EP2487418A2 - Brennkammer - Google Patents

Brennkammer Download PDF

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Publication number
EP2487418A2
EP2487418A2 EP12155001A EP12155001A EP2487418A2 EP 2487418 A2 EP2487418 A2 EP 2487418A2 EP 12155001 A EP12155001 A EP 12155001A EP 12155001 A EP12155001 A EP 12155001A EP 2487418 A2 EP2487418 A2 EP 2487418A2
Authority
EP
European Patent Office
Prior art keywords
liner
ridge
combustor
groove
approximately
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12155001A
Other languages
English (en)
French (fr)
Inventor
Prabhu Kumar Ippadi Siddagangaiah
Kodukulla Venkat Sridhar
Karthick Kaleeswaran
Nitin Subramanya Sarja
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2487418A2 publication Critical patent/EP2487418A2/de
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23R3/002—Wall structures

Definitions

  • the present invention generally involves a combustor.
  • various embodiments of the present invention include a combustor having a liner with enhanced durability.
  • Combustors are known in the art for igniting fuel with air to produce combustion gases having high temperature and pressure.
  • gas turbine systems typically include multiple combustors that mix a compressed working fluid from a compressor with fuel and ignite the mixture to produce high temperature and pressure combustion gases. The combustion gases then flow to a turbine where they expand to produce work.
  • Each combustor typically includes a liner that surrounds the combustion chamber to contain the working fluid and fuel during combustion.
  • the temperatures associated with the combustion often exceed 3500°F, and the liner typically has a maximum operating temperature on the order of approximately 1500°F. Therefore, various systems and methods have been developed to cool the liner.
  • the working fluid may be directed over the external surface of the liner prior to flow into the combustion chamber to provide film or convective cooling to the liner.
  • the thickness of the liner may be increased or thermal barrier coatings may be applied to the inside of the liner to protect the liner from excessive temperatures.
  • the present invention resides in a combustor that includes a combustion chamber and a liner surrounding the combustion chamber. A ridge on top of the liner extends continuously around the liner.
  • the combustor may include a groove extending continuously around the liner adjacent to the ridge, wherein both of the ridge and the groove are either substantially flat or curved.
  • the liner may include one or more ridges and/or one or more grooves that extend around the liner in a spiral or parallel pattern.
  • the liner may include one or more radii and substantially flat segments that extend around the liner in a spiral or parallel pattern.
  • the combination of ridges, grooves, radii, and/or substantially flat segments have been designed to improve the liner's resistance to premature buckling, creep, or deformation that may be caused over time by dynamic pressure and load changes.
  • the various embodiments have been designed to enhance film or convective cooling of the outside of the liner without increasing manufacturing costs or difficulty.
  • Figure 1 shows a simplified cross-section of a combustor 10 according to one embodiment of the present invention.
  • the combustor 10 may include one or more nozzles 12 radially arranged in a top cap 14.
  • a casing 16 may surround the combustor 10 to contain the air or compressed working fluid exiting the compressor (not shown).
  • An end cap 18 and a liner 20 generally surround a combustion chamber 22 downstream of the nozzles 12.
  • a flow sleeve 24 with flow holes 26 may surround the liner 20 to define an annular passage 28 between the flow sleeve 24 and the liner 20.
  • the compressed working fluid may pass through the flow holes 26 in the flow sleeve 24 to flow along the outside of the liner 20 to provide film or convective cooling to the liner 20.
  • the compressed working fluid then reverses direction to flow through the one or more nozzles 12 and into the combustion chamber 22 where it mixes with fuel and ignites to produce combustion gases having a high temperature and pressure.
  • Figures 2 and 3 show side plan views of the liner 20 according to first and second embodiments of the present invention.
  • a ridge 30 on top of the liner 20 extends continuously around the circumference of the liner 20 to strengthen the liner 20.
  • the ridge 30 may extend axially along a portion or the entire length of the liner 20, or a plurality of the ridges 30 may extend axially along some or all of the length of the liner 20.
  • the ridge 30 may form a continuous substantially parallel spiral around the liner 20.
  • the liner 20 may include a plurality of the ridges 30, with the ridges 30 forming substantially parallel circles or hoops around the circumference of the liner 20.
  • Figure 4 provides an enlarged view of a portion of the liner 20 shown in Figure 2 or 3 .
