CN104204679B - Low burning dynamically arranges with the improvement hole of the burner inner liner of the gas-turbine unit of discharge - Google Patents

Low burning dynamically arranges with the improvement hole of the burner inner liner of the gas-turbine unit of discharge Download PDF

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Publication number
CN104204679B
CN104204679B CN201280071988.XA CN201280071988A CN104204679B CN 104204679 B CN104204679 B CN 104204679B CN 201280071988 A CN201280071988 A CN 201280071988A CN 104204679 B CN104204679 B CN 104204679B
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CN
China
Prior art keywords
hole
wall element
combustion chamber
surface density
arrangement
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Expired - Fee Related
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CN201280071988.XA
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Chinese (zh)
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CN104204679A (en
Inventor
C.贾亚藤加
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Siemens AG
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Siemens AG
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Classifications

    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A kind of gas-turbine combustion chamber with inner casing and shell.Described inner casing has inner wall element (501), and it has the first hole arrangement and the arrangement of the second hole.Described inner wall element surrounds combustion furnace volume.Described first hole arrangement has the first hole arranged with first surface density, and described second hole arrangement has the second hole arranged with the second surface density, and described first surface density is different from described second surface density.Described shell has outer wall element (502), and it has the first other hole arrangement and the second other hole arrangement.The outer wall element (502) of described shell surrounds the inner wall element (501) of described inner casing, makes to form gap between.Described the first hole arrangement in addition has the first other hole arranged with other first surface density, described the second hole arrangement in addition has the second other hole arranged with the second other surface density, and described other first surface density is different from described the second surface density in addition.

Description

Low burning dynamically arranges with the improvement hole of the burner inner liner of the gas-turbine unit of discharge
Technical field
The present invention relates to a kind of housing of the combustion chamber for gas turbine and a kind of method of the combustion chamber for the manufacture of gas turbine.
Background technology
In the technical field of gas turbine, object reduces to produce environmental contaminants, such as various nitrogen oxide (NOx), carbon monoxide (CO) and unburned hydrocarbon (UHC).Therefore, object is the combustion process realizing a kind of reliable and stable lean burn in the combustion chamber of gas turbine.
In order to provide the combustion process of lean burn, guiding and particularly mixing with the fuel in combustion furnace near more air of chamber front end (combustion process starts at this).This is realized by rebalancing effective area, and this effective area is the accumulation hole area of burn pot and the area of combustion furnace and cyclone.But by guiding more air to flow through front end, combustion chamber promotes combustion instability, and this is the intrinsic problem be associated with the burning of lean burn.
In order to suppress the burning of combustion instability particularly in combustion chamber dynamic, the wall elements of burning chamber shell is provided with the hole that gas exchanges is occurred by it.
GB2309296A discloses a kind of gas turbine engine combustion stove, and wherein this combustion furnace comprises combustion furnace wall and outer furnace walls.Damping hole is formed into furnace walls.Damping hole is arranged on wall portion equably, and namely each damping hole has identical distance each other.
EP1104871A1 discloses a kind of combustion chamber for gas-turbine unit, and wherein this combustion chamber is double-walled combustion chamber.The inner and outer wall of this double-walled combustion chamber comprises cascading water hole (effusionhole), to provide impinging cooling.Cascading water hole is evenly distributed on effective inwall or outer wall.
EP1321713A2 discloses a kind of flame tube of improvement of gas-turbine combustion chamber.Cooling-air can be conducted through the hole of each wall of flame tube.
Summary of the invention
Object of the present invention can be to provide a kind ofly has the combustion instability of reduction and the combustion chamber of more low emission.
This object can be solved by the method for the housing of the combustion chamber for gas turbine according to independent claims, the combustion chamber for gas turbine and the combustion chamber for the manufacture of gas turbine.
According to a first aspect of the invention, a kind of housing of the combustion chamber for gas turbine is proposed.Described housing comprises wall elements, and it comprises the first hole arrangement and the arrangement of the second hole.Described first hole arrangement comprises the first hole, and fluid can flow through this first hole.Described first hole arrangement also comprises the first surface density in described first hole.Described second hole arrangement comprises the second hole, and fluid can flow through this second hole.Described second hole arrangement also comprises second surface density in described second hole.Described first surface density is different from described second surface density.
