WO2015034150A2

WO2015034150A2 - Blade for gas turbine

Info

Publication number: WO2015034150A2
Application number: PCT/KR2014/002210
Authority: WO
Inventors: 조명환; 심재경
Original assignee: 삼성테크윈 주식회사
Priority date: 2013-09-04
Filing date: 2014-03-17
Publication date: 2015-03-12
Also published as: KR20150027630A; WO2015034150A3

Abstract

A blade for a gas turbine comprises: a blade part comprising a front edge part and a rear edge part and having a streamlined cross section; a supporting part comprising inlets in which compressed air flows from the outside and supporting one end of the blade part; and a plurality of serpentine channels of which one end is connected with each inlet and which extend in parallel inside of the blade part so as to enable the compressed air received through each inlet to pass therethrough.

Description

Blades for Gas Turbines

Embodiments relate to blades for gas turbines, and more particularly, to blades for gas turbines, wherein the blades are cooled uniformly throughout and can increase the operating efficiency of the gas turbine.

A gas turbine is a device that generates power by compressing air by a compressor and burning fuel to heat the compressed air and then expand the air through the turbine. The gas turbine has a turbine blade in contact with the combustion gas, and as the output of the gas turbine increases, the temperature of the combustion gas also increases, so the turbine blade must be able to be cooled efficiently.

In general, turbine blades are cooled using compressed cooling air extracted from a compressor of a gas turbine. Since the compressed air compressed by the compressor is produced for use in the combustor of the gas turbine, increasing the amount of compressed air extracted from the compressor for cooling the turbine blades lowers the overall efficiency of the gas turbine.

Korean Laid-Open Patent Publication No. 2013-0023353 installs a meandering flow path (snake flow path) which is bent and extends along the inside of the turbine blade, but in order to uniformly cool the entire high-temperature turbine blade, the meandering flow path is formed in the entire turbine blade. Many bends should be formed to extend along the area. This increases the pressure loss of the compressed air passing through the meandering flow path and reduces the overall efficiency of the gas turbine since the use of high pressure compressed air is required to achieve cooling performance.

Japanese Laid-Open Patent Publication No. 2001-132406 attempts to improve the cooling effect of the end of the turbine blade by installing a meandering flow path inside the turbine blade and adding a separate flow path to the end of the turbine blade. When using a flow path, there is a limit in uniformly cooling the entire area of the hot turbine blade.

Korean Laid-Open Patent Publication No. 2006-0030114 is provided with a plurality of cooling ducts inside the turbine blades, and through a bore in the switching portion of the cooling ducts to prevent a portion of the turbine blades from being heated to a high temperature. A technique for further supplying compressed air for cooling is disclosed. According to such a configuration, since the amount of compressed air extracted from the compressor must be increased, not only the operation efficiency of the gas turbine is lowered, but also the cooling effect is uniform so that the overall temperature distribution of the turbine blade is uniform.

Japanese Laid-Open Patent Publication No. 2003-322003 attempts to reduce the amount of compressed air required for cooling by installing a serpentine flow path (a meandering flow path), a front supply flow path, and a rear supply flow path inside the turbine blade. Heat may be concentrated in a portion of the cooling effect so that the overall temperature distribution of the turbine blades is uniform.

An object of the embodiments is to provide a blade for a gas turbine with improved cooling efficiency.

Another object of the embodiments is to minimize the pressure loss of the compressed air used to cool the blades for the gas turbine.

Another object of the embodiments is to uniformly cool the entire area of the blade for the gas turbine.

A blade for a gas turbine according to an embodiment includes a wing having a leading edge and a trailing edge and having a streamlined cross section, an inlet through which compressed air is introduced from the outside, and a support for supporting one end of the wing, and one end of the inlet. It is provided with a plurality of meandering passages connected to each of which extends in parallel in the interior of the wing to pass the compressed air introduced from the inlets.

The meandering flow passages are connected to the inlets, and extend inflow passages extending along the leading edge from one end to the other end of the wing, discharge passages extending along the trailing edge of the wing, and an intermediate path connecting the inflow passages and the discharge flow passages. Flow paths may be provided.

The meandering flow passages are connected to each of the inflow passages and bent at the other ends of the wings and connected to the intermediate flow passages, and connected to each of the intermediate flow passages and bent at one end of the wing and connected to the discharge passages. Lower curved flow paths may be further provided.

