CN114491875B - Porous laminate profile design method and porous laminate flame tube - Google Patents

Porous laminate profile design method and porous laminate flame tube Download PDF

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CN114491875B
CN114491875B CN202210357428.6A CN202210357428A CN114491875B CN 114491875 B CN114491875 B CN 114491875B CN 202210357428 A CN202210357428 A CN 202210357428A CN 114491875 B CN114491875 B CN 114491875B
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porous laminate
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head
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CN114491875A (en
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王永明
黄兵
房人麟
邱伟
桂韬
黄顺洲
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AECC Sichuan Gas Turbine Research Institute
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation

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Abstract

The application provides a porous laminate profile design method and a porous laminate flame tube, wherein the design method comprises the following steps: obtaining structural parameters and pneumatic parameters, wherein the structural parameters comprise the inlet radius Rd of the head of the combustion chamber, the radius Ri of an inner ring of an outlet, the radius Ro of an outer ring of the outlet, the length L of a flame tube and the height Hd of the head; determining a central line OO' of the flame tube; determining the length Ld of the head splash plate and the length Lc of the rear adapter section; determining a point P and a point P'; determining an outer ring profile critical control point A, B, C0 and an inner ring profile critical control point D, E, F0 for the porous laminate; determining an outer ring profile Arc0 and an inner ring profile Arc 0'; the Arc0 and the Arc0' are respectively biased outwardly by the required flame tube thickness. Through the treatment scheme, the flow loss is small, the gas film is continuously covered, the high cold efficiency and the light weight of the porous layer plate are fully exerted, and the use requirements of a future high-temperature-rise main combustion chamber are met.

Description

Porous laminate profile design method and porous laminate flame tube
Technical Field
The application relates to the technical field of aero-engines and gas turbines, in particular to a porous laminate profile design method and a porous laminate flame tube.
Background
The main combustion chamber of the aircraft engine is faced with a series of severe environments such as high temperature, high pressure, oxidation corrosion, thermal shock fatigue and the like. For an aero engine with a thrust-weight ratio of 8 grades, the outlet temperature of a combustion chamber reaches 1750K, for an engine with a thrust-weight ratio of 10 grades, the outlet temperature of the combustion chamber reaches 1970K, and for an engine with a thrust-weight ratio of 15 grades in the future, the outlet temperature of the combustion chamber reaches 2000-2250K. For the aero-engine with the thrust-weight ratio of 12-15 or even more than 15, the inlet temperature of the combustion chamber is greatly improved compared with the thrust-weight ratio of 10, the cooling potential of the cooling gas for the combustion chamber is sharply reduced, the air inflow at the head of the combustion chamber is greatly increased to ensure that the combustion chamber does not smoke and burn in a large state, and the air amount for cooling the flame tube of the combustion chamber is greatly reduced. In order to meet the use requirement of a high-temperature-rise combustion chamber with a high thrust-weight ratio in the future, the development of a flame tube of a main combustion chamber with light weight and high cooling efficiency is urgently needed.
The multi-hole laminate cooling is a mode between divergent cooling and air film cooling, integrates impingement cooling, convection cooling and air film cooling, fully utilizes the cooling potential of cooling air, and has the obvious advantages of low cooling air consumption and high cooling efficiency.
However, most of the domestic research on the porous laminate is focused on the cooling mechanism, and a design method capable of being engineered and put into practical use is lacked.
Disclosure of Invention
In view of this, the embodiments of the present application provide a method for designing a porous laminate profile and a porous laminate flame tube, which at least partially solve the problems in the prior art, such as low welding rate, unsatisfactory welding strength, poor manufacturability, and insufficient cooling efficiency in the porous laminate flame tube engineering practice.
