CN116293791A

CN116293791A - Burner with resonator

Info

Publication number: CN116293791A
Application number: CN202210472538.7A
Authority: CN
Inventors: 拉马尔·詹妮丝·萨马拉辛赫; 韩飞; 克里什纳库马尔·文卡特桑
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2021-12-20
Filing date: 2022-04-29
Publication date: 2023-06-23
Also published as: US20230194090A1; EP4198397A1

Abstract

A turbine engine may include a compressor section, a combustion section, and a turbine section in a serial flow arrangement. The combustion section may include a combustor having a combustion chamber, a compressed air passage fluidly coupled to the combustion chamber, and a swirler. At least one acoustic resonator may be provided in the burner.

Description

Burner with resonator

Cross Reference to Related Applications

The present application claims priority from U.S. provisional patent application Ser. No. 63/291,539 filed on 12 months 20 of 2021 and U.S. patent application Ser. No. 17/672,946 filed on 16 months 2 of 2022, the entire contents of which are incorporated herein by reference.

Technical Field

The present subject matter relates generally to burners having resonators, and more particularly to burners having a set of acoustic resonators for damping.

Background

The turbine engine is driven by a flow of combustion gases through the engine to rotate a plurality of turbine blades. The combustor may be disposed within the turbine engine and fluidly coupled to a turbine into which the combustion gases flow.

In a typical turbine engine, air and fuel are supplied to a combustion chamber, mixed, and then ignited to produce hot gases. The hot gas is then supplied to a turbine where it rotates the turbine to generate power.

Drawings

In the drawings:

FIG. 1 is a schematic cross-sectional view of a turbine engine having a compressor, a combustor, and a turbine in accordance with various aspects described herein.

FIG. 2 is a cross-sectional view of a combustor in the turbine engine of FIG. 1 having a swirler in accordance with various aspects described herein.

FIG. 3 is a cross-sectional view of the swirler of FIG. 2 illustrating a ferrule assembly according to various aspects described herein.

FIG. 4 is a cross-sectional view of the swirler of FIG. 2 illustrating another ferrule assembly in accordance with various aspects described herein.

Detailed Description

Aspects of the disclosure described herein relate to a burner having a swirler. For purposes of illustration, the present disclosure will be described with respect to a turbine engine. However, it will be appreciated that aspects of the disclosure described herein are not limited thereto, and that the combustors described herein may be implemented in engines, including, but not limited to, turbojet engines, turboprop engines, turboshaft engines, and turbofan engines. The disclosed aspects discussed herein may have general applicability in non-aircraft engines having combustors, such as in other mobile and non-mobile industrial, commercial, and residential applications.

Turbine engine combustors typically introduce fuel that has been premixed with air and then combusted within the combustor to drive the turbine. The increase in efficiency and decrease in emissions have driven the need to use fuels that burn cleaner or at higher temperatures, such as hydrogen fuels. There is a need to improve the durability of the burner under these operating parameters, including reducing selected acoustic dynamics within the burner, such as ringing, vibration modes, and the like. The inventors' practice has been in a manner to design the burner to meet the increased engine temperature and durability requirements for hydrogen fuel use.

The term "exemplary" is used herein to mean "serving as an example, instance, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Moreover, all embodiments described herein are to be considered as exemplary unless expressly stated otherwise.

As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component from another and are not intended to represent the location or importance of the respective components.

The terms "forward" and "aft" refer to relative positions within the gas turbine engine or carrier, and refer to the normal operating attitude of the gas turbine engine or carrier. For example, for a gas turbine engine, reference is made to a location closer to the engine inlet and then to a location closer to the engine nozzle or exhaust.

As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, and the term "downstream" refers to the same direction as the direction of fluid flow. The term "forward" or "front" means in front of something and "back" or "rear" means behind something. For example, forward/forward may represent upstream and backward/backward may represent downstream when used for fluid flow.

The term "fluid" may be a gas or a liquid. The term "fluid communication" means that the fluid is capable of establishing a connection between designated areas.

Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a central longitudinal axis of the engine and the periphery of the engine.

All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, transverse, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, rearward, etc.) are used for identification purposes only to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the disclosed aspects described herein. Connection references (e.g., attached, coupled, connected, and joined) are to be construed broadly and may include structural elements between a collection of elements and relative movement between elements unless otherwise indicated. Thus, a connection reference does not necessarily mean that two elements are directly connected and fixed relative to each other. The exemplary drawings are for illustrative purposes only and the dimensions, positions, sequences and relative sizes reflected in the accompanying drawings may vary.

