Turbine engine with multi-cavity damper

Abstract

A gas turbine engine includes a compressor section for compressing air flowing therethrough to provide a compressed air flow; a combustor including a combustion chamber configured to combust a mixture of a fuel stream and a compressed air stream to produce a combustion product; and a turbine section having at least one turbine driven by the combustion products. The gas turbine engine includes a multi-cavity damper in fluid communication with the combustion chamber for attenuating instability created by combustion products within the combustion chamber. The multi-cavity damper has a plurality of cavity volumes, each cavity volume having a different length.

Description

Technical Field

[0001] This disclosure generally relates to a multi-cavity damper, such as a multi-cavity damper in a turbine engine. Background Technology

[0002] Turbine engines typically include propellers (e.g., fans or propellers) arranged in fluid communication with each other, and turbocharged engines. A turbocharged engine includes a compressor section, a combustion section, and a turbine section. The combustion section includes combustors for producing combustion products. Attached Figure Description

[0003] Features and advantages will become apparent from the more detailed description of various exemplary embodiments below, as shown in the accompanying drawings, wherein the same reference numerals generally denote the same, functionally similar and / or structurally similar elements.

[0004] Figure 1 A schematic cross-sectional view of a gas turbine engine according to the present disclosure, taken along the longitudinal centerline axis of the engine, is shown.

[0005] Figure 2 The following is shown in accordance with this disclosure: Figure 1 A schematic cross-sectional view of the combustor of a turbine engine along the longitudinal centerline of the engine.

[0006] Figure 3 The present disclosure shows the method for use Figure 2 A schematic partial cross-sectional view of the damper of the burner.

[0007] Figure 4 The present disclosure shows the method for use Figure 2 A schematic partial cross-sectional view of the damper of the burner.

[0008] Figure 5A The present disclosure shows the method for use Figure 2 A schematic partial cross-sectional view of the damper of the burner.

[0009] Figure 5B The present disclosure shows the method for use Figure 2 A schematic partial cross-sectional view of the damper of the burner.

[0010] Figure 6A A graph showing the damper effectiveness versus frequency according to this disclosure is provided.

[0011] Figure 6B A graph showing the damper effectiveness versus frequency according to this disclosure is provided.

[0012] Figure 6C A graph showing the damper effectiveness versus frequency according to this disclosure is provided. Detailed Implementation

[0013] The features, advantages, and embodiments of this disclosure are set forth or apparent from the following detailed description, the accompanying drawings, and the claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of protection claimed in this disclosure.

[0014] Various embodiments of this disclosure are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from the scope of this disclosure.

[0015] The terms “first” and “second” used in this article are used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of the components.

[0016] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid channel. For example, "upstream" refers to the direction from which fluid flows, and "downstream" refers to the direction from which fluid flows.

[0017] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and to the normal operating posture of the turbine engine or carrier. For example, for a turbine engine, "front" refers to the position closer to the engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust port.

[0018] As used herein, the terms “low,” “medium” (or “medium”) and “high,” or their respective comparatives (e.g., “lower” and “higher,” if applied), when used with compressors, turbines, shafts, fans, or turbine engine components, refer to relative pressure, relative speed, relative temperature, and / or relative power output within the engine, unless otherwise specified. For example, a “low power” setting defines an engine configured to operate at a power output lower than the engine’s “high power” setting, while a “medium power” setting defines an engine configured to operate at a power output higher than the “low power” setting but lower than the “high power” setting. The terms “low,” “medium” (or “medium”), or “high” in the foregoing can also be understood as relative to a minimum permissible speed, pressure, or temperature, or relative to the minimum or maximum permissible speed, pressure, or temperature for normal, desired, or steady-state operation of the engine.

[0019] Unless otherwise stated herein, the terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking via one or more intermediate components or features. These terms include integral and monolithic configurations (e.g., integral bladed disk rotor blade system).

[0020] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0021] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the turbine engine.

[0022] In this specification and claims, the scope is defined in a way that is combinable and interchangeable. Unless the context or language otherwise indicates, such scopes are explicit and include all subscopes contained therein. For example, all scopes disclosed herein include endpoints, and endpoints can be independently combined with each other.

[0023] This disclosure provides an acoustic damper for suppressing combustion instability in a burner. When instability occurs in the combustion chamber of a burner, it manifests as large-amplitude sinusoidal pressures that can damage the equipment. An acoustic damper can be used to attenuate or mitigate this instability. The acoustic damper of this disclosure divides the cavity into multiple cavity volumes to enhance the damper's performance. A single-cavity damper has a single volume and a single length, and can therefore be targeted at a single instability frequency (e.g., a target frequency). The multi-cavity damper of this disclosure provides multiple cavity volumes, each with a unique length. The multi-cavity damper of this disclosure can be customized and enhanced in acoustic attenuation characteristics to meet the specific needs of the combustion system. Multiple cavity volumes enable the damper to capture multi-tone behavior in the burner and can significantly broaden the frequency range (e.g., attenuation profile) of the acoustic damper's attenuation. The multi-cavity damper of this disclosure can target and attenuate multiple frequencies, including targeting and attenuating low-frequency and high-frequency tones with a single damper in any combination, even if the tones are independent in the frequency space. The multi-cavity damper of this disclosure helps to broaden two or more independent tones. The multi-cavity damper disclosed herein may contain two or more cavities. The number of cavities can be selected according to the number of target frequencies.