The embodiment of the application provides a method for designing a profile of a porous laminate, the porous laminate is connected between a front transition section and a rear transition section of a flame tube,
the method for designing the profile of the porous laminate comprises the following steps:
the method comprises the following steps of firstly, obtaining structural parameters and pneumatic parameters, wherein the structural parameters comprise a combustor head inlet radius Rd, an outlet inner ring radius Ri, an outlet outer ring radius Ro, a flame tube length L and a head height Hd;
determining a central line OO 'of the flame tube, wherein the distance from the point O to the central line KK' of the engine is equal to Rd, and the distance from the point O 'to the central line KK' of the engine is equal to (Ri + Ro)/2;
determining the length Ld of the head splash plate and the length Lc of the rear adapter section;
step four, determining a point P and a point P': determining a point P and a point P 'according to the pneumatic parameters and the structural parameters, wherein the distance from the point P to the point P' is equal to the height Hd of the head;
step five, determining an outer ring profile key control point A, B, C0 and an inner ring profile key control point D, E, F0 of the porous laminate, wherein points A and D are connection points of the porous laminate and the front transition section, points CO and FO are connection points of the porous laminate and the rear transition section, and points B and D are located in the middle area of the porous laminate and comprise the following steps:
making a parallel line of OO 'through the point P, wherein the point A and the point B are positioned on the parallel line of OO', the distance range from the point A to the point P is 2-4 mm, the distance range from the point A to the head splash plate is 1-3 mm, and the axial distance range from the point B to the point O is 0.5-0.6L;
connecting BC, wherein the point C0 is on the straight line BC, and the axial distance from the point C0 to the point C is equal to Lc;
determining an inner ring profile key control point D, E, F0 in the same manner as the outer ring profile key control point A, B, C0;
sixthly, determining an outer ring profile Arc0 and an inner ring profile Arc0', and including:
polyline ABC0 rotates around KK' to form volume Vm 3 A rotary body of (1);
an Arc1 is formed by A, B, C0 points, a tangent AA1 of Arc1 is formed by a point A, a tangent C0C1 of Arc1 is formed by a point C0 point, angular bisectors AA2 and C0C2 of & lt A1AB and & lt C1C0B are respectively formed by a bisection method, an Arc2 can be formed by the tangent point A, the tangent point C0, the tangent AA2 and the tangent C0C2, and the Arc2 rotates around KK', so that the volume of the Arc 3683 is V1m 3 Judging whether the (V1-V)/V is smaller than the precision requirement, if not, adopting a bisection method to respectively serve as angle A2AB and angle C2C0B angle bisectors AA3 and C0C3, and respectively serving as a circular Arc3 through a tangent point A, a tangent point C0, a tangent line AA3 and a tangent line C0C3, wherein the Arc3 rotates around KK', and the formed volume is V2m 3 Judging whether (V2-V)/V is smaller than the precision requirement or not until the precision requirement is met to obtain a final Arc 0;
determining an inner ring profile Arc0' according to the same determination method as the Arc 0;
seventhly, the Arc0 and the Arc0' are respectively outwards biased to design the required flame tube thickness, the point A is biased to the point A ', the point CO is biased to the point C0', the point D is biased to the point D ', the point F0 is biased to the point F0', the point AA ' C0' CO is the outer ring profile section of the porous laminate, and the point DD ' F0' F0 is the inner ring profile section of the porous laminate.
According to a specific implementation manner of the embodiment of the application, the length Ld of the head splash plate ranges from 10mm to 25mm, and the length Lc of the rear adapter section ranges from 15mm to 30 mm.
According to a specific implementation of an embodiment of the present application, the aerodynamic parameters include combustor inlet air flow, inlet air temperature, inlet air pressure, liner reference cross-sectional velocity, and flow distribution.
In a second aspect, an embodiment of the present application further provides a porous laminate flame tube, including a combustion chamber head, a splash shield, a head adapter, a front adapter, a rear adapter, and a porous laminate located between the front adapter and the rear adapter, where the porous laminate is designed by using the porous laminate profile design method described in any of the embodiments of the first aspect, the splash shield is connected to the combustion chamber head, and the head adapter is connected to the front adapter.