The meandering flow passages may include a first flow passage, a second flow passage, and a third flow passage arranged in parallel from the leading edge of the wing.

The wing may include front through holes formed through the leading edge to connect the inflow passage of the first flow passage to the outside.

The wing unit may include upper holes formed through the other end of the wing unit to connect the upper curved passage and the discharge passage of the first passage to the outside.

The wing may include rear holes formed through the trailing edge portion to connect the discharge passage of the third flow passage to the outside.

The wing portion may have intermediate through holes formed to penetrate the meandering passages to the outside at an intermediate surface connecting the leading edge and the trailing edge.

The intermediate through holes may have first intermediate through holes connecting at least one of the inflow passages to the outside.

The intermediate apertures may have second intermediate apertures that connect at least one of the intermediate passages to the outside.

The intermediate apertures may have third intermediate apertures connecting at least one of the discharge passages to the outside.

At least one of the lower bends can be enlarged to pass through the support.

The wing portion may be reduced in cross-sectional area from one end to the other end.

The blade for a gas turbine according to another embodiment has a streamlined cross-section having a support having an inlet through which compressed air is introduced from the outside, and having one end connected to the support and extending from the one end to the other end and extending from the one end to the other. Wing part having a discharge, connected to each of the inlets so that the compressed air introduced from the inlet flows into the inlet flow paths extending along the leading edge of the wing and extending along the trailing edge of the wing is discharged from the other end of the wing to the outside It includes a plurality of meandering passages extending in parallel with intermediate passages connecting the passages and the inflow passages and the discharge passages.

According to the blade for a gas turbine according to the embodiments as described above has a plurality of meandering flow paths extending in parallel in the inside of the wing, it is possible to minimize the pressure of the compressed air required for cooling the overall operating efficiency of the gas turbine This is greatly increased.

In addition, since a plurality of meandering flow paths installed to extend in parallel in the inside of the wing may perform a cooling function independently of each other, the entire area of the wing may be uniformly cooled.

1 is a perspective view of a blade for a gas turbine according to one embodiment.

FIG. 2 is a conceptual diagram schematically illustrating a layout structure of a cooling channel of the blade for a gas turbine of FIG. 1.

3 is a cross-sectional view of the blade for the gas turbine of FIG. 1.

4 is a cross-sectional view taken along the line VI-VI of the blade for the gas turbine of FIG. 3.

FIG. 5 is a cross-sectional view taken along the line VV of the blade for the gas turbine of FIG. 3.

FIG. 6 is a photograph of simulation data showing pressure loss of a blade for a gas turbine of the comparative example manufactured for comparison with the blade for a gas turbine of FIG. 1.

7 is a simulation data photograph showing the pressure loss during operation of the blade for a gas turbine.

Hereinafter, with reference to the embodiments of the accompanying drawings, the configuration and operation of the blade for the gas turbine according to the embodiments will be described in detail. The expression 'and / or' as used in the description refers to one or a combination of elements.

1 is a perspective view of a blade for a gas turbine according to one embodiment, and FIG. 2 is a conceptual view schematically showing a structure of a cooling channel of the blade for a gas turbine of FIG. 1, and FIG. 3 is a diagram of the blade for a gas turbine of FIG. 1. It is a cross section.

The gas turbine blade 100 according to the embodiment shown in FIGS. 1 to 3 has a streamlined wing portion 20, a support portion 10 for supporting the wing portion 20, and an inside of the wing portion 20. It has meandering flow paths 7 which are formed.

The bottom 20b of one end of the wing 20 is connected to the support 10, and the wing 20 extends in a direction away from the support 10. The wing unit 20 is a part that serves to generate a rotational force by contacting the hot combustion gas of the gas turbine.

The wing portion 20 has a streamlined cross section, is located on the upstream side of the flow of air, and the front edge portion 20f is in contact with the hot air first, and the trailing edge portion 20r located on the downstream side of the flow of air. And an intermediate surface 20m which connects the leading edge portion 20f and the trailing edge portion 20r and forms a streamlined curved surface.

2 and 3, meandering passages 7 through which compressed air passes are formed in the wing 20 to uniformly cool the blade 100 for the gas turbine as a whole. . The meandering flow paths 7 are bent and formed in a shape such that a snake twists and passes inside the wing 20.