[0024] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of a turbine engine 10 according to an embodiment of the present disclosure, taken along the longitudinal centerline axis 12 of the turbine engine 10. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 for reference), a radial direction R perpendicular to the axial direction A, and a circumferential direction C extending around the longitudinal centerline axis 12. Typically, the turbine engine 10 includes a fan section 14 and a turbine engine 16 disposed downstream of the fan section 14.

[0025] The turbocharged engine 16 includes a compressor section 22, a combustion section 28, and a turbine section 30 arranged in a series flow relationship. The turbocharged engine 16 is substantially surrounded by a casing 18, which is generally tubular and defines an annular inlet 20. Figure 1 As shown, compressor section 22 includes a turbocharger or low-pressure (LP) compressor 24, downstream of which is a high-pressure (HP) compressor 26. Combustion section 28 includes a combustor 200, located downstream of compressor section 22. Turbine section 30, located downstream of combustion section 28, includes a high-pressure (HP) turbine 32, downstream of which is a low-pressure (LP) turbine 34. Turbocharged engine 16 also includes an injection exhaust nozzle section 36, a high-pressure (HP) shaft 38 or spool, and a low-pressure (LP) shaft 40, located downstream of turbine section 30. HP shaft 38 drives HP turbine 32 to HP compressor 26. HP turbine 32 and HP compressor 26 rotate synchronously via HP shaft 38. LP shaft 40 drives LP turbine 34 to LP compressor 24. LP turbine 34 and LP compressor 24 rotate synchronously via LP shaft 40. Compressor section 22, combustion section 28, turbine section 30, and injection exhaust nozzle section 36 together define the core airflow path.

[0026] for Figure 1 In the illustrated embodiment, fan section 14 includes a fan 42 (e.g., a variable pitch fan) having a plurality of fan blades 44 spaced apart and coupled to disk 46. Figure 1 As shown, fan blades 44 extend outward from disk 46 generally in the radial direction R. For a variable-pitch fan, the fan blades 44 are operatively coupled to an actuating member 48, which is rotatable relative to disk 46 about a pitch axis P. This actuating member is configured to collectively change the pitch of the fan blades 44. The fan blades 44, disk 46, and actuating member 48 can rotate together via a fan shaft 50 about a longitudinal centerline axis 12, which is powered by an LP shaft 40 across a power gearbox (also referred to as gearbox assembly 52). Thus, fan 42 is drivenly coupled to and powered by a turbine engine 16, which is an indirect drive engine. Figure 1 The gearbox assembly 52 is schematically shown. Gearbox assembly 52 is a reduction gearbox assembly used to regulate the rotational speed of fan shaft 50 when power is transmitted from LP shaft 40 to fan shaft 50, thereby regulating the rotational speed of fan 42 relative to LP shaft 40.

[0027] Still referencing Figure 1In an exemplary embodiment, the disk 46 is covered by a rotatable fan hub 54 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 44. Furthermore, the fan section 14 includes an annular fan housing or nacelle 56 that circumferentially surrounds at least a portion of the fan 42 and the turbocharged engine 16 by a plurality of outlet guide vanes 58 circumferentially spaced around the nacelle 56 and the turbocharged engine 16. Additionally, a downstream section 60 of the nacelle 56 extends over the outer portion of the turbocharged engine 16 and, together with the housing 18, defines a bypass airflow passage 62 between them.

[0028] During operation of the turbine engine 10, a certain amount of air 64 enters the turbine engine 10 through the nacelle 56 or the inlet 66 of the fan section 14. As the air 64 passes through the fan blades 44, a first portion of air 68 (also referred to as bypass air 68) is directed to the bypass airflow passage 62, and a second portion of air 70 (also referred to as core air 70) is directed to the upstream section of the core air flow path through the annular inlet 20 of the LP compressor 24. The ratio between bypass air 68 and core air 70 is commonly referred to as the bypass ratio. The pressure of the core air 70 is then increased, producing compressed air 72. The compressed air 72 is directed through the HP compressor 26 and into the combustion section 28, where it mixes with fuel and ignites to produce combustion gases 74.

[0029] Combustion gas 74 is guided into and expanded by the HP turbine 32. In the HP turbine, a portion of the thermal and kinetic energy from the combustion gas 74 is extracted via one or more stages of HP turbine stator blades 76 and HP turbine rotor blades 78, which are connected to the HP shaft 38. This causes the HP shaft 38 to rotate, thereby supporting the operation of the HP compressor 26 (self-sustaining cycle). Thus, the combustion gas 74 performs work on the HP turbine 32. The combustion gas 74 is then guided into and expanded by the LP turbine 34. Here, a second portion of the thermal and kinetic energy is extracted from the combustion gas 74 via one or more stages of LP turbine stator blades 80 and LP turbine rotor blades 82, which are connected to the LP shaft 40. This causes the LP shaft 40 to rotate, thereby supporting the operation of the LP compressor 24 (self-sustaining cycle) and, via the gearbox assembly 52, supporting the rotation of the fan 42. Thus, the combustion gas 74 performs work on the LP turbine 34.