According to a specific implementation manner of the embodiment of the application, the porous laminate is welded with the front adapter coupling section and the rear adapter coupling section in a welding manner.
According to a specific implementation of the embodiment of the application, the weld of the porous laminate and the front adapter section is located on the back of the splash plate.
According to a specific implementation manner of the embodiment of the application, the porous layer plate is arranged in a welding structure with N subunits uniformly distributed along the circumferential direction, and the numerical value of N is less than or equal to 4.
According to a specific implementation manner of the embodiment of the present application, the sub-units are connected by electron beam welding or laser welding.
According to a specific implementation manner of the embodiment of the application, a small cooling hole is additionally drilled at the welding seam of each subunit for cooling.
According to a concrete implementation mode of the embodiment of the application, the multi-hole laminate is provided with the cooling holes and the turbulence columns, and the number of the cooling holes and the number of the turbulence columns along the circumferential direction are integer multiples of N.
Advantageous effects
According to the porous laminate profile design method and the porous laminate flame tube in the embodiment of the application, the formed porous laminate flame tube with the whole-ring curved surface structure has smooth transition, small flow loss and continuous gas film coverage, fully exerts the advantages of high cooling efficiency and light weight of the porous laminate, and can meet the use requirements of a future high-temperature-rise main combustion chamber; because the structural form of whole-section large-radius curved surface and block welding is adopted, the laminate welding rate is high, the welding strength is high, and the process realizability is good; the welding line of the front adapter section and the welding line of the rear adapter section are positioned at the back of the splash shield, so that the radiation of high-temperature fuel gas can be effectively blocked, the welding line of the rear adapter section and the welding line of the rear adapter section are positioned at the outlet of the combustion chamber, the temperature of the fuel gas is greatly reduced, the heat exchange amount is reduced, cooling holes are additionally arranged on the circumferential welding line, the thermal stress gradient is reduced, and the welding strength of the flame tube is ensured.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic view of a porous laminate profile design method according to one embodiment of the present invention;
FIG. 2 is an enlarged view taken at point I in FIG. 1;
FIG. 3 is an enlarged view taken at point II of FIG. 1;
FIG. 4 is a schematic view of a multi-layered laminate combustor basket according to one embodiment of the present invention.
In the figure: 1. a combustion chamber head; 2. a head adapter section; 3. a splash plate; 4. a front adapter section; 5. a porous laminate; 6. and a rear switching section.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It should be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to or other than one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
In a first aspect, embodiments of the present application provide a method for designing a porous laminate profile, which is described in detail below.
In the structure of the flame tube, the porous laminate 5 is connected between the front transition section 4 and the rear transition section 6 of the flame tube, and referring to fig. 1 to 4, the profile design method of the porous laminate 5 comprises the following steps:
the method comprises the steps of firstly, obtaining structural parameters and pneumatic parameters, wherein the structural parameters comprise the inlet radius Rd (O point) of the head of a combustion chamber, the outlet inner ring radius Ri (F point), the outlet outer ring radius Ro (C point), the length L of a flame tube and the head height Hd, and the pneumatic parameters mainly comprise the inlet air flow rate, the inlet air temperature, the inlet air pressure, the reference section speed of the flame tube and the flow distribution of the combustion chamber.
And step two, determining a central line OO 'of the flame tube, wherein the distance from the point O to the central line KK' of the engine is equal to Rd, and the distance from the point O 'to the central line KK' of the engine is equal to (Ri + Ro)/2.
And step three, determining the length Ld of the head splash plate and the length Lc of the rear switching section 6, wherein the value range of the length Ld of the head splash plate is 10-25 mm, and the value range of the length Lc of the rear switching section 6 is 15-30 mm.
Step four, determining a point P and a point P': point P and point P' can be determined by known combustion chamber design methods from head height Hd, combustion chamber inlet air flow, inlet air temperature, inlet air pressure, liner reference cross-sectional velocity, and flow distribution, with the distance from point P to point P being equal to head height Hd.