  • the ridge(s) 30 may be forged or cast with the liner 20 to facilitate ease of manufacturing, or the ridge(s) 30 may be added to the liner 20 by welding and subsequent machining, if desired.
  • the dimensions and spacing of the ridge(s) 30 may be selected according to various design considerations to optimize the strength, stiffness, and/or rigidity of the liner 20, as well as the cooling provided by the ridge(s) 30.
  • the height 32 and width 34 of the ridge(s) 30, as well as the distance 36 between adjacent ridge(s) 30 spiraling around or encircling the liner 20, may be selected based on the thickness 38 of the liner 20.
  • the height 32 and/or width 34 of the ridge(s) 30 may be approximately 0.3-1.4 times the thickness 38 of the liner 20, and the distance 36 between adjacent ridges 30 may be approximately 8-45 times the thickness 38 of the liner 20.
  • each ridge 30 may comprise a base 40 proximate to the liner 20 and a distal end 42.
  • the base 40 may include a radius 44 along at least a portion of the base 40.
  • the term "radius" includes any curved surface that reduces flow resistance across the outer surface of the liner 20.
  • the length of the radius 44 may be selected based on the thickness 38 of the liner 20. For example, the radius 44 may have a curved length 49 of approximately .15-1 times the thickness 38 of the liner.
  • the radius 44 may be forged or cast with the ridge(s) 30 during manufacture of the liner 20 or may be added separately, such as through lap welding and machining to produce a smooth, curved surface between the ridge(s) 30 and the liner 20.
  • the distal end 42 may also include a radius 46 and/or terminate at a point 48 along at least a portion of the distal end 42.
  • Figures 5 and 6 provide side plan views of the liner 20 according to third and fourth embodiments of the present invention.
  • the ridge 30 again extends continuously around the circumference of the liner 20; however, the ridge 30 is substantially wider than in the embodiments shown in Figures 2-4 .
  • the particular embodiments shown in Figures 5 and 6 further include a groove 50 that extends continuously around the liner 20 adjacent to the ridge 30.
  • a radius 52 between the ridge 30 and the groove 50 provides a smooth transition between the ridge 30 and the groove 50.
  • the ridge 30 and groove 50 may extend axially along a portion or the entire length of the liner 20, or a plurality of the ridges 30 and/or the grooves 50 may extend axially along some or all of the length of the liner 20. As shown in Figure 5 , the ridge 30 and groove 50 may form a continuous substantially parallel spiral around the liner 20. Alternately, as shown in the embodiment illustrated in Figure 6 , the liner 20 may include a plurality of the ridges 30 and grooves 50, with at least one groove 50 between adjacent ridges 30. In this manner, the ridges 30 and grooves 50 form substantially parallel circles or hoops around the circumference of the liner 20.
  • Figure 7 provides an enlarged view of a portion of the liner 20 shown in Figure 5 or 6 .
  • the ridge(s) 30, groove(s) 50, and radii 52 may be forged or cast with the liner 20 to facilitate ease of manufacturing, or the liner 20 may be pressed or stamped to form the ridge(s) 30, groove(s) 50, and radii 52, if desired.
  • the dimensions and spacing of the ridge(s) 30, groove(s) 50, and radii 52 may be selected according to various design considerations to optimize the strength, stiffness, and/or rigidity of the liner 20, as well as the cooling provided by the ridge(s) 30 and groove(s) 50.
  • the height 54 and width 56 of the ridge(s) 30 and/or the groove(s) 50 continuously spiraling around or encircling the liner 20 may be selected based on the thickness 38 of the liner 20.
  • the height 54 of the ridge(s) 30 and/or groove(s) 50 may be approximately 1.1-2.5 times the thickness 38 of the liner 20
  • the width 56 of the ridge(s) 30 and/or the groove(s) 50 may be approximately 8-45 times the thickness 38 of the liner 20 for liner thicknesses greater than approximately 0.09 inches and approximately 16-90 times the thickness 38 of the liner 20 for liner thicknesses less than approximately 0.09 inches.
  • the radius 52 may have a curved length 58 of approximately 0.5-2.5 times the thickness 38 of the liner 20.
  • the ridge(s) 30 and/or the groove(s) 50 may be substantially flat with the same height 54 and width 56, although such is not limitation of the present invention unless specifically recited in the claims.
  • Figures 8 and 9 provide side plan views of the liner 20 according to fifth and sixth embodiments of the present invention.
  • the ridge 30 again extends continuously around the circumference of the liner 20; however, the ridge 30 is curved with the convex surface facing outward.
  • the particular embodiments shown in Figures 8 and 9 further include a groove 50 that extends continuously around the liner 20 adjacent to the ridge 30. A smooth transition between the ridge 30 and the groove 50 produces a wavy surface on the outside of the liner 20.