[0030] Subsequently, combustion gases 74 are directed through the injector exhaust nozzle section 36 of the turbocharged engine 16 to provide propulsive thrust. Simultaneously, bypass air 68 is directed through bypass airflow passage 62 before exiting from the fan nozzle exhaust section 84 of the turbocharged engine 10, also providing propulsive thrust. The HP turbine 32, LP turbine 34, and injector exhaust nozzle section 36 at least partially define a hot gas path 86 for directing combustion gases 74 through the turbocharged engine 16.

[0031] The turbine engine 10 can be communicatively and operably coupled to the engine controller 100 along communication line 102. The engine controller 100 is configured to operate various aspects of the turbine engine 10. The engine controller 100 may be a full authority digital engine control (FADEC). In this embodiment, the engine controller 100 is a computing device having one or more processors 104 and one or more memories 106. The processor 104 may be any suitable processing device, including but not limited to microprocessors, microcontrollers, integrated circuits, logic devices, programmable logic controllers (PLCs), application-specific integrated circuits (ASICs), and / or field-programmable gate arrays (FPGAs). The memory 106 may include one or more computer-readable media, including but not limited to non-transitory computer-readable media, computer-readable non-volatile media (e.g., flash memory), RAM, ROM, hard disk drives, flash drives, and / or other memory devices.

[0032] Memory 106 may store information accessible to processor 104, including computer-readable instructions executable by processor 104. These instructions may be any set or sequence of instructions that, when executed by processor 104, cause processor 104 and engine controller 100 to perform operations. In some embodiments, these instructions may be executed by processor 104 to cause processor 104 to perform any operations and functions configured for engine controller 100, as described below. These instructions may be software written in any suitable programming language or hardware implemented. Additionally and / or alternatively, the instructions may be executed in logically and / or virtually independent threads on processor 104. Memory 106 may also store data accessible by processor 104.

[0033] The technologies discussed herein relate to computer-based systems, operations performed by computer-based systems, and information sent to and from computer-based systems. Those skilled in the art will recognize that the inherent flexibility of computer-based systems allows for a wide variety of possible configurations, combinations, and divisions of tasks and functions among components. For example, the processes discussed herein can be implemented using a single computing device or a combination of multiple computing devices. Databases, memory, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel.

[0034] The engine controller 100 can be communicatively coupled to one or more sensors used in the methods of this disclosure, such as vibration sensors (e.g., accelerometers), temperature sensors, speed sensors, and other sensors within the turbine engine 10. For example, the engine controller 100 can receive data or information from one or more sensors and optionally store or record such data or information. The engine controller 100 can also control the drive of the turbine engine (e.g., the rotation of the rotor, which will be described in more detail below).

[0035] Figure 1 The turbine engine 10 shown is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 42 may be configured in any other suitable manner (e.g., a variable-pitch fan or a fixed-pitch fan) and may also be supported using any other suitable fan frame configuration. Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In other exemplary embodiments, the engine may also be a direct-drive engine that does not have a power gearbox (e.g., no gearbox assembly 52). For a direct-drive engine, the fan speed is the same as the LP shaft speed. In other exemplary embodiments, various aspects of this disclosure may be incorporated into any suitable turbine engine, such as a turbofan engine, a propeller fan engine, a turboprop engine, a non-ducted engine, or a turboshaft engine.

[0036] Figure 2 It shows the axis 12 along the longitudinal centerline. Figure 1The image shows a cross-sectional view of the burner 200. The burner 200 has a longitudinal centerline axis 202. The burner 200 includes a burner housing 204 and a burner bushing 206. The burner housing 204 has an outer shell 208 and an inner shell 210, and the burner bushing 206 has an outer bushing 212 and an inner bushing 214. A combustion chamber 216 is formed within the burner bushing 206. More specifically, the outer bushing 212 and the inner bushing 214 are disposed between the outer shell 208 and the inner shell 210. The outer bushing 212 and the inner bushing 214 are radially spaced apart from each other, thereby defining the combustion chamber 216 between them. The outer shell 208 and the outer bushing 212 form an outer channel 218 therebetween, and the inner shell 210 and the inner bushing 214 form an inner channel 220 therebetween. As shown in the figure, the burner 200 is a single annular burner. However, in other embodiments, the burner 200 can be any other burner, such as a canister or canister annular arrangement, depending on the type of engine in which the burner 200 is located.

[0037] Combustion chamber 216 has a front end 222 (downstream end) and a rear end 224 (upstream end). A swirler / fuel nozzle assembly 226 is positioned at the front end 222 of combustion chamber 216. The swirler / fuel nozzle assembly 226 includes a fuel nozzle 228 and a swirler 230. In an example of an annular burner (e.g., burner 200), the swirler / fuel nozzle assembly 226 may be one of a plurality of swirler / fuel nozzle assemblies 226 arranged around a longitudinal centerline axis 12 ( Figure 1 They are arranged in a ring configuration in the circumferential direction.