Step five, determining an outer ring profile key control point A, B, C0 and an inner ring profile key control point D, E, F0 of the porous laminate 5, wherein points A and D are connection points of the porous laminate 5 and the front transition section 4, points CO and FO are connection points of the porous laminate 5 and the rear transition section 6, and points B and D are located in the middle area of the porous laminate 5, and the method comprises the following steps:
a parallel line passing through the point P and serving as OO ', wherein the point A and the point B are positioned on the parallel line of the OO', the distance h2 from the point A to the point P ranges from 2mm to 4mm, the distance h1 from the point A to the head splash disc ranges from 1mm to 3mm, and the axial distance from the point B to the point O ranges from 0.5L to 0.6L;
connecting BC, wherein the point C0 is on the straight line BC, and the axial distance from the point C0 to the point C is equal to Lc;
determining an inner ring profile key control point D, E, F0 in the same manner as the outer ring profile key control point A, B, C0;
sixthly, determining an outer ring profile Arc0 and an inner ring profile Arc0', and the method comprises the following steps:
the fold line ABC0 rotates around KK', forming a volume Vm 3 A rotary body of (2);
an Arc1 is made through A, B, C0, a tangent AA1 of Arc1 is made through a point A, a tangent C0C1 of Arc1 is made through a point C0, bisectors are respectively made into angle bisectors AA2 and C0C2 of a point A1AB and a point C1C0B, an Arc2 can be made through a tangent point A, a tangent point C0, a tangent AA2 and a tangent C0C2, and the Arc2 rotates around KK', so that a volume V1m is formed 3 Judging whether (V1-V)/V is smaller than the precision requirement, if the precision requirement is not met, respectively making angular bisectors AA3 and C0C3 of & lt A2AB and & lt C2C0B by adopting a bisection method, making an Arc3 by using a tangent point A, a tangent point C0, a tangent line AA3 and a tangent line C0C3, and rotating the Arc3 around KK' to form a volume of V2m 3 Judging whether (V2-V)/V is smaller than the precision requirement or not until the precision requirement is met to obtain a final Arc 0;
determining an inner ring profile Arc0' according to the same determination method as the Arc 0;
seventhly, the Arc0 and the Arc0' are respectively outwards biased to design the required flame tube thickness, the point A is biased to the point A ', the point CO is biased to the point C0', the point D is biased to the point D ', the point F0 is biased to the point F0', the point AA ' C0' CO is the outer ring profile section of the porous laminate 5, and the point DD ' F0' F0 is the inner ring profile section of the porous laminate 5.
In the embodiment, the flame tube profile is preliminarily determined through two straight lines according to the structural design parameters and the pneumatic design parameters of the combustion chamber(ii) a The key control points of the curved-surface-structure porous laminate 5 are determined by the length of the rear switching section 6, and a folding line formed by the three key control points rotates around the center line of the engine to form a volume Vm 3 The rotary body of the flame tube is used for making an arc through the key control points, making arc tangent lines through the front key control point and the rear key control point respectively, forming two acute angles by the two tangent lines and two straight lines of the primary profile of the flame tube respectively, making angle bisectors of the two acute angles by adopting a bisection method respectively, making a new arc by taking the two angle bisectors as tangent lines and the front control point and the rear control point as tangent points, and rotating the new arc around the central line of the engine to form a V1m volume 3 The revolution body is analogized in the same way, and the final molded surface of the porous laminated plate 5 with the curved surface structure is obtained until the volume of the revolution body formed by the new arc and the V meet the precision requirement. The curved surface structure porous laminate 5 is welded with the front transition section 4 and the rear transition section 6 into a whole to form a whole ring curved surface structure porous laminate 5 flame tube, the formed whole ring curved surface structure porous laminate 5 flame tube has smooth transition, the flow loss is small, the air film is continuously covered, the advantages of high cooling efficiency and light weight of the porous laminate 5 are fully exerted, and the use requirement of a future high-temperature-rise main combustion chamber can be met.
