Turbine blade and gas turbine

Patent metadata

Field	Value
Publication number	US-10890073-B2
Application number	US-201615576090-A
Country	US
Kind code	B2
Filing date	Aug 23, 2016
Priority date	Aug 25, 2015
Publication date	Jan 12, 2021
Grant date	Jan 12, 2021

Abstract

A turbine blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a leading edge-side cooling passage (64), a trailing edge-side cooling passage (67), and a middle cooling passage (65). The tip shroud (52) is provided with a first discharge passage (72), a second discharge passage (73), and a third discharge passage (74). The first discharge passage (72) discharges a cooling medium flowing through the leading edge-side cooling passage (64). The second discharge passage (73) discharges a cooling medium flowing through the trailing edge-side cooling passage (67). The third discharge passage (74) discharges a cooling medium flowing through the middle cooling passage (65).

First claim

The invention claimed is:

1. A turbine blade, comprising a blade main body having a leading edge and a trailing edge, and having a positive pressure surface and a negative pressure surface between the leading edge and the trailing edge, wherein
the blade main body comprises a cooling passage where a cooling medium flows, demarcated and formed by an inner peripheral wall extending along the positive pressure surface and the negative pressure surface of the blade main body,
the cooling passage comprises:
a first cooling passage portion provided near the leading edge;
a second cooling passage portion provided near the trailing edge; and
a pillar portion provided between the first cooling passage portion and the second cooling passage portion,

the first cooling passage portion comprises:
a leading edge-side cooling passage provided near the leading edge; and
a first middle cooling passage demarcated by a partition wall from the leading edge-side cooling passage and provided near the pillar portion,

the second cooling passage portion comprises:
a trailing edge-side cooling passage provided near the trailing edge; and
a second middle cooling passage demarcated by a partition wall from the trailing edge-side cooling passage and provided near the pillar portion,

a first mechanism that hinders a flow of a cooling medium flowing through the first middle cooling passage is provided such that the flow velocity of a cooling medium flowing through the leading edge-side cooling passage is higher than the flow velocity of the cooling medium flowing through the first middle cooling passage,
a second mechanism that hinders a flow of a cooling medium flowing through the second middle cooling passage is provided such that the flow velocity of a cooling medium flowing through the trailing edge-side cooling passage is higher than the flow velocity of the cooling medium flowing through the second middle cooling passage,
a flow channel cross-sectional area of the leading edge-side cooling passage is smaller than a flow channel cross-sectional area of the first middle cooling passage, and
a flow channel cross-sectional area of the trailing edge-side cooling passage is smaller than a flow channel cross-sectional area of the second middle cooling passage.

2. The turbine blade according to claim 1 , comprising a tip shroud provided on a blade tip of the blade main body, wherein
the tip shroud comprises:
a first discharge passage that discharges the cooling medium flowing through the leading edge-side cooling passage;
a second discharge passage that discharges the cooling medium flowing through the trailing edge-side cooling passage;
a third discharge passage that discharges the cooling medium flowing through the first middle cooling passage; and
a fourth discharge passage that discharges the cooling medium flowing through the second middle cooling passage, and
a passage length of each of the third discharge passage and the fourth discharge passage is longer than a passage length of each of the first discharge passage and the second discharge passage.

3. The turbine blade according to claim 2 , wherein the first discharge passage penetrates the tip shroud in a blade height direction, and extends such that the leading edge-side cooling passage is extended in the blade height direction.

4. The turbine blade according to claim 2 , wherein the second discharge passage penetrates the tip shroud in the blade height direction, and extends such that the trailing edge-side cooling passage is extended in the blade height direction.

5. The turbine blade according to claim 2 , wherein
the third discharge passage includes a first passage main body portion extending in a direction intersecting the blade height direction,
the fourth discharge passage includes a second passage main body portion extending in a direction intersecting the blade height direction, and
each of the first passage main body portion and the second passage main body portion opens in a side surface of the tip shroud.

6. The turbine blade according to claim 5 , wherein
the third discharge passage includes a first cavity portion connected to the first middle cooling passage and having a larger flow channel cross-sectional area than the first middle cooling passage,
the fourth discharge passage includes a second cavity portion connected to the second middle cooling passage and having a larger flow channel cross-sectional area than the second middle cooling passage,
the first passage main body portion extends from the first cavity portion in a direction intersecting the blade height direction, and opens in the side surface of the tip shroud, and
the second passage main body portion extends from the second cavity portion in a direction intersecting the blade height direction, and opens in the side surface of the tip shroud.

7. A gas turbine, comprising the turbine blade according to claim 1 .

8. The turbine blade according to claim 1 , wherein a width in a camber line direction of each of the partition walls is smaller than a width in the camber line direction of the pillar portion.

Assignees

• Mitsubishi Hitachi Power Sys
• Mitsubishi Power Ltd

Inventors

• Takamura Keita
• Hada Satoshi
• Atsumi Hidekatsu

Classifications

• F02C7/18

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

• F05D2240/81

  Cooled platforms · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title