The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. Furthermore, as used herein, the term "set" or "group" of elements may be any number of elements, including just one.

Approximating language, as used herein throughout the specification and claims, may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by one or more terms, such as "about," "approximately," "substantially," and "essentially," are not to be limited to the precise value specified. In at least some cases, the approximating language may correspond to the precision of an instrument for measuring the value or the precision of a method or machine for constructing or manufacturing a component and/or system. In at least some cases, the approximating language may correspond to the precision of an instrument for measuring the value or the precision of a method or machine for constructing or manufacturing a component and/or system. For example, approximating language may refer to the remaining 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the individual value, range of values, and/or the endpoints of the range of defined values. Here and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are capable of being combined independently of each other.

FIG. 1 is a schematic illustration of a turbine engine 10. As a non-limiting example, the turbine engine 10 may be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. The drive shaft 18 rotationally couples the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other and defines a rotational axis 20 of the turbine engine 10.

The compressor section 12 may include a Low Pressure (LP) compressor 22 and a High Pressure (HP) compressor 24 fluidly coupled to each other in series. The turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly coupled to each other in series. The drive shaft 18 may operably couple the LP compressor 22, the HP compressor 24, the HP turbine 26, and the LP turbine 28 together. Alternatively, the drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may couple the LP compressor 22 to the LP turbine 28, and the HP drive shaft may couple the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, the LP turbine 28, and the LP drive shaft such that rotation of the LP turbine 28 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, the HP turbine 26, and the HP drive shaft such that rotation of the HP turbine 26 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

The compressor section 12 may include a plurality of axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary vanes. The compressor blades for one stage of the compressor section 12 may be mounted to a disk that is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The vanes of the compressor section 12 may be mounted to a casing, which may extend circumferentially around the turbine engine 10. It should be appreciated that the representation of the compressor section 12 is merely illustrative and that there may be any number of blades, vanes, and stages. Further, it is contemplated that there may be any number of other components within the compressor section 12.

Similar to the compressor section 12, the turbine section 16 may include a plurality of axially spaced apart stages, with each stage having a set of circumferentially spaced apart rotating blades and a set of circumferentially spaced apart stationary vanes. The turbine blades of one stage of the turbine section 16 may be mounted to a disk that is mounted to the drive shaft 18. Each set of blades for a given stage may have its own disk. The buckets of the turbine section may be mounted to the casing in a circumferential manner. It is noted that there may be any number of blades, vanes, and turbine stages, as the illustrated turbine section is merely a schematic representation. Further, it is contemplated that there may be any other number of components within turbine section 16.

The combustion section 14 may be disposed in series between the compressor section 12 and the turbine section 16. The combustion section 14 may be fluidly coupled to at least a portion of the compressor section 12 and the turbine section 16 such that the combustion section 14 at least partially fluidly couples the compressor section 12 to the turbine section 16. As a non-limiting example, the combustion section 14 may be fluidly coupled to an HP compressor 24 at an upstream end of the combustion section 14 and to an HP turbine 26 at a downstream end of the combustion section 14.

During operation of turbine engine 10, ambient or atmospheric air is drawn into compressor section 12 via a fan (not shown) upstream of compressor section 12, the air being compressed at compressor section 12, defining pressurized air. The pressurized air may then flow into the combustion section 14, where the pressurized air is mixed with fuel and ignited, thereby generating combustion gases. The HP turbine 26 extracts some work from the combustion gases, and the HP turbine 26 drives the HP compressor 24. The combustion gases are discharged into the LP turbine 28, the LP turbine 28 extracts additional work to drive the LP compressor 22, and the exhaust gases are ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool to rotate a fan (not shown) and the LP compressor 22. The pressurized airflow and the combustion gases may together define a working airflow through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

Turning to FIG. 2, a general combustion section 29 suitable for use as the combustion section 14 of FIG. 1 is illustrated in further detail. The combustion section 29 may include a combustor 30. The combustor 30 may include a combustor inlet 135 fluidly coupled to the compressor section 12 and a combustor outlet 136 fluidly coupled to the turbine section 16. The combustion section 29 may include an annular arrangement of fuel injectors 90, each fuel injector 90 being connected to a combustor 30. It should be appreciated that the annularly arranged fuel injectors 90 may be one or more fuel injectors 90, and that one or more fuel injectors 90 may have different characteristics (e.g., geometric arrangement or profile, or supply different fuel types, etc.). It should also be appreciated that fuel injector 90 is shown for illustrative purposes only and is not intended to be limiting. The burner 30 may have a can, can ring, or ring arrangement, depending on the type of engine in which the burner 30 is located. In a non-limiting example, an annular arrangement is shown and disposed within the housing 92. The combustor 30 may include an annular combustor liner 94 and a dome assembly 96, the dome assembly 96 defining a combustion chamber 98 at least partially about a Longitudinal Axis (LA). The compressed air passage 110 may be at least partially defined by both the combustor liner 94 and the casing 92. The compressed air passage 110 may be fluidly coupled to a combustor inlet 135.