According to other aspects of the invention, a kind of combustion chamber for gas turbine is proposed.Described combustion chamber comprises: inner casing, and it comprises the feature of above-mentioned housing; And shell, it also can comprise the feature of above-mentioned housing.The outer wall element of described shell surrounds the inner wall element of described inner casing at least in part, makes to form gap between described inner wall element and described other outer wall element.
Term " interior " and " outward " refer to the relative position of the distance between the flame volume of described inside and outside wall elements relative in wall elements and combustion chamber.The central axis of described combustion chamber can be the line of symmetry of (being such as formed as columniform) combustion chamber (such as pot combustion chamber), namely through flame region, or it can such as with the rotor center line parallel of gas turbine (such as toroidal combustion chamber) or even overlap.
According to a further aspect in the invention, a kind of method of the combustion chamber for the manufacture of gas turbine is proposed.According to the method, the first hole arrangement comprising the first hole is formed as the inner wall element of inner housing, and wherein fluid can flow through this first hole, and wherein said first hole arrangement comprises the first surface density in described first hole.In addition, according to the method, the second hole arrangement comprising the second hole is formed as described inner wall element, and wherein fluid can flow through this second hole, and wherein said second hole arrangement comprises second surface density in described second hole.Described first surface density is different from described second surface density.
Term " surface density " (superficial density) limits the quantity in the hole of per unit area.Such as, if two adjacent hole arrangements comprise different surface densities, then each hole comprising varying number in described adjacent holes arrangement.This causing hole is non-uniform Distribution in the arrangement of corresponding hole.
Therefore, by the present invention, the wall elements for the housing of combustion chamber comprises the first hole arrangement with described first surface density and the second hole arrangement with described second surface density.Therefore, the pore size distribution of wall elements is uneven, and is particularly suitable for the respective flow characteristic of the corresponding fluids flowed along described wall elements.
Housing for the combustion chamber of gas turbine can be the inner casing of the combustion volume around such as combustion chamber.Described housing can also be partly around the shell of described inner casing.Therefore, by application inner casing and shell, double-walled combustion chamber (i.e. double-deck lining) can be formed.Gap can exist between described inner casing and described shell.Along the fluid of outer wall element flowing, such as cooling fluid/gas, can enter this gap, for cooling object by the first and second holes of described outer wall element.This fluid can also flow through described inner wall element the first and second holes from this gap enter the combustion space of combustion chamber, for cooling object.
The inwall of the inner housing of double-deck lining surrounds the combustion furnace volume of combustion chamber.Around described inner casing and thus around this combustion furnace volume, the outer wall of shell is with the inwall providing the mode in gap to surround so double-deck lining.Therefore, this gap is also round combustion furnace volume.The respective aperture that chilled fluid flow can flow through outer wall enters this gap.Cooling fluid also flows through described inwall hole from the gap between these two wall elements enters the combustion furnace volume of combustion chamber.
Therefore, by the conventional method of combustion chamber, the hole for the wall elements of the housing of combustion chamber distributes equably.In conventional methods where, the first hole arrangement and the second hole arrange one and identical surface density comprising respective aperture.According to the inventive method of the present invention, hole is anisotropically distributed in (inside and outside) housing of combustion chamber.Therefore, the distribution in hole can aim at the flow parameter of (burning) fluid of combustion chamber and aims at the flow parameter of refrigerating gas and customize.Therefore, the burning in combustion chamber dynamically can be reduced.Therefore, the life-span of housing and other combustion components becomes longer because of the minimizing of the fluctuation of the Temperature Distribution of such as wall elements.In addition, dynamic by the burning of the minimizing of wall portion, the running temperature that turbine puts rate and turbine can increase, and can not affect the life-span of burning chamber shell.Therefore, nitrogen (NOx) discharge can be reduced equally, such as, by adopting lean burn operating gas turbine, namely by pilot fuel lower in gas turbine shunting.In a word, hole arranged in a non-uniform manner, and pass through by the patterned arrangement in hole in the arrangement of corresponding hole, combustion chamber can be run with the discharge of lower nitrogen (NOx), because such as more air can be transported to combustion process, for providing lean burn.In addition, flame temperature is minimized because of lean burn.
According to further exemplary embodiment, described wall elements forms the central axis be used for around combustion chamber and circumferentially extends at least in part.Generally speaking, combustion chamber is formed as cylindrical shape (or conical).Such as, central axis forms the such as axis of symmetry of combustion chamber.According to further exemplary embodiment, the first hole of described first hole arrangement is one after the other formed in described wall elements along described circumferencial direction, for the formation of at least one first row in the first hole.
