripheral surface of the protrusion portion,
wherein the plurality of cooling passages are disposed in a range of a partial width instead of a full width in the circumferential direction from a negative pressure surface-side end portion to a positive pressure surface-side end portion of the one of the shrouds, and
a center position in the circumferential direction of the range in which the plurality of cooling passages are disposed is closer to a positive pressure surface-side end portion side with respect to a position of a leading edge of the blade body.
8 . The turbine static blade according to claim 1 ,
wherein for each cooling passage, the cooling passage is inclined toward the axial upstream side and toward the outlet opening from the inlet opening.
9 . The turbine static blade according to claim 1 ,
wherein for each cooling passage, the cooling passage forms an inclined flow path that is inclined toward a negative pressure surface-side end portion of the one of the shrouds from the inlet opening to the outlet opening.
10 . The turbine static blade according to claim 1 ,
wherein the shrouds include
an outer shroud formed at an end portion on an outer side in the blade height direction of the blade body, and
an inner shroud formed at an end portion on an inner side in the blade height direction of the blade body, and
the one of the shrouds is the inner shroud.
11 . A fitting structure comprising:
a combustor;
a turbine static blade that includes a blade body and a shroud; and
a seal member that faces a combustion gas flow path and that is disposed between the turbine static blade and the combustor,
wherein the shroud includes a main member which extends from an axial upstream end to an axial downstream end, and a protrusion portion which protrudes from a side end portion on a leading edge side of the main member toward an axial upstream side,
the protrusion portion includes a plurality of cooling passages which are disposed at predetermined intervals in a circumferential direction, and each of which connects an inlet opening formed on an inner peripheral surface of the protrusion portion or on an inner surface of the main member, and an outlet opening formed on an outer peripheral surface of the protrusion portion,
the seal member has a recessed portion recessed toward an axial upstream side, and the protrusion portion of the turbine static blade can be fitted into the recessed portion, and
the outlet opening opens into a gap portion which is formed between an inner peripheral surface of the seal member and the outer peripheral surface of the protrusion portion and which extends in the circumferential direction, on an upstream side with respect to a position of an axial downstream end of the seal member.
12 . The fitting structure according to claim 11 ,
wherein the seal member includes
a first main body portion which is in contact with the combustion gas flow path and extends in an axial direction,
a second main body portion which is connected to the first main body portion at the axial upstream end and extends in a blade height direction, and
a third main body portion which extends in an axial downstream direction from an intermediate position of the second main body portion in the blade height direction,
a plate-shaped fixed seal extending in the circumferential direction along an outer peripheral surface of the third main body portion is disposed on the outer peripheral surface, and
a seal surface is formed between an outer peripheral surface of the fixed seal and the inner peripheral surface of the protrusion portion.
13 . The fitting structure according to claim 11 ,
wherein the shroud includes
an outer shroud formed at an end portion on an outer side a blade height direction of the blade body, and
an inner shroud formed at an end portion on an inner side in the blade height direction of the blade body.
14 . A gas turbine comprising:
the turbine static blade according to claim 1 .
15 . A gas turbine comprising:
the fitting structure according to claim 11 .