At least one fuel injector 90 may be fluidly coupled to combustion chamber 98. At least one passage 112 may fluidly couple the compressed air passage 110 and the combustor 30. In some examples, the at least one passage 112 may be formed by a set of dilution openings 112a in the combustor liner 94. Any number of dilution openings may be provided in a set of dilution openings 112a. The set of dilution openings 112a may have any geometric profile, size, pattern, arrangement, etc. on or over the combustor liner 94, including combinations of different geometric profiles, sizes, patterns, or arrangements.

The fuel injector 90 may be coupled to the dome assembly 96 upstream of the flared cone 114 and disposed within the dome assembly 96 upstream of the flared cone 114 to define a fuel outlet 116. The fuel injector 90 may include a fuel inlet 118, which fuel inlet 118 may be adapted to receive a flow of fuel (F). In a non-limiting example, the fuel (F) may include any suitable fuel, including a hydrocarbon fuel or fuel mixture, or a hydrogen fuel or fuel mixture.

A fuel passage 122 may extend between the fuel inlet 118 and the fuel outlet 116. The swirler 124 may be provided and configured to swirl the incoming air in the vicinity of the fuel (F) exiting the fuel injector 90. In some examples, the cyclone 124 may be disposed at the dome inlet 120, but this is not necessarily the case. In some examples, the swirler 124 may also be configured to provide a uniform mixture of air and fuel to the combustor 30.

Combustor liner 94 may include a liner wall 126, with liner wall 126 having an outer surface 128 and an inner surface 130 at least partially defining combustion chamber 98. In some examples, the liner wall 126 may be made from one continuous portion including one continuous integral portion. In some examples, the liner wall 126 may include multiple portions that are assembled together to define the combustor liner 94. As a non-limiting example, the outer surface 128 may define a first piece of the liner wall 126, while the inner surface 130 may define a second piece of the liner wall 126, which when assembled together, forms the combustor liner 94. Further, the combustor liner 94 may have any suitable form, including, but not limited to, a double wall liner or a ceramic tile liner.

Igniter 132 may be coupled to liner wall 126 and fluidly coupled to combustion chamber 98. Igniter 132 may be disposed in any suitable location including, but not limited to, between adjacent dilution openings in a set of dilution openings 112a.

During operation, compressed air (C) may flow from the compressor section 12 to the combustor 30 through the compressed air passage 110. At least a portion of the compressed air (C) may pass from the compressed air passage 110 to the combustion chamber 98 through a set of dilution openings 112a, wherein the portion defines a dilution gas flow (D).

Some of the compressed air (C) may be mixed with fuel (F) and, once entering the combustor 30, the mixture is ignited within the combustion chamber 98 by one or more igniters 132 to generate combustion gases (G). The dilution gas flow (D) may be supplied through at least one set of dilution openings 112a and mixed into the combustion gas (G) within the combustion chamber 98, after which the combustion gas (G) may flow through the combustor outlet 136 and into the turbine section 16.

It should be appreciated that the passages illustrated herein, including the compressed air passage 110, the fuel passage 122, the passage 112, etc., may be displayed with components that visually appear to block the passage in the illustrated exemplary cross-sectional view without actually blocking the passage. For example, the inner wall, struts, etc. may be present in the plane of the exemplary cross-sectional view, while the channels extend into or out of the plane of the exemplary cross-sectional view such that the channels are not actually blocked.

Turning to FIG. 3, a portion of the combustor 30 is shown adjacent the dome assembly 96 and the swirler 124. A set of dilution openings 112a in combustor liner 94 are also shown. Compressed air (C) is shown within the compressed air channel 110. Fuel (F) is shown moving through fuel passage 122 and into combustion chamber 98. It will be appreciated that in some examples, the compressed air (C) may also be mixed with the fuel (F) within the fuel passage 122.