According to further exemplary embodiment, the second hole of described second hole arrangement is one after the other formed in described wall elements along described circumferencial direction, for the formation of at least one second row in the second hole.Circumferentially observe whole, the quantity in the first hole such as equals the quantity in the second hole, but for every round, the surface density between the first round from the second round is different.
According to further exemplary embodiment, the second hole of described second hole arrangement is one after the other formed in described wall elements along described circumferencial direction, for the formation of at least one second row in the second hole.Because the first surface density that the first hole in described first hole arrangement comprises is different from second surface density in the second hole of described second hole arrangement, so the quantity in the first hole is such as different from the quantity in described second hole.
Just comprise the above-mentioned exemplary embodiment of described first row and second row, the quantity of first row is different from the quantity of second row.Additionally or alternatively, the quantity in the first hole in first row is different from the quantity in the second hole of second row.This causes first surface density to be different from the second surface density, and therefore the first and second holes along wall elements non-uniform Distribution.
According to further exemplary embodiment, the first hole of described first hole arrangement is one after the other formed in described wall elements along first direction.Described first direction is different from described circumferencial direction, for the formation of at least one other first row in the first hole.
Especially, according to further exemplary embodiment, the first angle between described first direction and described circumferencial direction between about 10 ° and about 80 °, particularly between about 30 ° and about 60 °.Therefore, described first hole is aligned in wall elements, makes described other first row along corresponding (such as tubulose) wall elements layout in a helical pattern.
According to further exemplary embodiment, the second hole of described second hole arrangement is one after the other formed in described wall elements along second direction.Described second direction is different from described circumferencial direction and/or is different from described first direction, for the formation of at least one other second row in the second hole.
Especially, according to further exemplary embodiment, the second angle between described second direction and described circumferencial direction between about 10 ° and about 80 °, particularly between about 30 ° and about 60 °.By described other first row and described other second row, corresponding first and/or second hole is one after the other formed along corresponding first and second directions, first row other accordingly and second row other accordingly can be formed and move towards along the spiral (i.e. spirality) of wall elements around central axis.
According to the further exemplary embodiment of the method, relative to described inner wall element, arrange the outer wall element of shell, make described outer wall element surround described inner wall element at least in part, and make to form gap between described inner wall element and described outer wall element.
According to the further exemplary embodiment of the method, the first hole arrangement is in addition formed as outer wall element, wherein, described the first hole arrangement in addition comprises the first other hole, and other fluid (such as cooling fluid/gas) can flow through described the first hole in addition.Described the first hole arrangement in addition comprises the other first surface density in described the first hole in addition.In addition, the the second other hole arrangement comprising the second other hole is formed as outer wall element, and wherein, other fluid (such as cooling fluid/gas) can flow through described the second hole in addition, wherein, described the second hole arrangement in addition comprises the second other surface density in described second hole.Described other first surface density is different from described the second surface density in addition.
Total hole area of described inner and/or outer wall distributes throughout described wall, thus forms band or the region with different holes density.The standard of distribution depends on flow parameter, and it can be such as the temperature of described fluid and/or other fluid, flow velocity, flow direction and/or turbulent flow.
Therefore, by said method, the layout in described first hole and the second hole is designed and is formed, and take into account the flow parameter of corresponding fluids simultaneously.Therefore, provide hole effective pore size distribution and thus described fluid and described other fluid along the guiding of the improvement of respective wall element.Thus, the efficiency of combustion chamber is also achieved because of the arrangement of suitable hole.
Such as, in the beginning of the method, the hole of the hole arrangement in wall elements can distribute equably, and therefore comprises equal face density.Then, a some holes can be removed from the arrangement of existing hole, make to be formed the hole density of unequal distribution between point other hole arrangement and non-equal.Then, in flow test, measure total hole area how to reduce, as confirmation.Then, how calculating processes and arranges corresponding hole, to obtain Nominal flow parameter and to achieve good damping characteristic.Then, by corresponding pore size distribution in the arrangement of corresponding hole, make to form the uneven distribution in hole and/or uneven surface density, to match with total effective flow area of the Nominal flow parameter calculated and combustion chamber respectively.
