CN112178695A - Damper, burner assembly comprising a damper and method of manufacturing a damper - Google Patents
Damper, burner assembly comprising a damper and method of manufacturing a damper Download PDFInfo
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- CN112178695A CN112178695A CN202010619065.XA CN202010619065A CN112178695A CN 112178695 A CN112178695 A CN 112178695A CN 202010619065 A CN202010619065 A CN 202010619065A CN 112178695 A CN112178695 A CN 112178695A
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- 238000004519 manufacturing process Methods 0.000 title claims description 6
- 238000013016 damping Methods 0.000 claims abstract description 69
- 238000002485 combustion reaction Methods 0.000 claims abstract description 20
- 238000004891 communication Methods 0.000 claims abstract description 10
- 239000012530 fluid Substances 0.000 claims abstract description 10
- 230000004323 axial length Effects 0.000 claims description 28
- 238000000034 method Methods 0.000 claims description 7
- 238000004513 sizing Methods 0.000 claims 5
- 239000007789 gas Substances 0.000 description 17
- 239000000446 fuel Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000009795 derivation Methods 0.000 description 2
- 230000037406 food intake Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229910000856 hastalloy Inorganic materials 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
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Classifications
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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
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
- F23M20/005—Noise absorbing means
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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
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
A damper for a combustor assembly (3) of a gas turbine assembly (1) is provided with: at least two damping volumes (32, 35) defined by respective damping bodies (31, 34); the damping volumes (32, 35) being interconnected in fluid communication; at least one perforated connecting plate (36) connecting the two damping volumes (32, 35); at least one perforated end plate (38) configured to connect at least one of the two damping volumes (32, 35) with a combustion chamber (16; 14) of the burner assembly (3); the perforated connecting plate (36) and the perforated end plate (38) are provided with a plurality of openings (42); the size of the opening (42) is set so as to be in a low Strouhal shape according to the following formulaOperating in a state: (ɷ. R)H/Ub)<0.5, wherein: ɷ is the angular frequency related to the frequency to be damped according to the following relation ɷ =2 pi f; rHIs the equivalent radius of one of the openings (42); u isbIs the flow rate through one of the openings (42).
Description
Cross Reference to Related Applications
This patent application claims priority to european patent application No. 19183732.7 filed on 7/1/2019, the entire disclosure of which is incorporated herein by reference.
Technical Field
The present invention relates to a damper for a combustor assembly of a gas turbine assembly, and to a combustor assembly of a gas turbine comprising said damper. More particularly, the present invention relates to a damper for a sequential combustor assembly.
The invention also relates to a method of manufacturing a damper for a burner assembly.
Background
As is well known, a gas turbine power plant includes a compressor, a combustor assembly, and a turbine.
Specifically, the compressor is supplied with air, and includes a plurality of blades that compress the supplied air. The compressed air exiting the compressor flows into a plenum, i.e., an enclosed volume defined by an outer shell, and from there into the combustor assembly. In the combustor assembly, compressed air and at least one fuel are combusted.
The resulting hot gases exit the combustor assembly and expand in the turbine to produce work.
To achieve high efficiency, high temperatures are required during combustion. However, due to these high temperatures, high NOx emissions are generated.
To reduce these emissions and increase operational flexibility, sequential combustor assemblies may be used.
Typically, a sequential burner assembly includes two burners in series: a first stage combustor and a second stage combustor, the second stage combustor being arranged downstream of the first stage combustor along the gas flow.
Of course, a combustor assembly having a single combustion stage may also be used.
During operation, pressure oscillations may occur inside the combustor assembly, causing mechanical damage and limiting operating conditions. In fact, most combustor assemblies must be operated in a lean mode to meet the polluting emissions. During this mode of operation, the burner flame is extremely sensitive to flow disturbances and can easily couple with the dynamics of the combustor leading to thermo-acoustic instabilities. For this reason, the burner assembly is usually provided with damping means in order to damp these pressure oscillations.
The known damper comprises one damper volume, which serves as a resonator volume, and a neck, which fluidly connects the damper volume to at least one inner chamber of the burner assembly.
However, these dampers do not have sufficient flexibility and cannot damp a wide frequency range.
Disclosure of Invention
It is therefore an object of the present invention to provide a damper for a burner assembly that is flexible, simple and economical from both a functional and a constructional point of view.
