US 2026/0092528 A1Published application

Turbine stator vane and gas turbine

AssigneeMitsubishi Heavy Industries, Ltd.

InventorsYasuo MIYAHISA, Saki MATSUO, Shunsuke TORII, Keiya ISHIYAMA

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Abstract

A turbine stator vane includes a first partition wall and a second partition wall which partition the internal space of an airfoil, and a plurality of through-holes penetrating a vane wall constituting the airfoil. The first partition wall extends from the vane wall on the pressure side of the airfoil to the vane wall on the negative pressure side of the airfoil, and is provided at the position nearest to the leading edge. The second partition wall extends from the vane wall on the leading edge side of the airfoil to the first partition wall, and partitions the internal space into a pressure-side leading edge cavity and a negative pressure-side leading edge cavity. An intersection angle between a first virtual straight line and the extending direction of the vane wall is an obtuse angle at the leading edge and an acute angle at the trailing edge.

Claims11

Dependent claims

A turbine stator vane comprising:

a first partition wall and a second partition wall that partition an internal space of an airfoil;
and
a plurality of through-holes that penetrate vane walls constituting the airfoil,
wherein the first partition wall is a partition wall that extends from a pressure surface side connection position, which is a connection position between the first partition wall and the vane wall on a pressure surface side of the airfoil, to a suction surface side connection position, which is a connection position between the first partition wall and the vane wall on a suction surface side of the airfoil, and is provided closest to a leading edge of the airfoil,
the second partition wall extends from a leading edge side connection position, which is a connection position between the second partition wall and the vane wall on a leading edge side of the airfoil, to a trailing edge side connection position, which is a connection position between the second partition wall and the first partition wall, and partitions the internal space into a pressure surface side leading edge cavity and a suction surface side leading edge cavity,
of angles of intersection between a first virtual straight line that passes through the pressure surface side connection position and the suction surface side connection position and an extending direction of the vane wall at the suction surface side connection position, an angle of intersection that is on the leading edge side with respect to the first virtual straight line is an obtuse angle, and an angle of intersection that is on a trailing edge side of the airfoil with respect to the first virtual straight line is an acute angle as seen in a vane height direction of the airfoil,
the through-holes include pressure surface side through-holes that open into the pressure surface side leading edge cavity and suction surface side through-holes that open into the suction surface side leading edge cavity, and
of angles of intersection between a second virtual straight line that passes through the leading edge side connection position and the trailing edge side connection position and a third virtual straight line that passes through the pressure surface side connection position and the trailing edge side connection position, an angle of intersection that is on the pressure surface side with respect to the second virtual straight line and that is on the leading edge side with respect to the third virtual straight line is equal to or greater than 80 degrees and equal to or smaller than 100 degrees as seen in the vane height direction.

5 more elements

A turbine stator vane comprising:

a first partition wall and a second partition wall that partition an internal space of an airfoil;
and
a plurality of through-holes that penetrate vane walls constituting the airfoil,
wherein the first partition wall is a partition wall that extends from a pressure surface side connection position, which is a connection position between the first partition wall and the vane wall on a pressure surface side of the airfoil, to a suction surface side connection position, which is a connection position between the first partition wall and the vane wall on a suction surface side of the airfoil, and is provided closest to a leading edge of the airfoil,
the second partition wall extends from a leading edge side connection position, which is a connection position between the second partition wall and the vane wall on the leading edge side of the airfoil, to a trailing edge side connection position, which is a connection position between the second partition wall and the first partition wall, and partitions the internal space into a pressure surface side leading edge cavity and a suction surface side leading edge cavity,
of angles of intersection between a first virtual straight line that passes through the pressure surface side connection position and the suction surface side connection position and an extending direction of the vane wall at the suction surface side connection position, an angle of intersection that is on the leading edge side with respect to the first virtual straight line is an obtuse angle, and an angle of intersection that is on a trailing edge side of the airfoil with respect to the first virtual straight line is an acute angle as seen in a vane height direction of the airfoil,
the through-holes include pressure surface side through-holes that open into the pressure surface side leading edge cavity and suction surface side through-holes that open into the suction surface side leading edge cavity, and
a third partition wall that extends toward the trailing edge side from the trailing edge side connection position and that partitions the internal space is provided.

