CN104204679A - An improved hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions - Google Patents
An improved hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions Download PDFInfo
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- CN104204679A CN104204679A CN201280071988.XA CN201280071988A CN104204679A CN 104204679 A CN104204679 A CN 104204679A CN 201280071988 A CN201280071988 A CN 201280071988A CN 104204679 A CN104204679 A CN 104204679A
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- hole
- combustion chamber
- surface density
- wall elements
- wall element
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
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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
- F23R3/02—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
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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
- F23R3/002—Wall structures
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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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
- F23R3/42—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
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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
- 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
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
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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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
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- 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
Gas turbine combustion chamber with an inner housing and an outer housing. The inner housing has an inner wall element (501) with a first hole arrangement and a second hole arrangement. The inner wall element envelopes a burner volume. The first hole arrangement has first holes arranged in a first areal density, the second hole arrangement has second holes arranged in a second areal density, the first areal density differs from the second areal density. The outer housing has an outer wall element (502) with a further first hole arrangement and a further second hole arrangement. The outer wall element (502) of the outer housing envelops the inner wall element (501) of the inner housing so that a gap in between is formed. The further first hole arrangement has further first holes arranged in a further first areal density, the further second hole arrangement has further second holes arranged in a further second areal density, the further first areal density differs from further the second areal density.
Description
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 is to reduce to produce environmental contaminants, such as various nitrogen oxide (NOx), carbon monoxide (CO) and unburned hydrocarbon (UHC).Therefore, object is in the combustion chamber of gas turbine, to realize a kind of combustion process of reliable and stable lean burn.
For the combustion process of lean burn is provided, guiding particularly mixes with the fuel in combustion furnace near more air of chamber front end (combustion process starts at this).This realizes by rebalancing effective area, and this effective area is the accumulation hole area of burn pot and the area that combustion furnace is cyclone.Yet by guiding more air to flow through front end, combustion chamber promotes combustion instability, this is the intrinsic problem being associated with the burning of lean burn.
In order to suppress combustion instability, particularly the burning in combustion chamber is dynamic, and the wall elements of burning chamber shell is provided with the hole that gas exchange occurs by it.
GB 2 309 296 A disclose a kind of gas-turbine unit combustion furnace, and wherein this combustion furnace comprises internal fired furnace wall and outer furnace walls.Damping hole is formed into furnace walls.Damping hole is arranged on wall part equably, and each damping hole has identical distance each other.
EP 1 104 871 A1 disclose 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 (effusion hole), to provide impact cooling.Cascading water hole is evenly distributed on effective inwall or outer wall.
EP 1 321 713 A2 disclose a kind of improved flame tube 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 of the have combustion instability of reduction and the combustion chamber of low emission more.
This object can be by according to the housing of the combustion chamber for gas turbine described in independent claims, solve for the combustion chamber of gas turbine and for the manufacture of the method for the combustion chamber of gas turbine.
A kind of housing of the combustion chamber for gas turbine has been proposed according to a first aspect of the invention.Described housing comprises wall elements, and it comprises that arrange in the first hole and arrange in the second hole.Described the first hole is arranged and to be comprised that the first hole, fluid can flow through this first hole.The first surface density that also comprises described the first hole is arranged in described the first hole.Described the second hole is arranged and to be comprised that the second hole, fluid can flow through this second hole.The second surface density that also comprises described the second hole is arranged in described the second hole.Described first surface density is different from described the second surface density.
According to other aspects of the invention, a kind of combustion chamber for gas turbine has been 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 elements 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 elements.
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 (for example forming columniform) combustion chamber (such as tank type combustion chamber), through flame region, or its can be for example with the rotor center line parallel of gas turbine (such as toroidal combustion chamber) or even overlap.
A kind of method of the combustion chamber for the manufacture of gas turbine has been proposed according to a further aspect in the invention.According to the method, comprise that the inner wall element that forms inner housing is arranged in first hole in the first hole, wherein fluid can flow through this first hole, and the first surface density that comprises described the first hole is arranged in wherein said the first hole.In addition, according to the method, comprise that the second hole arrangement in the second hole forms described inner wall element, wherein fluid can flow through this second hole, and the second surface density that comprises described the second hole is arranged in wherein said the second hole.Described first surface density is different from described the second surface density.