In the illustrated example, the dome assembly 96 may include a deflector 140 and a dome plate 142, but this is not necessarily the case. The swirler 124 may be positioned within the compressed air passage 110 upstream of the dome assembly 96. The swirler 124 may include a ferrule assembly 144, the ferrule assembly 144 at least partially surrounding the fuel passage 122, as shown. The ferrule assembly 144 may include at least one internal fluid passage 145, the internal fluid passage 145 having an inlet 146 fluidly coupled to the compressed air passage 110 and an outlet 148 fluidly coupled to the fuel outlet 116. In the non-limiting example shown, the internal fluid passage 145 may include a first passage 147 extending through a wall of the ferrule assembly 144, and a plenum 149 at least partially surrounding the fuel passage 122. The first channel 147 may be fluidly coupled to the inlet 146 and the plenum 149 may be fluidly coupled to the outlet 148. Any number of internal fluid passages 145 may be provided. The internal fluid passages 145 may have any suitable geometric profile, arrangement, or positioning. Further, a single internal fluid passageway 145 may have a single inlet 146, multiple inlets 146, a single outlet 148, or multiple outlets 148. During operation, compressed air (C) may flow through the internal fluid passage 145 of the ferrule assembly 144 and into the combustion chamber 98.

At least one acoustic resonator 150 may be provided with the cyclone 124. Any number of acoustic resonators 150 may be provided. Acoustic resonator 150 may have any suitable form, arrangement, geometric profile, size, etc. In some examples, acoustic resonator 150 may include a helmholtz resonator, a quarter-wavelength resonator, a half-wavelength resonator, or the like, or a combination thereof.

In the example of fig. 3, the at least one acoustic resonator 150 includes a set of quarter wave resonators 152 coupled to the inlet 146 of the internal fluid channel 145 as shown. Any number of acoustic resonators 150 may be provided, including only one or two or more. Further, a set of quarter wave resonators 152 may include any number of quarter wave resonators, including only one or two or more. In the example shown, each quarter wave resonator of the set of quarter wave resonators 152 includes a resonator inlet 154 fluidly coupled to the compressed air channel 110 and a resonator outlet 156 fluidly coupled to the inlet 146 of the internal fluid channel 145. A resonator chamber 158 may be defined between the resonator inlet 154 and the resonator outlet 156. Any suitable geometric profile may be used for resonator chamber 158, including circular, curved, tapered, asymmetric, or irregular geometric profiles. Further, a length of each quarter wave resonator of the set of quarter wave resonators 152 may be defined between the resonator inlet 154 and the resonator outlet 156. In some examples, the first quarter wave resonator may have a first length and the second quarter wave resonator may have a second length. The second length may be the same as the first length, or less than the first length, or greater than the first length. It is also contemplated that in a non-limiting example, the inner diameter of the quarter wave resonators in the set of quarter wave resonators 152 may be variable, or the set of quarter wave resonators 152 may include a first quarter wave resonator having a smaller inner diameter than a second quarter wave resonator.

The resonator chamber 158 may be selected or sized to attenuate a particular frequency or range of frequencies of acoustic waves, including acoustic or pressure waves, flowing through the combustor 30. In a non-limiting example, the at least one acoustic resonator 150 may attenuate frequencies between 2000Hz and 5000Hz or between 4000Hz and 5000 Hz. In some examples, a plurality of acoustic resonators may be provided, wherein a first acoustic resonator may attenuate frequencies covering a first frequency range and a second acoustic resonator may attenuate frequencies covering a second frequency range. In a non-limiting example, the first acoustic resonator may have a first chamber volume that attenuates frequencies between 2000Hz and 2500Hz in a first portion of the combustor, and the second acoustic resonator may have a second chamber volume that attenuates frequencies between 3500Hz and 4000Hz in a second portion of the combustor. During operation, acoustic waves within the combustor 30 may pass through the ferrule assembly 144 and cause resonance within the at least one acoustic resonator 150, thereby damping at least one acoustic frequency and reducing noise, vibration, etc.

Referring now to FIG. 4, another cyclone 224 is shown that may be used with the burner 30 (FIG. 2). Cyclone 224 is similar to cyclone 124; accordingly, like parts will be identified with like numerals increased by 100, it being understood that the description of like parts of cyclone 124 applies to cyclone 224 unless otherwise indicated.