By foregoing invention, the burning of the fluid in combustion chamber dynamically can be reduced.In other words, described inner wall element and outer wall element can be bored a hole in mode that is non-homogeneous and customization.Therefore, due to dynamic reduction of burning, the life-span of combustion chamber components and the turbine stage parts that are positioned at downstream is achieved because of the flame fluctuation that reduces and Temperature Distribution.In addition, NOx emission is reduced because due to the burning reduced dynamic, lower pilot fuel shunting (pilot fuel/[pilot fuel+main fuel]) can be applied.
It must be noted that, with reference to different themes, embodiments of the invention are illustrated.Especially, comparable device type claims is to certain embodiments have been explanation, and reference method type claims is illustrated other embodiments.But, those skilled in the art will from above-mentioned and below description understand, except as otherwise noted, except belonging to any combination of the feature of the theme of a type, any combination between the feature of Method type claim described in the characteristic sum of the particularly described type of device claim between the feature relating to different themes is considered to open with the application equally.
Accompanying drawing explanation
According to the example of the embodiment that hereafter will describe, above-mentioned aspect of the present invention and other each side become apparent, and make an explanation to it with reference to the example of embodiment.With reference to the example of the embodiment that the present invention is not limited thereto, the present invention will be described hereinafter in further detail.
Fig. 1 shows the housing of the combustion chamber according to an exemplary embodiment of the present invention with the first and second rounds;
Fig. 2 shows the housing of the combustion chamber according to an exemplary embodiment of the present invention with the first and second rounds;
Fig. 3 and Fig. 4 shows the abstract view of the sectional hole patterns in the respective housings of combustion chamber according to an exemplary embodiment of the present invention;
Fig. 5 shows the schematic diagram of the combustion chamber comprising inner and outer shell; And
Fig. 6 shows the schematic diagram for the manufacture of the method for housing according to an exemplary embodiment of the present invention.
Detailed description of the invention
Diagram in each figure is schematic.It is to be noted, in various figures, similar or identical element is with identical Reference numeral.
Fig. 1 shows the housing of the combustion chamber 100 for gas turbine.This housing comprises wall elements 101, and it comprises the first hole arrangement I and the second hole arrangement II.First hole arrangement I comprises the first hole 110, and fluid can flow through this first hole 110.First hole arrangement I comprises the first surface density in the first hole 110.
Second hole arrangement II comprises the second hole 120, and fluid can flow through this second hole 120.Second hole arrangement II comprises second surface density in the second hole 120.
Described first surface density is different from described second surface density.That is, the quantity in the first hole 110 of per unit area is different from the quantity in the second hole 120 of per unit area.In other words, relative to the distribution in the second hole 110, hole 120, first in the second hole arrangement II, there is different patterns and/or different quantity and/or different size (such as bore dia).
Such as, as obtained from Fig. 1, the first hole arrangement I, the second hole arrangement II and such as the 3rd hole arrangement III comprise identical size.In addition, the first hole arrangement I, the second hole arrangement II and the 3rd hole arrangement III can limit such face unit, and namely this face unit can limit corresponding first, second and/or the 3rd surface density of this some holes.
In FIG, the density in the first hole 110 in the first hole arrangement I is respectively higher than the second hole arrangement II and the 3rd hole respective the second surface density of arrangement III and the 3rd surface density.
More hole can be arranged in the upstream front end of wall elements 101, because flame is positioned at this.Such as, as Fig. 1 exemplarily illustrates, the first hole arrangement I can have three first rows 111, be positioned at the second further downstream hole arrangement II and can have two second rows 121, and the 3rd hole arrangement III being positioned at farther downstream can have one the 3rd row 131.
Especially, as shown in Figure 1, along the central axis 102 of combustion chamber 100, relative to the flow direction of fluid, combustion chamber 100 is included in the upstream position combustion furnace part 104 (such as fore-end) of combustion chamber 100.Along central axis 102, relative to the flow direction of fluid, at the downstream end of combustion chamber 100, burning gases discharge combustion chamber 100, and such as flow to the turbine stage of gas turbine further.As obtained from Fig. 1, the surface density in corresponding hole 110,120,130 is reduce from the upstream extremity of combustion chamber 100 to downstream.By the exemplary distribution of Fig. 1 mesopore 110,120,130, first hole 110 of the first hole arrangement I circumferentially 103 is one after the other formed in wall elements 101, for the formation of the first row 111 in described first hole 110.Contiguous first row 111 and along downstream direction, second hole 120 of the second hole arrangement II circumferentially 103 is one after the other formed in wall elements 101, for the formation of two second rows 121 in such as the second hole 120.In addition, as shown in Figure 1, the 3rd hole 113 of the 3rd hole arrangement III circumferentially 103 is one after the other formed in wall elements 101, for the formation of at least three the 3rd rows 131 in described 3rd hole 130.
