CN115451428A - Flame tube wall assembly and method for machining impingement cooling wall thereof - Google Patents
Flame tube wall assembly and method for machining impingement cooling wall thereof Download PDFInfo
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- 238000001816 cooling Methods 0.000 title claims abstract description 147
- 238000000034 method Methods 0.000 title claims abstract description 42
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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Abstract
The invention relates to a flame tube wall assembly and an impact cooling wall machining method thereof. The flame tube wall assembly for the aircraft engine comprises a cylindrical film cooling wall positioned on the inner side of the flame tube wall assembly and a cylindrical impact cooling wall positioned on the outer side of the flame tube wall assembly, wherein the section molded line of the impact cooling wall is corrugated, and the impact cooling wall comprises an impact cooling wall base body and an impact cooling hole positioned in the impact cooling wall base body. The invention can achieve the following beneficial technical effects: the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Description
Technical Field
The invention relates to the technical field of aircraft engines, in particular to a flame tube wall assembly and an impact cooling wall machining method thereof.
Background
The cooling of the liner is important to the proper operation of the combustor and determines the life and reliability of the combustor. The combustion chamber is an important high-temperature component of an aircraft engine, and the performance of the combustion chamber is directly related to the working efficiency and reliability of the whole engine. The mechanical stress on the flame tube is small compared with other parts of the gas turbine, but the wall surface of the flame tube becomes a part with the highest internal temperature and the shortest service life of the engine due to high-temperature radiation and direct scouring of high-temperature gas. In order to ensure that the wall surface of the flame tube has no local hot spot and the temperature distribution of the space is uniform, namely the highest wall temperature and the wall temperature gradient of the flame tube are controlled within the allowable temperature range of the material of the flame tube, measures must be adopted to transfer high-temperature fuel gas to the heat of the flame tube, and the heat is transferred to the annular cavity air and the casing through convection heat transfer and radiation heat transfer to ensure that the wall temperature and the gradient of the flame tube are within the allowable temperature range of the material.
The modern novel aero-engine combustion chamber, especially the annular combustion chamber flame tube, mostly adopts the technologies of airflow impingement cooling, air film covering, thermal barrier coating and the like, can effectively reduce the temperature of the flame tube wall at the hot side, and realizes extremely high combustion temperature and combustion efficiency at the allowable material temperature. However, with the technological progress, the thrust-weight ratio of the aero-engine is continuously increased, the temperature rise of the combustion chamber and the working temperature of the combustion chamber are also continuously increased, and the performances of high temperature resistance, creep resistance and the like of the combustion chamber, particularly the flame tube material, are increasingly strict. Combustor designs therefore require a more efficient cooling configuration to accommodate the high temperature sustained operation requirements.
Disclosure of Invention
It is an object of the present invention to provide a flame tube wall assembly for an aircraft engine that solves the problems of the prior art, reduces the hot sidewall surface temperature, and achieves higher combustion chamber temperature rise and combustion chamber operating temperature.
The above objects of the present invention are achieved by a flame tube wall assembly for an aircraft engine comprising a cylindrical film cooling wall on an inner side thereof and a cylindrical impingement cooling wall on an outer side thereof, wherein a cross-sectional profile of the impingement cooling wall is corrugated, and the impingement cooling wall comprises an impingement cooling wall base and impingement cooling holes in the impingement cooling wall base.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Preferably, the corrugation is a simple harmonic.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: through a proper wavy structure, the temperature of the hot side wall surface can be further reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Preferably, the corrugation is a combination of a plurality of simple harmonics.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: through more suitable wavy structure, can further reduce hot side wall face temperature, realize higher combustion chamber temperature rise and combustion chamber operating temperature.
Preferably, the ratio of the wavelength λ of the simple harmonic to the amplitude A of the simple harmonic is in the range of 2-20.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: not only can strengthen the heat transfer effect, but also can prevent the air flow resistance from being overlarge.
Preferably, the ratio of the wavelength λ of the simple harmonic to the diameter d of the impingement cooling holes is in the range of 3-30.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the cooling requirement can be met, and the strength reduction of the impact cooling wall can be prevented.
Preferably, the impingement cooled wall has a longitudinal weld.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the tubular impingement cooling wall can be closed better, so that the temperature of the hot side wall surface is further reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Preferably, the temperature resistance of the material of the impingement cooling wall is lower than that of the material of the film cooling wall.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the material cost of the impingement cooled wall can be reduced.