In a preferred embodiment, in step three, the length Ld of the head splash plate is set to 15mm, and the length Lc of the rear adapter section 6 is set to 20 mm; in the fifth step, the distance h2 from the point A to the point P is 3mm, the distance h1 from the splash disc is 2mm, and the axial distance from the point B to the point O is 0.55L; in step seven, Arc0 and Arc0' are respectively biased outwardly to the design requirement for a liner thickness of 2 mm.
In a second aspect, an embodiment of the present invention further provides a porous laminate 5 flame tube, referring to fig. 4, including a combustor head 1, a splash shield 3, a head adapter 2, a front adapter 4, a rear adapter 6, and a porous laminate 5 located between the front adapter 4 and the rear adapter 6, where the porous laminate 5 is designed by using the porous laminate profile design method according to any of the embodiments of the first aspect, the splash shield 3 is connected to the combustor head 1, the head adapter 2 is connected to the front adapter 4, and the porous laminate 5, the front adapter 4, and the rear adapter 6 are welded together to form a porous laminate flame tube with a full toroidal curved surface structure.
In a preferred embodiment, the welding seam of the porous layer plate 5 and the front adapter section 4 is positioned at the back of the splash shield 3 to prevent high-temperature fuel gas from directly radiating, and the welding seam of the rear adapter section is positioned at the outlet position of a combustion chamber, so that the temperature of the fuel gas is greatly reduced to reduce the heat exchange amount.
Furthermore, the porous laminated plate 5 is of a welding structure with N subunits uniformly distributed along the circumferential direction, the numerical value of N is less than or equal to 4, and the structural form of welding the whole section of large-radius curved surface in blocks is adopted, so that the laminated plate is high in welding rate, high in welding strength and good in process realizability.
In the above embodiment, the sub-units are connected by electron beam welding or laser welding.
Preferably, the welding seam of each subunit is additionally provided with a small cooling hole for cooling, the circumferential welding seam additionally provided with the cooling hole can reduce the thermal stress gradient, and the welding strength of the flame tube is ensured.
In one embodiment, the porous laminate 5 is provided with cooling holes and turbulence columns, and the number of the cooling holes and the turbulence columns in the circumferential direction are both integer multiples of N.
The porous laminate flame tube with the whole-ring curved surface structure designed by the method adopts the structural form of welding the whole section of large-radius curved surface in blocks, so that the laminate welding rate is high, the welding strength is high, the process realizability is good, the flow loss is small, the air film is continuously covered, the advantages of high cooling efficiency and light weight of the porous laminate are fully exerted, and the use requirement of a future high-temperature-rise main combustion chamber can be met.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (10)

1. A design method for the profile of a porous laminate is characterized in that the porous laminate is connected between a front transition section and a rear transition section of a flame tube,
the method for designing the profile of the porous laminate comprises the following steps:
the method comprises the following steps of firstly, obtaining structural parameters and pneumatic parameters, wherein the structural parameters comprise a combustor head inlet radius Rd, an outlet inner ring radius Ri, an outlet outer ring radius Ro, a flame tube length L and a head height Hd;
determining a central line OO 'of the flame tube, wherein the distance from the point O to the central line KK' of the engine is equal to Rd, and the distance from the point O 'to the central line KK' of the engine is equal to (Ri + Ro)/2;
step three, determining the length Ld of the head splash plate and the length Lc of the rear adapter section;
step four, determining a point P and a point P': determining a point P and a point P 'according to the pneumatic parameters and the structural parameters, wherein the distance from the point P to the point P' is equal to the height Hd of the head;