Such as, if each hole arrangement I, II, III comprise identical restriction area, then the quantity in hole 110,120,130 and the quantity of row 111,121,131 reduce along from the upstream extremity of combustion chamber 100 to the direction of the downstream in combustion chamber 100.Such as, distance in other words, between described two second rows 121 is less than the distance between described 3rd row 131.Such as, the distance between the first row 111 of the upstream extremity of combustion chamber 100 can be the half of the distance between the 3rd row 131 of the downstream part of combustion chamber 100.
In FIG, hole arrangement I, II, III as shown in Figure 1 can be applied to inner wall element 501 (with reference to Fig. 5) (neck bush).Due to from combustion chamber 100 upstream extremity to the pore size distribution heterogeneous along central axis 102 of combustion chamber 100 downstream, the surface density in the hole of downstream part, combustion chamber is lower than the surface density in the hole of upstream portion.In addition, compared to the hole arrangement be evenly arranged, can also realize particularly in the suitable cascading water cooling of wall elements 101 upstream portion.In addition, by pore size distribution as shown in Figure 1, the suitable dynamically damping characteristic of the burning in combustion chamber 100 is achieved.Respectively based on the minimizing desired by the effective area of combustion chamber with by the mass flow desired by the cooling fluid in point other hole 110,120,130 of running through inwall, draw this layout of axially row 111,121,131.
Fig. 2 shows combustion chamber 100, and wherein, wall elements 101 comprises the first hole arrangement I and the second hole arrangement II.First hole 110 of described first hole arrangement I is one after the other formed in wall elements 101 along first direction 201.First direction 201 is different from circumferencial direction 103, for the formation of at least one other first row 211 in the first hole 110.
Additionally or alternatively, second hole 120 of described second hole arrangement II is one after the other formed in wall elements 101 along second direction 202.Second direction 202 is different from circumferencial direction 103, for the formation of at least another one second row 221 in the second hole 120.
As obtained from Fig. 2, other first row 211 can comprise such as two the first holes 110.Other second row 221 comprises such as three the second holes 120.Therefore, the surface density in the second hole 120 in the second hole arrangement II arranges the surface density in the first hole 110 in I higher than the first hole.
In addition, as shown in Figure 2, by respectively along the hole 110,120 that the first and second directions are arranged, spiral (spirality) trend along wall elements 101 around central axis 102 is defined.In other words, the respective aperture 110,120 in Fig. 2 is relative to circumferencial direction 103 (with spirality pattern) layout in an inclined manner.
Especially, the housing comprising sectional hole patterns as shown in Figure 2 may be used for the shell with outer wall element 502 (with reference to Fig. 5).Especially, the first direction of the other first row 211,221 of inclination can be in the direction identical with the screw of the burning gases in combustion chamber 100 with second direction.In addition, the spacing between the other row 211,221 of two adjacent inclinations circumferentially 103 can or uniform or heterogeneous, be determined by the required flow parameter in each hole 110,120,130.
The combustion chamber 100 comprising the shell shown in the inner casing shown in Fig. 1 and Fig. 2 has surprising effect: efficient flame dynamic antivibration and stable flame characteristics in cooling performance, combustion chamber efficiently.
Fig. 3 shows the more abstract view of sectional hole patterns as shown in Figure 2.In figure 3, especially, the sectional hole patterns of the outer wall 502 (with reference to Fig. 5) of the shell of combustion chamber 100 is shown.In figure 3, the first hole arrangement I and the second hole arrangement II is schematically illustrated.First hole 110 is one after the other arranged along other first row 211.Other first row 211 extends along first direction 201.First angle [alpha] 1 is limited between first direction 201 and circumferencial direction 103.
Second hole 120 is one after the other arranged in the second hole arrangement II along second direction 202, and defines other second row 221.Second angle [alpha] 2 is limited between second direction 202 and circumferencial direction 103.