Another objective of the present invention is to provide a method for processing a liner impingement cooled wall, which can solve the problems of the prior art, reduce the temperature of the hot sidewall, and achieve higher temperature rise and working temperature of the combustion chamber.
The above object of the present invention is achieved by a method for machining a flame tube impingement cooling stave, comprising the steps of:
(a) Selecting a flat plate which is relatively high temperature resistant and has good bending performance;
(b) Machining impingement cooling holes in the flat plate;
(c) Machining the flat plate with impingement cooling holes into a corrugated plate;
(d) Processing the corrugated sheet into a substantially annular structure;
(e) Closing the substantially annular structure to form a corrugated annular cylinder wall.
According to the technical scheme, the processing method of the flame tube impingement cooling wall has the following beneficial technical effects: the flame tube corrugated impact cooling wall is processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Preferably, the step (c) and the step (d) may be performed in a reversed order or may be combined into one process.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper processing step sequence, the flame tube corrugated impact cooling wall can be processed better, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
Preferably, the step (b) uses a process including machining, electric discharge drilling, or laser drilling.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper impingement cooling hole machining process, the flame tube corrugated impingement cooling wall can be machined better, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
Preferably, the step (c) is performed by a process including stamping or rolling.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper corrugated plate processing technology, the flame tube corrugated impingement cooling wall can be processed better, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
Preferably, the process used in step (d) includes cold bending or sheet metal working.
According to the technical scheme, the processing method of the flame tube impingement cooling wall has the following beneficial technical effects: through a proper basic annular structure processing technology, the flame tube corrugated impact cooling wall can be better processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
Preferably, the step (e) uses a process including argon arc welding, laser welding, or electron beam welding.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper closed processing technology, the flame tube corrugated impact cooling wall can be better processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Preferably, the processing method further comprises the step (f): after step (e), perforating the weld.
According to the technical scheme, the processing method of the flame tube impingement cooling wall has the following beneficial technical effects: the original impingement cooling holes on the corrugated plate may be blocked by welding, and the number and density of the impingement cooling holes can be ensured by a supplementary welding seam punching process.
Drawings
FIG. 1 is a schematic view of an aircraft engine combustion chamber in accordance with an embodiment of the invention.
FIG. 2 is a schematic view of a flame tube wall assembly according to an embodiment of the invention.
FIG. 3 is a schematic view of an impingement cooled wall in a flame cartridge wall assembly according to an embodiment of the invention.
FIG. 4 is a partial cross-sectional view of an impingement cooled wall in a flame cartridge wall assembly according to an embodiment of the invention.
FIG. 5 is a schematic diagram of the heat transfer of a combustor basket according to one embodiment of the present invention.
List of reference numerals
1. A combustion chamber outer casing;
2. a diffuser;
3. a flame tube wall assembly;
4. a head adapter structure;
5. a swirler;
6. a fuel nozzle;
7. impingement cooling staves;
8. a film cooling wall;
701. impingement cooling the stave base;
702. impingement cooling holes;
703. welding;
λ, wavelength of simple harmonic;
A. the amplitude of the simple harmonics;
r1, the radiation thermal resistance of combustion gas in the flame tube to the air film cooling wall;
r2, convective heat transfer resistance of the hot side of the air film cooling wall;
r3, convective heat transfer resistance of the cold side of the air film cooling wall;
r4, impacting the heat transfer convection resistance of the cold side of the cooling wall;
two, impingement cooled wall temperature;
twi, wall temperature of the air film cooling wall;
to, the temperature of the airflow outside the flame tube;
ti and the temperature of fuel gas in the flame tube.
Detailed Description
While specific embodiments of the invention will be described below, it should be noted that in the course of the detailed description of these embodiments, in order to provide a concise and concise description, all features of an actual implementation may not be described in detail. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are often made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and tedious, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, given the benefit of this disclosure, without departing from the scope of this disclosure.
Unless otherwise defined, technical or scientific terms used in the claims and the specification should have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The use of "first," "second," and similar terms in the description and claims of the present application do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, means that the element or item appearing in front of the word "comprising" or "comprises" includes reference to the element or item listed after the word "comprising" or "comprises" and equivalents thereof, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.
As the name implies, the term "impingement cooling" refers to: the technique of using cooled gas to impact the surface of an object to carry out thermal convection cooling.