According to the present invention, there is provided a damper for a combustor assembly of a gas turbine assembly, the damper comprising:
at least two damping volumes defined by respective damping bodies; the damping volumes are interconnected in fluid communication;
at least one perforated connecting plate connecting the two damping volumes;
at least one perforated end plate configured to connect at least one of the two damping volumes with a combustion chamber of the combustor assembly;
the perforated connecting plate and the perforated end plate are provided with a plurality of openings; the size of the opening is set to operate in a low Strouhal (Strouhal) regime according to the following equation:
(ɷ·RH / Ub) < 0.5
wherein:
ɷ is the angular frequency related to the frequency to be damped according to the following relation ɷ =2 pi f;
RHis the equivalent radius of one of the openings (42);
Ubis the flow rate through one of the openings (42).
The construction of the damper according to the invention is flexible and can also be compact.
Flexibility can be given by the possibility of damping different frequencies, since the size of the damping volume can be suitably adjusted depending on the need.
In other words, due to the damper according to the invention, a wide-band damping of the combustion dynamics is obtained.
According to a variant of the invention, at least one of the damping bodies comprises at least one inlet configured to be in fluid communication with at least one air source. In this manner, the air helps cool the damper body and avoids hot gas ingestion, which can detune the damper body and potentially cause damage to the damper body.
According to a variant of the invention, at least two damping volumes are interconnected in parallel.
According to a variant of the invention, at least two damping volumes are interconnected in series.
According to a variant of the invention, at least one of the damping volumes is a quarter-wave tube.
For example, at least one of the damping volumes is dimensioned according to the following formula:
f = c/4(L +)
wherein
f is the frequency to be damped
L is the axial length of the corresponding cavity defined by the damper body
c is the speed of sound
Is a tip correction that allows to take into account the inertia of the acoustic flow at the end of the volume just outside the opening.
According to a variant of the invention, at least one of the damping volumes is a helmholtz resonator.
For example, at least one of the damping volumes is dimensioned according to the following formula:
f=(c/2π)·(A/(V·(l+2*')))1/2
wherein
f is the frequency to be damped
c is the speed of sound
A is the equivalent surface area of all openings
V is the damping volume
l is the thickness of the perforated plate coupled to the damping volume
' is an end correction which allows to take into account the acoustic flow inertia outside and inside the opening.
According to a variant of the invention, the damper comprises: a first damping body extending along an extension axis and having a first axial length; and a second damping body extending along an extension axis and having a second axial length; the ratio between the larger axial length between the first axial length and the second axial length and the smaller axial length between the first axial length and the second axial length is substantially an integer, preferably an even number.
It is another object of the present invention to provide a reliable combustor assembly for a gas turbine plant in which acoustic oscillations are significantly reduced.
In accordance with this purpose, the present invention relates to a burner assembly according to claim 9.
It is yet another object of the present invention to provide a simple and economical method for manufacturing a damper for a combustor assembly of a gas turbine. In accordance with this object, the present invention relates to a method for manufacturing a damper according to claim 11.
Drawings
The invention will now be described with reference to the accompanying drawings, which illustrate some non-limiting embodiments, in which:
figure 1 is a schematic view of a gas turbine assembly;
FIG. 2 is a schematic side view, partly in section and partly removed, of a detail of a burner assembly of the gas turbine assembly of FIG. 1;
fig. 3 is a schematic front view, partly in section and partly removed, of a detail of a burner assembly according to the present invention;
FIG. 4 is a schematic side view, partly in section and partly removed, of a damper for a burner assembly according to the invention;
figure 5 represents a graph relating to the absorption characteristics of a damper according to the invention used in a burner assembly.
Detailed Description
In fig. 1, reference numeral 1 denotes a gas turbine assembly. The gas turbine assembly 1 comprises a compressor 2, a sequential combustor assembly 3 and a turbine 5. The compressor 2 and the turbine 5 extend along a main axis a.
In use, a gas stream compressed in compressor 2 is mixed with fuel and combusted in sequential combustor assembly 3. The combusted mixture is then expanded in a turbine 5 and converted to mechanical power by a shaft 6, the shaft 6 being connected to an alternator (not shown).
Preferably, a mixer 11 is arranged between the first stage combustor 8 and the second stage combustor 9.
The first stage combustor 8 defines a first combustion chamber 14, the second stage combustor 9 defines a second combustion chamber 16, and the mixer 11 defines a mixing chamber 17.
