JPH0727335A - Production of combustion chamber liner for gas turbine - Google Patents

Abstract

PURPOSE:To provide a method of manufacturing a combustion chamber liner, for use in a gas turbine, which is provided with a cooling passage in its interior and is excellent in cooling function to meet the requirement for a high temperature performance of the gas turbine. CONSTITUTION:The material of a combustion chamber liner 11 is produced by a method wherein a heat resistant, anti-corrosive grooved metal plate 11a having a plurality of grooves 60 formed parallel to one another in the one side face thereof and a heat resistant, anti-corrosive flat metal plate 11b are joined together in such a manner as to include the grooves 60 in their joint faces and such joint faces are welded together along the raised parts between each adjacent groove 60 by laser or electron beam welding process. Therefore, a high temperature strength of the joint parts of the combustion chamber liner members is made equal to that of the members.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method of manufacturing a combustion chamber liner for a gas turbine, and more particularly to a liner material which constitutes a peripheral wall of a combustion chamber of a high temperature gas turbine combustor and which can be cooled with high efficiency. On how to do.

[0002]

2. Description of the Related Art A plurality of gas turbine combustors are installed per gas turbine, and a combustion chamber, which is a main part of the gas turbine, has a cylindrical shape. Fuel is supplied from one end into the cylinder to burn inside the cylinder, and the other end is combusted. It is configured to emit a higher temperature, high pressure gas. Generally, a heat and corrosion resistant alloy is used as a material for the liner forming the peripheral wall of the combustion chamber, and the combustion chamber liner is protected by cooling with high pressure air. Explaining the conventional cooling method in more detail, the outer surface of the combustion chamber liner is cooled by high-pressure air, and since a high temperature combustion gas flow path is formed in the combustion chamber, cooling air is formed into a film on the inner surface of the combustion chamber liner. A flowing film cooling method is adopted to prevent overheating of the combustion chamber liner.

However, in recent years, attempts have been made to increase the temperature and pressure of the combustion gas for the purpose of improving the efficiency of the gas turbine, but as described above, a combined cooling system of cooling the outer surface of the combustion chamber liner and the film cooling of the inner surface is used. However, there is a limit to the cooling effect, and it is not possible to achieve higher efficiency of the combustor.
Further, in order to further improve the efficiency of the combustor, it is required to increase the amount of combustion air as compared with the conventional method and to cool the combustion chamber liner more effectively than before. Therefore, in addition to the above-described cooling method for the inner and outer surfaces of the combustion chamber liner, a cooling method has been devised in which a cooling passage is also provided inside the liner to forcibly send cooling air. However, it does not describe how to form the cooling passages inside the combustion chamber liner. (JP-A 47-9053, JP-A 5
6-168041, JP-A-3-221720) Conventionally, since a certain type of combustion chamber liner has been composed of a single plate, a heat and corrosion resistant alloy plate is formed into a cylindrical shape,
This cylindrical member was used as the combustion chamber. Therefore, it is not necessary to purposely manufacture the material for the combustion chamber liner, which is advantageous in terms of the number of manufacturing steps of the combustor. However, in the combustor manufactured by this method, as described above, since the heat-resistant and corrosion-resistant alloy plate forming the combustion chamber is a single plate, it is not possible to cope with cooling when the combustion temperature rises.

Further, as a method of manufacturing a combustion chamber liner having a cooling passage inside, a method for manufacturing a combustion chamber liner is disclosed in Japanese Patent Laid-Open No. 63-281767.
There is a method of manufacturing a laminated heat-resistant alloy plate disclosed in Japanese Patent Publication No.
In this method, a plurality of grooves are formed in parallel on one surface of one plate, and other plates are stacked so as to cover these grooves,
A combustion chamber wall material is manufactured by joining the contact surfaces of these two plate materials with a Ni-based brazing material, but the melting temperature of the brazing portion is low, so it is necessary to cope with the high temperature of the gas turbine. There was a problem that I could not do it.

[0005]

The present invention has been made in view of the above circumstances, and an object thereof is to provide a gas having an excellent cooling capacity by providing a cooling passage inside thereof in response to a high temperature of a gas turbine. A method of manufacturing a combustion chamber liner for a turbine is provided.