As shown in Figure 3, other first row 211 and other second row 221 have spirality (inclination) trend relative to circumferencial direction 103.Especially, as shown in Figure 3, circumferentially 103, the distance between each other row 211,221 is different among each other.Such as, as as shown in the first hole arrangement I, first hole arrangement I comprises 3 to other first row 211, and larger than between every two other first rows 211 of the distance wherein existed between often pair of other first row 211, which defines each to other first row 211.
By contrast, as shown in the second hole arrangement II, the second hole arrangement II comprises two to other second row 221 and an other second row arrangement, and described other second row arrangement comprises three other second rows 221.
Therefore, along shown circumferencial direction, the distance between each row 211,221 is in addition different, thus provides the non-uniform Distribution in hole 110,120.
Fig. 4 shows the abstract view as the sectional hole patterns be schematically shown in FIG.Especially, when the sectional hole patterns shown in Fig. 4 may be favourable when being applied to the inwall 501 (with reference to Fig. 5) of inner casing of combustion chamber 100.The first row 111 in the first hole 110 and the second row 121 in the second hole 120 are one after the other arranged along axis direction 102, and wherein said first row 111 and second row 121 are parallel relative to circumferencial direction 103.Distance between first row 111 in first hole arrangement I is less than the distance between the second row 121 of the second hole arrangement II.
In order to observe better, Fig. 5 shows the cross section of the combustion chamber 100 of double wall pot.The inwall 501 of inner casing surrounds the combustion furnace volume of combustion chamber 100.Around this inner casing, the outer wall 502 of shell is to be provided with the mode in gap around inwall 501.Chilled fluid flow 503 can flow through the respective aperture 110,120 of outer wall 502 in this gap.Chilled fluid flow 503 forms chilled fluid flow 504 at least partially, and described chilled fluid flow 504 is passed through hole 110,120,130 flowing in combustion chamber 100 of inwall 501 from the gap between these two wall elements 501,502.Chilled fluid flow 504 may be less than or greater than chilled fluid flow 503, depends on whether cooling fluid has been added into gap between these two wall elements 501 and 502 or from wherein removing.
As shown in Figure 5, inwall 501 and outer wall 502 round central axis 102, and form the cylindrical portion of combustion chamber 100 thus.
Fig. 6 shows the method for hole arrangement I, II, III of calibration and the inner wall element 501 desired by layout and outer wall element 502.In step 601, initial combustion chamber design is limited.Initial combustion chamber designs the sectional hole patterns of the even or non-uniform Distribution in includable wall elements 501 and/or in outer wall element 502.
Then, under nominal operating conditions combustion chamber operated, measure or analyze, make inner wall element 501 and outer wall element 502 be exposed to chilled fluid flow 503 and other chilled fluid flow 504 respectively.With its point, other runs point other hole that flow parameter flows through inner wall element 501 and outer wall element 502 to cooling fluid.
Then, in step 602, hole arrangement I, II, III of inner wall element 501 is determined.The effective area of inner wall element 501 is determined by the sum in the hole 110,120,130 of inner wall element 501.Similarly, in step 603, hole arrangement I, II, III of outer wall element 502 is determined.The effective area of outer wall element (external bushing) 502 is determined by the sum in the hole 120,130,140 of outer wall element 502.
Then, in step 605, based on hole arrangement I, II, III of inner wall element 501 and hole arrangement I, II, III of outer wall element 502, the effective area of total combustion chamber 100 is determined.
In addition, determine to leave the flow parameter (speed of such as, other chilled fluid flow 504) (with reference to step 604) that inner wall element 501 enters the fluid in the combustion space of combustion chamber 100.
Then, in step 606, the geometric parameter of inside and outside wall element 501,502 (i.e. combustion chamber 100) of the value of the determination of the flow parameter of cooling fluid 503,504 and combination and the nominal value of such as speed of cooling fluid 503,504 and the effective area of combustion chamber 100 are compared.
If the nominal value of the geometric parameter of the flow parameter recorded and/or combustion chamber 100 does not correspond to corresponding nominal value, then in step 607, other sectional hole patterns is divided to revise individually thus, until reach the nominal value of flow parameter/geometric parameter to the first surface density of the respective aperture in inner wall element 501 and/or outer wall element 502, other first surface density, the second surface density and/or the second other surface density.
If reach nominal value, then the final design of the sectional hole patterns of inner wall element 501 and outer wall element 502 is achieved (with reference to step 608).