The first, second and mixing chambers 14, 16, 17 are in fluid communication and are defined by a liner 18 (see fig. 2, where the liner 18 is partially visible) extending along the longitudinal axis B.
Referring to fig. 2, a supply assembly 20 is disposed in the second combustion chamber 16 of the second stage combustor 9.
The feed assembly 20 comprises a central body 21 provided with a plurality of fingers 22 (also schematically shown in fig. 3).
The fingers 22 are preferably defined by streamlined bodies, each of which is provided with a plurality of nozzles 24 and is supplied with air and at least one fuel.
Referring to fig. 2 and 3, the second stage combustor 9 includes at least one damper 30.
In the non-limiting example disclosed and illustrated herein, the second stage combustor 9 includes a plurality of dampers 30 (sixteen dampers in the example illustrated herein). The use of more than one damper 30 gives the possibility to increase the damping amplitude.
Preferably, the damper 30 is arranged around the central body 21 of the supply assembly 20. More preferably, the dampers 30 are evenly distributed around the central body 21.
Referring to fig. 2 and 3, the damper 30 is preferably coupled to the panel 26 surrounding the central body 21 of the supply assembly 20. Preferably, the panel 26 is also provided with a plurality of cooling holes 25 evenly distributed along the panel 26.
It should be understood that damper 30 may also be disposed in another portion of combustor assembly 3.
For example, the damper 30 may be coupled to the liner 18, preferably to a portion of the liner 18 facing the second combustion chamber 16. The damper 30 may also be arranged so as to face the first combustion chamber 14.
Referring to fig. 4, the damper 30 extends along an extension axis C and includes a first damper body 31 having a first cavity defining a first damping volume 32, a second damper body 34 having a second cavity defining a second damping volume 35, a perforated connecting plate 36 connecting the first and second damping volumes 32, 35, and at least one perforated end plate 38. The perforated end plate 38 is configured to connect the first damping volume 32 with the exterior of the damper 30, which is in fluid communication with the first combustion chamber 14 and/or the second combustion chamber 16 of the combustor assembly 3.
The first and second damping volumes 32, 35 are interconnected in fluid communication by a perforated connecting plate 36.
In the non-limiting example disclosed and illustrated herein, the first and second damping volumes 32, 35 are interconnected in series.
According to a variant not shown, the first 32 and the second damping volume 35 are interconnected in parallel.
In the non-limiting example disclosed and illustrated herein, the second damper body 34 is provided with at least one inlet 40 configured to be in fluid communication with at least one air source. Specifically, the inlet 40 is connected to a plenum (not visible in the drawings) that receives air from the compressor 2. In the non-limiting example disclosed and illustrated herein, the second damper body 34 is provided with two or more inlets 40 arranged at the bottom of the second chamber.
In use, air enters through the inlet 40, flows into the second damping volume 35, through the perforated connecting plate 36, into the first damping volume 32, and out through the perforated end plate 38 into the first combustion chamber 14 and/or the second combustion chamber 16 of the burner assembly 3.
The air helps cool the first and second damper bodies 31 and 34 and avoids hot gas ingestion, which may detune the first and second damper bodies 31 and 34 and may cause damage to the first and second damper bodies 31 and 34. Preferably, the inlets 40 are disposed on opposite sides of the second damper body 34.
The perforated connecting plate 36 and the perforated end plate 38 have a similar structure. The perforated connecting plate 36 and the perforated end plate 38 are each provided with a plurality of openings 42.
In the example disclosed and illustrated herein, the opening 42 has a circular shape. However, according to a variant not shown, the shape of the opening can be different, for example polygonal or oval or rectangular, etc.
Both the perforated connecting plate 36 and the perforated end plate 38 are designed to operate in a low sduruhal regime. The sduhal state is defined by the value of the sduhal number.
Here and hereinafter, "low sduhal state" means a sduhal number below 0.5.
To operate in the low sduhal regime, the openings 42 of the perforated connection plate 36 and the perforated end plate 38 are sized according to the following conditions:
(ɷ·RH / Ub) < 0.5
wherein
ɷ is the angular frequency related to the frequency to be damped according to the following relation ɷ =2 pi f;
RHis the equivalent radius of one of the openings, calculated as RH= a/P, where a is the cross-sectional area of the flow and P is the wetted perimeter of the cross-section (in the example disclosed and illustrated herein, the hydraulic radius is the radius of the circular opening 42);
ub is the bias flow velocity of the flow through one of the openings.