[0006]

In order to achieve the above object, a method of manufacturing a combustion chamber liner for a gas turbine according to the present invention comprises forming a cooling channel inside the combustion chamber liner,
The material of the liner is manufactured by the following process.

In the first manufacturing method, the material of the combustion chamber liner includes a grooved heat resistant and corrosion resistant metal plate having a plurality of grooves formed in parallel on one surface and a flat plate-shaped heat resistant and corrosion resistant metal plate inside. As described above, it is characterized in that they are manufactured by welding them by a laser welding method or an electron beam welding method along a convex portion between adjacent grooves.

The second manufacturing method is that the material of the combustion chamber liner is formed by stacking two grooved heat-resistant and corrosion-resistant metal plates having a plurality of grooves formed in parallel on one surface, with the grooves aligned with each other. It is characterized in that it is manufactured by welding from one side along the convex portion of by a laser welding method or an electron beam welding method.

In the first and second manufacturing methods, it is preferable that the groove of the grooved heat-resistant and corrosion-resistant metal plate is formed by etching, laser machining or electric discharge machining.

The third manufacturing method is that the material of the combustion chamber liner is formed by arranging a plurality of square bar members made of heat-resistant and corrosion-resistant metal in parallel between two heat-resistant and corrosion-resistant metal plates, and the outer surface of each heat-resistant and corrosion-resistant metal plate is arranged. It is characterized in that it is manufactured by welding from a side along a square bar material by a laser welding method or an electron beam welding method.

The fourth manufacturing method is that the corrugated plate made of heat-resistant and corrosion-resistant metal is sandwiched between two heat-resistant and corrosion-resistant metal plates, and the heat-resistant and corrosion-resistant metal plate is placed from the outer surface side of each heat-resistant and corrosion-resistant metal plate. It is characterized in that it is manufactured by welding along the top of the corrugated plate abutting against the laser by a laser welding method or an electron beam welding method.

A fifth manufacturing method uses a material for a combustion chamber liner, a grooved heat-resistant and corrosion-resistant metal plate having a plurality of grooves formed in parallel on one surface, and a flat plate-shaped heat-resistant and corrosion-resistant metal plate, and a heat-resistant and corrosion-resistant metal chemistry. It is characterized in that a foil-shaped insert material made of an alloy having an increased amount of Si and B added to the composition is sandwiched, the grooves are superposed so as to include the groove therein, and they are bonded by a liquid phase diffusion bonding method.

In the sixth manufacturing method, a material for the combustion chamber liner is used, a corrugated plate made of a heat-resistant and corrosion-resistant metal plate is placed between two heat-resistant and corrosion-resistant metal plates, and heat-resistant between each heat-resistant and corrosion-resistant metal plate and the top of the corrugated plate. It is characterized in that it is manufactured by sandwiching a foil-shaped insert material made of an alloy in which Si is added and B is added to the chemical composition of a corrosion-resistant metal, and joining by a liquid phase diffusion joining method.

[0014]

As described above, the grooved heat-resistant and corrosion-resistant metal plate and the flat plate-shaped heat-resistant and corrosion-resistant metal plate are overlapped, or two grooved heat-resistant and corrosion-resistant metal plates are overlapped, or they are placed between two heat-corrosion-resistant metal plates. By arranging a plurality of square bar materials of the same material in parallel or sandwiching a corrugated plate of the same material between two heat-resistant and corrosion-resistant metal plates, by laser welding or electron beam welding Since the combustion chamber liner material is manufactured by joining, the joining portion of the members in the combustion chamber liner can obtain high temperature strength equivalent to that of the members. In addition, a grooved heat and corrosion resistant metal plate and a flat plate heat and corrosion resistant metal plate are superposed, or a corrugated plate made of the same material is sandwiched between two heat and corrosion resistant metal plates, and the heat and corrosion resistance is between the members. Since a combustion chamber liner material is manufactured by interposing a foil-like insert material made of an alloy in which Si is added to the chemical composition of metal and adding B, and is joined by a liquid phase diffusion bonding method, the insert material is Si and Since the melting point is lowered by B to facilitate the joining, and the main component of the joint is almost the same as that of the heat and corrosion resistant metal plate, the high temperature strength of the joint can be made equal to that of the member.

