EP2851618A1 - Verbrennungssystem einer Strömungsmaschine - Google Patents

Verbrennungssystem einer Strömungsmaschine Download PDF

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Publication number
EP2851618A1
EP2851618A1 EP13165158.0A EP13165158A EP2851618A1 EP 2851618 A1 EP2851618 A1 EP 2851618A1 EP 13165158 A EP13165158 A EP 13165158A EP 2851618 A1 EP2851618 A1 EP 2851618A1
Authority
EP
European Patent Office
Prior art keywords
resonator
combustion system
manifold
combustion
orifices
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP13165158.0A
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English (en)
French (fr)
Inventor
Charith Jayatunga
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP13165158.0A priority Critical patent/EP2851618A1/de
Priority to PCT/EP2014/056803 priority patent/WO2014173660A1/en
Priority to GB1516231.6A priority patent/GB2527688A/en
Priority to KR1020157033163A priority patent/KR20160003733A/ko
Priority to US14/784,794 priority patent/US20160076766A1/en
Publication of EP2851618A1 publication Critical patent/EP2851618A1/de
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/06—Liquid fuel from a central source to a plurality of burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/002—Gaseous fuel
    • F23K5/005—Gaseous fuel from a central source to a plurality of burners
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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

Definitions

  • the present invention relates to a combustion system of a flow engine comprising at least a resonator having a resonator cavity and a method for determining a dimension of this resonator cavity of the aforementioned resonator.
  • Combustors of a flow engine like a gas turbine, comprise a combustion chamber provided with a combustion air inlet and with a fuel passage connected to a fuel injector arranged to discharge fuel into the combustion chamber. Combustion air as well as fuel enters the combustion chamber under pressure.
  • the resultant combustion is basically very fast and generates dynamic forces in the form of pressure fluctuations, which may manifest on a casing of the combustor as vibrations.
  • combustion dynamics also occur due to a coupling between pressure oscillations and unsteady heat release.
  • One of the major causes of unsteady heat release is due to fuel flow rate perturbations.
  • WO 93/10401 it is for example known to provide a fuel supply line of a gas turbine system with a so-called Helmholtz resonator to suppress combustion-cause vibrations.
  • Helmholtz type resonators provided damping at a very specific frequency. Problems arise with this resonator types in case of the necessity to attenuate a broad range of frequencies.
  • a combustion system of a flow engine comprising at least one combustion chamber, a shared manifold to feed a flow medium via at least two injectors to the at least one combustion chamber and at least one resonator with at least one resonator cavity, wherein the at least one resonator is arranged functionally in/at the manifold.
  • the resonator comprises at least one perforated section with at least two orifices, wherein the at least two orifices provide access to the at least one resonator cavity of the at least one resonator.
  • the life of downstream components such as turbine blades or vanes may be improved compared to state of the art systems through a reduction in heat release fluctuations.
  • the combustion system may be operated over a wide range of Wobbe indices, resulting in flexibility concerning the used fuel.
  • combustion dynamics may be effectively reduced compared to a state of the art system.
  • this invention is also concerned with the interaction between the dynamic forces caused by combustion and those caused by the flow of fuel, air and other gases.
  • a flow engine is intended to mean any engine or machine suitable for a person skilled in the art, e.g. a thermal heating plant, a gas turbine or an internal combustion engine.
  • an injector is intended to mean a nozzle for e.g. fuel, air and/or other gases and especially a fuel nozzle.
  • the term "shared manifold” should be understood as “shared by the at least two injectors” or in case of an embodiment with at least two combustion chambers alternatively and/or additionally as “shared by the at least two combustion chamber” and the term “manifold” as a passage for a flow medium and especially as fuel manifold and/or fuel gallery.
  • a flow medium may be any medium feasible for a person skilled in the art, like a fuel (gaseous), air or other gases.
  • a resonator is intended to mean a device for modulating and/or damping perturbations, especially of a flow rate of the flow medium e.g. in the manifold and/or that is used to provide damping to an established standing or rotating wave e.g. in the manifold.