The meandering passages 7 of the blade 100 for a gas turbine according to the embodiment are arranged in parallel and extend in the same direction, the first passage 30, the second passage 40, and the third passage 50. ). The 1st flow path 30, the 2nd flow path 40, and the 3rd flow path 50 are arrange | positioned in parallel from the leading edge part 20f of the blade | wing part 20 in order.

In the illustrated embodiment, the meandering passages 7 are made up of three flow paths, but the embodiment is not limited to the number of meandering passages 7 and may vary in various numbers according to the size of the wing 20. It can be modified.

One end of the wing 20 is supported by the support 10. The support 10 supports the wing 20 and functions to connect the blade 100 for the gas turbine to the body of the blade assembly. The support part 10 includes

inlets

31a, 41a, and 51a through which compressed air is introduced from the outside.

Each of the

inlets

31a, 41a, 51a of the support 10 is connected to one end of the meandering passages 7. When the compressed air supplied from the outside is introduced through the

inlets

31a, 41a, and 51a of the support 10, the compressed air can flow along the meandering passages 7 through the entire area of the wing 20. have.

The meandering flow paths 7 include

inlet flow paths

31, 41, and 51 extending along the leading edge part 20f in a direction from the one end of the wing part 20 toward the other end (Z-axis direction).

Discharge passages

35, 45, 55 extending along the trailing edge portion 20r of 20, each of the

inflow passages

31, 41, 51 and each of the

discharge passages

35, 45, 55. Intermediate flow paths (33, 43, 53) for connecting the.

The inflow passage 31 of the first flow passage 30 is disposed to contact the leading edge 20f of the wing portion 20. The leading edge portion 20f includes front through holes 21 formed to penetrate the inflow passage 31 of the first flow passage 30 to the outside. The front through holes 21 may be formed to be inclined with respect to the direction from one end of the wing portion 20 toward the other end. The front through holes 21 discharge a portion of the compressed air passing through the first flow path 30 to the outside of the wing 20 so that the compressed air covers the leading edge 20f to cover the leading edge film. By forming, the front edge 20f can be cooled.

Each of the

inflow passages

31, 41, and 51 is connected to the upper

curved passages

32, 42, and 52. The upper

curved flow paths

32, 42, and 52 are bent at the other end of the wing 20 and are connected to each of the

intermediate flow paths

33, 43, and 53.

4 is a cross-sectional view taken along the line VI-VI of the blade for the gas turbine of FIG. 3, and FIG. 5 is a cross-sectional view taken along the line V-V of the blade for the gas turbine of FIG.

The wing 20 has a cross-sectional area that decreases from one end connected to the support 10 to the other end. The wing 20 maintains a streamlined cross-sectional shape with respect to the entire area from one end to the other end.

In Figs. 4 and 5, each of the circle with the arrow and the dot inside and the circle with the x-shape therein indicates the traveling direction of the compressed air flowing along the inside of the meandering flow paths 7. A circle with a dot therein indicates a flow of compressed air traveling in a direction exiting the drawing, and a circle with x-shape inside indicates a flow of compressed air traveling in a direction entering the drawing.

The upper curved flow path 32 of the first flow path 30 among the upper

curved flow paths

32, 42, and 52 is disposed to contact the upper surface portion 20t of the other end of the wing portion 20.

The wing portion 20 has upper holes 23 formed to penetrate the upper surface portion 20t. The upper through holes 23 connect the upper curved flow path 32 and the upper ends of the

discharge flow paths

35, 45, and 55 of the first flow path 30 to the outside. The upper through holes 23 allow a part of the compressed air passing through the first flow path 30 to be discharged to the outside of the wing 20, so that the other end of the wing 20 is discharged by the discharged compressed air. It functions to cool.

The

intermediate passages

33, 43, 53 extend in a direction substantially parallel to the

inflow passages

31, 41, 51 and the

intermediate passages

33, 43, 53. The

intermediate flow paths

33, 43, 53 are connected to the lower

bend flow paths

34, 44, 54 formed at one end of the wing 20. Lower

curved flow paths

34, 44, and 54 are connected to each of the

intermediate flow paths

33, 43, and 53, and are bent at one end of the wing 20 so that each of the

discharge flow paths

35, 45, and 55 are respectively. Is connected to.

The lower curved flow path 34 of the first flow path 30 among the lower

curved flow paths

34, 44, and 54 extends from one end of the wing part 20 toward the support part 10 so as to pass through the support part 10. It is provided with an enlarged portion 54b. The embodiment is not limited by the structure of the enlarged portion 54b, and the lower curved flow paths 44 of the second flow path 40 or the third flow path 50 among the lower

curved flow paths

34, 44, and 54. , 54 may also extend to extend toward the support 10.

