US20120180492A1 - Apparatus for vibration support in combustors and method for forming apparatus - Google Patents
Apparatus for vibration support in combustors and method for forming apparatus Download PDFInfo
- Publication number
- US20120180492A1 US20120180492A1 US13/006,518 US201113006518A US2012180492A1 US 20120180492 A1 US20120180492 A1 US 20120180492A1 US 201113006518 A US201113006518 A US 201113006518A US 2012180492 A1 US2012180492 A1 US 2012180492A1
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- United States
- Prior art keywords
- sleeve component
- support
- support feature
- combustor
- assembly
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- 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.)
- Abandoned
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D25/00—Special casting characterised by the nature of the product
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00018—Manufacturing combustion chamber liners or subparts
Definitions
- the subject matter disclosed herein relates generally to turbine systems, and more particularly to apparatus for reducing vibrations in combustors of turbine systems and methods for forming the apparatus.
- Turbine systems are widely utilized in fields such as power generation.
- a conventional gas turbine system includes a compressor, a combustor, and a turbine.
- various components in the system may be subjected to high temperature flows, which can cause the components to fail. Since higher temperature flows generally result in increased performance, efficiency, and power output of the gas turbine system, the components that are subjected to high temperature flows must be cooled to allow the gas turbine system to operate at increased temperatures.
- an improved apparatus for reducing structural vibrations in a combustor of a turbine system and a method for forming the apparatus, would be desired in the art.
- a method and apparatus that provide support features that are integral with an existing combustor component would be advantageous.
- a method and apparatus that provide support features that may be configured for optimal vibratory and heat transfer capabilities would be desired.
- a sleeve component assembly for a combustor includes a sleeve component, the sleeve component comprising one of an inner sleeve component or an outer sleeve component.
- the sleeve component assembly further includes at least one support feature extending from the sleeve component, the at least one support feature configured to contact and provide vibratory support to an adjacent sleeve component.
- the at least one support feature is integral with the sleeve component.
- a method for forming a sleeve component assembly for a combustor includes flowing a sleeve component substrate into a mold through at least one gate, the mold comprising the at least one gate and at least one shell configured to form a sleeve component therein, the sleeve component comprising one of an inner sleeve component or an outer sleeve component.
- the method further includes solidifying the sleeve component substrate in the mold to form the sleeve component assembly, the sleeve component assembly comprising the sleeve component and at least one support feature, the at least one support feature integral with the sleeve component and disposed in the at least one gate.
- the method further includes removing the sleeve component assembly from the mold, and adjusting a height of the at least one support feature such that the at least one support feature is configured to contact and provide vibratory support to an adjacent sleeve component.
- FIG. 1 is a schematic illustration of a gas turbine system
- FIG. 2 is a side cutaway view of one embodiment of various components of the gas turbine system of the present disclosure
- FIG. 3 is a side view of one embodiment of a sleeve component assembly of the present disclosure.
- FIG. 4 is a cross-sectional view of one embodiment of a mold for a sleeve component assembly of the present disclosure.
- FIG. 1 is a schematic diagram of a gas turbine system 10 .
- the system 10 may include a compressor 12 , a combustor 14 , and a turbine 16 . Further, the system 10 may include a plurality of compressors 12 , combustors 14 , and turbines 16 .
- the compressors 12 and turbines 16 may be coupled by a shaft 18 .
- the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form shaft 18 .
- the combustor 14 is generally fluidly coupled to the compressor 12 and the turbine 16 .
- the compressor 12 may include a diffuser 20 and a discharge plenum 22 that are coupled to each other in fluid communication, so as to facilitate the channeling of a working fluid 24 to the combustor 14 .
- working fluid 24 may flow through the diffuser 20 and be provided to the discharge plenum 22 .
- the working fluid 24 may then flow from the discharge plenum 22 to the combustor 14 , wherein the working fluid 24 is combined with fuel from fuel nozzles 26 .
- the working fluid 24 /fuel mixture may be ignited within combustion chamber 28 to create hot gas flow 30 .
- the hot gas flow 30 may be channeled through the combustion chamber 28 along a hot gas path 32 into a transition piece cavity 34 and through a turbine nozzle 36 to the turbine 16 .
- the combustor 14 may comprise a hollow annular wall configured to facilitate working fluid 24 .
- the combustor 14 may include a combustor liner 40 disposed within a flow sleeve 42 .
- the arrangement of the combustor liner 40 and the flow sleeve 42 is generally concentric and may define an annular passage or flow path 44 therebetween.
- the flow sleeve 42 and the combustor liner 40 may define a first or upstream hollow annular wall of the combustor 14 .
- the flow sleeve 42 may include a plurality of inlets 46 , which provide a flow path for at least a portion of the working fluid 24 from the compressor 12 through the discharge plenum 22 into the flow path 44 .
- the flow sleeve 42 may be perforated with a pattern of openings to define a perforated annular wall.
- the interior of the combustor liner 40 may define the substantially cylindrical or annular combustion chamber 28 and at least partially define the hot gas path 32 through which hot gas flow 30 may be directed.
- an impingement sleeve 50 may be coupled to the flow sleeve 42 .
- the flow sleeve 42 may include a mounting flange 52 configured to receive a mounting member 54 of the impingement sleeve 50 .
- a transition piece 56 may be disposed within the impingement sleeve 50 , such that the impingement sleeve 50 surrounds the transition piece 56 .
- a concentric arrangement of the impingement sleeve 50 and the transition piece 56 may define an annular passage or flow path 58 therebetween.
- the impingement sleeve 50 may include a plurality of inlets 60 , which may provide a flow path for at least a portion of the working fluid 24 from the compressor 12 through the discharge plenum 22 into the flow path 58 .
- the impingement sleeve 50 may be perforated with a pattern of openings to define a perforated annular wall.
- Interior cavity 34 of the transition piece 56 may further define hot gas path 32 through which hot gas flow 30 from the combustion chamber 28 may be directed into the turbine 16 .
- the flow path 58 is fluidly coupled to the flow path 44 .
- the flow paths 44 and 58 define a flow path configured to provide working fluid 24 from the compressor 12 and the discharge plenum 22 to the fuel nozzles 26 , while also cooling the combustor 14 .
- the turbine system 10 may intake working fluid 24 and provide the working fluid 24 to the compressor 12 .
- the compressor 12 which is driven by the shaft 18 , may rotate and compress the working fluid 24 .