  • the ridge 30 and groove 50 may extend axially along a portion or the entire length of the liner 20, or a plurality of the ridges 30 and/or the grooves 50 may extend axially along some or all of the length of the liner 20. As shown in Figure 8 , the ridge 30 and groove 50 may form a continuous substantially parallel spiral around the liner 20. Alternately, as shown in the embodiment illustrated in Figure 9 , the liner 20 may include a plurality of the ridges 30 and grooves 50, with at least one groove 50 between adjacent ridges 30. In this manner, the ridges 30 and grooves 50 form substantially parallel circles or hoops around the circumference of the liner 20.
  • Figure 10 provides an enlarged view of a portion of the liner 20 shown in Figure 8 or 9 .
  • the ridge(s) 30 and groove(s) 50 may be forged or cast with the liner 20 to facilitate ease of manufacturing, or the liner 20 may be pressed or stamped to form the ridge(s) 30 and groove(s) 50, if desired.
  • the dimensions and spacing of the ridge(s) 30 and groove(s) 50 may be selected according to various design considerations to optimize the strength, stiffness, and/or rigidity of the liner 20, as well as the cooling provided by the ridge(s) 30 and groove(s) 50.
  • the height 54 and width 56 of the ridge(s) 30 and/or the groove(s) 50 continuously spiraling around or encircling the liner 20 may be selected based on the thickness 38 of the liner 20.
  • the height 54 of the ridge(s) 30 and/or groove(s) 50 may be approximately 1.1-5 times the thickness 38 of the liner 20
  • the width 56 of the ridge(s) 30 and/or groove(s) 50 may be approximately 8-45 times the thickness 38 of the liner 20 for liner thicknesses greater than approximately 0.09 inches and approximately 16-90 times the thickness 38 of the liner 20 for liner thicknesses less than approximately 0.09 inches.
  • Figures 11 and 12 provide side plan views of the liner 20 according to seventh and eighth embodiments of the present invention.
  • Each particular embodiment shown in Figures 11 and 12 may include a corrugated surface 60 with a radius 62 and a substantially flat segment 64 adjacent to the radius 62.
  • the radius 62 and segment 64 extend continuously around the liner 20 to define an outer circumference of the liner 20.
  • the segment 64 has a first end 66 and a second end 68, and the outer circumference of the liner 20 at the first end 66 is greater than the outer circumference of the liner 20 at the second end 68 to provide the corrugated surface 60.
  • the direction of the corrugated surface 60 may vary according to particular embodiments. For example, in the embodiment shown in Figure 11 , the first end 66 is upstream from the second end 68, and in the embodiment shown in Figure 12 , the first and 66 is downstream from the second end 68.
  • the radius 62 and segment 64 may extend axially along a portion or the entire length of the liner 20, or a plurality of the radii 62 and/or the segments 64 may extend axially along some or all of the length of the liner 20. As shown in Figure 11 , the radius 62 and the segment 64 may form a continuous substantially parallel spiral around the liner 20. Alternately, as shown in the embodiment illustrated in Figure 12 , the liner 20 may include a plurality of the continuous radii 62 and segments 64, with at least one segment 64 between adjacent radii 62. In this manner, the radii 62 and segments 64 form substantially parallel circles or hoops around the circumference of the liner 20.
  • Figure 13 provides an enlarged view of a portion of the liner 20 shown in Figure 11 or 12 .
  • the radii 62 and segments 64 may be forged or cast with the liner 20 to facilitate ease of manufacturing, or the liner 20 may be pressed or stamped to form the radii 62 and segments 64, if desired.
  • the dimensions and spacing of the radii 62 and segments 64 may be selected according to various design considerations to optimize the strength, stiffness, and/or rigidity of the liner 20, as well as the cooling provided by the radii 62 and segments 64.
  • the slope 70 of the segments 64 may be approximately 2-8 degrees with respect to the axis of the liner 20.
  • the height 72 of the corrugated surface 60 and the distance 74 between adjacent radii 62 or adjacent segments 64 continuously spiraling around or encircling the liner 20 may be selected based on the thickness 38 of the liner 20.
  • the height 72 of the corrugated surface 60 may be approximately 1.1-3.0 times the thickness 38 of the liner 20.
  • the distance 74 between adjacent radii 62 or adjacent segments 64 may be approximately 8-45 times the thickness 38 of the liner 20 for liner thicknesses greater than approximately 0.09 inches and approximately 16-90 times the thickness 38 of the liner 20 for liner thicknesses less than approximately 0.09 inches.
  • the radii 62 may have a curved length 76 of approximately 0.5-2.5 times the thickness 38 of the liner 20.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12155001A 2011-02-14 2012-02-10 Brennkammer Withdrawn EP2487418A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/026,373 US20120208141A1 (en) 2011-02-14 2011-02-14 Combustor