In use, the perforated end plate 38 directly faces the first combustion chamber 14 and/or the second combustion chamber 16, and is therefore designed to withstand high temperatures. The thickness and material of the perforated end plate 38 are therefore selected to ensure high reliability.
The perforated web 36 is also subjected to high temperatures, albeit in a lesser manner than the perforated end plate 38.
In the non-limiting example disclosed and illustrated herein, the perforated connecting plate 36 and the perforated end plate 38 are made of the same material. For example, the perforated connection plate 36 and the perforated end plate 38 are made of a high temperature resistant material, for example, a superalloy such as hastelloy X.
In the non-limiting example disclosed and illustrated herein, the perforated connecting plate 36 and the perforated end plate 38 have different thicknesses. The perforated end plate 38 is preferably thicker than the perforated connecting plate 36 as it faces the combustion chamber.
Referring to fig. 3, the openings 42 are arranged substantially according to a cross-grid pattern. Alternatively, the openings 42 may be arranged substantially according to a square grid pattern or according to a rectangular grid pattern or other pattern.
In the non-limiting example disclosed and illustrated herein, the grid pattern of the perforated connecting plate 36 is the same as the grid pattern of the perforated end plate 38. In this manner, the openings 42 of the perforated connecting plate 36 are aligned with the openings 42 of the perforated end plate 38.
However, the grid patterns of the perforated connection plate 36 and the perforated end plate 38 may be different from each other, and the openings 42 of the perforated connection plate 36 may be misaligned with the openings 42 of the perforated end plate 38. This solution is useful when the distance between the perforated connecting plate 36 and the perforated end plate 38 is less than a threshold value. In other words, when the length L1 of the first cavity is less than the threshold value, the openings 42 of the perforated connecting plate 36 are misaligned with the openings 42 of the perforated end plate 38.
Referring to fig. 4, the openings 42 of the perforated connecting plate 36 and the perforated end plate 38 are arranged so as to be perpendicular to the plane a along which the respective perforated connecting plate 36 or perforated end plate 38 extends1、a2。
The first chamber of the first damper body 31 and the second chamber of the second damper body 34 are sized so that the damper 30 has a desired damping effect.
In the non-limiting example disclosed and illustrated herein, the first cavity of the first damper body 31 and the second cavity of the second damper body 34 are cylindrical. According to a variant not shown, the first cavity of the first damper body 31 and the second cavity of the second damper body 34 may also be prismatic or may have a shape adjusted on the basis of the space available in the burner assembly 3.
The first cavity of the first damper body 31 and the second cavity of the second damper body 34 are designed as quarter-wave tubes.
The first cavity of the first damper body 31 and the second cavity of the second damper body 34 are sized, for example, according to the following formula (quarter wave tube formula):
f = c/4(L +)
wherein
f is the frequency to be damped
L is the axial length of the respective chamber defined by the damper body (first chamber L1, second chamber L2)
c is the speed of sound
Is a tip correction that allows to take into account the inertia of the acoustic flow at the end of the volume just outside the opening.
According to a variant not shown, the dimensions can be set according to the derivation of the quarter-wave tube formula described above.
Alternatively, the first cavity of the first damper body 31 and the second cavity of the second damper body 34 are designed so as to be helmholtz resonators.
The first chamber of the first damper body 31 and the second chamber of the second damper body 34 are sized according to the following formula (helmholtz formula), for example:
f=(c/2π)·(A/(V·(l+2*')))1/2
wherein
f is the frequency to be damped
c is the speed of sound
A is the equivalent surface area of all openings of the respective perforated plates (i.e., perforated connecting plate 36 sized for the second chamber and perforated end plate 38 sized for the first chamber)
V is the volume of the cavity
l is the thickness of the respective perforated plate coupled to the damping volume (i.e., the thickness l of the perforated connecting plate 36 sized for the second cavity)cAnd the thickness l of the perforated end plate 38 sized for the first cavitye）
' is an end correction which allows to take into account the acoustic flow inertia outside and inside the opening.
According to a variant not shown, the dimensioning can be set according to the derivation of the helmholtz formula described above.
The dimensioning is preferably done with the quarter wave formula, since it is independent of the characteristics of the respective perforated plate.
However, if the thickness of the respective perforated plate is greater than a threshold value and/or if the length of the cavity obtained according to the quarter wave equation is not acceptable due to geometric constraints in combustor assembly 3, then the helmholtz equation is used to set the dimensions.