FIG. 1 is a schematic view of an aircraft engine combustion chamber according to an embodiment of the invention. FIG. 2 is a schematic view of a flame tube wall assembly according to an embodiment of the invention. FIG. 3 is a schematic view of an impingement cooled wall in a flame cartridge wall assembly according to an embodiment of the invention. FIG. 4 is a partial cross-sectional view of an impingement cooled wall in a flame cartridge wall assembly according to an embodiment of the invention. FIG. 5 is a schematic diagram of the heat transfer of a combustor basket according to an embodiment of the present invention.
As shown in fig. 1, according to an embodiment of the invention, an aircraft engine combustion chamber comprises: the device comprises a combustion chamber outer casing 1, a diffuser 2, a flame tube wall assembly 3, a head adapter structure 4, a swirler 5, a fuel nozzle 6 and the like.
As shown in fig. 1-5, a flame tube wall assembly for an aircraft engine, according to an embodiment of the invention, includes a cylindrical film cooling wall 8 on an inner side thereof and a cylindrical impingement cooling wall 7 on an outer side thereof, wherein a cross-sectional profile of the impingement cooling wall 7 is corrugated, and the impingement cooling wall 7 includes an impingement cooling wall base 701 and impingement cooling holes 702 in the impingement cooling wall base 701. That is, the film stave 8 and the impingement stave 7 are two cylindrical staves nested in each other, and the impingement stave 7 is located radially outside the film stave 8.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
Specifically, the flame tube in the prior art usually adopts a single-layer flame tube wall, and the single-layer flame tube wall is directly contacted with the fuel gas, so that the cooling air is not beneficial to forming an effective air film on the fuel gas side to achieve the effect of isolating the heat convection. The flame tube wall assembly provided by the invention comprises the impact cooling wall and the air film cooling wall, the corrugated structure is suitable for the impact cooling wall, and the effect of reducing the temperature of the air film cooling wall is achieved by strengthening the convection heat transfer at the two sides of the impact cooling wall. The corrugated impact cooling wall is combined with the air film cooling wall, so that the cold-side convective heat resistance of the flame tube can be reduced, the temperature of the side surface of the hot wall is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
In some embodiments, as shown in FIG. 4, impingement cooling holes 702 are distributed substantially uniformly throughout impingement cooling wall 7.
In some embodiments, as shown in FIG. 4, the corrugation of the impingement cooled wall 7 is a simple harmonic.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: through a proper wavy structure, the temperature of the hot side wall surface can be further reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
In some embodiments, as shown in FIG. 4, the corrugation of the impingement cooling wall 7 is a simple harmonic of the regular shape. In other embodiments, the corrugation of the impingement cooling wall 7 is a combination of a plurality of simple harmonics.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: through more suitable wavy structure, can further reduce hot side wall face temperature, realize higher combustion chamber temperature rise and combustion chamber operating temperature.
The ratio of the wavelength lambda of the simple harmonic to the amplitude A of the simple harmonic needs to be in a proper range, and if the ratio is too large, the amplitude is relatively too small, so that the heat transfer enhancement effect cannot be achieved; too small a ratio results in a relatively excessive amplitude and an excessive air flow resistance. Preferably, the ratio of the wavelength λ of the simple harmonic to the amplitude A of the simple harmonic is in the range of 2-20.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: not only can strengthen the heat transfer effect, but also can prevent the air flow resistance from being overlarge.
The ratio of the wavelength lambda of the simple harmonic to the aperture d of the impingement cooling hole needs to be in a proper range, and if the ratio is too large, the cooling requirement cannot be met; too small a ratio results in too dense cooling holes and reduced impingement stave strength. Preferably, the ratio of the wavelength λ of the simple harmonic to the diameter d of the impingement cooling holes is in the range of 3-30.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: not only can meet the cooling requirement, but also can prevent the strength reduction of the impact cooling wall.
In some embodiments, as shown in FIG. 3, there is one longitudinal weld 703 of the impingement cooling wall 7.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the tubular impingement cooling wall 7 can be closed better, thereby further reducing the temperature of the hot side wall surface and realizing higher temperature rise and working temperature of the combustion chamber.