Term " surface density " (superficial density) limits the quantity in the hole of per unit area.For example, if arrange in two adjacent holes, comprise different surface densities, each in described adjacent holes arrangement comprises the hole of varying number.This causes hole to arrange non-uniform Distribution in corresponding hole.
Therefore,, by the present invention, for the wall elements of the housing of combustion chamber, comprise that arrange in first hole with described first surface density and arrange in second hole with described the second surface density.Therefore, the pore size distribution of wall elements is inhomogeneous, and is particularly suitable for along the respective flow characteristic of the mobile corresponding fluids of described wall elements.
The housing that is used for the combustion chamber of gas turbine can be the inner casing around the combustion volume of for example combustion chamber.Described housing can also be partly around the shell of described inner casing.Therefore,, by application inner casing and shell, can form double-walled combustion chamber (being double shall).Gap can exist between described inner casing and described shell.Along the mobile fluid of outer wall elements, for example cooling fluid/gas, can enter this gap by the first and second holes of described outer wall elements, for cooling object.The first and second holes that this fluid can also flow through from this gap described inner wall element enter the combustion space of combustion chamber, for cooling object.
The inwall of the inner housing of double shall surrounds the combustion furnace volume of combustion chamber.Thereby around described inner casing and around this combustion furnace volume, the outer wall of shell is to provide the mode in gap to surround the inwall of such double shall.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, for the hole of the wall elements of the housing of combustion chamber, distribute equably.In conventional method, arrange in the first hole and and the identical surface density that comprises respective aperture arranged in the second hole.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 combustion chamber (burning) fluid 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 for example wall elements.In addition, the burning of the minimizing by wall portion is dynamic, and the running temperature that turbine is put rate and turbine can increase, and can not affect the life-span of burning chamber shell.Therefore, nitrogen (NOx) discharge can be reduced equally, for example, by adopting lean burn operating gas turbine, by pilot fuel lower in gas turbine, shunt.In a word, hole arranged in mode heterogeneous, and by by the patterned arrangement in hole in arrange in corresponding hole, combustion chamber can be with lower nitrogen (NOx) discharge operation, because for example more air can be transported to combustion process, for lean burn is provided.In addition, flame temperature is minimized because of lean burn.
According to further exemplary embodiment, described wall elements is formed for extending at least in part along circumferencial direction around the central axis of combustion chamber.Generally speaking, combustion chamber forms cylindrical shape (or conical).For example, central axis forms for example axis of symmetry of combustion chamber.According to further exemplary embodiment, the first hole that arrange in described the first hole is one after the other formed in described wall elements along described circumferencial direction, is used to form at least one first row in the first hole.
According to further exemplary embodiment, the second hole that arrange in described the second hole is one after the other formed in described wall elements along described circumferencial direction, is used to form at least one second row in the second hole.On whole circumference, observe, the quantity in the first hole for example equals the quantity in the second hole, but for every round, different from the surface density between the second round at the first round.
According to further exemplary embodiment, the second hole that arrange in described the second hole is one after the other formed in described wall elements along described circumferencial direction, is used to form at least one second row in the second hole.Because the first surface density that the first hole in described the first hole arrangement comprises is different from second surface density in second hole of arranging in described the second hole, so the quantity in the first hole is for example different from the quantity in described the 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 that arrange in described the first hole is one after the other formed in described wall elements along first direction.Described first direction is different from described circumferencial direction, is used to form 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 is between approximately 10 ° and approximately 80 °, particularly between approximately 30 ° and approximately 60 °.Therefore, described the first hole is aligned in wall elements, make described other first row for example, along corresponding (tubulose) wall elements the mode layout with spiral.
According to further exemplary embodiment, the second hole that arrange in described the second hole 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, is used to form 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 is between approximately 10 ° and approximately 80 °, particularly between approximately 30 ° and approximately 60 °.By described other first row and described other second row, the corresponding first and/or second hole one after the other forms along corresponding the first and second directions, makes corresponding other first row and corresponding other second row can form spiral (the being spirality) trend around central axis along wall elements.
According to the further exemplary embodiment of the method, with respect to described inner wall element, the outer wall elements of arranging shell, makes described outer wall elements surround at least in part described inner wall element, and makes to form gap between described inner wall element and described outer wall elements.