  • a resonator should be understood as a functional unity, thus it may comprise more than one piece or may be a selected arrangement of several pieces.
  • the resonator is especially a so called cavity resonator.
  • the statement the "resonator is arranged functionally in/at the manifold" should be understood as a functional interaction of the parts and may be independent of a spatial arrangement of the resonator and the manifold.
  • a perforated section is intended to mean a part of the resonator embodied with a perforation, wherein the perforation has at least two orifices. Alternatively, the perforation may have more than two orifices or a plurality of orifices.
  • the wording to "provide access to the at least one resonator cavity of the at least one resonator" should be understood as an access for a wave propagation of a wave that may be established in or travel in the manifold and/or flow medium during operation of the combustion system.
  • a direction of the wave propagation is preferably from the manifold, precisely from its lumen, to the resonator cavity of the resonator.
  • the phrases "at least one resonator/at least one resonator cavity/at least one perforated section/at least one combustion chamber/the at least two injectors/at least two orifices" are referred to as "the resonator/the resonator cavity/the perforated section/the combustion chamber/the two injectors/the two orifices”.
  • An orifice may have any size or shape, like circular, oval, triangular, rectangular square, etc., feasible for a person skilled in the art.
  • said orifice is embodied with a circular shape.
  • the perforation can be easily manufactured.
  • both orifices or all orifices in case of a plurality of orifices, have a circular shape.
  • the resonator has a shape of a linear body, like a pipe or a box, which has an axial extension.
  • a slight bent in a part or the shape of the linear body should not hinder the definition of body as linear and with an axial extension.
  • the perforated section is arranged basically along or basically in parallel to the axial extension of the linear body of the resonator. In the scope of an arrangement of the perforated section as "basically parallel" to an axial extension of the linear body should also lie a divergence of the strictly parallel arrangement of about 30°.
  • the perforated section is oriented parallel to the axial extension of the linear body.
  • the perforated section is in radial direction of the resonator spatially arranged between a part, like the lumen or a jacket, of the manifold and a part, e.g. a wall, of the resonator cavity of the resonator. Hence, access to the resonator cavity through the orifices can be easily provided.
  • the resonator and the manifold may be constructed out of separate pieces or they may share pieces.
  • the perforated section is formed in a part of the manifold.
  • the perforated section is a part of the manifold or it is formed integrally with the manifold or the perforated section continues the shape of the manifold.
  • the perforated section has a shape of a hollow cylinder. Consequently, a robust a reliable part that is easy to manufacture can be provided.
  • the cylinder is e.g. a wall of the manifold.
  • the perforated section comprises a plurality of orifices, which are distributed along a whole circumference of a jacket of the hollow cylinder. Due to this, the resonator has a very broad response to frequency, especially compared to a resonator with a hollow space, like a classical Helmholtz type resonator, where the resonator provides damping only at a very specific frequency.
  • the inventive resonator is especially useful, since the frequency of oscillations varies according to operating conditions of the combustion system and the fuel composition.
  • the inventive resonator thus may be called a resonator of a perforated liner type.
  • These perforated liner type resonators provide broadband absorption in the frequency domain therefore would be adequate to provide damping to combustion dynamics of varying frequencies as the Wobbe index of the fuel varies.
  • the resonator has a shape of a linear body having an axial extension and the perforated section may comprise a plurality of orifices.
  • the perforated section may comprise a plurality of orifices.
  • plurality of orifices is distributed along the whole extension of the linear body. This results in a reliable and good damping of frequencies of the combustion system.
  • the linear body may be a rectangular box or a cylinder or a tubular pipe.
  • Both the resonator cavity and the perforated section may be embodied as a linear body with the same direction of their axial extension or the directions of the axial extensions may diverge from one another (see below).
  • the resonator comprises at least one wall (referred to as the wall in the following text), which is arranged basically along the axial extension of the linear body of the resonator (for the definition of basically along see the definition of basically in parallel above).