In some embodiments, the impingement stave 7 is made of a material having a temperature resistance lower than that of the film stave 8. Preferably, the impingement cooling wall 7 may be made of high temperature alloy such as GH3536, GH738, etc.; the material of the film cooling wall 8 can be GH5188 or other high-temperature alloy.
According to the technical scheme, the flame tube wall assembly for the aircraft engine has the following beneficial technical effects: the material cost of the impingement cooled wall can be reduced.
As shown in fig. 1 to 5, according to an embodiment of the present invention, a method for manufacturing a combustor basket impingement cooling wall comprises the following steps:
(a) Selecting a flat plate which is relatively high temperature resistant and has good bending performance;
(b) Machining impingement cooling holes 702 in the plate;
(c) The flat plate with impingement cooling holes 702 is corrugated;
(d) Processing the corrugated plate into a basically annular structure;
(e) The substantially annular structure is closed to form a corrugated annular cylinder wall.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: the flame tube corrugated impact cooling wall is processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
In some embodiments, steps (c) and (d) may be reversed in order or combined in one process.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper processing step sequence, the flame tube corrugated impact cooling wall can be better processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
In some embodiments, step (b) employs a process comprising machining, electrical discharge drilling, or laser drilling.
According to the technical scheme, the processing method of the flame tube impingement cooling wall has the following beneficial technical effects: through a proper impingement cooling hole machining process, the flame tube corrugated impingement cooling wall can be machined better, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
In some embodiments, the process used in step (c) comprises stamping, or rolling.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper corrugated plate processing technology, the flame tube corrugated impingement cooling wall can be processed better, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
In some embodiments, the process used in step (d) comprises cold bending, or sheet metal working.
According to the technical scheme, the processing method of the flame tube impingement cooling wall has the following beneficial technical effects: through a proper basic annular structure processing technology, the flame tube corrugated impact cooling wall can be better processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of a combustion chamber are realized.
In some embodiments, the process used in step (e) comprises argon arc welding, laser welding, or electron beam welding.
According to the technical scheme, the method for processing the flame tube impingement cooling wall has the following beneficial technical effects: through a proper closed processing technology, the flame tube corrugated impact cooling wall can be better processed, so that the temperature of the hot side wall surface is reduced, and higher temperature rise and working temperature of the combustion chamber are realized.
In some embodiments, the method of processing further comprises step (f): after step (e), perforations are made at weld 703.
According to the technical scheme, the processing method of the flame tube impingement cooling wall has the following beneficial technical effects: the original impingement cooling holes on the corrugated plate may be blocked by welding, and the number and density of the impingement cooling holes can be ensured by a supplementary welding seam punching process.
According to the processing method of the flame tube impingement cooling wall, the flame tube wall assembly is formed based on the proposed impingement cooling wall and the air film cooling wall, so that the influence of the effective area of impingement cooling holes on the effective cooling area of the whole flame tube wall is small, and the influence of the deformation of the impingement cooling holes on the effective cooling area of the whole flame tube in the process of forming the corrugated plate structure and the basic annular structure is small. Because the impingement cooling wall is lower to cooling hole inclination angle requirement for the gas film cooling wall, the cooling hole can be for straight hole, consequently can process the cooling hole earlier on the flat board, and its advantage lies in, compares and processes the cooling hole on annular buckled plate, and it is higher to process cooling hole efficiency on the flat board, and the cost is lower, and the processing ripple structure compares and forms annular section of thick bamboo wall postprocessing degree of difficulty and reduces before the welding forms annular section of thick bamboo wall.
The heat transfer principle of the flame tube wall assembly for an aircraft engine of the invention is shown in fig. 5: since the liner impingement stave and the film stave are typically metallic materials and are typically thin, their thermal conduction resistance is negligible compared to their convective resistance. In fig. 5, R1 is the radiation thermal resistance of the combustion gas in the flame tube To the air film cooling wall, R2 is the convection heat transfer thermal resistance of the hot side of the air film cooling wall, R3 is the convection heat transfer thermal resistance of the cold side of the air film cooling wall, R4 is the convection heat transfer thermal resistance of the cold side of the impingement cooling wall, two is the wall temperature of the impingement cooling wall, twi is the wall temperature of the air film cooling wall, to is the temperature of the air flow outside the flame tube, and Ti is the temperature of the combustion gas in the flame tube.