The

discharge passages

35, 45, and 55 extend in parallel along the trailing edge portion 20r in a direction from one end of the wing portion 20 toward the other end (Z-axis direction). The discharge flow path 55 of the third flow path 50 among the

discharge flow paths

35, 45, and 55 is disposed to contact the trailing edge portion 20r of the wing portion 20.

The wing portion 20 has rear holes 24 formed to penetrate the trailing edge portion 20r. The rear through holes 24 connect the discharge passage 55 of the third passage 50 to the outside. The rear through holes 24 allow a part of the compressed air passing through the third flow path 50 to be discharged to the outside of the wing 20, and thus the rear edge portion 20r of the wing 20 by the discharged compressed air. It functions to cool.

Referring to FIG. 1,

intermediate apertures

22a, 22b, 22c are formed in the intermediate surface 20m connecting the front edge 20f and the trailing edge 20r of the wing 20. The intermediate through

holes

22a, 22b and 22c are formed to penetrate the intermediate surface 20m to connect the meandering passages 7 to the outside.

The intermediate through

holes

22a, 22b and 22c allow the compressed air passing through the meandering passages 7 to be discharged to the outside of the wing 20 so that the compressed air forms a film on the intermediate surface 20m so that the intermediate surface (20m) to cool the film (film cooling).

The intermediate through

holes

22a, 22b, and 22c may be formed of the first intermediate through holes 22a connecting at least one of the

inflow passages

31, 41, and 51 to the outside, and the intermediate through

holes

33, 43, 53. Second intermediate holes 22b connecting at least one to the outside and third intermediate holes 22c connecting at least one of the

discharge passages

35, 45 and 55 to the outside.

Embodiments are defined by the position and number of arrangement of the front through holes 21, the upper through holes 23, the rear through holes 24, and the intermediate through

holes

22a, 22b and 22c shown in the drawings. It can be modified in various arrangements and numbers.

6 is a meandering line having a first flow path 30, a second flow path 40, and a third flow path 50 in the wing 20 of the blade for the gas turbine shown in the embodiment shown in FIGS. 1 to 5. The degree of pressure loss when the flow paths 7 are provided is shown.

Referring to FIG. 6, even when compressed air having a relatively low pressure of 2.449 X 10 ⁶ Pa is supplied to the meandering passages 7, the minimum pressure inside the meandering passages 7 becomes 2.349 X 10 ⁶ Pa. . That is, by using the plurality of meandering passages 7, the pressure of the compressed air required for cooling the wing 20 may be greatly reduced.

FIG. 7 shows the degree of pressure loss when a meandering passage 307 is provided on the wing 300 of the blade for the gas turbine, which continues and extends along the inside of the wing 300.

When installing one meandering flow path 307 in the wing 300, in order to uniformly cool the entire area of the wing 300, the bent portion (307a, 307b) must be provided a lot. However, as the number of

bends

307a and 307b of the meandering passage 307 increases, the pressure loss of the compressed air in the meandering passage 307 increases.

Referring to FIG. 7, the compressed air having a high pressure of 3.20 × 10 ⁶ Pa needs to be supplied to the meandering passage 307 so that the minimum pressure value is 2.35 × 10 ⁶ Pa in the meandering passage 307.

To increase the pressure of the compressed air, compressed air extracted from the high compression stage of the gas turbine should be used. If the pressure of the compressed air required to cool the blade for the gas turbine is increased, the overall efficiency of the gas turbine is reduced because high pressure compressed air has to be consumed for cooling.

However, according to the blade for a gas turbine according to the embodiment shown in FIGS. 1 to 6, since the pressure of the compressed air required for cooling the wing portion 20 can be minimized, the overall operating efficiency of the gas turbine is greatly increased.

In addition, as shown in FIG. 7, when one meandering passage is installed on the wing to extend long, the temperature of the compressed compressed air passing through the meandering passage increases toward the rear end of the meandering passage, so that cooling in some areas of the wing is effectively performed. Can't be done.

However, in the blade for the gas turbine according to the embodiment shown in FIGS. 1 to 6, since a plurality of meandering passages 7 are installed to extend in parallel, a path through which compressed air passes in each of the meandering passages 7 is determined. The shortened time for which the heated compressed air stays inside the wing 20 is reduced. That is, since each of the meandering flow paths 7 arranged in parallel may independently perform a cooling function, uniform cooling may be performed over the entire area of the wing 20.