  • the wall of the resonator cavity and a part of the manifold, which is arranged basically along the axial extension of the linear body are arranged like in a so-called - known in the art - pipe in pipe system.
  • the term "pipe in pipe system” should not be applied to strictly tubular arrangements.
  • a combination of one or more circular pipe(s) with one or more rectangular pipe(s) or box(es) as well as the combination of two or more rectangular shapes should be understood as a "pipe in pipe system”.
  • the orifices of the plurality of orifices are evenly distributed over the at least one perforated section.
  • the damping effect may be established homogeneously.
  • the feeding of flow medium to the combustion chamber is constructively easy and most reliable, if the manifold has, seen in feeding direction of the combustion chamber, a circular shape or in other words has an overall shape of a closed ring.
  • the perforated section is a part of the manifold, the perforated section has a shape of a part cycle. Consequently, in that case, an axial extension of the perforated section is also a circumferential extension/direction (referred to the circumference of the manifold).
  • the axial extensions are both oriented in direction of the circumference of the manifold.
  • the axial extensions differ slightly by an arrangement of a circular manifold (e.g. with integrated perforated section) and a linear body of the resonator embodied as a rectangular box or as a cylindrical pipe.
  • the axial extension of the manifold is in direction of the circumference of the manifold and the resonator box/cylindrical pipe has a classical axial extension.
  • the manifold is embodied as a torus, advantageously, as a ring torus.
  • the transporting of flow medium in the manifold can be accomplished homogeneously.
  • the combustion system comprises a selected number of injectors and a selected number of resonators, wherein the number of resonators is equal or less than the number of injectors. Due to this, the damping of the perturbations is most effective.
  • the combustion system may comprise one or more combustion chambers and a selected number of resonators, wherein the number of resonators is equal or less than the number of combustion chambers. Further, measures may be taken for each injector and/or combustion chamber or its feeding region in the manifold, respectively, individually by selectively choose or adjust different resonators depending on their position in reference to the different injectors and/or combustion chambers.
  • the resonator has at least one restriction device (referred to as the restriction device in the following text) that is constructed to prevent a flow of flow medium through the two orifices from the manifold into the resonator cavity.
  • the restriction device may be any feature feasible for a person skilled in the art, like a membrane or a pressure.
  • the restriction device is a pressure in the resonator cavity.
  • the advantages of the restriction device may be constructively easy accomplished if a pressure in the resonator cavity is higher than a pressure in the manifold to prevent a flow of flow medium through the two orifices from the manifold into the resonator cavity. This is not required during resonance condition as pressure in the cavity will always be higher than pressure in the manifold during resonance. However, a pressure difference across the perforation may be required, say during shut down, to purge any flow that may be in the cavity out to the manifold.
  • damping could be increased compared to the use of only one resonator.
  • two or multiple resonators in the same fuel line avoid placing a resonator in a pressure node in the case of an established standing wave in the manifold pipe.
  • the first resonator and the second resonator differ in at least one characteristic.
  • This characteristic may be any function, feature, property, or parameter of the resonator or parts thereof or their arrangement or function together feasible for a person skilled in the art.
  • This may be for example a feature of the perforated section, like an axial (circumferential) length, a diameter, a shape, a size or a pattern of the orifices etc.; or of the linear body, like an axial length, a diameter etc.; or of the resonator cavity of the resonator, like a volume, a shape etc.; or of a special arrangement of a resonator in respect to a specific injector and/or combustion chamber.
  • different resonators could have e.g. different orifice sizes, shapes and lengths depending on the frequencies that should be attenuated. For example if multiple frequencies should be damped and they should be attenuated at the same time, then resonators may be designed with different orifice sizes/shapes and resonator lengths such that each resonator deals with a particular frequency. Moreover, since in case of a circular manifold the feeding of fuel to the successively arranged injectors and/or combustion chambers is consecutively, the conditions differ for each injector and/or combustion chamber. This could be considered by designing each resonator differently and individually.
  • the resonator(s) will be designed to provide optimum damping around the combustion dynamics frequency, using the Helmholtz equation, and specifically in dependency of beforehand determined conditions using the Helmholtz equation.
