Turbine blade and gas turbine

Patent metadata

Field	Value
Publication number	US-12281594-B2
Application number	US-202218708086-A
Country	US
Kind code	B2
Filing date	Nov 25, 2022
Priority date	Dec 7, 2021
Publication date	Apr 22, 2025
Grant date	Apr 22, 2025

Abstract

A turbine blade includes a blade body, cooling passages extending in the blade height direction inside the blade body and connected to each other via folded portions, and a bypass portion that is provided in a partition wall portion partitioning a pair of adjacent cooling passages and that allows the pair of cooling passages to communicate with each other. The pair of cooling passages includes an upstream passage and a downstream passage. The turbine blade is provided with: a plurality of cooling holes formed in the blade body so as to be arranged along the blade height direction, that communicate with the downstream passage, and open in the surface of the blade body; a plurality of turbulators provided on the inner wall surface of the downstream passage and arranged along the blade height direction; or a thermal barrier coating that covers the surface of the blade body.

First claim

The invention claimed is:

1. A turbine blade comprising:
a blade body;
a plurality of cooling passages that extend along a blade height direction inside the blade body and are connected to each other via a folded portion; and
a bypass portion that is provided in a partition wall portion for partitioning a pair of adjacent cooling passages among the plurality of cooling passages and allows the pair of cooling passages to communicate with each other, wherein
the pair of cooling passages includes an upstream-side passage and a downstream-side passage located on a downstream side of the upstream-side passage with respect to a flow of a cooling fluid,
the turbine blade includes a plurality of cooling holes, the plurality of cooling holes being formed in the blade body so as to be arranged along the blade height direction, communicating with the downstream-side passage, and being open to a surface of the blade body,
values of parameters indicating characteristics of the plurality of cooling holes are different between an upstream-side region and a downstream-side region, the upstream-side region being located on an upstream side of a position corresponding to the bypass portion in the blade height direction with respect to the flow of the cooling fluid in the downstream-side passage, and the downstream-side region being located on a downstream side of the upstream-side region with respect to the flow of the cooling fluid in the downstream-side passage, and

at least one of the following conditions (i) to (iv) is satisfied:
(i) an opening density of the plurality of cooling holes is lower in the downstream-side region than in the upstream-side region;
(ii) a pitch of a pair of cooling holes in the blade height direction is larger in the downstream-side region than in the upstream-side region, the pair of cooling holes being adjacent to each other in the blade height direction;
(iii) a diameter of the plurality of cooling holes is smaller in the downstream-side region than in the upstream-side region; and
(iv) surface roughness of inner wall surfaces of the plurality of cooling holes is smaller in the downstream-side region than in the upstream-side region.

2. The turbine blade according to claim 1 , wherein
the turbine blade includes a plurality of turbulators that are provided on an inner wall surface of the downstream-side passage and arranged along the blade height direction, and
an angle between a direction of the flow of the cooling fluid in the downstream-side passage and an extending direction of the turbulators is different in the downstream-side region and the upstream-side region.

3. The turbine blade according to claim 1 , wherein
the downstream-side passage is a cooling passage located closest to a leading edge side or closest to a trailing edge side in a chord direction of the blade body among the plurality of cooling passages, and
the position corresponding to the bypass portion in the blade height direction is located on a downstream side of the bypass portion with respect to the flow of the cooling fluid in the downstream-side passage.

4. A gas turbine comprising:
the turbine blade according to claim 1 ; and
a combustor that generates a combustion gas flowing through a combustion gas passage in which the turbine blade is provided.

5. A turbine blade comprising:
a blade body;
a plurality of cooling passages that extend along a blade height direction inside the blade body and are connected to each other via a folded portion; and
a bypass portion that is provided in a partition wall portion for partitioning a pair of adjacent cooling passages among the plurality of cooling passages and allows the pair of cooling passages to communicate with each other, wherein
the pair of cooling passages includes an upstream-side passage and a downstream-side passage located on a downstream side of the upstream-side passage with respect to a flow of a cooling fluid,
the turbine blade includes a plurality of turbulators, the plurality of turbulators being provided on an inner wall surface of the downstream-side passage and arranged along the blade height direction,
values of parameters indicating characteristics of the plurality of turbulators are different between an upstream-side region and a downstream-side region, the upstream-side region being located on an upstream side of a position corresponding to the bypass portion in the blade height direction with respect to the flow of the cooling fluid in the downstream-side passage, and the downstream-side region being located on a downstream side of the upstream-side region with respect to the flow of the cooling fluid in the downstream-side passage, and
at least one of the following conditions (i) to (iii) is satisfied:
(i) the plurality of turbulators are provided such that a heat transfer coefficient between the cooling fluid and the inner wall surface of the downstream-side passage is smaller in the downstream-side region than in the upstream-side region;
(ii) a pitch of the plurality of turbulators in the blade height direction is larger in the downstream-side region than in the upstream-side region; and
(iii) a height of the turbulators with reference to the inner wall surface of the downstream-side passage is lower in the downstream-side region than in the upstream-side region.

6. A gas turbine comprising:
the turbine blade according to claim 5 ; and
a combustor that generates a combustion gas flowing through a combustion gas passage in which the turbine blade is provided.

7. A turbine blade comprising:
a blade body;
a plurality of cooling passages that extend along a blade height direction inside the blade body and are connected to each other via a folded portion; and
a bypass portion that is provided in a partition wall portion for partitioning a pair of adjacent cooling passages among the plurality of cooling passages and allows the pair of cooling passages to communicate with each other, wherein
the pair of cooling passages includes an upstream-side passage and a downstream-side passage located on a downstream side of the upstream-side passage with respect to a flow of a cooling fluid,
the turbine blade includes a thermal barrier coating that covers a surface of the blade body,
values of parameters indicating characteristics of the plurality of cooling holes are different between an upstream-side region and a downstream-side region, the upstream-side region being located on an upstream side of a position corresponding to the bypass portion in the blade height direction with respect to the flow of the cooling fluid in the downstream-side passage, and the downstream-side region being located on a downstream side of the upstream-side region with respect to the flow of the cooling fluid in the downstream-side passage, and
a thickness of the thermal barrier coating is smaller in the downstream-side region than in the upstream-side region.

8. A gas turbine comprising:
the turbine blade according to claim 7 ; and
a combustor that generates a combustion gas flowing through a combustion gas passage in which the turbine blade is provided.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Hirayama Taku
• Ito Ryuta

Classifications

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2260/202

  by film cooling · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• F01D5/183

  Blade walls being porous · CPC title