According to the further exemplary embodiment of the method, the first hole is in addition arranged and is formed outer wall elements, wherein, described the first other hole is arranged and is comprised that the first other hole, other fluid (for example cooling fluid/gas) can flow through described the first other hole.The other first surface density that comprises described the first other hole is arranged in described the first other hole.In addition, the the second other hole arrangement that comprises the second other hole forms outer wall elements, and wherein, other fluid (for example cooling fluid/gas) can flow through described the second other hole, wherein, the second other surface density that comprises described the second hole is arranged in described the second other hole.Described other first surface density is different from described the second other surface density.
Total hole area of described inner and/or outer wall spreads all over described wall and distributes, thereby forms band or the region with different holes density.The standard distributing depends on flow parameter, and it can be for example temperature, flow velocity, flow direction and/or the turbulent flow of described fluid and/or other fluid.
Therefore,, by said method, the layout in described the first hole and the second hole is designed and is formed, and has considered the flow parameter of corresponding fluids simultaneously.Therefore, thus the effective pore size distribution in hole and described fluid and the described other fluid improved guiding along respective wall element is provided.Thus, the efficiency of combustion chamber is also arranged and is achieved because of suitable hole.
For example, in the beginning of the method, the hole that arrange in the hole in wall elements can distribute equably, and therefore comprises equal face density.Then, some holes can be removed from arrange in existing hole, make to form unequal distribution and the non-equal hole density between minute other hole arrangement.Then, in flow test, measure total hole area and how to reduce, as confirmation.Then, calculate how to process and arrange corresponding hole, to obtain nominal flow parameter and to have realized good damping characteristic.Then, corresponding pore size distribution, in arrange in corresponding hole, is made to form the inhomogeneous distribution in hole and/or inhomogeneous surface density, to match with total effective flow area of the nominal flow parameter calculating 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 elements can be bored a hole in mode non-homogeneous and customization.Therefore, because burning is dynamic, reduce, combustion chamber components and the life-span that is positioned at the turbine stage parts in downstream are achieved because of flame fluctuation and the Temperature Distribution reducing.In addition, NOx discharge is reduced, because because the burning reducing is dynamic, can apply lower pilot fuel shunting (pilot fuel/[pilot fuel+main fuel]).
It must be noted that, with reference to different themes, embodiments of the invention are illustrated.Especially, comparable device type claim is illustrated some embodiment, and reference method type claim is illustrated other embodiment.Yet, those skilled in the art will from above-mentioned and below description understand, except as otherwise noted, except belonging to any combination of feature of theme of a type, relate to the feature of particularly described type of device claim between the feature of different themes and any combination between the feature of described Method type claim and be considered to equally disclose with the application.
Accompanying drawing explanation
According to the example of the embodiment that below will describe, above-mentioned aspect of the present invention and other each side become apparent, and with reference to the example of embodiment, it are made an explanation.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 show 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 that comprises inner and outer shell; And
Fig. 6 shows for the manufacture of the schematic diagram of the method for housing according to an exemplary embodiment of the present invention.
The specific embodiment
Diagram in each figure is schematic.It is to be noted, in different figure, similar or identical element is with identical Reference numeral.
Fig. 1 shows the housing for the combustion chamber 100 of gas turbine.This housing comprises wall elements 101, and it comprises that I is arranged in the first hole and II is arranged in the second hole.The first hole is arranged I and is comprised the first hole 110, and fluid can flow through this first hole 110.The first surface density that I comprises the first hole 110 is arranged in the first hole.
The second hole is arranged II and is comprised the second hole 120, and fluid can flow through this second hole 120.The second surface density that II comprises the second hole 120 is arranged in the second hole.
Described first surface density is different from described the second surface density.That is to say, 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.The distribution of in other words, arranging 120, the first holes 110, the second hole in II with respect to the second hole has different patterns and/or different quantity and/or different sizes (for example bore dia).
For example, as obtained from Fig. 1, the first hole arrangement I, the second hole arrangement II and for example the 3rd hole are arranged III and are comprised identical size.In addition, the first hole is arranged I, the second hole and is arranged II and the 3rd hole and arrange III and can limit such face unit, and namely this face unit can limit corresponding first, second and/or the 3rd surface density in these holes.
In Fig. 1, the first hole is arranged the density in the first hole 110 in I and higher than the second hole, is arranged II and the 3rd hole arrangement III the second surface density and the 3rd surface density separately respectively.
More hole can be arranged in the upstream front end of wall elements 101, because flame is positioned at this.For example, as Fig. 1 exemplarily illustrates, I is arranged in the first hole can have three first rows 111, be positioned at more second hole in downstream and arrange II and can have two second rows 121, and the 3rd hole that is positioned at farther downstream is arranged III and can be had one the 3rd row 131.