step five, determining an outer ring profile key control point A, B, C0 and an inner ring profile key control point D, E, F0 of the porous laminate, wherein points A and D are connection points of the porous laminate and the front transition section, points CO and FO are connection points of the porous laminate and the rear transition section, and points B and D are located in the middle area of the porous laminate and comprise the following steps:
making a parallel line of OO 'through the point P, wherein the point A and the point B are positioned on the parallel line of OO', the distance range from the point A to the point P is 2-4 mm, the distance range from the point A to the head splash plate is 1-3 mm, and the axial distance range from the point B to the point O is 0.5-0.6L;
connecting BC, wherein the point C0 is on the straight line BC, and the axial distance from the point C0 to the point C is equal to Lc;
determining an inner ring profile key control point D, E, F0 in the same manner as the outer ring profile key control point A, B, C0;
sixthly, determining an outer ring profile Arc0 and an inner ring profile Arc0', and including:
the fold line ABC0 rotates around KK', forming a volume Vm 3 A rotary body of (2);
making an Arc1 through A, B, C0 points, making a tangent AA1 of Arc1 through A point, making a tangent C0C1 of Arc1 through C0 point, respectively making angle bisectors AA2 and C0C2 of & lt A1AB and & lt C1C0B by adopting a bisection method, and then cuttingPoint A, tangent point C0, tangent line AA2, and tangent line C0C2 may make Arc2, Arc2 rotates around KK', forming a volume V1m 3 Judging whether (V1-V)/V is smaller than the precision requirement, if the precision requirement is not met, respectively making angular bisectors AA3 and C0C3 of & lt A2AB and & lt C2C0B by adopting a bisection method, making an Arc3 by using a tangent point A, a tangent point C0, a tangent line AA3 and a tangent line C0C3, and rotating the Arc3 around KK' to form a volume of V2m 3 Judging whether (V2-V)/V is smaller than the precision requirement or not until the precision requirement is met to obtain a final Arc 0;
determining an inner ring profile Arc0' according to the same determination method as the Arc 0;
seventhly, the Arc0 and the Arc0' are respectively outwards biased to design the required flame tube thickness, the point A is biased to the point A ', the point CO is biased to the point C0', the point D is biased to the point D ', the point F0 is biased to the point F0', the point AA ' C0' CO is the outer ring profile section of the porous laminate, and the point DD ' F0' F0 is the inner ring profile section of the porous laminate.
2. The method of claim 1, wherein the length Ld of the head splash plate ranges from 10mm to 25mm, and the length Lc of the rear adapter section ranges from 15mm to 30 mm.
3. The method of claim 1, wherein the aerodynamic parameters comprise combustor inlet air flow, inlet air temperature, inlet air pressure, liner reference cross-sectional velocity, and flow distribution.
4. A multi-layer flame tube comprising a burner head, a splash plate, a head transition section, a front transition section, a rear transition section, and a multi-layer plate located between the front transition section and the rear transition section, wherein the multi-layer plate is designed by the multi-layer plate profile design method as claimed in any one of claims 1 to 3, the splash plate is connected to the burner head, and the head transition section is connected to the front transition section.
5. The multi-layer laminate flame tube of claim 4, wherein the multi-layer laminate is welded to the front transition section and the rear transition section by welding.
6. The porous laminate combustor basket of claim 5, wherein the weld of the porous laminate to the forward transition is located at the back of the splash plate.
7. The porous laminate combustor basket of claim 4, wherein said porous laminate is provided as a welded structure of N subunits distributed uniformly in the circumferential direction, N being equal to or less than 4.
8. The multi-layer laminate flame tube of claim 7 wherein each of said sub-units is joined by electron beam welding or laser welding.
9. The porous laminate combustor basket of claim 7 wherein the welds of each of said sub-units are cooled by applying additional cooling apertures.
10. The multi-layer plate flame tube according to claim 7, wherein the multi-layer plate is provided with cooling holes and turbulence columns, and the number of the cooling holes and the turbulence columns in the circumferential direction are both integer multiples of N.
CN202210357428.6A 2022-04-07 2022-04-07 Porous laminate profile design method and porous laminate flame tube Active CN114491875B (en)

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