- the compressed working fluid 24 may then be discharged into the diffuser 20 .
- the majority of the compressed working fluid 24 may then be discharged from the compressor 12 , by way of the diffuser 20 , through the discharge plenum 22 and into the combustor 14 .
- a small portion (not shown) of the compressed working fluid 24 may be channeled downstream for cooling of other components of the turbine engine 10 .
- a portion of the compressed working fluid 24 within the discharge plenum 22 may enter the flow path 58 by way of the inlets 60 .
- the working fluid 24 in the flow path 58 may then be channeled upstream through flow path 44 , such that the working fluid 24 is directed over the combustor liner 34 .
- a flow path is defined in the upstream direction by flow path 58 (formed by impingement sleeve 50 and transition piece 56 ) and flow path 44 (formed by flow sleeve 42 and combustor liner 40 ).
- flow path 44 may receive working fluid 24 from both flow path 58 and inlets 46 .
- the working fluid 24 through the flow path 44 may then be channeled upstream towards the fuel nozzles 26 , as discussed above.
- the combustor liner 40 , transition piece 56 , flow sleeve 42 , and impingement sleeve 50 are all sleeve components for the combustor 14 .
- both the combustor liner 40 and the transition piece 56 are inner sleeve components 100 configured to at least partially provide a flow boundary in the combustor 14 .
- an inner sleeve component 100 may be configured to provide a flow boundary by providing a physical boundary between various flows or directions of flow in the combustor 14 .
- the various flows or directions of flow may have different temperatures, and the inner sleeve component 100 may thus further provide a temperature boundary in the combustor 14 .
- the combustor liner 40 and the transition piece 56 provide a flow boundary between the flow of working fluid 24 and the hot gas flow 30 , as discussed above. Further, the working fluid 24 is generally cooler than the hot gas flow 30 , and is used to cool the combustor liner 40 and the transition piece 56 . Thus, the combustor liner 40 and transition piece 56 further provide a temperature boundary.
- both the flow sleeve 42 and impingement sleeve 50 are outer sleeve components 102 .
- an outer sleeve component 102 is a component of the combustor 14 is disposed adjacent an inner sleeve component 100 .
- the outer sleeve component 102 may act as an outer sleeve or casing for the inner sleeve component 100 , and may provide an outer boundary for flows flowing past the inner sleeve component 100 .
- the flow sleeve 42 and impingement sleeve 50 are outer sleeve components 102 for the combustor liner 40 and the transition piece 56 , respectively.
- the outer sleeve component 102 may vibrate undesirably.
- devices and apparatus are needed to provide vibratory support to the outer sleeve component 102 in order to reduce or eliminate the vibration of the outer sleeve component 102 .
- the present disclosure is further directed to a sleeve component assembly 104 for the turbine system 10 .
- the sleeve component assembly 104 may include a sleeve component.
- the sleeve component may in exemplary embodiments be an inner sleeve component 100 , or alternatively may be an outer sleeve component 102 .
- the sleeve component may be a transition piece 56 .
- the sleeve component assembly 104 further includes at least one support feature 110 .
- the sleeve component assembly 104 includes a plurality of support features 110 .
- Each support feature 110 extends from the sleeve component, such as the inner sleeve component 100 or outer sleeve component 102 .
- each support feature 110 may extend from a surface 112 of the sleeve component that faces an adjacent sleeve component, which may be the other of the inner sleeve component 100 or the outer sleeve component 102 .
- the support features 110 may extend from the surface 112 of the transition piece 56 facing the adjacent impingement sleeve 50 .
- the support features 110 may be configured to contact and provide vibratory support to the adjacent sleeve component.
- the support features 110 may be configured to generally continuously contact and provide vibratory support to the adjacent sleeve component. The support features 110 may thus interact with the adjacent sleeve component to support the component and reduce the structural vibrations of the component.
- the support features 110 may each define a height 114 .
- the height 114 of each support feature 110 may allow the support feature 110 to contact and interact with the adjacent sleeve component, such as the adjacent outer sleeve component 102 , to provide the required vibratory support.
- the height 114 of each support feature 110 may be adjusted as desired to ensure that the support feature 110 properly supports the adjacent sleeve component.
- the height 114 may be adjusted such that the support features 110 generally continuously contact and provide vibratory support to the adjacent sleeve component.
- the height 114 may be such that when the turbine system 10 is non-operational, the adjacent sleeve component and the support features 110 are in contact. It should be understood, however, that during operation, vibrations may cause the generally continuously contacting support features 110 and adjacent sleeve component to occasionally separate, and that this vibrational movement of the support features 110 and adjacent sleeve component relative to one another is within the scope and spirit of the generally continuously contacting support features 110 and adjacent sleeve component.
- the height 114 may be adjusted such that the support features 110 contact and provide vibratory support to the adjacent sleeve component during operation of the system 10 .
- the height 114 may be such that when the turbine system 10 is non-operational, the adjacent sleeve component and the support features 110 are not in contact.
- vibrations may cause the generally continuously contacting support features 110 and adjacent sleeve component to occasionally contact, and the support features 110 may thus contact and provide vibratory support to the adjacent sleeve component.
- Each support feature 110 is integral with the sleeve component, such as with the inner sleeve component 100 or outer sleeve component 102 .
- the sleeve component and the support features 110 extending therefrom may be formed from the same materials, and may be formed together as a singular unit.
- the sleeve component and the support features 110 may in exemplary embodiments be formed from a nickel or cobalt based alloy or super alloy.
- the sleeve component and the support features 110 may be formed from any materials suitable for use in a combustor 14 .
- the support features 110 may be formed during casting of the sleeve component.
- the mold shells for casting the sleeve component assembly 104 therein may be designed and configured to form a sleeve component assembly 104 including the sleeve component and at least one support feature 110 .
- the gates utilized during casting to flow a sleeve component substrate therethrough into the mold shells may form the support features 110 .
- the support features 110 may be formed by the gates during casting of the sleeve component.
- the sleeve component assembly 104 may thus be formed as an integral unit during casting.
- each support feature 110 may be configured to provide a desired vibratory characteristic.
- each support feature 110 may be individually tailored to impart a desired vibratory characteristic onto the adjacent sleeve component, such as the adjacent outer sleeve component 102 , that the support feature 110 is providing vibratory support to.
