Turbine blade and gas turbine

Patent metadata

Field	Value
Publication number	US-2018128116-A1
Application number	US-201615569247-A
Country	US
Kind code	A1
Filing date	Aug 8, 2016
Priority date	Aug 25, 2015
Publication date	May 10, 2018
Grant date	—

Abstract

A blade main body ( 51 ) of a gas turbine is provided with a first cooling passage part ( 58 ), a second cooling passage part ( 59 ), a column part ( 60 ), and a plurality of protrusions. The first cooling passage part ( 58 ) is provided at the side near to a leading edge ( 55 ). The second cooling passage part ( 59 ) is provided at the side near to a trailing edge ( 56 ). The column part ( 60 ) is provided between the first cooling passage part ( 58 ) and the second cooling passage part ( 59 ), and is continuously formed between a base part and an end part of the blade main body ( 51 ). The protrusions protrude from the inner wall surfaces of the first cooling passage part ( 58 ) and the second cooling passage part ( 59 ).

First claim

1 - 10 . (canceled)

11 . A turbine blade comprising a blade main body comprising a leading edge, a trailing edge, and a pressure surface and a suction surface disposed between the leading edge and the trailing edge,
the blade main body comprising: a first cooling passage part disposed near the leading edge, a cooling medium flowing through the first cooling passage part; a second cooling passage part disposed near the trailing edge, the cooling medium flowing through the second cooling passage part; and a column part disposed between the first cooling passage part and the second cooling passage part and continuously formed between a base part and an end part of the blade main body, the first cooling passage part comprising a plurality of cooling passages divided by a partition wall continuously formed between the base part and the end part of the blade main body so that the cooling passages extend in a blade height direction between the column part and the leading edge and are aligned along a mean line, the second cooling passage part comprising a plurality of cooling passages divided by a partition wall so that the cooling passages extend in the blade height direction between the column part and the trailing edge and are aligned along the mean line, and the column part having a thickness in an extending direction of the mean line greater than the thickness of each of the partition walls in the extending direction of the mean line.

12 . A turbine blade comprising a blade main body comprising a leading edge, a trailing edge, and a pressure surface and a suction surface disposed between the leading edge and the trailing edge,
the blade main body comprising: a first cooling passage part disposed near the leading edge, a cooling medium flowing through the first cooling passage part in a flowing direction; a second cooling passage part disposed near the trailing edge, the cooling medium flowing through the second cooling passage part; and a column part disposed between the first cooling passage part and the second cooling passage part and continuously formed between a base part and an end part of the blade main body, the first cooling passage part comprising a plurality of cooling passages divided by a partition wall so that the cooling passages extend in a blade height direction between the column part and the leading edge and are aligned along a mean line, the cooling medium flowing through the cooling passages from the base part to the end part of the blade main body without changing the flowing direction, the second cooling passage part comprising a plurality of cooling passages divided by a partition wall so that the cooling passages extend in the blade height direction between the column part and the trailing edge and are aligned along the mean line, the cooling medium flowing through the cooling passages from the base part to the end part of the blade main body without changing a flowing direction, and the column part having a thickness in an extending direction of the mean line greater than the thickness of each of the partition walls in the extending direction of the mean line.

13 . A turbine blade comprising a blade main body comprising a leading edge, a trailing edge, and a pressure surface and a suction surface disposed between the leading edge and the trailing edge,
the blade main body comprising: a first cooling passage part disposed near the leading edge, a cooling medium flowing through the first cooling passage part; a second cooling passage part disposed near the trailing edge, the cooling medium flowing through the second cooling passage part; and a column part disposed between the first cooling passage part and the second cooling passage part and continuously formed between a base part and an end part of the blade main body, the first cooling passage part comprising a plurality of cooling passages divided by a partition wall so that the cooling passages extend in a blade height direction between the column part and the leading edge and are aligned along a mean line, the second cooling passage part comprising a plurality of cooling passages divided by a partition wall so that the cooling passages extend in the blade height direction between the column part and the trailing edge and are aligned along the mean line, the column part having a thickness in an extending direction of the mean line greater than the thickness of each of the partition walls in the extending direction of the mean line, and the column part comprising no cooling passage through which the cooling medium flows.

14 . The turbine blade according to claim 11 , wherein
the cooling passages of the first cooling passage part comprise a leading edge side cooling passage and a first intermediate cooling passage, the leading edge side cooling passage extending in the blade height direction between the column part and the leading edge, being arranged along the mean line, and being arranged closest to the leading edge, the first intermediate cooling passage being arranged closer to the column part than the leading edge side cooling passage is and having a flow channel cross-sectional area larger than that of the leading edge side cooling passage, and the cooling passages of the second cooling passage part comprise a trailing edge side cooling passage and a second intermediate cooling passage, the trailing edge side cooling passage extending in the blade height direction between the column part and the trailing edge, being arranged along the mean line, and being arranged closest to the trailing edge, the second intermediate cooling passage being arranged closer to the column part than the trailing edge side cooling passage is and having a flow channel cross-sectional area larger than that of the trailing edge side cooling passage.

15 . The turbine blade according to claim 14 , further comprising a plurality of protrusions protruding from an inner wall surface of the first cooling passage part and an inner wall surface of the second cooling passage part.

16 . The turbine blade according to claim 15 , wherein
the protrusions comprise first protrusions and second protrusions smaller than the first protrusions, the first protrusions are disposed in at least one of the first intermediate cooling passage and the second intermediate cooling passage, and the second protrusions are disposed in at least one of the leading edge side cooling passage and the trailing edge side cooling passage.

17 . The turbine blade according to claim 11 , further comprising a tip shroud disposed at a blade tip of the blade main body, wherein
the tip shroud comprises: a first discharge passage discharging the cooling medium flowing through a leading edge side cooling passage arranged closest to the leading edge among the cooling passages of the first cooling passage part; a second discharge passage discharging the cooling medium flowing through a trailing edge side cooling passage arranged closest to the trailing edge among the cooling passages of the second cooling passage part; and a third discharge passage discharging the cooling medium flowing through an intermediate cooling passage disposed between the leading edge side cooling passage and the trailing edge side cooling passage.

18 . The turbine blade according to claim 17 , wherein the first discharge passage extends through the tip shroud in an extending direction of the leading edge side cooling passage.

19 . The turbine blade according to claim 17 , wherein the second discharge passage extends through the tip shroud in an extending direction of the trailing edge side cooling passage.

20 . The turbine blade according to claim 17 , wherein
the third discharge

Assignees

• Mitsubishi Hitachi Power Sys

Inventors

• Takamura Keita
• Hada Satoshi
• Atsumi Hidekatsu

Classifications

• F01D5/22

  Blade-to-blade connections, {e.g. for damping vibrations} · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F01D5/225

  by shrouding · CPC title