The swirler 224 may be positioned within the combustor 30 upstream of the dome assembly 96 within the compressed air passage 110. The cyclone 224 may include a ferrule assembly 244 similar to the ferrule assembly 144 (fig. 3). As shown, the ferrule assembly 244 may at least partially surround the fuel passage 122. The ferrule assembly 244 may include an internal fluid passage 245, the internal fluid passage 245 having an inlet 246 fluidly coupled to the compressed air passage 110 and an outlet 248 fluidly coupled to the fuel outlet 116. During operation, compressed air (C) may flow through the internal fluid passage 245 of the ferrule assembly 244 and into the combustion chamber 98.

At least one acoustic resonator 250 may be provided with the cyclone 224. One difference compared to the acoustic resonator 150 of fig. 3 is that the acoustic resonator 250 may include a helmholtz resonator 252 having a resonator inlet 254, a resonator outlet 256, and a resonator chamber 258. Resonator outlet 256 may be fluidly coupled to inlet 246 of internal fluid passageway 245. The helmholtz resonator 252 may also include a neck 253, the neck 253 being formed by a resonator inlet 254 and defining a neck volume 255. The resonator chamber 258 may include a chamber fluidly coupled to the neck and defining a chamber volume.

Another difference is that the at least one acoustic resonator 250 may include a variable chamber volume within the resonator chamber 258. In some examples, a single resonator chamber 258 may be provided having a wall 260, the wall 260 having a thickness that is variable in a circumferential direction around the combustor 30. In some examples, a plurality of inner circumferentially arranged partition walls 261 may be provided to form a plurality of circumferentially arranged acoustic resonators 250 with corresponding resonator chambers 258. In some examples, the first resonator chamber 258A may have a first chamber volume 259A and the second resonator chamber 258B may have a second chamber volume 259B, the second chamber volume 259B being less than the first chamber volume 259A. It should be appreciated that in the illustrated example, the first resonator chamber 258A extends behind the fuel passage 122. In other examples, the resonator chamber 258 may include walls having a constant thickness, increasing or decreasing spacing between adjacent walls, variable geometric contours along a predetermined axis, or the like, or a combination thereof. In some non-limiting examples, a set of acoustic resonators 250 may attenuate frequencies between 1000Hz and 5000 Hz.

Benefits of the present disclosure include the ability to attenuate one or more acoustic waves, including pressure waves, high frequency waves, flow disturbances, or other flow dynamics that may exist within a combustor. In some examples, multiple frequencies may be attenuated simultaneously by selecting the volume of the chamber formed by the ferrule assembly with the integrated acoustic resonator. The use of variable chamber volumes may additionally provide selective frequency attenuation in different regions of the burner. Attenuation of undesirable acoustic waves may provide increased engine efficiency and increased component part life.

Although described with respect to a turbine engine, it should be appreciated that aspects of the present disclosure may have general applicability to any combustor. In a non-limiting example, aspects of the present disclosure described herein may also be applicable to engines, turbojet engines, or turboshaft engines having a propeller section, a fan, and a booster section.

The different features and structures of the various embodiments may be used in combination or in place of one another as desired within the scope not yet described. Not having illustrated a feature in all embodiments does not mean that it cannot be so illustrated, but rather that it is done so for the sake of brevity of description. Thus, the various features of the different embodiments can be mixed and matched as desired to form new embodiments, whether or not the new embodiments are explicitly described. All combinations or permutations of features described herein are covered by this disclosure.

Further aspects of the disclosure are provided by the subject matter of the following clauses:

a turbine engine, comprising: a compressor section, a combustion section, and a turbine section in a serial flow arrangement, and the combustion section having a combustor comprising: a combustor liner at least partially defining a combustion chamber; a compressed air passage fluidly coupled to the compressor section and the combustion chamber; a fuel passage fluidly coupled to the combustion chamber; and a swirler at least partially surrounding the fuel passage, the swirler comprising: an internal fluid passage having an inlet fluidly coupled to the compressed air passage and an outlet fluidly coupled to the fuel passage; and an acoustic resonator having a resonator chamber fluidly coupled to the inlet of the internal fluid passage.

The turbine engine of any of the preceding clauses, wherein the swirler comprises a ferrule assembly at least partially surrounding the fuel passage.

The turbine engine of any of the preceding clauses, further comprising a first passage extending through a wall of the ferrule assembly, and further comprising a plenum at least partially surrounding the fuel passage.

The turbine engine of any of the preceding clauses, wherein the first passage and the plenum at least partially define the internal fluid passage.

The turbine engine as in any one of the preceding clauses, wherein the acoustic resonator comprises one of a quarter-wavelength resonator, a half-wavelength resonator, or a helmholtz resonator.

The turbine engine of any of the preceding clauses, wherein the acoustic resonator comprises a quarter wave resonator coupled to the inlet of the internal fluid passage and extending into the compressed air passage.