- Each support feature 110 may be formed with a desired shape, size, and/or height 114 , and/or the location of the support feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired vibratory characteristic.
- the desired vibratory characteristic may be the natural frequency of the adjacent sleeve component, such as the adjacent outer sleeve component 102 .
- Each support feature 110 may be configured to raise or lower the natural frequency of the adjacent sleeve component or to cause the adjacent sleeve component to have a certain desired natural frequency.
- the height 114 of the support features 110 may be raised to raise the natural frequency of the adjacent sleeve component or lowered to lower the natural frequency of the adjacent sleeve component.
- the present disclosure is not limited to adjusting the above characteristics of the support features 110 to adjust the natural frequency of the adjacent sleeve component. Rather, the adjustment of any suitable characteristics of the support features 110 to adjust any suitable vibratory characteristics of the adjacent sleeve component are within the scope and spirit of the present disclosure.
- each support feature 110 may be configured to provide a desired heat transfer characteristic.
- the sleeve component such as in exemplary embodiments the inner sleeve component 102 , may provide a temperature boundary between, for example, a relatively hotter flow and a relatively cooler flow.
- the sleeve component is a transition piece 56 , for example, the sleeve component may provide a temperature boundary between a hot gas flow 30 and a working fluid 24 .
- the support features 110 may thus be utilized to provide desired heat transfer characteristics for the sleeve component.
- Each support feature 110 may be formed with a desired shape, size, and/or height 114 , and/or the location of the support feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired heat transfer characteristic. For example, it may be desirable that the heat exchange through the sleeve component is relatively uniform. Thus, various support features 110 may be formed as relatively thick support features 110 , and may thus act as insulators to heat cold spots on the sleeve component, while other support features 110 may be formed as relatively thin support features 110 , and may thus act as fins to cool hot spots on the sleeve component. The support features 110 may thus assist in providing a relatively uniform heat exchange through the sleeve component.
- the present disclosure is not limited to adjusting the above characteristics of the support features 110 to provide uniform heat exchange through the sleeve component. Rather, the adjustment of any suitable characteristics of the support features 110 to adjust any suitable heat transfer characteristic of the sleeve component assembly 104 or adjacent sleeve component are within the scope and spirit of the present disclosure.
- the present disclosure is further directed to a method for forming a sleeve component assembly 104 for a combustor 14 .
- the sleeve component assembly 104 includes a sleeve component, such as an inner sleeve component 100 or an outer sleeve component 102 , and at least one support feature 110 or a plurality of support features 110 . Further, the sleeve component in exemplary embodiments is a transition piece 56 .
- the method includes, for example, flowing a sleeve component substrate 200 into a mold 202 through at least one gate 204 , or through a plurality of gates 204 .
- the mold 202 may comprise the gates 204 and at least one shell configured to form the sleeve component 100 .
- the mold 202 may include at least one inner shell 206 , or a plurality of inner shells 206 , and at least one outer shell 208 , or a plurality of outer shells 208 .
- the inner and outer shells 206 , 208 may fit together to form an interior molding area 210 therein for the sleeve component 100 .
- the gates 204 may provide access points through the outer shells 208 and/or the inner shells 206 for the sleeve component substrate 200 to flow into the interior molding area 210 .
- the mold 202 in some embodiments may further include a pour spout 212 or a plurality of pour spouts 212 , a sprue 214 or a plurality of sprues 214 , and a runner 216 or a plurality of runners 216 .
- the pour spouts 212 may be provided as inlets to the mold for the sleeve component substrate 200 .
- the component substrate 200 may be flowed through the pour spouts 212 into the mold 202 in general.
- the sprues 214 and runners 216 may provide a network of channels for the sleeve component substrate 200 to flow through before flowing into the interior molding area 210 .
- the sprues 214 and runners 216 may distribute the sleeve component substrate 200 through the mold 202 , such that the sleeve component substrate 200 enters the interior molding area 210 relatively evenly and is allowed to solidify relatively evenly.
- the gates 204 provide access points through the outer shells 208 and/or the inner shells 206 for the sleeve component substrate 200 to flow into the interior molding area 210 .
- the sprues 214 and/or runners 216 may be in fluid communication with the gates 204 , such that the sleeve component substrate 200 flows from the sprues 214 and/or runners 216 through the gates 204 and generally into the interior molding area 210 .
- the present method may further include solidifying, such as curing, the sleeve component substrate 200 in the mold 202 to form the sleeve component assembly 104 .
- solidifying such as curing
- the sleeve component substrate 200 is flowed into the mold 202 , a portion of the substrate 200 may remain in the gates 204 rather than flow into the interior molding area 210 .
- the substrate 200 in the gates 204 may thus form the support features 110 of the sleeve component assembly 104 .
- the sleeve component assembly 104 may comprise the sleeve component and at least one support feature 110 , and the support feature 110 may be integral with the sleeve component and disposed in the at least one gate 204 .
- the present method may further include removing the sleeve component assembly 104 from the mold 202 .
- the various shells 206 , 208 , gates 204 , and other components of the mold 202 may be removed from the sleeve component assembly 104 using any suitable methods or devices.
- the present method may further include adjusting the heights 114 of the support features 110 .
- the heights 114 may be adjusted such that the support features 110 are configured to provide vibratory support in the turbine system 10 .
- the heights 114 may be adjusted such that the support features 110 are configured to contact and provide vibratory support to adjacent sleeve components.
- the support features 110 may be measured and trimmed, cut, sanded, or otherwise reduced as required so that the support features 110 contact and interact as desired with the adjacent sleeve components.
- the present method may include the step of, for example, designing the gates 204 such that the support features 110 provide a desired vibratory characteristic.
- the support features 110 may be configured to provide a desired vibratory characteristic.
- each support feature 110 may be formed with, for example, a desired shape, size, and/or height 114 , and/or the location of the support feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired vibratory characteristic.
- the gates 204 may be sized and positioned such that the support features 110 formed therein generally have these configurations.
- the present method may include the step of, for example, designing the gates 204 such that the support features 110 provide a desired heat transfer characteristic.
- the support features 110 may be configured to provide a desired heat transfer characteristic.
- each support feature 110 may be formed with, for example, a desired shape, size, and/or height 114 , and/or the location of the support feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired heat transfer characteristic.
- the gates 204 may be sized and positioned such that the support features 110 formed therein generally have these configurations.