Therefore, by said method as shown in Figure 6, under the actual operating conditions of combustion chamber, realize the customization of inner wall element 501 and outer wall element 502 and the wall pattern of optimization, thus design the fluid flowing of optimization and effective combustion chamber 100.In traditional method, sectional hole patterns is being calculated and given surface is distributing fifty-fifty.By this method, determine the sectional hole patterns in given surface, to use as shown in Figure 6 and repetitive process as above balances requirement in damping and the requirement from the teeth outwards in distribution cooling-air.In other words, sectional hole patterns aims at the condition of work of the gas turbine that combustion chamber 100 and combustion chamber 100 are mounted to and customizes.
For the sake of clarity, in above-mentioned each accompanying drawing, not every hole 110,120,130 and row 111,121,131,211,221 are indicated point other Reference numeral.
It should be noted that term " comprises " and do not get rid of other elements or step, and "a" or "an" is not got rid of multiple.In addition, can be combined in conjunction with the element described by different embodiment.Should also be noted that the Reference numeral in claim should not be interpreted as limiting the scope of claim.

Claims (15)

1. the combustion chamber for gas turbine (100), described combustion chamber (100) comprising:
Inner casing and shell,
Wherein, described inner casing comprises inner wall element (501), and it comprises the first hole arrangement (I) and the second hole arrangement (II), wherein, described inner wall element (501) surrounds the combustion furnace volume of described combustion chamber (100)
Wherein, described first hole arrangement (I) comprises the first hole (110), and fluid can flow through this first hole (110), and wherein, described first hole (110) is arranged with first surface density,
Wherein, described second hole arrangement (II) comprises the second hole (120), and fluid can flow through this second hole (120), and wherein, described second hole (120) is arranged with the second surface density, and
Wherein, described first surface density is different from described second surface density, and
Wherein, described shell comprises outer wall element (502), described outer wall element comprises the first other hole arrangement and the second other hole arrangement, wherein, the outer wall element (502) of described shell surrounds the inner wall element (501) of described inner casing at least in part, make to form gap between described inner wall element (501) and described outer wall element (502)
Wherein, described the first hole arrangement in addition comprises the first other hole, and fluid can flow through described the first hole in addition, and wherein, described the first hole is in addition arranged with other first surface density,
Wherein, described the second hole arrangement in addition comprises the second other hole, and fluid can flow through described the second hole in addition, and wherein, described the second hole is in addition arranged with the second other surface density, and
Wherein, described other first surface density is different from described the second surface density in addition.
2. combustion chamber according to claim 1 (100),
Wherein, described inner wall element (501) around described combustion chamber (100) central axis (102) circumferentially (103) extend, and/or
Wherein, described outer wall element (502) is around central axis (102) circumferentially (103) extension of described combustion chamber (100).
3. combustion chamber according to claim 1 (100),
Wherein, described inner wall element (501) around gas turbine central axis (102) circumferentially (103) extend, and/or
Wherein, described outer wall element (502) is around central axis (102) circumferentially (103) extension of gas turbine.
4. the combustion chamber (100) according to Claims 2 or 3,
Wherein, first hole (110) in described first hole arrangement (I) is one after the other formed in described inner wall element (501) along described circumferencial direction (103), for the formation of at least one first row (111) of the first hole (110), and/or
Wherein, the first other hole of described the first hole arrangement in addition is one after the other formed in described outer wall element (502), for the formation of at least one other first row in the first other hole along described circumferencial direction (103).
5. the combustion chamber (100) according to any one of Claims 2 or 3,
Wherein, second hole (120) in described second hole arrangement (II) is one after the other formed in described inner wall element (501) along described circumferencial direction (103), for the formation of at least one second row (121) of the second hole (120), and/or
Wherein, the second other hole of described the second hole arrangement in addition is one after the other formed in described outer wall element (502), for the formation of at least one other second row in the second other hole along described circumferencial direction (103).
6. the combustion chamber (100) according to Claims 2 or 3,
Wherein, first hole (110) in described first hole arrangement (I) is one after the other formed in described inner wall element (501) along first direction (201),
Wherein, described first direction (201) is different from described circumferencial direction (103), for the formation of at least one other first row (211) of the first hole (110),
Wherein, the first other hole of described the first hole arrangement in addition is one after the other formed in described outer wall element (502) along other first direction,
Wherein, described other first direction is different from described circumferencial direction (103), for the formation of at least one other outer first row in the first other hole.