  • the perturbations establish themselves as a standing or rotating wave e.g. in the manifold. If it is a rotating wave then the position of the resonator(s) may not be of a concern. In turn, if it is a standing wave, the location of the resonator had to be purposefully chosen.
  • the resonator is placed in a location of a pressure anti-node of the standing wave established in the manifold due to perturbations of a flow rate of a flow medium travelling in the manifold.
  • multiple resonators in such locations may be required to damping the perturbations to an acceptable level.
  • the resonator cavity has a volume, which is adjustable.
  • the frequency of damping of the resonator may be controlled.
  • the combustion system is allowed to operate over a wide range of Wobbe indices i.e. providing a high flexibility in the choice of fuel. It would be either possible to vary the volume beforehand of the operation of the combustion system according to expected conditions or during the operation of the combustion system depending of in situ measurements.
  • the resonator has an adjustable wall to adjust the volume and the resonator capacity of the resonator. This would be a very easy and effective construction.
  • a method for determining a dimension of a resonator cavity of a resonator of a combustion system of a flow engine is presented.
  • the method comprises at least the following steps: determining at least one frequency that will be established in the combustion system under defined conditions and that needs modulation to provide optimum damping around a combustion dynamics frequency of the combustion system, evaluating the dimension of the resonator cavity of the resonator using the Helmholtz equation in dependency of the at least one determined frequency and adjusting the dimension according to the evaluation.
  • the resonator will be designed to provide optimum damping around the combustion dynamics frequency. This results advantageously in a suppression of pressure fluctuations in the fuel flow.
  • a combustion system may be operated even if frequency of oscillations varies according to operating conditions and fuel composition.
  • equivalence ratio fluctuations in a combustor mixing region may be beneficially reduced leading to a better control of emissions, e.g. NO x emissions.
  • a damage of pieces of the combustion system, like a combustor can, caused by combustion dynamic pulsations may be prevented.
  • the life of downstream components such as turbine blades or vanes may be improved compared to state of the art systems through a reduction in heat release fluctuations.
  • the combustion system may be operated over a wide range of Wobbe indices, resulting in flexibility concerning the used fuel.
  • combustion dynamics may be effectively reduced compared to a state of the art system.
  • this invention is also concerned with the interaction between the dynamic forces caused by combustion and those caused by the flow of fuel, air and other gases.
  • All steps may be executed beforehand of the operation or during the operation of the combustion system.
  • FIG 1 shows in a schematically view a flow engine 12, e.g. a gas turbine.
  • the flow engine 12 comprises a compressor 48, a combustion system 10 and a turbine 50, which are arranged one after another in a flow direction 52 of a first flow medium, e.g. air (see arrows pointing from left hand side to right hand side of FIG 1 ).
  • a first flow medium e.g. air
  • the combustion system 10 may comprise one combustion chamber e.g. of an annular type or several combustion chambers 14, 16 e.g. of a can type (see also FIG 2 ).
  • a second flow medium like fuel (referred to as fuel in the following text), is introduced into the combustion chambers 14, 16 from a shared manifold 18 via a separate fuel line 54, 54' and an injector 56 for each combustion chamber 14, 16 separately.
  • the fuel is mixed with a part of the compressed first flow medium leaving the compressor 48.
  • Hot gases created by combustion in the combustion chambers 14, 16 are directed to the turbine 50 having a set of turbine blades 60, being guided in the process by a set of guide vanes 58, and the turbine blades 60 and the shaft forming an axis are turned as a result.
  • the turbine blades 60 in turn rotate the blades of the compressor 48, so that the compressed flow medium is supplied by the flow engine 12 itself once this is in operation.
  • FIG 2 shows a schematic back view of the combustion system 10 in direction of the arrows II in FIG 1 .
  • the combustion system 10 has in this exemplary embodiment six combustion chambers 14, 16 (only two combustion chambers are equipped with reference signs), which are arranged one after another evenly spaced in a circumferential direction 62 around the turbine shaft.