- the present method may include the step of, for example, modifying the support features 110 such that the support features 110 provide a desired vibratory characteristic.
- the support features 110 may not have the appropriate configurations to provide a desired vibratory characteristic.
- various characteristics of various support features 110 such as the shape, size, and/or height 114 may be modified, and/or various support features 110 may be eliminated, and/or the various support features 110 may be otherwise modified, to provide the desired vibratory characteristic.
- various portions of the support features 110 may be removed, or the support features 110 may be reshaped, or the support features 110 may be otherwise modified as desired.
- the present method may include the step of, for example, modifying the support features 110 such that the support features 110 provide a desired heat transfer characteristic.
- the support features 110 may not have the appropriate configurations to provide a desired heat transfer characteristic.
- various characteristics of various support features 110 such as the shape, size, and/or height 114 may be modified, and/or various support features 110 may be eliminated, and/or the various support features 110 may be otherwise modified, to provide the desired heat transfer characteristic.
- various portions of the support features 110 may be removed, or the support features 110 may be reshaped, or the support features 110 may be otherwise modified as desired.
- the present disclosure thus advantageously utilizes the gates 204 of the mold 202 for forming the sleeve component to additionally form the support features 110 .
- the forming process which may in exemplary embodiments be a casting process, it is generally advantageous to have a multitude of gates 204 to provide a variety of access points for a substrate to enter the mold. More gates 204 allow for better, more uniform solidifying of the substrate into the desired component. However, previously, the addition of gates 204 had to be weighed against the cost of removing the resulting protrusions from the desired component. The present disclosure reduces this cost by requiring that the resulting protrusions, rather than being removed, be configured to provide vibratory support in the combustor 14 . Thus, more gates 204 may be advantageously utilized during the forming process according to the present disclosure. More gates 204 will provide for higher quality sleeve component assemblies 104 with more support features 110 , which may provide improved vibratory support.
Abstract
A sleeve component assembly for a combustor, and a method for forming the sleeve component assembly for the combustor, are disclosed. The sleeve component assembly includes a sleeve component, the sleeve component comprising one of an inner sleeve component or an outer sleeve component. The sleeve component assembly further includes at least one support feature extending from the sleeve component, the at least one support feature configured to contact and provide vibratory support to an adjacent sleeve component. The at least one support feature is integral with the sleeve component.
Description
- The subject matter disclosed herein relates generally to turbine systems, and more particularly to apparatus for reducing vibrations in combustors of turbine systems and methods for forming the apparatus.
- Turbine systems are widely utilized in fields such as power generation. For example, a conventional gas turbine system includes a compressor, a combustor, and a turbine. During operation of the turbine system, various components in the system may be subjected to high temperature flows, which can cause the components to fail. Since higher temperature flows generally result in increased performance, efficiency, and power output of the gas turbine system, the components that are subjected to high temperature flows must be cooled to allow the gas turbine system to operate at increased temperatures.
- During operation of a turbine system, many components of the system may be subject to significant structural vibrations. These vibrations can stress the components and eventually cause the components to fail. For example, in gas turbine systems, the combustor impingement sleeves are particularly vulnerable to structural vibrations.
- Previous attempts to reduce structural vibrations in impingement sleeves have involved thickening the walls of the impingement sleeves or adding ribs or gussets to the impingement sleeves. Thickening the walls, however, may make the impingement sleeves undesirably heavy, and may further make the impingement sleeves more expensive and difficult to manufacture. The addition of ribs or gussets may also make the impingement sleeves more expensive and difficult to manufacture, and may potentially add failure points to the system.
- Thus, an improved apparatus for reducing structural vibrations in a combustor of a turbine system, and a method for forming the apparatus, would be desired in the art. For example, a method and apparatus that provide support features that are integral with an existing combustor component would be advantageous. Further, a method and apparatus that provide support features that may be configured for optimal vibratory and heat transfer capabilities would be desired.
- Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- In one embodiment, a sleeve component assembly for a combustor is disclosed. The sleeve component assembly includes a sleeve component, the sleeve component comprising one of an inner sleeve component or an outer sleeve component. The sleeve component assembly further includes at least one support feature extending from the sleeve component, the at least one support feature configured to contact and provide vibratory support to an adjacent sleeve component. The at least one support feature is integral with the sleeve component.
- In another embodiment, a method for forming a sleeve component assembly for a combustor is disclosed. The method includes flowing a sleeve component substrate into a mold through at least one gate, the mold comprising the at least one gate and at least one shell configured to form a sleeve component therein, the sleeve component comprising one of an inner sleeve component or an outer sleeve component. The method further includes solidifying the sleeve component substrate in the mold to form the sleeve component assembly, the sleeve component assembly comprising the sleeve component and at least one support feature, the at least one support feature integral with the sleeve component and disposed in the at least one gate. The method further includes removing the sleeve component assembly from the mold, and adjusting a height of the at least one support feature such that the at least one support feature is configured to contact and provide vibratory support to an adjacent sleeve component.
- These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
- A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:
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FIG. 1 is a schematic illustration of a gas turbine system; -
FIG. 2 is a side cutaway view of one embodiment of various components of the gas turbine system of the present disclosure; -
FIG. 3 is a side view of one embodiment of a sleeve component assembly of the present disclosure; and -
FIG. 4 is a cross-sectional view of one embodiment of a mold for a sleeve component assembly of the present disclosure. - Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.