A combustor having a combustion chamber manufactured by forming the liner material manufactured by these methods into a cylindrical shape is capable of forced cooling from the inside of the liner in addition to the cooling method of the conventional combustor. Therefore, not only can the cooling air for the combustion chamber liner be cooled efficiently with a smaller amount than in the past, but the amount of the combustion air can be increased and the efficiency of the gas turbine can be improved.

[0016]

Embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is a schematic configuration diagram of a gas turbine combustor provided with a combustion chamber liner manufactured according to the present invention, and FIG. 2 is a sectional view of the combustion chamber liner in the axial direction of the combustor.

As shown in FIG. 1, a gas turbine combustor (simply referred to as a combustor) has an outer cylinder 1, an inner cylinder 2 installed in the outer cylinder 1, and a tail cylinder 3 connected to the rear of the inner cylinder 2. And the inside of the inner cylinder 2 forms a combustion chamber. The high-pressure air 31 supplied from the outside of the combustor between the outer cylinder 1 and the inner cylinder 2 flows into the combustion chamber through a large number of air introduction ports 61 provided in the wall of the inner cylinder 2.

The combustion chamber liner 1 forming the peripheral wall of the inner cylinder 2
As shown in FIG. 2, 1 (hereinafter, simply referred to as liner 11) has a hole or cooling channel 60 extending in the axial direction of the inner cylinder 2 inside the liner 11, and an outer surface of the liner 11 to the cooling channel 60. Air inlet 61 and cooling channel 60 communicating with
Is provided with an air lead-out port 62 communicating with the inner surface of the liner 11. High pressure air 31 flowing outside the inner cylinder 2
Simultaneously cools the outer wall portion of the liner 11, and at the same time, a part of the high pressure air 31a flows into the cooling flow passage 60 from the air introduction port 61 to cool the inside of the liner 11, and then from the air outlet port 62 to the inside of the inner cylinder 2. That is, it flows out into the combustion chamber, and at that time, it is guided by the claw 12 provided on the outlet side of the air outlet 62 and flows as film air 31b along the inner surface of the inner cylinder 2 to cool the inner wall portion of the inner cylinder 2. The liner 11 is protected from the high temperature combustion gas 40 flowing in the inner cylinder 2. The liner 11 of the inner cylinder 2 is composed of a laminated plate in which a heat-resistant and corrosion-resistant alloy plate 11a that serves as an outer wall portion and a grooved heat-resistant and corrosion resistant alloy sheet 11b that serves as an inner wall portion and has a cooling channel 60 are laminated. The claw 12 is annular and is joined along the inner circumference of the inner cylinder 2.

[Embodiment 1] FIG. 3 is a view for explaining a first embodiment of the present invention, and shows a method of manufacturing a liner having a laminated structure.
First, on one surface of one of the two heat-resistant and corrosion-resistant alloy plates, a plurality of grooves 60 serving as cooling channels are formed by an electric discharge machining method so as to be parallel to the axial direction of the inner cylinder 2, and the heat-resistant and corrosion-resistant alloy with grooves is formed. Board 11
get b. Next, another flat heat-resistant and corrosion-resistant alloy plate 11a is
The groove 60 is overlaid on the grooved heat-resistant and corrosion-resistant alloy plate 11b so as to cover the groove 60. Then, from the surface of the flat plate 11a, CO
₂ Laminated plate that becomes a liner by welding with the laser welding method 1
Produce 1. At this time, the welding bead 51 is formed such that the width thereof is wide at the portion corresponding to the convex portion between the grooves 60, 60 of the grooved heat-resistant and corrosion-resistant alloy plate 11b, and the two plates 11a, 11 are formed.
The b is integrated into a laminated plate 11. It is preferable to improve the heat conduction between the plates 11a and 11b by widening the width of the welding bead 51, which allows effective heat dissipation.

The heat and corrosion resistant alloy plates 11a and 11b are made of Hastelloy material, and the grooved heat resistant and corrosion resistant alloy plate 11a has an approximate size of 2 × 30 × 400 (mm), the grooves 60 are 1 × 1 (mm), and the interval is 5 mm. The heat-resistant and corrosion-resistant alloy plate 11b has an approximate size of 1.
When it was set to 2 × 30 × 400 (mm), as an example, the CO ₂ laser welding condition example was output: 2 kw and welding speed: 1 m / min. FIG. 4 shows a sectional shape of the laminated plate 11. The heat and corrosion resistant alloy plates 11a and 11b of this type have a plate thickness of 0.5 to 5 mm.