The calculation formula of the heat flux density of heat transfer from the inner part of the flame tube to the outer part is as follows:
the calculation formula of the wall temperature of the air film cooling wall is as follows:
Twi＝Ti-q(R1+R2) (2)
the corrugated plate structure is beneficial to reducing the thickness of the laminar boundary layer of the impact cooling wall and reducing the heat convection and heat transfer resistances at two sides of the impact cooling wall, namely the heat convection and heat transfer resistance R3 at the cold side of the air film cooling wall and the heat convection and heat transfer resistance R4 at the cold side of the impact cooling wall are reduced, and the heat flow density q of heat transfer from the inside of the flame tube to the outside is increased according to the formula 1. When the combustion temperature Ti, the radiation thermal resistance R1 of the combustion gas in the flame tube to the air film cooling wall and the convection heat transfer thermal resistance R2 of the hot side of the air film cooling wall are not changed, twi is reduced according to the calculation of the formula 2.
As can be seen from the above description, the beneficial effects of the present invention at least include:
1. the thermal convection resistance of the cold side of the flame tube can be reduced, and the temperature of the side wall of the hot side can be further reduced;
2. the method for processing the corrugated impingement cooling wall of the flame tube is simple, reliable and low in cost;
3. higher combustion chamber temperature rise and combustion chamber operating temperatures can be achieved.
While particular embodiments of the present invention have been described above, it will be understood by those skilled in the art that they are not intended to limit the invention, and that various modifications may be made by those skilled in the art based on the above disclosure without departing from the scope of the invention.
Claims (14)
1. The flame tube wall assembly for the aircraft engine is characterized by comprising a cylindrical film cooling wall positioned on the inner side of the flame tube wall assembly and a cylindrical impact cooling wall positioned on the outer side of the flame tube wall assembly, wherein the cross-section molded line of the impact cooling wall is corrugated, and the impact cooling wall comprises an impact cooling wall base body and an impact cooling hole positioned in the impact cooling wall base body.
2. A flameholder wall assembly for an aircraft engine as claimed in claim 1, wherein said corrugation is a simple harmonic.
3. The flameless cylinder wall assembly for an aircraft engine as claimed in claim 2, wherein said corrugation is a combination of a plurality of simple harmonics.
4. A flame barrel wall assembly for an aircraft engine, as in claim 2, wherein the ratio of the wavelength λ of said simple harmonic to the amplitude a of said simple harmonic is in the range of 2-20.
5. A flame tube wall assembly for an aircraft engine, as in claim 2, wherein the ratio of the wavelength λ of the simple harmonic to the aperture d of the impingement cooling holes is in the range of 3-30.
6. The flameless cylinder wall assembly for an aircraft engine as claimed in claim 1, wherein said impingement cooling wall has a longitudinal weld.
7. The flame barrel wall assembly for an aircraft engine, as in claim 1, wherein said impingement cooling wall material has a temperature resistance less than a temperature resistance of said film cooling wall material.
8. A method for processing a flame tube impingement cooling wall comprises the following steps:
(a) Selecting a flat plate which is relatively high temperature resistant and has good bending performance;
(b) Machining impingement cooling holes in the flat plate;
(c) Machining the flat plate with impingement cooling holes into a corrugated plate;
(d) Processing the corrugated sheet into a substantially annular structure;
(e) Closing the substantially annular structure to form a corrugated annular cylinder wall.
9. The method of claim 8, wherein the steps (c) and (d) are performed in a reversed order or combined in one step.
10. The method of claim 8, wherein the step (b) comprises machining, spark drilling, or laser drilling.
11. The method of claim 8, wherein the step (c) comprises stamping or rolling.
12. The method of claim 8 wherein the step (d) comprises cold bending or sheet metal forming.
13. The method of claim 8, wherein the step (e) comprises argon arc welding, laser welding, or electron beam welding.
14. The method of claim 13 wherein the method further comprises step (f):
after step (e), perforating the weld.
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| CN202110638992.0A CN115451428A (en) | 2021-06-08 | 2021-06-08 | Flame tube wall assembly and method for machining impingement cooling wall thereof |
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| CN202110638992.0A CN115451428A (en) | 2021-06-08 | 2021-06-08 | Flame tube wall assembly and method for machining impingement cooling wall thereof |
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| CN202110638992.0A Pending CN115451428A (en) | 2021-06-08 | 2021-06-08 | Flame tube wall assembly and method for machining impingement cooling wall thereof |
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Application publication date: 20221209 |