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FIG. 1 is a schematic diagram of agas turbine system 10. Thesystem 10 may include acompressor 12, acombustor 14, and aturbine 16. Further, thesystem 10 may include a plurality ofcompressors 12,combustors 14, andturbines 16. Thecompressors 12 andturbines 16 may be coupled by ashaft 18. Theshaft 18 may be a single shaft or a plurality of shaft segments coupled together to formshaft 18. - As illustrated in
FIG. 2 , thecombustor 14 is generally fluidly coupled to thecompressor 12 and theturbine 16. Thecompressor 12 may include adiffuser 20 and adischarge plenum 22 that are coupled to each other in fluid communication, so as to facilitate the channeling of a workingfluid 24 to thecombustor 14. For example, after being compressed in thecompressor 12, workingfluid 24 may flow through thediffuser 20 and be provided to thedischarge plenum 22. The workingfluid 24 may then flow from thedischarge plenum 22 to thecombustor 14, wherein the workingfluid 24 is combined with fuel fromfuel nozzles 26. After mixing with the fuel, the workingfluid 24/fuel mixture may be ignited withincombustion chamber 28 to createhot gas flow 30. Thehot gas flow 30 may be channeled through thecombustion chamber 28 along ahot gas path 32 into atransition piece cavity 34 and through aturbine nozzle 36 to theturbine 16. - The
combustor 14 may comprise a hollow annular wall configured to facilitate workingfluid 24. For example, thecombustor 14 may include acombustor liner 40 disposed within aflow sleeve 42. The arrangement of thecombustor liner 40 and theflow sleeve 42, as shown inFIG. 2 , is generally concentric and may define an annular passage orflow path 44 therebetween. In certain embodiments, theflow sleeve 42 and thecombustor liner 40 may define a first or upstream hollow annular wall of thecombustor 14. Theflow sleeve 42 may include a plurality ofinlets 46, which provide a flow path for at least a portion of the workingfluid 24 from thecompressor 12 through thedischarge plenum 22 into theflow path 44. In other words, theflow sleeve 42 may be perforated with a pattern of openings to define a perforated annular wall. The interior of thecombustor liner 40 may define the substantially cylindrical orannular combustion chamber 28 and at least partially define thehot gas path 32 through whichhot gas flow 30 may be directed. - Downstream from the
combustor liner 40 and theflow sleeve 42, animpingement sleeve 50 may be coupled to theflow sleeve 42. Theflow sleeve 42 may include amounting flange 52 configured to receive amounting member 54 of theimpingement sleeve 50. Atransition piece 56 may be disposed within theimpingement sleeve 50, such that theimpingement sleeve 50 surrounds thetransition piece 56. A concentric arrangement of theimpingement sleeve 50 and thetransition piece 56 may define an annular passage orflow path 58 therebetween. Theimpingement sleeve 50 may include a plurality ofinlets 60, which may provide a flow path for at least a portion of the workingfluid 24 from thecompressor 12 through thedischarge plenum 22 into theflow path 58. In other words, theimpingement sleeve 50 may be perforated with a pattern of openings to define a perforated annular wall.Interior cavity 34 of thetransition piece 56 may further definehot gas path 32 through which hot gas flow 30 from thecombustion chamber 28 may be directed into theturbine 16. - As shown, the
flow path 58 is fluidly coupled to theflow path 44. Thus, together, theflow paths fluid 24 from thecompressor 12 and thedischarge plenum 22 to thefuel nozzles 26, while also cooling thecombustor 14. - As discussed above, the
turbine system 10, in operation, mayintake working fluid 24 and provide the workingfluid 24 to thecompressor 12. Thecompressor 12, which is driven by theshaft 18, may rotate and compress the workingfluid 24. The compressed workingfluid 24 may then be discharged into thediffuser 20. The majority of the compressed workingfluid 24 may then be discharged from thecompressor 12, by way of thediffuser 20, through thedischarge plenum 22 and into thecombustor 14. Additionally, a small portion (not shown) of the compressed workingfluid 24 may be channeled downstream for cooling of other components of theturbine engine 10. - A portion of the compressed working
fluid 24 within thedischarge plenum 22 may enter theflow path 58 by way of theinlets 60. The workingfluid 24 in theflow path 58 may then be channeled upstream throughflow path 44, such that the workingfluid 24 is directed over thecombustor liner 34. Thus, a flow path is defined in the upstream direction by flow path 58 (formed byimpingement sleeve 50 and transition piece 56) and flow path 44 (formed byflow sleeve 42 and combustor liner 40). Accordingly, flowpath 44 may receive workingfluid 24 from both flowpath 58 andinlets 46. The workingfluid 24 through theflow path 44 may then be channeled upstream towards thefuel nozzles 26, as discussed above. - Thus, the
combustor liner 40,transition piece 56,flow sleeve 42, andimpingement sleeve 50 are all sleeve components for thecombustor 14. As shown inFIG. 2 , both thecombustor liner 40 and thetransition piece 56 areinner sleeve components 100 configured to at least partially provide a flow boundary in thecombustor 14. In general, aninner sleeve component 100 according to the present disclosure may be configured to provide a flow boundary by providing a physical boundary between various flows or directions of flow in thecombustor 14. In some embodiments, the various flows or directions of flow may have different temperatures, and theinner sleeve component 100 may thus further provide a temperature boundary in thecombustor 14. - For example, the
combustor liner 40 and thetransition piece 56 provide a flow boundary between the flow of workingfluid 24 and thehot gas flow 30, as discussed above. Further, the workingfluid 24 is generally cooler than thehot gas flow 30, and is used to cool thecombustor liner 40 and thetransition piece 56. Thus, thecombustor liner 40 andtransition piece 56 further provide a temperature boundary. - Further, as shown in
FIG. 2 , both theflow sleeve 42 andimpingement sleeve 50 areouter sleeve components 102. In general, anouter sleeve component 102 is a component of thecombustor 14 is disposed adjacent aninner sleeve component 100. Theouter sleeve component 102 may act as an outer sleeve or casing for theinner sleeve component 100, and may provide an outer boundary for flows flowing past theinner sleeve component 100. For example, theflow sleeve 42 andimpingement sleeve 50 areouter sleeve components 102 for thecombustor liner 40 and thetransition piece 56, respectively. - During operation of the turbine system, the
outer sleeve component 102 according to the present disclosure may vibrate undesirably. Thus, devices and apparatus are needed to provide vibratory support to theouter sleeve component 102 in order to reduce or eliminate the vibration of theouter sleeve component 102. Thus, the present disclosure is further directed to asleeve component assembly 104 for theturbine system 10. - As shown in
FIGS. 2 and 3 , thesleeve component assembly 104 may include a sleeve component. The sleeve component may in exemplary embodiments be aninner sleeve component 100, or alternatively may be anouter sleeve component 102. For example, in exemplary embodiments, as discussed above, the sleeve component may be atransition piece 56. - The
sleeve component assembly 104 further includes at least onesupport feature 110. In exemplary embodiments, thesleeve component assembly 104 includes a plurality of support features 110. Eachsupport feature 110 extends from the sleeve component, such as theinner sleeve component 100 orouter sleeve component 102. For example, eachsupport feature 110 may extend from asurface 112 of the sleeve component that faces an adjacent sleeve component, which may be the other of theinner sleeve component 100 or theouter sleeve component 102. In exemplary embodiments wherein thesleeve component 100 is atransition piece 56, the support features 110 may extend from thesurface 112 of thetransition piece 56 facing theadjacent impingement sleeve 50. - The support features 110 may be configured to contact and provide vibratory support to the adjacent sleeve component. In some embodiments, for example, the support features 110 may be configured to generally continuously contact and provide vibratory support to the adjacent sleeve component. The support features 110 may thus interact with the adjacent sleeve component to support the component and reduce the structural vibrations of the component.
