Manufacturing method of combustor liner

Description: TECHNICAL FIELD [Detailed description of the invention]

【0001】

[Industrial application field]

The present invention relates to a method for manufacturing a combustor liner for a gas turbine.

【0002】

[Conventional technology]

As a conventional technique, as described in Japanese Patent Publication No. 59-49493 shown in FIGS. 8 and 9, a plurality of coolings in which cooling air flowing outside the gas turbine combustor liner 2 is provided in the circumferential direction of the liner 2 are provided. The structure was such that cooling air was ejected in the flow direction of the combustion gas through the overhanging lip 8 inside the liner 2 through which the combustion gas flowed through the air hole 9. In this structure, the liner 2 is cooled mainly by convection cooling by the cooling air on the outside of the liner 2 and the pressure difference between the cooling air pressure on the outside of the liner 2 and the pressure on the inside of the liner through which the combustion gas flows. The wall of line 2 was cooled by film cooling with cooling air flowing through the cooling hole 9. Due to this structure, the cooling air flowing from the cooling air hole 9 flows along the inner wall of the liner 2 by the lip 8, and the combustion gas flowing near the inner wall of the liner flows along the inner wall of the liner relatively flatly by the lip 8. And pour it into the turbine section (not shown). However, the cooling air that flows from the cooling air hole 9 and flows along the inner wall of the liner 2 is effective for cooling the liner wall, but has the disadvantage that it is used only for cooling and flows into the turbine section and is not used as combustion air. there were.

【0003】

[Problems to be Solved by the Invention]

When cooling the combustor liner by eliminating the membrane cooling and strengthening the cooling by convection, the purpose is to supplement the amount of cooling heat that the membrane cooling has been responsible for so far. The film-cooled lip 8 which is the conventional cooling method has a double structure together with the integrated liner material, and is also effective for maintaining the strength of the liner 2.

【0004】

[Means for solving problems]

Convex ribs are formed on the circumferential cooling air flow side path of the integral material forming the liner, and an integral rib provided with a plurality of the ribs in the axial direction and a joint convex rib provided by a plurality of joints are provided. , A material of the same quality as the integral rib material is joined to the inside of the integral rib so that there are no voids and the inner side wall of the liner is flat. A method for manufacturing a liner in which the width of the integral rib is A, the height is H, the width of the joint rib is a, and the height is h, and A a and H h.

【0005】

[Action]

The one-piece material that forms the liner is formed into a liner structure in which convex ribs are formed on the side of the cooling air flow path in the circumferential direction of the liner and a plurality of ribs are provided in the axial direction. The strength can be increased compared to the liner.

【0006】

Since a plurality of convex ribs are provided on the cooling air flow path side, it is possible to promote turbulence of the cooling air on the liner wall surface and promote heat transfer. As a result, the liner wall temperature can be kept low.

【0007】

Since a material of the same quality as the liner is joined to the inside of the integral rib so that the inner wall of the liner has no voids and is at the same height as the inner wall, the combustion gas in contact with the liner wall can flow smoothly.

【0008】

[Example]

Examples of the present invention are shown. FIG. 7 is a block diagram of the gas turbine. The air sucked by the compressor is pressurized and heated and sent to the combustor. This air burns fuel in the combustor and becomes a higher temperature combustion gas, which expands in the turbine. The turbine drives the compressor and the remaining power drives the load. For example, electricity can be obtained by connecting a generator as a load and rotating it.

【0009】

FIG. 8 is a cross-sectional view of the combustor. The air pressurized and heated by the compressor 1 is sent in the direction indicated by the arrow, and the fuel 3 supplied from another pipe is injected from the pilot burners 4c, F1 fuel nozzle 4a, and F2 fuel nozzle 4b, and is mainly used. Combustion occurs in the combustion zones of combustion chamber R1 and sub-combustion chamber R2. The combustion gas passes through the transition piece 7 and expands in the turbine 6. A high-temperature combustion gas (about 1400 ° C) flows inside the liner 2 of the main combustion chamber R1, and the liner 2 wall temperature becomes high. Although the air flowing outside the liner 2 wall is pressurized and heated, it is lower than the combustion gas temperature (about 380 ° C), so the compressed air flowing outside the liner 2 wall heats the liner 2 wall temperature. Must be cooled to be within the permissible temperature of the material.