5 more elements

A turbine stator vane comprising:

a first partition wall and a second partition wall that partition an internal space of an airfoil;
and
a plurality of through-holes that penetrate vane walls constituting the airfoil,
wherein the first partition wall is a partition wall that extends from a pressure surface side connection position, which is a connection position between the first partition wall and the vane wall on a pressure surface side of the airfoil, to a suction surface side connection position, which is a connection position between the first partition wall and the vane wall on a suction surface side of the airfoil, and is provided closest to a leading edge of the airfoil,
the second partition wall extends from a leading edge side connection position, which is a connection position between the second partition wall and the vane wall on the leading edge side of the airfoil, to a trailing edge side connection position, which is a connection position between the second partition wall and the first partition wall, and partitions the internal space into a pressure surface side leading edge cavity and a suction surface side leading edge cavity,
of angles of intersection between a first virtual straight line that passes through the pressure surface side connection position and the suction surface side connection position and an extending direction of the vane wall at the suction surface side connection position, an angle of intersection that is on the leading edge side with respect to the first virtual straight line is an obtuse angle, and an angle of intersection that is on a trailing edge side of the airfoil with respect to the first virtual straight line is an acute angle as seen in a vane height direction of the airfoil,
the through-holes include pressure surface side through-holes that open into the pressure surface side leading edge cavity and suction surface side through-holes that open into the suction surface side leading edge cavity, and
the first partition wall is linearly formed along the first virtual straight line as seen in the vane height direction.

5 more elements

A turbine stator vane comprising:

a first partition wall and a second partition wall that partition an internal space of an airfoil;
and
a plurality of through-holes that penetrate vane walls constituting the airfoil,
wherein the first partition wall is a partition wall that extends from a pressure surface side connection position, which is a connection position between the first partition wall and the vane wall on a pressure surface side of the airfoil, to a suction surface side connection position, which is a connection position between the first partition wall and the vane wall on a suction surface side of the airfoil, and is provided closest to a leading edge of the airfoil,
the second partition wall extends from a leading edge side connection position, which is a connection position between the second partition wall and the vane wall on the leading edge side of the airfoil, to a trailing edge side connection position, which is a connection position between the second partition wall and the first partition wall, and partitions the internal space into a pressure surface side leading edge cavity and a suction surface side leading edge cavity,
of angles of intersection between a first virtual straight line that passes through the pressure surface side connection position and the suction surface side connection position and an extending direction of the vane wall at the suction surface side connection position, an angle of intersection that is on the leading edge side with respect to the first virtual straight line is an obtuse angle, and an angle of intersection that is on a trailing edge side of the airfoil with respect to the first virtual straight line is an acute angle as seen in a vane height direction of the airfoil,
the through-holes include pressure surface side through-holes that open into the pressure surface side leading edge cavity and suction surface side through-holes that open into the suction surface side leading edge cavity,
the first partition wall is bent at the trailing edge side connection position as seen in the vane height direction, and
the trailing edge side connection position is positioned to be closer to the trailing edge side than the first virtual straight line is.

6 more elements

Dependencies are inferred from the claim text.

Facts

Application: 19/111,513Filed 16 Aug 2023
Priority: JP 2022-14911520 Sep 2022
Published: 2 Apr 2026
Term ends: Not estimatedThe source records don’t support an estimate.

Classification12 codes

F01D 5/186
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: film cooling
F01D 5/187
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: convection cooling
F01D 5/189
With an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall: the insert having a tubular cross-section, e.g.…
F01D 9/041
Forming ring or sector: using blades