Preferably, the first cavity of the first damper body 31 is sized to dampen a first frequency and the second cavity of the second damper body 34 is sized to dampen a second frequency different from the first frequency.
The damper 30 thus sized and designed is capable of damping a wide frequency band. In fact, the damper 30 is capable of damping at least three frequencies: one frequency depends on the size of the first cavity, one frequency depends on the size of the second cavity, and one frequency depends on the size of the first cavity plus the second cavity.
Specifically, the relationship between the axial length L1 of the first chamber of the first damper body 31 and the axial length L2 of the second chamber of the second damper body 34 affects the response of the damper 30.
In practice, the reflection coefficient is driven primarily by the eigenmodes of the two cavities together (i.e., L2 + L1), while the response is modulated by the dimensions L1 and L2 of each cavity.
Accordingly, the lengths L1 and L2 of the first and second chambers are sized as desired. The length can be substantially dimensioned according to three possibilities: l2 ═ L1, L2> L1 and L2 < L1.
Equal lengths L1 and L2 (L2 = L1) may be selected if uniform damping over the frequency band is required.
When L2 is different from L1, pattern consistency can be achieved if the ratio between lengths (L2/L1 if L2> L1, or L1/L2 if L2 < L1) is substantially an integer.
The uniformity of the modes results in higher damping at the uniform frequency.
Since the damper 30 is broadband, the response of the damper 30 does not change excessively even if the ratio is not an exact integer. For example, if L2/L1 is 3.1 instead of 3, the response of damper 30 is similar. Therefore, the ratio is defined as "substantially integer".
Specifically, if the ratio L2/L1 is an even integer (i.e., L2> L1), the uniformity of the mode is between the eigenmodes of the two cavities together (i.e., L2 + L1) and the eigenmode of the first cavity (L1), as shown by the solid line in fig. 5. This solution results in a high damping of the center of the modulation.
If the ratio L1/L2 is an even integer (i.e., L2 < L1), the mode identity is between the eigenmodes of the two cavities together (i.e., L2 + L1) and the eigenmode of the second cavity (L2). Such a solution would result in a damping as shown by the dashed line in fig. 5, which would be higher at the edges of the bounce sequence.
In fig. 5, a graph of the reflection coefficient modulus and the phase of the damper 30 having the above-described structure used in the combustor assembly 3 is shown.
The trend of fig. 5 with respect to the reflection coefficient modulus and phase indicates that the damper 30 is capable of damping a wide frequency band. The trend shown in fig. 5 is related to the values of inverted lengths L1 and L2. In other words, the dashed line represents the solution where L2> L1, and the solid line represents the solution with the length inverted (i.e., L2 < L1).
If the ratio L2/L1 or the ratio L1/L2 is an odd integer, the mode uniformity is between the eigenmode L1 of the first cavity and the eigenmode L2 of the second cavity.
As mode uniformity increases, the damping and reflection coefficients are driven primarily by the 2 cavity-together eigenmodes (i.e., L2 + L1), and the damping is maximized when the eigenmodes of the first or second cavity have the same frequency as the two cavity-together eigenmodes (i.e., L2 + L1).
Finally, it is clear that modifications and variants can be made to the damper and burner assembly described herein, without departing from the scope of the present invention, as defined in the appended claims.
Claims (14)
1. Damper for a combustor assembly (3) of a gas turbine assembly (1), comprising:
-at least two damping volumes (32, 35) defined by respective damping bodies (31, 34); the damping volumes (32, 35) being interconnected in fluid communication;
-at least one perforated connecting plate (36) connecting the two damping volumes (32, 35); at least one perforated end plate (38) configured to connect at least one of the two damping volumes (32, 35) with a combustion chamber (16; 14) of the burner assembly (3);
the perforated connecting plate (36) and the perforated end plate (38) are provided with a plurality of openings (42); the opening (42) is sized to operate in a low Strouhal regime according to the following equation:
(ɷ·RH / Ub) < 0.5
wherein:
ɷ is the angular frequency related to the frequency to be damped according to the following relation ɷ =2 pi f;
•RHis an equivalent radius of one of the openings (42);
•Ubis the flow rate through one of the openings (42).
2. The damper according to claim 1, wherein at least one of the damping bodies (31, 34) comprises at least one inlet (40), the at least one inlet (40) being configured to be in fluid communication with at least one air source.