FIG. 5 is a view showing a state in which the laminated plate 11 is processed into a cylindrical shape. The laminated plate 11 is formed into a ring shape by bending, and then the abutting portion at the end of the laminated plate 11 is welded to produce an inner cylinder segment. A plurality of the inner cylinder segments are joined together in the axial direction and welded to manufacture the inner cylinder 2 having a predetermined length. The above welding is actually TIG welding using a Ni-based filler wire [welding current: 55 A, shielding gas: A
r (10 l / min)].

The method for forming the cooling passages in the laminated plate was carried out by a method different from that of Example 1 below, so that Example will be described.

[Second Embodiment] FIG. 6 shows a second embodiment of the present invention. A groove 60a is formed on one surface of the corrosion-resistant heat-resistant alloy plate 11a, and a groove 60b is formed on one surface of the corrosion-resistant heat-resistant alloy plate 11b by an electric discharge machining method. Similarly, welding was performed to form the cooling flow channel 60 in the laminated plate 11. The welding conditions are the same as in Example 1.

[Third Embodiment] FIG. 7 shows a third embodiment of the present invention. Two flat, corrosion-resistant and heat-resistant alloy plates without processing 11
A corrugated plate material 13 made of the same material as the flat plate is sandwiched between b, and a portion where the corrosion-resistant heat-resistant alloy plate 11a and the top portion on one side of the corrugated plate material 13 linearly contact each other, and the corrosion-resistant heat-resistant alloy plate 11b and the corrugated shape. The portion of the plate member 13 that is in linear contact with the top of the other surface is CO ₂
The laminated plate 11 was manufactured by welding using a laser welding method.
The cooling flow path 60 includes the corrosion-resistant and heat-resistant alloy plate 11 a and the corrugated plate material 13.
It is formed by a space defined by and a space defined by the corrosion-resistant and heat-resistant alloy plate 11b and the corrugated plate material 13. As an example, the welding conditions for the Hastelloy corrosion-resistant heat-resistant alloy plates 11a and 11b are that the corrugated plate material 13 does not melt too much,
The laser output was 1.5 kw and the welding speed was 1 m / min.

[Fourth Embodiment] FIG. 8 shows a fourth embodiment of the present invention. A square bar 14 made of the same material as the flat plate is parallelly arranged and sandwiched between two flat plates of the corrosion resistant heat resistant alloy plate 11b, and the two corrosion resistant heat resistant alloy plates 11b and the square bar 14 are integrated by welding from the upper surface of each flat plate. By doing so, the laminated plate 11 was manufactured. Figure 9
The laminated plate 11 shown in FIG. 8 is one in which a coffered groove 16 is formed on the facing surface of two corrosion-resistant and heat-resistant alloy plates 11b so that the square members 14 can be positioned. Others are the same as those of the laminated plate shown in FIG. When the thickness of the Hastelloy corrosion-resistant heat-resistant alloy plates 11a and 11b was 1 mm, the welding conditions were the same as in Example 1.

[Fifth Embodiment] FIG. 10 shows a fifth embodiment of the present invention. The grooved corrosion-resistant and heat-resistant alloy plate 11a and the corrosion-resistant and heat-resistant alloy plate 11b produced by the same method as in Example 1 were overlapped by the same method as in Example 1 and welded by the electron beam welding method to produce the laminated plate 11. 53 is an electron beam weld.
Welding conditions are acceleration voltage: 150V, beam current: 50m
A, welding speed: 1 m / min, vacuum degree: 1 × 10 to ⁴ Tor
It was r.

[Sixth Embodiment] FIG. 11 shows a sixth embodiment of the present invention. A grooved corrosion-resistant heat-resistant alloy plate 11a and a corrosion-resistant heat-resistant alloy plate 11b produced by the same method as in Example 1 were liquid-phase diffusion-bonded to produce a laminated plate 11. The chemical composition of the alloy plates 11a and 11b is C: 0.1%, Si: 0.5%, M by weight ratio.
n: 0.5%, Co: 15%, Mo: 9%, balance Ni,
The insert material sandwiched between the alloy plates 11a and 11b had a slightly higher Si content than the corrosion-resistant heat-resistant alloy plate, and was a foil containing 1 to 4% of boride added thereto. The bonding condition is 1 in vacuum
The temperature was kept at 200 ° C. × 1 h (pressurization: 3 gf / mm ² ). 7
0 indicates a liquid phase diffusion bonding part.