Especially, as shown in Figure 1,100 the central axis 102 along combustion chamber, with respect to the flow direction of fluid, combustion chamber 100 is included in the upstream position combustion furnace part 104 (for example fore-end) of combustion chamber 100.Along central axis 102, with respect to the flow direction of fluid, 100 the downstream end in combustion chamber, burning gases are discharged combustion chamber 100, and for example further flow to the turbine stage of gas turbine.As obtained from Fig. 1, from combustion chamber, 100 upstream extremity to downstream reduces the surface density in corresponding hole 110,120,130.By the exemplary distribution of Fig. 1 mesopore 110,120,130, the first hole 110 that I is arranged in the first hole is one after the other formed in wall elements 101 along circumferencial direction 103, is used to form the first row 111 in described the first hole 110.Contiguous first row 111 and along downstream direction, the second hole 120 that II is arranged in the second hole is one after the other formed in wall elements 101 along circumferencial direction 103, is used to form for example two second rows 121 in the second hole 120.In addition, as shown in Figure 1, the 3rd hole 113 that III is arranged in the 3rd hole is one after the other formed in wall elements 101 along circumferencial direction 103, is used to form at least three the 3rd rows 131 in described the 3rd hole 130.
For example, if I, II are arranged in each hole, III comprises identical restriction area, the direction of the downstream of the quantity in hole 110,120,130 and row's 111,121,131 quantity along the upstream extremity from combustion chamber 100 to combustion chamber 100 reduces.In other words, for example, the distance between described two second rows 121 is less than the distance between described the 3rd row 131.For example, the distance between the first row 111 of the upstream extremity of combustion chamber 100 can be half of the distance of the 3rd row between 131 of the downstream part of combustion chamber 100.
In Fig. 1, I, II are arranged in hole as shown in Figure 1, III can be applied to inner wall element 501 (with reference to Fig. 5) (neck bush).Due to the pore size distribution heterogeneous along central axis 102 of 100 upstream extremities, 100 downstream to combustion chamber from combustion chamber, 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, than the hole being evenly arranged, arrange, can also realize particularly cooling in the suitable cascading water of wall elements 101 upstream portion.In addition,, by pore size distribution as shown in Figure 1, the dynamic suitable damping characteristic of burning in combustion chamber 100 is achieved.Desired minimizing based on combustion chamber effective area and by running through the desired mass flow of cooling fluid in minute other hole 110,120,130 of inwall respectively, draws axial row's 111,121,131 this layout.
Fig. 2 shows combustion chamber 100, and wherein, wall elements 101 comprises that I is arranged in the first hole and II is arranged in the second hole.The first hole 110 that I is arranged in described the first hole is one after the other formed in wall elements 101 along first direction 201.First direction 201 is different from circumferencial direction 103, is used to form at least one other first row 211 in the first hole 110.
Additionally or alternatively the second hole 120 that, II is arranged in described the second hole is one after the other formed in wall elements 101 along second direction 202.Second direction 202 is different from circumferencial direction 103, is used to form at least another one second row 221 in the second hole 120.
As obtained from Fig. 2, other first row 211 can comprise for example two the first holes 110.Other second row 221 comprises for example three the second holes 120.Therefore, the surface density in the second hole 120 in II is arranged higher than the surface density in the first hole 110 in the first hole arrangement I in the second hole.
In addition, as shown in Figure 2, by the hole 110,120 of arranging along the first and second directions respectively, formed spiral (spirality) trend along wall elements 101 around central axis 102.In other words, the respective aperture in Fig. 2 110,120 is arranged in the mode (with spirality pattern) tilting with respect to circumferencial direction 103.
Especially, comprise that the housing of sectional hole patterns as shown in Figure 2 can be for having the shell of outer wall elements 502 (with reference to Fig. 5).Especially, the identical direction of screw that the first direction of the other first row 211,221 of inclination and second direction can be in the burning gases with in combustion chamber 100.In addition, the spacing between the other row 211,221 of two adjacent inclinations along circumferencial direction 103 can or uniform or heterogeneous, depend on by the required flow parameter in each hole 110,120,130.
The combustion chamber 100 that comprises 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 efficient cooling performance, combustion chamber.