The configuration and effects of the above-described embodiments are merely exemplary, and it will be understood by those skilled in the art that various modifications and equivalent other embodiments are possible. Therefore, the true technical protection scope of the invention should be defined by the appended claims.

Embodiments relate to blades for a gas turbine that can cool the wings uniformly throughout and increase the operating efficiency of the gas turbine.

Claims

A wing having a leading edge and a trailing edge and having a streamlined cross section;

A support part having one inlet port through which compressed air is introduced from the outside and supporting one end of the wing part; And

And a plurality of meandering passages, one end of which is connected in parallel to each of the inlets and extends in parallel in the wing to allow compressed air introduced from the inlets to pass therethrough.
The method of claim 1,

The meandering euros,

Inflow passages connected to the inlets and extending along the leading edge toward the other end from the one end of the wing, discharge passages extending along the trailing edge of the wing, the inflow passages and the discharge passage. A blade for a gas turbine, having intermediate flow paths connecting the two.
The method of claim 2,

The meandering euros,

Upper curved flow paths connected to each of the inflow passages and bent at the other end of the wing part and connected to the intermediate flow paths, and connected to each of the intermediate flow paths, and are bent at the one end of the wing part to discharge the discharge flow path. A blade for a gas turbine, further comprising lower curved flow paths connected to the field.
The method of claim 3,

The meandering flow passages include a first flow passage, a second flow passage, and a third flow passage arranged in parallel from the leading edge of the wing portion, the blade for a gas turbine.
The method of claim 3,

The blade portion has a gas turbine blade having front through-holes formed through the leading edge to connect the inflow passage of the first flow passage to the outside.
The method of claim 3,

The blade unit has a gas turbine blade having upper through-holes formed through the other end of the wing portion to connect the upper curved flow path and the discharge flow path of the first flow path with the outside.
The method of claim 3,

The blade portion has a gas turbine blade having back through-holes formed through the trailing edge portion to connect the discharge passage of the third flow path to the outside.
The method of claim 3,

And the wing portion has intermediate through holes formed to penetrate the meandering passages to the outside at an intermediate surface connecting the leading edge portion and the trailing edge portion.
The method of claim 8,

Wherein said intermediate apertures have first intermediate apertures connecting at least one of said inflow passages to the outside.
The method of claim 8,

And the intermediate apertures have second intermediate apertures connecting at least one of the intermediate passages to the outside.
The method of claim 8,

And the intermediate apertures have third intermediate apertures connecting at least one of the discharge passages to the outside.
The method of claim 3,

At least one of the lower bends extends through the support.
The method of claim 3,

The blade portion is a gas turbine blade, the cross-sectional area is reduced from the one end to the other end.
A support having inlets through which compressed air is introduced from the outside;

A wing portion having one end portion connected to the support portion and having a leading edge portion and a trailing edge portion extending from the one end portion to the other end portion and having a streamlined cross section; And

Inflow passages connected to each of the inlets so that the compressed air introduced from the inlets are introduced and extend along the leading edge of the wing, and extend along the trailing edge of the wing to extend from the other end of the wing to the outside. And a plurality of meandering passages extending in parallel with discharge passages connected to each other, and intermediate passages connecting the inflow passages and the discharge passages.
The method of claim 14,

The meandering euros,

Upper curved flow paths connected to each of the inflow passages and bent at the other end of the wing part and connected to the intermediate flow paths, and connected to each of the intermediate flow paths, and are bent at the one end of the wing part to discharge the discharge flow path. A blade for a gas turbine, further comprising lower curved flow paths connected to the field.
The method of claim 15,

The blade portion comprises a front through-holes formed through the leading edge to connect any one of the inflow passages to the outside, blade for a gas turbine.
The method of claim 15,

The blade portion has a gas turbine blade having upper through holes formed through the other end of the wing portion to connect any one of the upper curved passages and the discharge passage to the outside.
The method of claim 15,

The blade portion has a blade for the gas turbine having a rear through-hole formed through the trailing edge portion to connect any one of the discharge passage to the outside.
The method of claim 15,

And the wing portion has intermediate through holes formed to penetrate the meandering passages to the outside at an intermediate surface connecting the leading edge portion and the trailing edge portion.