[Seventh Embodiment] FIG. 12 shows a seventh embodiment of the present invention. A corrugated plate material 13 made of the same material as this flat plate is sandwiched between two flat plates of the corrosion resistant heat resistant alloy plate 11b, and one of the corrosion resistant heat resistant alloy plate 11b and the top portion of the corrugated plate material 13 on one surface side linearly contact each other. A portion and a portion where the other corrosion-resistant and heat-resistant alloy plate 11b and the apex on the other surface side of the corrugated plate material 13 linearly abut were liquid-phase diffusion bonded to each other to manufacture a laminated plate 11. Corrosion-resistant heat-resistant alloy plate 1
The chemical composition of 1b is the same as in Example 8 above, and the insert material foil sandwiched between the contact portions has a thickness of 50 μm.
It had a chemical composition of Si: 4%, Co: 15%, Mo: 9%, B: 3%, and residual Ni. The joining conditions are heating to 1150 ° C in a vacuum and pressurizing (0.5 gf / mm ² ).
It was something to do.

[0029]

According to the present invention, a method for manufacturing a combustion chamber liner for a gas turbine is performed by stacking a grooved heat-resistant and corrosion-resistant metal plate and a flat plate heat-resistant and corrosion-resistant metal plate so that the groove is located inside, or by using a groove. The two heat-resistant and corrosion-resistant metal plates are stacked so that the groove is located inside, or a plurality of square bar members or corrugated plates made of the same material are sandwiched between the two heat-resistant and corrosion-resistant metal plates, and these are laminated. Since the members are joined by the laser welding method or the electron beam welding method, the joining portion of the members can obtain high temperature strength equivalent to that of the members.

In addition, another method for manufacturing a combustion chamber liner for a gas turbine according to the present invention may be performed by superposing a grooved heat-resistant and corrosion-resistant metal plate and a flat plate heat-resistant and corrosion-resistant metal plate, or by using them between two heat-resistant and corrosion-resistant metal plates. The corrugated plates made of the same material are sandwiched together, and a foil-like insert material made of an alloy containing more Si and B than the chemical composition of the heat-resistant and corrosion-resistant metal is interposed between these members and joined by the liquid phase diffusion joining method. Since the insert material has a low melting point of Si and B to facilitate the joining, and the main component of the joint is almost the same as that of the heat and corrosion resistant metal plate, the high temperature strength of the joint is equivalent to that of the member. Can be

The combustor made of the combustion chamber liner material produced by these methods has a cooling passage inside the liner, and forced cooling can be performed from the inside as well. Therefore, in combination with film cooling, The combustor can be cooled effectively.

[Brief description of drawings]

FIG. 1 is a schematic configuration diagram of a gas turbine combustor including a combustion chamber liner manufactured according to the present invention.

FIG. 2 is a combustor axial sectional view showing a combustion chamber liner structure.

FIG. 3 is a perspective view of an inner cylinder wall laminated plate manufactured by the method according to the first embodiment of the present invention.

FIG. 4 is a cross-sectional view showing a welded portion of a laminated plate manufactured by the method of Example 1.

FIG. 5 is a view showing a combustor inner cylinder manufactured from a laminated plate through inner cylinder segments.

FIG. 6 is a sectional view of a welded portion of a laminated plate manufactured by the method of Example 2 of the present invention.

FIG. 7 is a sectional view of a welded portion of a laminated plate manufactured by the method of Example 3 of the present invention.

FIG. 8 is a cross-sectional view of a welded portion of a laminated plate manufactured by the method of Example 4 of the present invention.

FIG. 9 is a cross-sectional view of a welded portion of a laminated plate manufactured by the method of Example 5 of the present invention.

FIG. 10 is a cross-sectional view of a welded portion of a laminated plate according to a modification of the method of Example 5.

FIG. 11 is a sectional view of a welded portion of a laminated plate manufactured by the method of Example 6 of the present invention.