Fig. 3 shows the more abstract view of sectional hole patterns as shown in Figure 2.In Fig. 3, especially, show the sectional hole patterns of outer wall 502 (with reference to Fig. 5) of the shell of combustion chamber 100.In Fig. 3, exemplarily show the first hole and arrange I and the second hole arrangement II.The first hole 110 is one after the other arranged along other first row 211.Other first row 211 extends along first direction 201.The first angle [alpha] 1 is limited between first direction 201 and circumferencial direction 103.
The second hole 120 is one after the other arranged in the second hole along second direction 202 and arranges in II, and has formed other second row 221.The 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 with respect to circumferencial direction 103.Especially, as shown in Figure 3, along circumferencial direction 103, the distance between each other row 211,221 is being different each other.For example, as arranged as shown in I in the first hole, the first hole is arranged I and is comprised 3 pairs of other first rows 211, larger than between every two other first rows 211 in the distance existing between every pair of other first row 211 wherein, and it defines each to other first row 211.
By contrast, as arranged as shown in II in the second hole, the second hole is arranged II and is comprised two pairs of other second rows 221 and an other second row arrangement, and described other second row is arranged and comprised three other second rows 221.
Therefore, along shown in circumferencial direction, distance between each other row 211,221 is different, thereby the non-uniform Distribution in hole 110,120 is provided.
Fig. 4 shows the abstract view of the sectional hole patterns as being schematically shown in Fig. 1.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 one after the other arrange along axis direction 102, and wherein said first row 111 is parallel with second row 121 with respect to circumferencial direction 103.Distance between first row 111 in the first hole arrangement I is less than the second hole and arranges the distance between the second row 121 of II.
In order to observe better, Fig. 5 shows the cross section of the combustion chamber 100 of double wall tank type.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 arrange gapped mode 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 at least a portion of chilled fluid flow 504, and the gap of described chilled fluid flow 504 between these two wall elements 501,502 is by hole 110,120,130 flowing in combustion chambers 100 of inwall 501.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 be round central axis 102, and form thus the cylindrical portion of combustion chamber 100.
Fig. 6 shows calibration and arranges hole arrangement I, the II of desired inner wall element 501 and outer wall elements 502, the method for III.In step 601, limit initial combustion chamber design.Initial combustion chamber design in includable wall elements 501 and/or outside in wall elements 502 evenly or the sectional hole patterns of non-uniform Distribution.
Then, under nominal working conditions, combustion chamber operated, measured or analyzes, making inner wall element 501 and outer wall elements 502 be exposed to respectively chilled fluid flow 503 and other chilled fluid flow 504.With its minute, other moves minute other hole that flow parameter flows through inner wall element 501 and outer wall elements 502 to cooling fluid.
Then,, in step 602, determine that I, II, III are arranged in the hole of inner wall element 501.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, determine that I, II, III are arranged in the hole of outer wall elements 502.The effective area of outer wall elements (external bushing) 502 is determined by the sum in the hole 120,130,140 of outer wall elements 502.
Then,, in step 605, the hole based on inner wall element 501 is arranged the hole of I, II, III and outer wall elements 502 and is arranged I, II, III, determines the effective area of total combustion chamber 100.
In addition, determine the flow parameter (for example, the speed of other chilled fluid flow 504) (with reference to step 604) leave the fluid in the combustion space that inner wall element 501 enters combustion chamber 100.
Then, in step 606, the nominal value of for example speed and the effective area of combustion chamber 100 of the geometric parameter of the inside and outside wall element of definite value of the flow parameter of cooling fluid 503,504 and combination 501,502 (being combustion chamber 100) and cooling fluid 503,504 are compared.
If the nominal value of the geometric parameter of the flow parameter recording and/or combustion chamber 100 does not correspond to corresponding nominal value, in step 607, to the first surface density of the respective aperture in inner wall element 501 and/or outer wall elements 502, other first surface density, the second surface density and/or other the second surface density and divide thus other sectional hole patterns to revise individually, until reach the nominal value of flow parameter/geometric parameter.
If reach nominal value, the final design of the sectional hole patterns of inner wall element 501 and outer wall elements 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 wall pattern of customization and the optimization of inner wall element 501 and outer wall elements 502, thereby the fluid of designing optimization flows and effective combustion chamber 100.In traditional method, sectional hole patterns be calculated and given surface on distribute fifty-fifty.By this method, determine the sectional hole patterns in given surface, use as shown in Figure 6 and repetitive process balance as above requirement aspect damping and the requirement that distributes from the teeth outwards cooling-air aspect.In other words, sectional hole patterns aims at the condition of work of the gas turbine that 100Ji combustion chamber, combustion chamber 100 is 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 minute other Reference numeral.