- For example, the support features 110 may each define a
height 114. As shown inFIG. 3 , theheight 114 of eachsupport feature 110 may allow thesupport feature 110 to contact and interact with the adjacent sleeve component, such as the adjacentouter sleeve component 102, to provide the required vibratory support. As discussed below, theheight 114 of eachsupport feature 110 may be adjusted as desired to ensure that thesupport feature 110 properly supports the adjacent sleeve component. - In some embodiments, the
height 114 may be adjusted such that the support features 110 generally continuously contact and provide vibratory support to the adjacent sleeve component. In these embodiments, theheight 114 may be such that when theturbine system 10 is non-operational, the adjacent sleeve component and the support features 110 are in contact. It should be understood, however, that during operation, vibrations may cause the generally continuously contacting support features 110 and adjacent sleeve component to occasionally separate, and that this vibrational movement of the support features 110 and adjacent sleeve component relative to one another is within the scope and spirit of the generally continuously contacting support features 110 and adjacent sleeve component. - In other embodiments, the
height 114 may be adjusted such that the support features 110 contact and provide vibratory support to the adjacent sleeve component during operation of thesystem 10. In these embodiments, theheight 114 may be such that when theturbine system 10 is non-operational, the adjacent sleeve component and the support features 110 are not in contact. During operation, vibrations may cause the generally continuously contacting support features 110 and adjacent sleeve component to occasionally contact, and the support features 110 may thus contact and provide vibratory support to the adjacent sleeve component. - Each
support feature 110 according to the present disclosure is integral with the sleeve component, such as with theinner sleeve component 100 orouter sleeve component 102. Thus, the sleeve component and the support features 110 extending therefrom may be formed from the same materials, and may be formed together as a singular unit. The sleeve component and the support features 110 may in exemplary embodiments be formed from a nickel or cobalt based alloy or super alloy. Alternatively, the sleeve component and the support features 110 may be formed from any materials suitable for use in acombustor 14. - Further, in exemplary embodiments, the support features 110 may be formed during casting of the sleeve component. For example, in some embodiments, the mold shells for casting the
sleeve component assembly 104 therein, as discussed below, may be designed and configured to form asleeve component assembly 104 including the sleeve component and at least onesupport feature 110. In other exemplary embodiments, as discussed below, the gates utilized during casting to flow a sleeve component substrate therethrough into the mold shells may form the support features 110. The support features 110 may be formed by the gates during casting of the sleeve component. Thesleeve component assembly 104 may thus be formed as an integral unit during casting. - In exemplary embodiments, each
support feature 110 may be configured to provide a desired vibratory characteristic. For example, eachsupport feature 110 may be individually tailored to impart a desired vibratory characteristic onto the adjacent sleeve component, such as the adjacentouter sleeve component 102, that thesupport feature 110 is providing vibratory support to. Eachsupport feature 110 may be formed with a desired shape, size, and/orheight 114, and/or the location of thesupport feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired vibratory characteristic. In exemplary embodiments, the desired vibratory characteristic may be the natural frequency of the adjacent sleeve component, such as the adjacentouter sleeve component 102. Eachsupport feature 110 may be configured to raise or lower the natural frequency of the adjacent sleeve component or to cause the adjacent sleeve component to have a certain desired natural frequency. For example, theheight 114 of the support features 110 may be raised to raise the natural frequency of the adjacent sleeve component or lowered to lower the natural frequency of the adjacent sleeve component. - It should be understood, however, that the present disclosure is not limited to adjusting the above characteristics of the support features 110 to adjust the natural frequency of the adjacent sleeve component. Rather, the adjustment of any suitable characteristics of the support features 110 to adjust any suitable vibratory characteristics of the adjacent sleeve component are within the scope and spirit of the present disclosure.
- In exemplary embodiments, each
support feature 110 may be configured to provide a desired heat transfer characteristic. As discussed above, the sleeve component, such as in exemplary embodiments theinner sleeve component 102, may provide a temperature boundary between, for example, a relatively hotter flow and a relatively cooler flow. In embodiments wherein the sleeve component is atransition piece 56, for example, the sleeve component may provide a temperature boundary between ahot gas flow 30 and a workingfluid 24. The support features 110 may thus be utilized to provide desired heat transfer characteristics for the sleeve component. Eachsupport feature 110 may be formed with a desired shape, size, and/orheight 114, and/or the location of thesupport feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired heat transfer characteristic. For example, it may be desirable that the heat exchange through the sleeve component is relatively uniform. Thus, various support features 110 may be formed as relatively thick support features 110, and may thus act as insulators to heat cold spots on the sleeve component, while other support features 110 may be formed as relatively thin support features 110, and may thus act as fins to cool hot spots on the sleeve component. The support features 110 may thus assist in providing a relatively uniform heat exchange through the sleeve component. - It should be understood, however, that the present disclosure is not limited to adjusting the above characteristics of the support features 110 to provide uniform heat exchange through the sleeve component. Rather, the adjustment of any suitable characteristics of the support features 110 to adjust any suitable heat transfer characteristic of the
sleeve component assembly 104 or adjacent sleeve component are within the scope and spirit of the present disclosure. - The present disclosure is further directed to a method for forming a
sleeve component assembly 104 for acombustor 14. Thesleeve component assembly 104, as discussed above, includes a sleeve component, such as aninner sleeve component 100 or anouter sleeve component 102, and at least onesupport feature 110 or a plurality of support features 110. Further, the sleeve component in exemplary embodiments is atransition piece 56. - As shown in
FIG. 4 , the method includes, for example, flowing asleeve component substrate 200 into amold 202 through at least onegate 204, or through a plurality ofgates 204. Themold 202 may comprise thegates 204 and at least one shell configured to form thesleeve component 100. For example, in some embodiments as shown inFIG. 4 , themold 202 may include at least oneinner shell 206, or a plurality ofinner shells 206, and at least oneouter shell 208, or a plurality ofouter shells 208. The inner andouter shells interior molding area 210 therein for thesleeve component 100. Thegates 204 may provide access points through theouter shells 208 and/or theinner shells 206 for thesleeve component substrate 200 to flow into theinterior molding area 210. - The