FIG. 12 is a sectional view of a welded portion of a laminated plate manufactured by the method of Example 7 of the present invention.

[Explanation of symbols]

 1 Outer Cylinder 2 Inner Cylinder 11 Combustion Chamber Liner (Laminate Plate) 11a, 11b Heat Resistant Corrosion Resistant Alloy Plate 12 Claw 13 Corrugated Plate Material 14 Square Bar 51 Laser Weld Bead 52 TIG Weld Bead 53 Electron Beam Weld Bead 60 Cooling Channel 60a, 60b Groove 61 Cooling Air Inlet 62 Cooling Air Outlet 70 Liquid Phase Diffusion Joint

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Hisanobu Okamura 7-1-1, Omika-cho, Hitachi-shi, Ibaraki Hitachi Ltd. Hitachi Research Laboratory

Claims (7)

[Claims] 1. A method for manufacturing a combustion chamber liner for a gas turbine having a cooling flow passage formed therein, wherein the material of the combustion chamber liner is a grooved heat-resistant and corrosion-resistant metal having a plurality of grooves formed in parallel on one surface. A plate and a flat plate-shaped heat-resistant and corrosion-resistant metal plate are overlapped so as to include the groove therein, and welded by a laser welding method or an electron beam welding method along the convex portion between the adjacent grooves to manufacture. A method for manufacturing a combustion chamber liner for a gas turbine. 2. A method of manufacturing a combustion chamber liner for a gas turbine having a cooling flow passage formed therein, wherein the material of the combustion chamber liner is a grooved heat-resistant and corrosion-resistant metal having a plurality of grooves formed in parallel on one surface. Combustion for a gas turbine, characterized in that two plates are superposed with the grooves aligned and welded from one side by a laser welding method or an electron beam welding method along a convex portion between the adjacent grooves to manufacture. Chamber liner manufacturing method. 3. The method for producing a combustion chamber liner for a gas turbine according to claim 1, wherein the groove is formed by etching, laser machining or electric discharge machining. 4. A method of manufacturing a combustion chamber liner for a gas turbine having a cooling flow passage formed therein, wherein the material of the combustion chamber liner is a plurality of rectangular molds made of heat resistant and corrosion resistant metal between two heat resistant and corrosion resistant metal plates. Arrange the bar materials in parallel,
A method for manufacturing a combustion chamber liner for a gas turbine, characterized in that the heat resistant and corrosion resistant metal plate is welded from the outer surface side along a rectangular bar material by a laser welding method or an electron beam welding method. 5. A method of manufacturing a combustion chamber liner for a gas turbine having a cooling flow passage formed therein, wherein the material of the combustion chamber liner is a corrugated plate made of heat resistant and corrosion resistant metal between two heat resistant and corrosion resistant metal plates. A gas characterized by being produced by welding by sandwiching the heat-corrosion-resistant metal plate from the outer surface side along the top of the corrugated plate that contacts the heat-corrosion-resistant metal plate by a laser welding method or an electron beam welding method. Manufacturing method of combustion chamber liner for turbine. 6. A method of manufacturing a combustion chamber liner for a gas turbine having a cooling channel formed therein, wherein the material of the combustion chamber liner is a grooved heat-resistant and corrosion-resistant metal having a plurality of grooves formed in parallel on one surface. A plate and a flat plate heat-resistant and corrosion-resistant metal plate are superposed so as to include the groove inside by sandwiching a foil-shaped insert material made of an alloy in which Si is added to the heat-resistant and corrosion-resistant metal chemical composition and B is added, A method for manufacturing a combustion chamber liner for a gas turbine, which is manufactured by bonding by a phase diffusion bonding method. 7. A method of manufacturing a combustion chamber liner for a gas turbine having a cooling channel formed therein, wherein the material of the combustion chamber liner is a corrugated plate made of a heat and corrosion resistant metal plate between two heat and corrosion resistant metal plates. Between the heat-corrosion-resistant metal plate and the top of the corrugated plate with a foil-shaped insert material made of an alloy containing Si added to the chemical composition of the heat-resistant corrosion-resistant metal and B added, A method for manufacturing a combustion chamber liner for a gas turbine, which is manufactured by bonding by a diffusion bonding method.