3. The damper according to any of the preceding claims, wherein the at least two damping volumes (32, 35) are interconnected in parallel.
4. A damper according to any of the preceding claims, wherein the at least two damping volumes (32, 35) are interconnected in series.
5. Damper according to any of the preceding claims, wherein at least one of the damping volumes (32, 35) is a quarter wave tube.
6. A damper according to any one of the preceding claims, wherein at least one of the damping volumes (32, 35) is a helmholtz resonator.
7. A damper as claimed in any preceding claim comprising: a first damping body (31; 34) extending along an extension axis (C) and having a first axial length (L1; L2); and a second damping body (34; 31) extending along an extension axis (C) and having a second axial length (L2; L1); the ratio (L1/L2; L2/L1) between a larger axial length (L1, L2; L2, L1) between the first axial length (L1; L2) and the second axial length (L2; L1) and a smaller axial length between the first axial length (L1; L2) and the second axial length (L2; L1) is substantially an integer, preferably an even number.
8. Burner assembly for a gas turbine assembly (1), comprising at least one combustion chamber (14; 16) and at least one damper (30) according to any one of the preceding claims.
9. Gas turbine assembly comprising a compressor (2), a gas turbine (5) and a combustor assembly (3) according to claim 8.
10. Method for manufacturing a damper (30) for a combustor assembly (3) of a gas turbine assembly (1), comprising the steps of:
-providing at least two damping volumes (32, 35) defined by respective damping bodies (31, 34) extending along respective extension axes (C); the damping volumes (32, 35) being interconnected in fluid communication;
-providing at least one perforated connecting plate (36) having a plurality of openings (42) and connecting the two damping volumes (32, 35);
-providing at least one perforated end plate (38) having a plurality of openings (42) and configured to connect at least one of the two damping volumes (32, 35) with a combustion chamber (16; 14) of the burner assembly (3);
wherein the step of providing at least one perforated connecting plate (36) comprises sizing the opening (42) to operate in a low Strouhal regime according to the formula:
（ɷ·RH / Ub）< 0.5
wherein:
ɷ is the angular frequency related to the frequency to be damped according to the following relation ɷ =2 pi f;
RHis an equivalent radius of one of the openings (42);
Ubis the flow rate through one of the openings (42).
11. The method of claim 10, wherein the step of providing at least two damping volumes (32, 35) comprises: sizing a first cavity of a first damper body (31) to damp a first frequency; and sizing a second cavity of a second damper body (34) to damp a second frequency different from the first frequency.
12. The method according to claim 10 or claim 11, wherein the step of providing at least two damping volumes (32, 35) comprises sizing at least one of the two damping volumes (32, 35) to be a quarter wave tube.
13. The method according to any one of claims 10 to 12, wherein the step of providing at least two damping volumes (32, 35) comprises sizing at least one of the two damping volumes (32, 35) as a helmholtz resonator.
14. Method according to any one of claims 10-13, wherein the step of providing at least two damping volumes (32, 35) comprises dimensioning a first chamber of a first damper body (31; 34) having a first axial length (L1; L2) and a second chamber of a second damper body (34; 31) having a second axial length (L2; L1) such that the ratio (L1/L2; L2/L1) between a larger axial length (L1, L2; L2, L1) between the first axial length (L1; L2) and the second axial length (L2; L1) and a smaller axial length (L1/L2; L2/L1) between the first axial length (L1; L2) and the second axial length (L2; L1) is substantially an integer, preferably an even number.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP19183732.7A EP3760925A1 (en) | 2019-07-01 | 2019-07-01 | Damper for a combustor assembly of a gas turbine assembly, combustor assembly comprising said damper and method for manufacturing a damper for a combustor assembly |
| EP19183732.7 | 2019-07-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112178695A true CN112178695A (en) | 2021-01-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010619065.XA Pending CN112178695A (en) | 2019-07-01 | 2020-07-01 | Damper, burner assembly comprising a damper and method of manufacturing a damper |
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| EP (1) | EP3760925A1 (en) |
| CN (1) | CN112178695A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115682033A (en) * | 2021-07-28 | 2023-02-03 | 北京航空航天大学 | Vibration-proof combustion chamber and vibration-proof method for combustion chamber |
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| Publication number | Publication date |
|---|---|
| EP3760925A1 (en) | 2021-01-06 |
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