7. combustion chamber according to claim 6 (100),
Wherein, the first angle (α 1) between described first direction (201) and described circumferencial direction (103) between 10 ° and 80 °, and/or
Wherein, the first other angle between described other first direction and described circumferencial direction (103) is between 10 ° and 80 °.
8. the first angle (α 1) combustion chamber according to claim 7 (100), wherein, between described first direction (201) and described circumferencial direction (103) between 30 deg. and 60 deg..
9. the first other angle combustion chamber according to claim 7 (100), wherein, between described other first direction and described circumferencial direction (103) between 30 deg. and 60 deg..
10. the combustion chamber (100) according to Claims 2 or 3,
Wherein, second hole (120) in described second hole arrangement (II) is one after the other formed in described inner wall element (501) along second direction (202),
Wherein, described second direction (202) is different from described circumferencial direction (103), for the formation of at least one other second row of the second hole (120), and/or
Wherein, the second other hole of described the second hole arrangement in addition is one after the other formed in described outer wall element (502) along other second direction,
Wherein, described other second direction is different from described circumferencial direction (103), for the formation of at least one other outer second row in the second other hole.
11. combustion chambers according to claim 10 (100),
Wherein, the second angle (α 2) between described second direction (202) and described circumferencial direction (103) between 10 ° and 80 °, and/or
Wherein, the second other angle between described other second direction and described circumferencial direction (103) is between 10 ° and 80 °.
12. combustion chambers according to claim 11 (100), wherein, the second angle (α 2) between described second direction (202) and described circumferencial direction (103) between 30 deg. and 60 deg..
13. combustion chambers according to claim 11 (100), wherein, the second other angle between described other second direction and described circumferencial direction (103) between 30 deg. and 60 deg..
The method of 14. 1 kinds of combustion chambers for the manufacture of gas turbine (100), described method comprises:
Form the first hole arrangement (I), it is included in the first hole (110) in the inner wall element (501) of the inner casing of combustion chamber (100), wherein, fluid can flow through this first hole (110), wherein, described first hole (110) is arranged with first surface density, and
Form the second hole arrangement (II), it is included in the second hole (120) in described inner wall element (501), wherein, fluid can flow through this second hole (120), wherein, described second hole (120) is arranged with the second surface density
Wherein, described first surface density is different from described second surface density, and
Wherein, described inner wall element (501) surrounds the combustion furnace volume of described combustion chamber (100),
Relative to described inner wall element (501), arrange the outer wall element (502) of the shell of combustion chamber (100), described outer wall element (502) is made to surround described inner wall element (501) at least in part, and make to form gap between described inner wall element (501) and described outer wall element (502)
The first other hole arrangement is formed in described outer wall element (502), described the first hole arrangement in addition comprises the first other hole, and other fluid can flow through described the first hole in addition, wherein, described the first hole is in addition arranged with other first surface density, and
The second other hole arrangement is formed in described outer wall element (502), described the second hole arrangement in addition comprises the second other hole, and other fluid can flow through described the second hole in addition, wherein, described the second hole is in addition arranged with the second other surface density
Wherein, described other first surface density is different from described the second surface density in addition.
15. methods according to claim 14, described method also comprises:
Fluid stream (503) is made to flow through described first hole arrangement (I) and described second hole arrangement (II),
Make other fluid stream (504) flow through described the first hole in addition to arrange and described the second hole arrangement in addition,
Determine the flow parameter of described fluid stream (503) and/or described other fluid stream (504), and
Revise described first surface density, described other first surface density, described second surface density and/or described the second surface density in addition, until the measured value of the geometric parameter of the flow parameter of described fluid stream (503) and/or combustion chamber (100) meets the respective nominal values of the geometric parameter of this flow parameter and/or combustion chamber (100).
CN201280071988.XA 2012-03-27 2012-12-05 Low burning dynamically arranges with the improvement hole of the burner inner liner of the gas-turbine unit of discharge Expired - Fee Related CN104204679B (en)

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EP20120161509 EP2644995A1 (en) 2012-03-27 2012-03-27 An improved hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions
EP12161509.0 2012-03-27
PCT/EP2012/074459 WO2013143627A1 (en) 2012-03-27 2012-12-05 An improved hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions

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RU2582378C1 (en) 2016-04-27
US20150101335A1 (en) 2015-04-16
CN104204679A (en) 2014-12-10
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JP6005836B2 (en) 2016-10-12
JP2015511696A (en) 2015-04-20

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