mold 202 in some embodiments may further include a pourspout 212 or a plurality of pourspouts 212, asprue 214 or a plurality ofsprues 214, and arunner 216 or a plurality ofrunners 216. The pour spouts 212 may be provided as inlets to the mold for thesleeve component substrate 200. Thus, thecomponent substrate 200 may be flowed through the pourspouts 212 into themold 202 in general. Thesprues 214 andrunners 216 may provide a network of channels for thesleeve component substrate 200 to flow through before flowing into theinterior molding area 210. Thus, thesprues 214 andrunners 216 may distribute thesleeve component substrate 200 through themold 202, such that thesleeve component substrate 200 enters theinterior molding area 210 relatively evenly and is allowed to solidify relatively evenly. As discussed above, thegates 204 provide access points through theouter shells 208 and/or theinner shells 206 for thesleeve component substrate 200 to flow into theinterior molding area 210. Thus, thesprues 214 and/orrunners 216 may be in fluid communication with thegates 204, such that thesleeve component substrate 200 flows from thesprues 214 and/orrunners 216 through thegates 204 and generally into theinterior molding area 210. - The present method may further include solidifying, such as curing, the
sleeve component substrate 200 in themold 202 to form thesleeve component assembly 104. When thesleeve component substrate 200 is flowed into themold 202, a portion of thesubstrate 200 may remain in thegates 204 rather than flow into theinterior molding area 210. When thesleeve component substrate 200 solidifies, thesubstrate 200 in thegates 204 may thus form the support features 110 of thesleeve component assembly 104. Thus, thesleeve component assembly 104 may comprise the sleeve component and at least onesupport feature 110, and thesupport feature 110 may be integral with the sleeve component and disposed in the at least onegate 204. - The present method may further include removing the
sleeve component assembly 104 from themold 202. For example, thevarious shells gates 204, and other components of themold 202 may be removed from thesleeve component assembly 104 using any suitable methods or devices. - The present method may further include adjusting the
heights 114 of the support features 110. Theheights 114 may be adjusted such that the support features 110 are configured to provide vibratory support in theturbine system 10. For example, theheights 114 may be adjusted such that the support features 110 are configured to contact and provide vibratory support to adjacent sleeve components. To adjust theheights 114, the support features 110 may be measured and trimmed, cut, sanded, or otherwise reduced as required so that the support features 110 contact and interact as desired with the adjacent sleeve components. - In some embodiments, the present method may include the step of, for example, designing the
gates 204 such that the support features 110 provide a desired vibratory characteristic. For example, as discussed above, the support features 110 may be configured to provide a desired vibratory characteristic. Thus, eachsupport feature 110 may be formed with, for example, a desired shape, size, and/orheight 114, and/or the location of thesupport feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired vibratory characteristic. To form the support features 110 with these configurations in order to provide the desired vibratory characteristic, thegates 204 may be sized and positioned such that the support features 110 formed therein generally have these configurations. - In some embodiments, the present method may include the step of, for example, designing the
gates 204 such that the support features 110 provide a desired heat transfer characteristic. For example, as discussed above, the support features 110 may be configured to provide a desired heat transfer characteristic. Thus, eachsupport feature 110 may be formed with, for example, a desired shape, size, and/orheight 114, and/or the location of thesupport feature 110 may be individually tailored, and/or the spacing between various support features 110 may be tailored, to provide the desired heat transfer characteristic. To form the support features 110 with these configurations in order to provide a desired heat transfer characteristic, thegates 204 may be sized and positioned such that the support features 110 formed therein generally have these configurations. - In some embodiments, the present method may include the step of, for example, modifying the support features 110 such that the support features 110 provide a desired vibratory characteristic. For example, after forming of the
sleeve component assembly 104, the support features 110 may not have the appropriate configurations to provide a desired vibratory characteristic. Thus, various characteristics of various support features 110 such as the shape, size, and/orheight 114 may be modified, and/or various support features 110 may be eliminated, and/or the various support features 110 may be otherwise modified, to provide the desired vibratory characteristic. To modify the support features 110, various portions of the support features 110 may be removed, or the support features 110 may be reshaped, or the support features 110 may be otherwise modified as desired. - In some embodiments, the present method may include the step of, for example, modifying the support features 110 such that the support features 110 provide a desired heat transfer characteristic. For example, after forming of the
sleeve component assembly 104, the support features 110 may not have the appropriate configurations to provide a desired heat transfer characteristic. Thus, various characteristics of various support features 110 such as the shape, size, and/orheight 114 may be modified, and/or various support features 110 may be eliminated, and/or the various support features 110 may be otherwise modified, to provide the desired heat transfer characteristic. To modify the support features 110, various portions of the support features 110 may be removed, or the support features 110 may be reshaped, or the support features 110 may be otherwise modified as desired. - In exemplary embodiments, the present disclosure thus advantageously utilizes the
gates 204 of themold 202 for forming the sleeve component to additionally form the support features 110. During the forming process, which may in exemplary embodiments be a casting process, it is generally advantageous to have a multitude ofgates 204 to provide a variety of access points for a substrate to enter the mold.More gates 204 allow for better, more uniform solidifying of the substrate into the desired component. However, previously, the addition ofgates 204 had to be weighed against the cost of removing the resulting protrusions from the desired component. The present disclosure reduces this cost by requiring that the resulting protrusions, rather than being removed, be configured to provide vibratory support in thecombustor 14. Thus,more gates 204 may be advantageously utilized during the forming process according to the present disclosure.More gates 204 will provide for higher qualitysleeve component assemblies 104 with more support features 110, which may provide improved vibratory support. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (20)
1. A sleeve component assembly for a combustor, the sleeve component assembly comprising:
a sleeve component, the sleeve component comprising one of an inner sleeve component or an outer sleeve component; and,
at least one support feature extending from the sleeve component, the at least one support feature configured to contact and provide vibratory support to an adjacent sleeve component,
wherein the at least one support feature is integral with the sleeve component.
2. The sleeve component assembly of claim 1 , wherein the at least one support feature is formed during casting of the sleeve component.