Publications (1)

Publication Number Publication Date
EP2487418A2 true EP2487418A2 (de) 2012-08-15

Family

ID=45607042

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12155001A Withdrawn EP2487418A2 (de) 2011-02-14 2012-02-10 Brennkammer

Country Status (3)

Country Link
US (1) US20120208141A1 (de)
EP (1) EP2487418A2 (de)
CN (1) CN102635876A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015150098A1 (de) * 2014-03-31 2015-10-08 Siemens Aktiengesellschaft Silobrennkammer für eine gasturbine
CN110657454A (zh) * 2018-06-29 2020-01-07 中国航发商用航空发动机有限责任公司 一种冷却结构以及包括该冷却结构的燃烧室测量段

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US9511447B2 (en) * 2013-12-12 2016-12-06 General Electric Company Process for making a turbulator by additive manufacturing
JP6066065B2 (ja) * 2013-02-20 2017-01-25 三菱日立パワーシステムズ株式会社 伝熱装置を備えたガスタービン燃焼器
US9989255B2 (en) * 2014-07-25 2018-06-05 General Electric Company Liner assembly and method of turbulator fabrication
US20180001423A1 (en) * 2016-07-01 2018-01-04 General Electric Company Methods and thin walled reinforced structures for additive manufacturing
CN108317542B (zh) * 2018-01-03 2020-02-07 南方科技大学 航空发动机燃烧室的冷却结构及航空发动机燃烧室
US11306918B2 (en) * 2018-11-02 2022-04-19 Chromalloy Gas Turbine Llc Turbulator geometry for a combustion liner

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015150098A1 (de) * 2014-03-31 2015-10-08 Siemens Aktiengesellschaft Silobrennkammer für eine gasturbine
CN110657454A (zh) * 2018-06-29 2020-01-07 中国航发商用航空发动机有限责任公司 一种冷却结构以及包括该冷却结构的燃烧室测量段

Also Published As

Publication number Publication date
US20120208141A1 (en) 2012-08-16
CN102635876A (zh) 2012-08-15

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