The turbine engine of any of the preceding clauses, wherein the acoustic resonator includes an outer wall defining the resonator chamber.

The turbine engine of any of the preceding clauses, wherein the outer wall includes a resonator inlet fluidly coupled to the compressed air passage and a resonator outlet fluidly coupled to the inlet of the internal fluid passage.

The turbine engine of any of the preceding clauses, wherein the resonator chamber comprises a first chamber volume, and further comprising a second resonator chamber having a second chamber volume that is less than the first chamber volume.

The turbine engine of any of the preceding clauses, wherein the fuel passage is configured to supply hydrogen fuel to the combustion chamber.

A combustor for a turbine engine, comprising: a combustor liner at least partially defining a combustion chamber; a compressed air passage fluidly coupling a compressed air source and the combustion chamber; a fuel passage fluidly coupled to the combustion chamber; and a swirler at least partially surrounding the fuel passage, the swirler comprising: an internal fluid passage having an inlet fluidly coupled to the compressed air passage and an outlet fluidly coupled to the fuel passage; and an acoustic resonator having a resonator chamber fluidly coupled to the inlet of the internal fluid passage.

The burner of any of the preceding clauses, wherein the swirler comprises a ferrule assembly at least partially surrounding the fuel passage.

The burner of any of the preceding clauses, further comprising a first passage extending through a wall of the ferrule assembly, and further comprising a plenum at least partially surrounding the fuel passage.

The burner of any of the preceding clauses, wherein the first channel and the plenum at least partially define the internal fluid channel.

The burner of any of the preceding clauses, wherein the acoustic resonator comprises one of a quarter-wavelength resonator, a half-wavelength resonator, or a helmholtz resonator.

The burner of any of the preceding clauses, wherein the acoustic resonator comprises a quarter wave resonator coupled to the inlet of the internal fluid passage and extending into the compressed air passage.

The burner of any of the preceding clauses, wherein the acoustic resonator comprises an outer wall defining the resonator chamber.

The combustor of any of the preceding clauses, wherein the outer wall comprises a resonator inlet fluidly coupled to the compressed air channel and a resonator outlet fluidly coupled to the inlet of the internal fluid channel.

The burner of any of the preceding clauses, wherein the resonator chamber comprises a first chamber volume, and further comprising a second resonator chamber having a second chamber volume that is less than the first chamber volume.

The burner of any of the preceding clauses, wherein the fuel passage is configured to supply hydrogen fuel to the combustion chamber.

Claims

1. A turbine engine, comprising:

a compressor section, a combustion section, and a turbine section in a serial flow arrangement, and the combustion section having a combustor comprising:

a combustor liner at least partially defining a combustion chamber;

a compressed air passage fluidly coupled to the compressor section and the combustion chamber;

a fuel passage fluidly coupled to the combustion chamber; and

a swirler at least partially surrounding the fuel passage, the swirler comprising:

an internal fluid passage having an inlet fluidly coupled to the compressed air passage and an outlet fluidly coupled to the fuel passage; and

an acoustic resonator having a resonator chamber fluidly coupled to the inlet of the internal fluid passage.

2. The turbine engine of claim 1, wherein the swirler includes a ferrule assembly at least partially surrounding the fuel passage.

3. The turbine engine of claim 2, further comprising a first passage extending through a wall of the ferrule assembly, and further comprising a plenum at least partially surrounding the fuel passage.

4. The turbine engine of claim 3, wherein the first passage and the plenum at least partially define the internal fluid passage.

5. The turbine engine of any of claims 1-4, wherein the acoustic resonator comprises one of a quarter wave resonator, a half wave resonator, or a helmholtz resonator.

6. The turbine engine of claim 1, wherein the acoustic resonator comprises a quarter wave resonator coupled to the inlet of the internal fluid passage and extending into the compressed air passage.

7. The turbine engine of claim 1, wherein the acoustic resonator includes an outer wall defining the resonator chamber.

8. The turbine engine of claim 7, wherein the outer wall includes a resonator inlet fluidly coupled to the compressed air passage and a resonator outlet fluidly coupled to the inlet of the internal fluid passage.

9. The turbine engine of claim 1, wherein the resonator chamber includes a first chamber volume and further comprising a second resonator chamber having a second chamber volume that is less than the first chamber volume.

10. The turbine engine of any of claims 1-4 or 6-9, wherein the fuel passage is configured to supply hydrogen fuel to the combustion chamber.