[0038] As described above, and with reference Figure 1 and 2The compressor section 22, combustion section 28 (including burner 200), and turbine section 30 at least partially form the flow path of the core air 70. The core air 70 entering the annular inlet 20 is compressed by the LP compressor 24 and HP compressor 26 and flows to the burner 200 in the form of compressed air flow 236. A shroud assembly 232 is connected to the upstream ends of the outer bushing 212 and the inner bushing 214, respectively. An annular opening 234 formed in the shroud assembly 232 allows a first portion 238 of the compressed air flow 236 to enter the burner 200. The first portion 238 flows through the annular opening 234 to support combustion within the combustion chamber 216. A second portion 240 of the compressed air flow 236 flows around the outer side of the burner bushing 206 through outer passages 218 and inner passages 220. The second portion 240 can be introduced into the combustion chamber 216 via a plurality of circumferentially spaced dilution orifices 242 formed in the burner bushing 206 at one or more locations downstream of the cyclone / fuel nozzle assembly 226. While a single dilution orifice 242 is shown in each of the outer bushing 212 and the inner bushing 214, a plurality of dilution orifices 242 may be provided in the circumferential direction surrounding the longitudinal centerline axis 202. Furthermore, the dilution orifices 242 may be provided in either the outer bushing 212 or the inner bushing 214, or simultaneously in both.

[0039] Each of the plurality of swirler / fuel nozzle assemblies 226 is coupled to a dome plate 244. Each swirler / fuel nozzle assembly 226 receives a first portion 238 of a compressed air flow 236 from an annular opening 234. Swirlers 230 of the swirler / fuel nozzle assembly 226 generate turbulence in the first portion 238. The fuel nozzle 228 injects fuel into the turbulent air flow, which promotes rapid mixing of fuel and air. The fuel and compressed air mixture is discharged into a combustion chamber 216 and burned there, producing combustion gases (combustion products) that accelerate as they leave the combustion chamber 216.

[0040] like Figure 2 and Figure 3 As shown, the burner 200 includes a multi-cavity damper 300 that extends through an opening 324 in the housing 208 and an opening 326 in the outer bushing 212 of the burner 200. While the multi-cavity damper 300 shown extends through the opening 324 in the housing 208, in some examples, the multi-cavity damper 300 may be entirely within the housing 208, so that the multi-cavity damper 300 only extends through the opening 326 on the outer bushing 212 and not through the housing 208. The multi-cavity damper 300 is an acoustic damper. Figure 2A single multi-cavity damper 300 is shown. However, the multi-cavity damper 300 may also comprise multiple dampers distributed circumferentially along the combustor 200. Each provided multi-cavity damper 300 extends through a single opening (e.g., opening 324) in the outer bushing 212, such that the multiple cavities of the multi-cavity damper 300 communicate with the combustion chamber 216 through the single opening 324. As described in more detail below, this allows for multi-tone and wide-frequency damping using a single damper and a single opening in the outer bushing 212.

[0041] Figure 3 The multi-cavity damper 300 is shown in more detail. The multi-cavity damper 300 includes a damper body 302 having a first damper body portion 302a and a second damper body portion 302b fastened or joined together. In other examples, the damper body 302 is a single, integral piece.

[0042] The multi-cavity damper 300 includes a main damper cavity 304 within a damper body 302. The main damper cavity 304 is a multi-cavity volume, including a first cavity volume 306 and a second cavity volume 308. As discussed in more detail below, the number of cavities is not limited to two, and more cavities may be provided. The damper body 302 includes an inner cylindrical surface 316 having a top surface 314 and a bottom surface 318, which together define the main damper cavity 304. The top surface 314 and the bottom surface 318 may be planar. The main damper cavity 304 defines a longitudinal axis 305 and a radial axis 307 perpendicular to the longitudinal axis 305. The radial axis 307 may define the diameter of the main damper cavity 304. A first inner wall 310 extends parallel to the longitudinal axis 305. Figure 3 In one example, a first inner wall 310 extends from the bottom surface 318. The first inner wall 310 may extend the entire diameter of the main damper cavity 304 in the direction of the radial axis 307, such that the first inner wall 310 bisects the main damper cavity 304. A second inner wall 312 extends parallel to the radial axis 307 between the first inner wall 310 and the inner cylindrical surface 316. In some examples, the second inner wall 312 extends completely between the first inner wall 310 and the inner cylindrical surface 316, such that the second inner wall 312 is semi-circular.

[0043] The first inner wall 310 and the second inner wall 312 divide the main damper cavity 304 into multiple cavities, such as a first cavity volume 306 and a second cavity volume 308. Specifically, the first cavity volume 306 is defined between the inner cylindrical surface 316, the bottom surface 318, the first inner wall 310, and the second inner wall 312. The first cavity volume 306 has a semi-circular shape. The second cavity volume 308 is defined by the inner cylindrical surface 316, the bottom surface 318, the top surface 314, the first inner wall 310, and the second inner wall 312.

[0044] Each of the first cavity volume 306 and the second cavity volume 308 is in fluid communication with the combustion chamber 216 through one or more openings 320. Each of the first cavity volume 306 and the second cavity volume 308 is in fluid communication with the outer passage 218 through one or more openings 322. Within the multi-cavity damper 300, the first cavity volume 306 and the second cavity volume 308 are isolated and not in fluid communication with each other.