  • the manifold 18 is arranged, in respect to the combustion chambers 14, 16, with a greater radial distance from the shaft than the combustion chambers 14, 16. Moreover, it has the shape of a closed ring and/or is a circular pipe and, as could be seen in FIG 1 , is embodied as a torus.
  • the manifold 18 is a shared manifold 18. Thus, all combustion chambers 14, 16 are fed via the same manifold 18 with fuel from the same source.
  • combustion oscillations may manifest in the combustion chambers 14, 16. These oscillations or vibrations travel through the fuel lines 54, 54' and into the manifold 18. Inside the manifold 18, either a travelling (rotating) or standing acoustic wave 46 is formed. The wave 46 may fluctuate the fuel being fed to the fuel manifold 18. Consequently, the flame in the combustion chamber 14, 16 is fed with an unsteady (fluctuating) fuel supply which causes even more combustion dynamics.
  • FIG 3 depicts a snap-shot of an established wave 46 in the manifold 18 due to perturbations of the flow rate of the fuel travelling in the manifold 18.
  • the combustion system 10 comprises in this exemplary embodiment two resonators 20, 20' (In the following text also specified as the first resonator 20 and the second resonator 20' to distinguish when needed between the two resonators 20, 20'.), wherein each resonator 20, 20' has a resonator cavity 22 (for details see FIG 4 and 5 ).
  • the resonators 20, 20' are arranged functionally in the manifold 18. Hence, by placing the resonators 20, 20' in the manifold 18 they are placed directly at the source of fuel flow fluctuations.
  • the combustion system 10 comprises a selected number of injectors 56 as well as combustion chambers 14, 16, specifically in this exemplary embodiment in each case six, and a selected number of resonators 20, 20', namely in this exemplary embodiment two, thus the number of resonators 20, 20' is less than the number of injectors 56 and combustion chambers 14, 16.
  • the established wave 46 is a standing wave 46 at least one of the resonators 20 is placed in a location of a pressure anti-node 44 of the standing wave 46.
  • FIG 4 and 5 show exemplarily the first resonator 20 from FIG 3 in more detail and in a linear configuration for better presentability.
  • the resonator 20 has a shape of a linear, rectangular, box-like body 34 having an axial extension 36.
  • the linear body 34 is only shown partially in FIG 1 (without reference sign) and in phantom in FIG 1 and FIG 5 for better presentability of the perforated section 24 (see below).
  • the resonator 20 comprises a perforated section 24 with at least two or a plurality of orifices 26.
  • the orifices 26 provide access for a wave propagation of the wave 46 from a lumen 64 of the manifold 18 to the resonator cavity 22 of the resonator 20. All orifices 26 are embodied with a circular shape.
  • the perforated section 24 has a shape of a hollow cylinder 28 (see FIG 5 ). Hence, it is a perforated liner.
  • the orifices 26 of the plurality of orifices 26 are evenly distributed over the perforated section 24 and along a whole circumference 30 of a jacket 32 of the hollow cylinder 28 (see FIG 5 ). Furthermore, they are distributed along the whole axial extension 36 of the linear body 34.
  • the perforated section 24 is formed in a part of the manifold 18 or is a part of the manifold 18.
  • the resonator 20 is embodied with a restriction device.
  • the restriction device is a pressure P in the resonator cavity 22, wherein the pressure P in the resonator cavity 22 is higher than a pressure p in the manifold 18.
  • a pressure difference of 0.5 bar would for example be sufficient.
  • the resonator cavity 22 of the resonator 20 is encased by six walls, wherein two of these walls are walls 38 that are arranged along or in parallel to the axial extension 36 of the linear body 34 of the resonator 20.
  • These walls 38 and a part 40 of the manifold 18, which is also arranged along or in parallel to the axial extension 36 of the linear body 34, are arranged like in a so-called pipe in pipe system 42.
  • the part 40 of the manifold 18 is at least a region of the perforated section 24.