3. The sleeve component assembly of claim 1 , further comprising a plurality of support features.
4. The sleeve component assembly of claim 1 , wherein the sleeve component is an inner sleeve component.
5. The sleeve component assembly of claim 1 , wherein the sleeve component is a transition piece.
6. The sleeve component assembly of claim 1 , wherein the at least one support feature is configured to generally continuously contact the adjacent sleeve component.
7. The sleeve component assembly of claim 1 , wherein the at least one support feature is configured to provide a desired heat transfer characteristic.
8. The sleeve component assembly of claim 1 , wherein the at least one support feature is configured to provide a desired vibratory characteristic.
9. A combustor for a turbine system, the combustor comprising:
an inner sleeve component;
an outer sleeve component disposed adjacent to the inner sleeve component; and,
at least one support feature extending from one of the inner sleeve component or the outer sleeve component, the at least one support feature configured to contact and provide vibratory support to the other of the inner sleeve component or the outer sleeve component,
wherein the at least one support feature is integral with the one of the inner sleeve component or the outer sleeve component.
10. The combustor of claim 9 , wherein the at least one support feature is formed during casting of the one of the inner sleeve component or the outer sleeve component.
11. The combustor of claim 9 , further comprising a plurality of support features.
12. The combustor of claim 9 , wherein the at least one support feature extends from the inner sleeve component.
13. The combustor of claim 9 , wherein the inner sleeve component is a transition piece and the outer sleeve component is an impingement sleeve.
14. A method for forming a sleeve component assembly for a combustor, the method comprising:
flowing a sleeve component substrate into a mold through at least one gate, the mold comprising the at least one gate and at least one shell configured to form a sleeve component therein, the sleeve component comprising one of an inner sleeve component or an outer sleeve component;
solidifying the sleeve component substrate in the mold to form the sleeve component assembly, the sleeve component assembly comprising the sleeve component and at least one support feature, the at least one support feature integral with the sleeve component and disposed in the at least one gate;
removing the sleeve component assembly from the mold; and,
adjusting a height of the at least one support feature such that the at least one support feature is configured to contact and provide vibratory support to an adjacent sleeve component.
15. The method of claim 14 , wherein the at least one support feature is a plurality of support features.
16. The method of claim 14 , wherein the sleeve component is a transition piece.
17. The method of claim 14 , further comprising designing the at least one gate such that the at least one support feature provides a desired heat transfer characteristic.
18. The method of claim 14 , further comprising designing the at least one gate such that the at least one support feature provides a desired vibratory characteristic.
19. The method of claim 14 , further comprising modifying the at least one support feature such that the at least one support feature provides a desired heat transfer characteristic.
20. The method of claim 14 , further comprising modifying the at least one support feature such that the at least one support feature provides a desired vibratory characteristic.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/006,518 US20120180492A1 (en) | 2011-01-14 | 2011-01-14 | Apparatus for vibration support in combustors and method for forming apparatus |
JP2012002795A JP2012149877A (en) | 2011-01-14 | 2012-01-11 | Apparatus for vibration support in combustor, and method for forming the apparatus |
DE102012100268A DE102012100268A1 (en) | 2011-01-14 | 2012-01-12 | Device for vibration support in combustion chambers and method for producing a device |
CN2012100205712A CN102607028A (en) | 2011-01-14 | 2012-01-13 | Apparatus for vibration support in combustors and method for forming apparatus |
FR1250356A FR2970549A1 (en) | 2011-01-14 | 2012-01-13 | SUPPORT DEVICE FOR REDUCING VIBRATIONS IN COMBUSTION DEVICES AND METHOD OF MAKING SAME |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US13/006,518 US20120180492A1 (en) | 2011-01-14 | 2011-01-14 | Apparatus for vibration support in combustors and method for forming apparatus |
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Publication Number | Publication Date |
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US20120180492A1 true US20120180492A1 (en) | 2012-07-19 |
Family
ID=46397777
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US13/006,518 Abandoned US20120180492A1 (en) | 2011-01-14 | 2011-01-14 | Apparatus for vibration support in combustors and method for forming apparatus |
Country Status (5)
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US (1) | US20120180492A1 (en) |
JP (1) | JP2012149877A (en) |
CN (1) | CN102607028A (en) |
DE (1) | DE102012100268A1 (en) |
FR (1) | FR2970549A1 (en) |
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CN103231026B (en) * | 2013-04-28 | 2015-06-10 | 济南誉腾工贸有限公司 | Improved intercooler casting mold |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090293488A1 (en) * | 2003-10-23 | 2009-12-03 | United Technologies Corporation | Combustor |
US20100223931A1 (en) * | 2009-03-04 | 2010-09-09 | General Electric Company | Pattern cooled combustor liner |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9106085D0 (en) * | 1991-03-22 | 1991-05-08 | Rolls Royce Plc | Gas turbine engine combustor |
FR2714152B1 (en) * | 1993-12-22 | 1996-01-19 | Snecma | Device for fixing a thermal protection tile in a combustion chamber. |
FR2752916B1 (en) * | 1996-09-05 | 1998-10-02 | Snecma | THERMAL PROTECTIVE SHIRT FOR TURBOREACTOR COMBUSTION CHAMBER |
GB9926257D0 (en) * | 1999-11-06 | 2000-01-12 | Rolls Royce Plc | Wall elements for gas turbine engine combustors |
-
2011
- 2011-01-14 US US13/006,518 patent/US20120180492A1/en not_active Abandoned
-
2012
- 2012-01-11 JP JP2012002795A patent/JP2012149877A/en active Pending
- 2012-01-12 DE DE102012100268A patent/DE102012100268A1/en not_active Withdrawn
- 2012-01-13 FR FR1250356A patent/FR2970549A1/en not_active Withdrawn
- 2012-01-13 CN CN2012100205712A patent/CN102607028A/en active Pending
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090293488A1 (en) * | 2003-10-23 | 2009-12-03 | United Technologies Corporation | Combustor |
US20100223931A1 (en) * | 2009-03-04 | 2010-09-09 | General Electric Company | Pattern cooled combustor liner |
Also Published As
Publication number | Publication date |
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CN102607028A (en) | 2012-07-25 |
FR2970549A1 (en) | 2012-07-20 |
JP2012149877A (en) | 2012-08-09 |
DE102012100268A1 (en) | 2012-07-19 |
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