[0045] One or more openings 320 act as a neck, making the multi-cavity damper 300 a Helmholtz resonator or a quarter-wavelength tube. When instability exists in the combustion chamber 216, it manifests as sinusoidal pressure with a large amplitude, potentially damaging the equipment. The multi-cavity damper 300 attenuates or mitigates this instability. The multi-cavity damper 300 can customize and enhance the acoustic attenuation characteristics within the combustion chamber 216. The multiple cavity volumes of the multi-cavity damper 300 enable it to capture multi-tone characteristics within the combustion chamber 216 and broaden the attenuation curve.

[0046] Figure 4 An exemplary multi-cavity damper 400 is shown. Except as described below, this multi-cavity damper 400 is similar to... Figure 3 The multi-cavity damper 300 shown is similar. Therefore, components in the multi-cavity damper 400 that are the same as or similar to those in the multi-cavity damper 300 described above will use the same reference numerals. In some cases, for clarity, Figure 4 Reference numbers have been omitted. However, the components shown in the figure should be understood as being related to... Figure 3 The same applies to the components described above. The above description of these components applies to this embodiment, therefore, they will not be described in detail here.

[0047] Figure 3 The multi-cavity damper 300 includes two damper cavities within a main damper cavity 304, a first cavity volume 306 and a second cavity volume 308. The multi-cavity damper 400 includes a main damper cavity 404 with three damper cavities: a first cavity volume 406, a second cavity volume 408, and a third cavity volume 424. Similar to the multi-cavity damper 300, the first cavity volume 406 is defined by an inner cylindrical surface 316, a bottom surface 318, a first inner wall 310, and a second inner wall 312.

[0048] Similarly, as with the multi-cavity damper 300, the second cavity volume 408 is defined between the inner cylindrical surface 316, the bottom surface 318, the top surface 314, and the first inner wall 310. However, in the multi-cavity damper 400, the second cavity volume 408 is not defined by the second inner wall 312, but is further defined by the third inner wall 426 and the fourth inner wall 428. The third inner wall 426 extends parallel to the longitudinal axis 305 and is coplanar with the first inner wall 310. The fourth inner wall 428 extends parallel to the radial axis 307 and can extend the entire diameter of the main damper cavity 404. The fourth inner wall 428 is parallel to the second inner wall 312 and offset from the second inner wall 312.

[0049] The third chamber volume 424 is defined by a radially inner cylindrical surface 316, a first inner wall 310, a second inner wall 312, a third inner wall 426, and a fourth inner wall 428. The first inner wall 310 is offset from the third inner wall 426 such that the third chamber volume 424 is in fluid communication with the second chamber volume 408. The first chamber volume 406 is isolated and is not in fluid communication with the second chamber volume 408 or the third chamber volume 424. Each of the first chamber volume 406, the second chamber volume 408, and the third chamber volume 424 (via the second chamber volume 408) is in fluid communication with the combustion chamber 216 via one or more openings 320.

[0050] Figure 5A An exemplary multi-cavity damper 500a is shown. Except as described below, the multi-cavity damper 500a is similar to... Figure 3 The multi-cavity damper 300 is similar to that in the multi-cavity damper 500a. Therefore, for components in the multi-cavity damper 500a that are the same as or similar to those in the multi-cavity damper 300 described above, the same reference numerals will be used. In some cases, for clarity, Figure 5A Reference numbers have been omitted. However, similar components shown in the figure should be understood as... Figure 3 The same applies to the components described above. The above description of these components applies to this embodiment, therefore detailed descriptions of these components are omitted herein.

[0051] The multi-cavity damper 500a includes two damper cavities within a main damper cavity 504a: a first cavity volume 506a and a second cavity volume 508a. The first cavity volume 506a is defined by an inner cylindrical surface 516a, a bottom surface 318, a first inner wall 510a, and a second inner wall 312. The second cavity volume 508a is defined by the inner cylindrical surface 516a, the bottom surface 318, the first inner wall 510a, and a top surface 314. Figure 3 Multi-cavity damper 300 and Figure 5A The difference between the multi-cavity damper 500a and the previous one is that there is no cavity volume above the second inner wall 312. Instead, the damper body 302, more specifically, the first damper body portion 302a, is solid. Figure 5AIn the example, since the solid first inner wall 510a separates the two volumes, the first cavity volume 506a and the second cavity volume 508a are not fluidly connected to each other within the multi-cavity damper 500a.

[0052] Figure 5B An exemplary multi-cavity damper 500b is shown. Except as described below, multi-cavity damper 500b is similar to multi-cavity damper 500a. Therefore, for components in multi-cavity damper 500b that are identical or similar to those in multi-cavity damper 500a described above, the same reference numerals will be used. In some cases, for clarity, Figure 5B Reference numbers have been omitted. However, similar components shown in the figure should be understood as... Figure 5A (and Figure 3 The components described above are the same as those described in [the previous section]. The above description of these components applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0053] The multi-cavity damper 500b includes two damper cavities within a main damper cavity 504b: a first cavity volume 506b and a second cavity volume 508b. The first cavity volume 506b is defined by an inner cylindrical surface 516b, a bottom surface 318, a first inner wall 510b, a second inner wall 312, and a third inner wall 526. The second cavity volume 508b is defined by the inner cylindrical surface 516b, the bottom surface 318, the first inner wall 510b, the third inner wall 526, and a top surface 314. Figure 5A Multi-cavity damper 500a and Figure 5B The difference between the multi-cavity dampers 500b is that the first cavity volume 506b and the second cavity volume 508b are fluidly connected within the multi-cavity damper 500b through the space or gap between the first inner wall 510b and the third inner wall 526.