It should be noted in the discussion above that term " comprises " does not get rid of other elements or step, and " one " or " one " does not get rid of a plurality of.In addition in conjunction with the described element of different embodiment, can be combined.Should also be noted that the Reference numeral in claim should not be interpreted as limiting the scope of claim.
Claims (11)
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 that (I) arranged in the first hole and (II) arranged in the second hole, and wherein, described inner wall element (501) is surrounded the combustion furnace volume of described combustion chamber (100),
Wherein, described the first hole is arranged (I) and is comprised the first hole (110), and fluid can flow through this first hole (110), and wherein, described the first hole (110) arranges with first surface density,
Wherein, described the second hole is arranged (II) and is comprised the second hole (120), and fluid can flow through this second hole (120), and wherein, described the second hole (120) arranges with the second surface density, and
Wherein, described first surface density is different from described the second surface density, and
Wherein, described shell comprises outer wall elements (502), described outer wall elements comprises that (I) arranged in the first other hole and (II) arranged in the second other hole, wherein, the outer wall elements (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 elements (502)
Wherein, described the first other hole is arranged (I) and is comprised other the first hole (110), and fluid can flow through described other the first hole (110), and wherein, described other the first hole (110) arranges with other first surface density,
Wherein, described the second other hole is arranged (II) and is comprised other the second hole (120), and fluid can flow through described other the second hole (120), and wherein, described other the second hole (120) arranges with the second other surface density, and
Wherein, described other first surface density is different from described the second other surface density.
2. combustion chamber according to claim 1 (100),
Wherein, described inner wall element (501) is extended along circumferencial direction (103) around the central axis (102) of described combustion chamber (100), and/or
Wherein, described outer wall elements (502) extends along circumferencial direction (103) around the central axis (102) of described combustion chamber (100).
3. combustion chamber according to claim 1 (100),
Wherein, described inner wall element (501) is extended along circumferencial direction (103) around the central axis (102) of gas turbine, and/or
Wherein, described outer wall elements (502) extends along circumferencial direction (103) around the central axis (102) of gas turbine.
4. according to the combustion chamber described in claim 2 or 3 (100),
Wherein, the first hole (110) that (I) arranged in described the first hole is one after the other formed in described inner wall element (501) along described circumferencial direction (103), be used to form at least one first row (111) in the first hole (110), and/or
Wherein, other the first hole (110) that (I) arranged in described the first other hole is one after the other formed in described outer wall elements (502) along described circumferencial direction (103), is used to form at least one other first row (111) in other the first hole (110).
5. according to the combustion chamber described in any one in claim 2 to 4 (100),
Wherein, the second hole (120) that (II) arranged in described the second hole is one after the other formed in described inner wall element (501) along described circumferencial direction (103), be used to form at least one second row (121) in the second hole (120), and/or
Wherein, other the second hole (120) that (II) arranged in described the second other hole is one after the other formed in described outer wall elements (502) along described circumferencial direction (103), is used to form at least one other second row (121) in other the second hole (120).
6. according to the combustion chamber described in any one in claim 2 to 5 (100),
Wherein, the first hole (110) that (I) arranged in described the first hole 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), is used to form at least one other first row (211) in the first hole (110),
Wherein, other the first hole (110) that (I) arranged in described the first other hole is one after the other formed in described outer wall elements (502) along other first direction (201),
Wherein, described other first direction (201) is different from described circumferencial direction (103), is used to form at least one other outer first row (211) in other the first hole (110).
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 °, particularly between 30 ° and 60 °, and/or
Wherein, the first other angle (α 1) between described other first direction (201) and described circumferencial direction (103) is between 10 ° and 80 °, particularly between 30 ° and 60 °.
8. according to the combustion chamber described in any one in claim 2 to 7 (100),
Wherein, the second hole (120) that (II) arranged in described the second hole 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), is used to form at least one other second row (221) in the second hole (120), and/or
Wherein, other the second hole (120) that (II) arranged in described the second other hole is one after the other formed in described outer wall elements (502) along other second direction (202),
Wherein, described other second direction (202) is different from described circumferencial direction (103), is used to form at least one other outer second row (221) in other the second hole (120).