【0010】

A perspective view of the combustor liner of the present invention is shown in FIG. 1, and a partially enlarged view of FIG. 1 is shown in FIG. A plurality of integrated ribs 11 formed by shaping the integrated liner material into a convex shape in the liner cooling air flow side path and the liner circumferential direction are formed in the liner axial direction. Joining that promotes cooling of the liner wall The convex rib 10 is joined in the circumferential direction of the liner wall surface on the cooling air flow path side. At this time, the relationship between the width A and the height H of the integral rib and the width a and the height h of the joint convex rib is set so that A a and H = h. A reinforcing material 12 made of the same material as the liner is joined to the inside of the integrated rib 11 without a gap so that the inside of the integrated rib 11 and the reinforcing material 12 are in contact with each other so as to be at the same height as the inner wall of the liner.

【0011】

As shown in FIGS. 3 to 6, the shape of the joint convex rib 10 that promotes the cooling of the liner wall is a quadrangular, trapezoidal, triangular, or chevron shape that is cooled by the air flow velocity (flow rate) and the shape of the joint convex rib 11. Select the required shape according to the relationship between the heat transfer rate (cooling heat amount) and the flow path pressure loss, and make it a joint convex rib shape. The figure shows a case where the cooling air flow direction and the combustion gas flow in a countercurrent manner, but the same relationship holds even if the air flow direction and the combustion gas flow direction become the same parallel flow.

【0012】

[Effect of the invention]

Since the integral material constituting the combustor liner is formed into a convex shape in the liner cooling air flow path side circumferential direction, a plurality of ribs are provided in the liner axial direction, so that the liner strength can be increased.

【0013】

Since convex ribs are provided on the liner wall surface on the cooling air flow path side by joining, the heat transfer coefficient of the liner wall surface due to convection can be improved, and the amount of cooling heat of the liner wall can be increased, so that the liner wall temperature can be kept low and the liner can be kept low. The reliability against creep, heat exhaustion, etc. can be improved, and the service life of the liner can be extended.

【0014】

A material of the same quality as the liner material is joined to the inside of the integrally shaped rib so that the peripheral edge of the combustion gas flow path is flat, so that the combustion gas flows smoothly through the inner wall of the liner and the stagnation point of the combustion gas. Since there are no peeling points, local high temperature parts (hot spots) are eliminated, and local material changes and cracks due to thermal stress are eliminated.

【0015】

Since the liner material and the same material are joined to the inside of the integrally shaped rib so that there are no voids, the heat expansion and contraction are the same, and it is possible to prevent the occurrence of defects due to the heat expansion and contraction non-uniformity due to the combination of different materials. Since there are no voids, the temperature rise in the same part as in the case with voids does not occur.

【0016】

Since the width A and height H of the integrally shaped rib and the width a and height h of the joining rib are set to A a, H = h, the strength of the liner is increased and the flow path on the cooling air side is increased. The pressure loss becomes constant, the generation of uneven flow of cooling air can be prevented, the non-uniformity of liner cooling due to the non-uniform flow velocity distribution can be prevented, and the wall temperature can be made uniform. Further, since the drift is eliminated, it is easy to make the mixture of fuel and air uniform in the combustor, and stable combustion can be maintained.

[Simple explanation of drawings]

[Figure 1]

Perspective view of the combustor liner.

[Figure 2]

Partial sectional view of the combustor liner.

[Fig. 3]

Partial enlarged view of the combustor liner.

[Fig. 4]

Partial enlarged view of the combustor liner.

[Fig. 5]

Partial enlarged view of the combustor liner.

[Fig. 6]

Explanatory drawing of the joint rib shape.

[Fig. 7]

Block diagram of gas turbine.

[Fig. 8]

Sectional view of the combustor.

[Fig. 9]

The liner side view which shows the conventional membrane cooling structure.

[Explanation of symbols]

2 ... liner, 10 ... joint convex ribs, 11 ... integral ribs, 12 ... reinforcements.