[0054] Figures 3 to 5B Each of the figures illustrates a damper with various cavity volumes and corresponding cavity volumes. Although the figures depict multiple inner walls for defining multiple cavities, only a single inner wall is actually required. That is, multiple cavities can be defined between the inner cylindrical surface and a single inner wall. Similarly, it is also possible to consider using a method larger than shown in the figures (e.g., Figure 4 (As shown) more inner walls to define multiple cavities.

[0055] For example, when comparing Figures 3 to 5A At that time, the first cavity volume 306 and the first cavity volume 506a have the same volume. However, the second cavity volume 308 has a larger volume than the second cavity volume 508a. This is because... Figure 3 An additional cavity volume extending between the second inner wall 312 and the top surface 314.

[0056] Compare Figure 3 aspects and Figure 4In terms of volume, the second cavity volume 308 and the second cavity volume 408 have the same volume. Since the third cavity volume 424 is contained between the second inner wall 312 and the fourth inner wall 428, the first cavity volume 306 has a larger volume than the first cavity volume 406.

[0057] Will Figure 4 aspects and Figure 5A and 5B In comparison, the volumes of all the cavities are different. The first cavity volume 406 has a smaller volume than the first cavity volume 506a (again, this is due to the inclusion of the third cavity volume 424). The second cavity volume 408 has a larger volume than the second cavity volume 508a (this is due to the additional cavity volume extending between the second inner wall 312 and the top surface 314).

[0058] Figures 3 to 5B The examples shown are several examples of damper cavities. Other exemplary cavities can have any number of cavity volumes, as long as each cavity volume is in fluid communication with the combustion chamber 216. In this way, the number of cavity volumes and the volume of each cavity volume can be selected to achieve the desired effect in the combustion chamber 216 ( Figure 2 The required damping is achieved within the multi-cavity damper, as described in more detail below. In each damper described herein, each cavity within the same damper has a unique length (e.g., a dimension extending parallel to the longitudinal axis 305). That is, for example, in multi-cavity damper 300, the length of the first cavity volume 306 differs from the length of the second cavity volume 308. In multi-cavity damper 400, each of the first cavity volume 406, the second cavity volume 408, and the third cavity volume 424 has a different length. In multi-cavity dampers 500a and 500b, the lengths of the first cavity volumes 506a and 506b differ from the lengths of the second cavity volumes 508a and 508b. As described above, additional multi-cavity dampers (e.g., having four, five, six, etc. volumes) can be considered. For each volume of the multi-cavity damper, its length is unique relative to the other volumes within the multi-cavity damper.

[0059] Figures 6A to 6C An exemplary graph illustrating the effect of a multi-cavity damper is shown. Figure 6A The effect of a multi-cavity damper with four volumes is shown. Figure 6B The effect of a multi-cavity damper with three volumes is shown. Figure 6C The effect of a multi-cavity damper with two volumes is shown.

[0060] like Figures 6A to 6C As shown, the number of independent cavity volumes within a multi-cavity damper is directly proportional to the number of discrete frequencies (also known as tones) attenuated or damped. This can be efficiently written as:

[0061] nds ∝n fp

[0062] Where, n ds n is the number of independent damper volumes. fp This represents the number of discrete frequencies (pitches) that are attenuated or damped. The damper volume n ds It can range from one volume to ten volumes, therefore the target frequency n fp It can also range from one frequency to ten frequencies. In one example, the damper volume n ds It can range from one volume to four volumes, therefore the target frequency n fp It can also operate at one to four frequencies.

[0063] As the dimensions of multiple cavity volumes become increasingly similar, the target frequencies begin to approach each other and gradually move away from the discrete target frequencies. In this situation, the attenuation curves begin to blend. Therefore, in order to maintain the discrete target frequencies, these cavity volumes must differ from the other volumes within the multi-cavity damper by at least 20%.

[0064] Refer again Figure 6B , Figure 6B The multi-cavity damper in the table contains three cavity volumes. Table 1 shows the relationship between the unique length of each cavity volume and the target frequency (also known as the peak frequency).

[0065] cavity volume length Target (peak) frequency L F 1.032*L 0.966*F 1.095*L 0.901*F

[0066] Table 1

[0067] In this example, the length difference between each volume is less than 20%, so the frequency peaks begin to merge with adjacent frequencies. As mentioned above, this merging not only allows for localization of discrete frequencies but also broadens the damping performance across the entire frequency band. The frequency band refers to the range of frequencies within which the multi-cavity damper is effectively effective. Broadening the damping frequency band means widening the range of frequencies within which the multi-cavity damper is effectively effective. That is, with... Figure 6C In contrast, for example, more frequencies (between the target frequencies, also known as peak frequencies) are attenuated due to the mixing or merging of attenuation curves.

[0068] exist Figure 6C In this example, the multi-cavity damper comprises two cavity volumes. Table 2 shows the relationship between the length of each cavity volume and the target frequency.