9. combustion chamber according to claim 8 (100),
Wherein, the second angle (α 2) between described second direction (202) and described circumferencial direction (103) between 10 ° and 80 °, particularly between 30 ° and 60 °, and/or
Wherein, the second other angle (α 2) between described other second direction (202) and described circumferencial direction (103) is between 10 ° and 80 °, particularly between 30 ° and 60 °.
10. for the manufacture of a method for the combustion chamber (100) of gas turbine, described method comprises:
Form the first hole and arrange (I), it is included in the first hole (110) in the inner wall element (501) of inner casing of combustion chamber (100), wherein, fluid can flow through this first hole (110), wherein, described the first hole (110) arranges with first surface density, and
Form the second hole and arrange (II), it is included in the second hole (120) in described inner wall element (501), and wherein, fluid can flow through this second hole (120), and wherein, described the second hole (120) arranges with the second surface density,
Wherein, described first surface density is different from described the second surface density, and
Wherein, described inner wall element (501) is surrounded the combustion furnace volume of described combustion chamber (100),
With respect to described inner wall element (501), arrange the outer wall elements (502) of the shell of combustion chamber (100), make described outer wall elements (502) surround at least in part described inner wall element (501), and make to form gap between described inner wall element (501) and described outer wall elements (502)
(I) arranged in the first other hole to be formed in described outer wall elements (502), described the first other hole is arranged and is comprised other the first hole (110), other fluid can flow through described other the first hole (110), wherein, described other the first hole (110) arranges with other first surface density, and
(II) arranged in the second other hole to be formed in described outer wall elements (502), described the second other hole is arranged and is comprised other the second hole (120), other fluid can flow through described other the second hole (120), wherein, described other the second hole (120) is arranged with the second other surface density
Wherein, described other first surface density is different from described the second other surface density.
11. methods according to claim 10, described method also comprises:
Make fluid stream (503) flow through described the first hole and arrange (I) and described the second hole arrangement (II),
Make other fluid stream (504) flow through described the first other hole and arrange (I) and described the second other hole arrangement (II),
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 the second surface density and/or described the second other surface density, until the measured value of the described fluid stream flow parameter of (503) and/or the geometric parameter of combustion chamber (100) meets the respective nominal values of the geometric parameter of this flow parameter and/or combustion chamber (100).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104204679A true CN104204679A (en) | 2014-12-10 |
| CN104204679B CN104204679B (en) | 2016-04-20 |
Family
ID=47324137
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280071988.XA Expired - Fee Related CN104204679B (en) | 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 |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20150101335A1 (en) |
| EP (2) | EP2644995A1 (en) |
| JP (1) | JP6005836B2 (en) |
| CN (1) | CN104204679B (en) |
| RU (1) | RU2582378C1 (en) |
| WO (1) | WO2013143627A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102016207057A1 (en) * | 2016-04-26 | 2017-10-26 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustor |
| RU173450U1 (en) * | 2016-11-15 | 2017-08-28 | федеральное государственное бюджетное образовательное учреждение высшего образования "Ульяновский государственный технический университет" | HEAT PIPE OF THE COMBUSTION CHAMBER OF A GAS-TURBINE ENGINE WITH DAMPING CAVES |
| US20180266687A1 (en) * | 2017-03-16 | 2018-09-20 | General Electric Company | Reducing film scrubbing in a combustor |
| DE102019105442A1 (en) | 2019-03-04 | 2020-09-10 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing an engine component with a cooling duct arrangement and engine component |
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- 2012-12-05 EP EP12798272.6A patent/EP2831506B1/en not_active Not-in-force
- 2012-12-05 CN CN201280071988.XA patent/CN104204679B/en not_active Expired - Fee Related
- 2012-12-05 JP JP2015502114A patent/JP6005836B2/en not_active Expired - Fee Related
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Also Published As
| Publication number | Publication date |
|---|---|
| JP6005836B2 (en) | 2016-10-12 |
| WO2013143627A1 (en) | 2013-10-03 |
| EP2644995A1 (en) | 2013-10-02 |
| JP2015511696A (en) | 2015-04-20 |
| EP2831506B1 (en) | 2016-04-06 |
| EP2831506A1 (en) | 2015-02-04 |
| CN104204679B (en) | 2016-04-20 |
| RU2582378C1 (en) | 2016-04-27 |
| US20150101335A1 (en) | 2015-04-16 |
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