  • the axial extension 36, the walls 38 and the part 40 - the region of perforated section 24 are arranged in parallel to one another.
  • both resonators 20, 20' differ in a characteristic, specifically, as an exemplary embodiment, in their axial length L.
  • both resonators 20, 20' are designed specifically for their location and function in reference to the locations and properties of the injectors 56 and the combustion chambers 14, 16.
  • the resonators 20, 20' may differ in more than one characteristic and/or in another characteristic (see listing above).
  • the determines conditions and the peak resonance frequency that will need damping define the dimensions of the orifices 26 (like a height, a length or a diameter), a number of orifices 26 and/or a volume V of the resonator cavity 22.
  • a dimension (volume) of the resonator cavity 22 of exemplarily the resonator 20 at least one frequency and preferably a broad range of frequencies that will be established in the combustion system 10 under defined conditions and that need(s) modulation to provide optimum damping around the combustion dynamics frequency of the combustion system 10 is determined. Subsequently, the dimension of the resonator cavity 22 of the resonator 20 using the Helmholtz equation in dependency of the at least one determined frequency or the determined range of frequencies is evaluated and finally the dimension according to the evaluation is adjusted (not shown in detail).
  • the resonator cavity 22 has a volume V, which is adjustable. Therefore, a moveable wall 66 is provided. That may be any of the walls encasing the resonator volume 22. As an exemplary embodiment the moveable wall 66 is one of the walls 38, arranged in parallel to the axial extension 36 of the linear body 34. This is shown in FIG 4 as a dashed line with a bidirectional arrow.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP13165158.0A 2013-04-23 2013-04-24 Verbrennungssystem einer Strömungsmaschine Withdrawn EP2851618A1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP13165158.0A EP2851618A1 (de) 2013-04-24 2013-04-24 Verbrennungssystem einer Strömungsmaschine
PCT/EP2014/056803 WO2014173660A1 (en) 2013-04-23 2014-04-04 Combustion system of a flow engine and method for determining a dimension of a resonator cavity
GB1516231.6A GB2527688A (en) 2013-04-23 2014-04-04 Combustion system of a flow engine and method for determining a dimension of a resonator cavity
KR1020157033163A KR20160003733A (ko) 2013-04-23 2014-04-04 플로 엔진의 연소 시스템 및 공진기 캐비티의 치수 판정 방법
US14/784,794 US20160076766A1 (en) 2013-04-23 2014-04-04 Combustion system of a flow engine and method for determining a dimension of a resonator cavity

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Application Number Priority Date Filing Date Title
EP13165158.0A EP2851618A1 (de) 2013-04-24 2013-04-24 Verbrennungssystem einer Strömungsmaschine

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018191170A1 (en) * 2017-04-13 2018-10-18 General Electric Company Gas turbine engine fuel manifold damper and method of dynamics attenuation
US10386074B2 (en) 2016-12-09 2019-08-20 Solar Turbines Incorporated Injector head with a resonator for a gas turbine engine
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
CN115325564A (zh) * 2022-07-21 2022-11-11 北京航空航天大学 一种结合气动导流燃烧振荡抑制方法和装置

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US20060000220A1 (en) * 2004-07-02 2006-01-05 Siemens Westinghouse Power Corporation Acoustically stiffened gas-turbine fuel nozzle
EP2192290A1 (de) * 2007-11-21 2010-06-02 Mitsubishi Heavy Industries, Ltd. Dämpfungsvorrichtung und gasturbinenbrennkammer
EP2273096A2 (de) * 2009-07-08 2011-01-12 Ford Global Technologies, LLC Brennkraftmaschine mit Ladeluftkühler

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1274529A (en) * 1968-09-12 1972-05-17 Snecma Vibration damping device for a combustion chamber
WO1993010401A1 (de) 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Einrichtung zur unterdrückung von verbrennungsschwingungen in einer brennkammer einer gasturbinenanlage
DE19818874A1 (de) * 1998-04-28 1999-11-04 Man B & W Diesel As Hubkolbenbrennkraftmaschine
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