[0069] cavity volume length Target (peak) frequency L F 2*L 0.685*F

[0070] Table 2

[0071] In this example, the length difference exceeds 20%, resulting in clear and distinct peaks without mixing. This allows for targeting two different tones.

[0072] Therefore, the multicavity damper of this disclosure allows (1) for discrete frequencies and (2) for widening the target frequency band.

[0073] Therefore, the damper of the present invention can be customized and its acoustic performance enhanced as needed to suppress specific tones. This allows for wider attenuation and multi-tone attenuation with a single damper. In other words, the multi-cavity damper of the present invention can attenuate a wide frequency range or multiple discrete tones with a single damper. That is, a single damper (e.g., multi-cavity damper 300, multi-cavity damper 400, multi-cavity damper 500a, or multi-cavity damper 500b) provides a single inlet into the combustion chamber, enabling multi-tone attenuation and wider attenuation within a single damper. This is highly advantageous because each additional inlet into the combustion chamber negatively impacts performance. Therefore, the damper of this disclosure dampens acoustic behavior with only a single inlet into the combustion chamber.

[0074] Further aspects are provided by the following items.

[0075] A gas turbine engine includes: a compressor section for compressing air flowing therethrough to provide a compressed air flow; a combustor including a combustion chamber configured to burn a mixture of a fuel flow and the compressed air flow to produce combustion products; a turbine section having at least one turbine driven by the combustion products; and a multi-cavity damper in fluid communication with the combustion chamber for attenuating instabilities generated by the combustion products in the combustion chamber, the multi-cavity damper having a plurality of cavity volumes, each cavity volume having a different length, wherein the number of cavity volumes of the multi-cavity damper is proportional to the number of target frequencies.

[0076] A gas turbine engine includes: a compressor section for compressing air flowing therethrough to provide a compressed air flow; a combustor including a combustion chamber configured to burn a mixture of a fuel flow and the compressed air flow to produce combustion products; a turbine section having at least one turbine driven by the combustion products; and a multi-cavity damper in fluid communication with the combustion chamber for attenuating instabilities generated in the combustion chamber by the combustion products, the multi-cavity damper having a plurality of cavity volumes, wherein the number of cavity volumes of the multi-cavity damper is proportional to the number of target frequencies.

[0077] A gas turbine engine includes: a compressor section for compressing air flowing therethrough to provide a compressed air flow; a combustor including a combustion chamber configured to burn a mixture of a fuel flow and the compressed air flow to produce combustion products; a turbine section having at least one turbine driven by the combustion products; and a multi-chamber damper in fluid communication with the combustion chamber for attenuating instabilities generated in the combustion chamber by the combustion products, the multi-chamber damper having a plurality of chamber volumes, each chamber volume having a different length.

[0078] A gas turbine engine includes: a compressor section for compressing air flowing therethrough to provide a compressed air flow; a combustor including a combustion chamber configured to burn a mixture of a fuel flow and the compressed air flow to produce combustion products; a turbine section having at least one turbine driven by the combustion products; and a plurality of multi-chamber dampers in fluid communication with the combustion chamber, each multi-chamber damper being in fluid communication with the combustion chamber through a corresponding single opening in a combustion liner of the combustion chamber.

[0079] According to the gas turbine engine described in the foregoing clause, each of the plurality of cavity volumes in the multi-cavity damper is fluidly isolated from each other.

[0080] According to any of the preceding clauses, the lengths of each chamber volume differ from each other by less than 20 percent.

[0081] According to any of the preceding clauses, in a gas turbine engine, the lengths of each chamber volume differ from each other by more than 20 percent.

[0082] According to any of the preceding clauses, in a gas turbine engine, the length of the first chamber volume differs from the length of the second chamber volume by less than 20 percent, and the length of the first chamber volume differs from the length of the third chamber volume by more than 20 percent.

[0083] According to any of the preceding clauses, in a gas turbine engine, the length of the first chamber volume differs from the length of the second chamber volume by less than 20 percent, and the length of the second chamber volume differs from the length of the third chamber volume by more than 20 percent.

[0084] The gas turbine engine according to any of the preceding clauses, wherein the plurality of chamber volumes includes a first chamber volume having a first chamber volume length and a second chamber volume having a second chamber volume length.

[0085] According to any of the preceding clauses, in a gas turbine engine, the first cavity volume attenuates a first target frequency and the second cavity volume attenuates a second target frequency, wherein the first target frequency is different from the second target frequency.

[0086] According to any of the preceding clauses, in a gas turbine engine, the difference between the volume length of the first cavity and the volume length of the second cavity is less than 20 percent, such that the attenuation curve of the multi-cavity damper includes two frequency curves with different frequency peaks, the two frequency curves being combined to provide a wider attenuation bandwidth.

[0087] According to any of the preceding clauses, in a gas turbine engine, the volume length of the first cavity differs from that of the volume length of the second cavity by more than 20 percent, such that the attenuation curve of the multi-cavity damper includes two frequency curves with different frequency peaks, the two frequency curves being different and separate, and the frequency curves not being mixed.

[0088] The gas turbine engine according to any of the preceding clauses further includes a third cavity volume having a third cavity volume length, wherein the third cavity volume attenuation is a third target frequency different from the first target frequency and the second target frequency.

[0089] According to any of the preceding clauses, the gas turbine engine has a body and a main damper cavity defined by the inner cylindrical surface of the body, and the main damper cavity is divided into the plurality of damper cavity volumes by an inner wall.

[0090] According to any of the preceding clauses, the gas turbine engine has a main damper cavity having a longitudinal axis and a radial axis, and the inner wall includes a first inner wall extending parallel to the longitudinal axis to separate a first cavity volume from a second cavity volume among the plurality of cavity volumes.

[0091] The gas turbine engine according to any of the preceding clauses further includes a second inner wall extending parallel to the radial axis to separate the first cavity volume from the second cavity volume.

[0092] According to any of the preceding clauses, in a gas turbine engine, the length of the first cavity volume is less than the length of the main damper cavity, and the length of the second cavity volume is greater than the length of the main damper cavity.

[0093] The gas turbine engine according to any of the preceding clauses further includes a third inner wall extending parallel to the longitudinal axis and a fourth inner wall extending parallel to the radial axis, wherein the main damper cavity includes a third cavity volume defined between each of the first inner wall, the second inner wall, the third inner wall and the fourth inner wall.

[0094] According to any of the preceding clauses of the gas turbine engine, wherein the length of the first cavity volume is less than the length of the main damper cavity, and the length of the second cavity volume is equal to the length of the main damper cavity.

[0095] According to any of the preceding clauses of the gas turbine engine, wherein the multi-chamber damper is connected to the outer bushing through a single opening in the outer bushing of the burner.

[0096] In any of the preceding clauses of the gas turbine engine, the multi-cavity damper is one of a plurality of multi-cavity dampers arranged circumferentially around the combustor.

[0097] In any of the preceding clauses, each of the plurality of multi-chamber dampers is identical.

[0098] According to any of the preceding clauses, in the gas turbine engine, wherein the multi-cavity damper is composed of n ds ∝n fp Limited, where n ds n is the number of independent damper volumes. fp It is the number of discrete frequencies (pitches) that are attenuated or damped.

[0099] The gas turbine engine according to any of the preceding clauses, wherein the number of independent damper volumes is from one to ten volumes, and the number of discrete frequencies is from one to ten frequencies.

[0100] The gas turbine engine according to any of the preceding clauses, wherein the number of independent damper volumes is from one to four volumes, and the number of discrete frequencies is from one to four frequencies.

[0101] According to any of the preceding clauses, the number of independent damper volumes is equal to the number of discrete frequencies in the gas turbine engine.

[0102] The gas turbine engine according to any of the foregoing clauses, wherein the length of each chamber volume is different.

[0103] According to any of the preceding clauses, in a gas turbine engine, the number of cavity volumes of the multi-cavity damper is proportional to the number of target frequencies.

[0104] According to any of the preceding clauses, in a gas turbine engine, each of the first cavity volume and the second cavity volume has a length equal to that of the main damper cavity.

[0105] Although the foregoing description pertains to preferred embodiments of this disclosure, those skilled in the art will understand that other changes and modifications can be made without departing from the scope of this disclosure. Furthermore, even if not explicitly stated above, features described in connection with one embodiment of this disclosure can be used in conjunction with other embodiments.

Claims

1. A gas turbine engine characterized by, Comprising: a compressor section for compressing air flowing therethrough to provide a compressed air stream; a combustor comprising a combustion chamber configured to combust a mixture of a fuel stream and the compressed air stream to produce a combustion product; a turbine section having at least one turbine driven by the combustion product; and a multi-cavity damper in fluid communication with the combustion chamber to attenuate instabilities produced by the combustion product in the combustion chamber, the multi-cavity damper having a plurality of cavity volumes, and each cavity volume being of a different length. Wherein, 2. The gas turbine engine of claim 1, wherein, within the multi-cavity damper, each of the plurality of cavity volumes is fluidically isolated from one another. Wherein, 3. The gas turbine engine of claim 1, wherein, the length of each cavity volume differs from one another by less than twenty percent. Wherein, 4. The gas turbine engine of claim 1, wherein, the length of each cavity volume differs from one another by more than twenty percent. Wherein, 5. The gas turbine engine of claim 1, wherein, the length of a first cavity volume differs from a length of a second cavity volume by less than twenty percent, and the length of the first cavity volume differs from a length of a third cavity volume by more than twenty percent. Wherein, 6. The gas turbine engine of claim 1, wherein, the length of a first cavity volume differs from a length of a second cavity volume by less than twenty percent, and the length of the second cavity volume differs from a length of a third cavity volume by more than twenty percent. Wherein, 7. The gas turbine engine of claim 1, wherein, a number of cavity volumes of the multi-cavity damper is directly proportional to a number of target frequencies. Wherein, 8. The gas turbine engine of claim 1, wherein, the multi-cavity damper is coupled to an outer liner of the combustor through a single opening in the outer liner. Wherein, 9. The gas turbine engine of claim 8, wherein, the multi-cavity damper is one of a plurality of multi-cavity dampers circumferentially disposed about the combustor. Wherein, 10. The gas turbine engine of claim 1, wherein, the plurality of cavity volumes includes a first cavity volume having a first cavity volume length and a second cavity volume having a second cavity volume length. ​

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