IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0755560
(2004-01-09)
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발명자
/ 주소 |
- Kuhn, Terrel E.
- Freeman, William G.
- Maszk, Francis S.
- Freiberg, Douglas P.
- Struzek, Kenneth A.
- Kobold, Lawrence A.
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출원인 / 주소 |
- Honeywell International Inc.
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인용정보 |
피인용 횟수 :
15 인용 특허 :
17 |
초록
▼
An apparatus and method for controlling combustor liner carbon formation is provided. The apparatus includes a dome subassembly that is removeably affixed to a modular outer panel subassembly and a modular inner panel subassembly. Each panel subassembly includes panels that are removeably affixed to
An apparatus and method for controlling combustor liner carbon formation is provided. The apparatus includes a dome subassembly that is removeably affixed to a modular outer panel subassembly and a modular inner panel subassembly. Each panel subassembly includes panels that are removeably affixed to one another.
대표청구항
▼
1. A combustor liner, comprising:a dome subassembly; a modular inner panel subassembly interfacing said dome subassembly; a modular outer panel subassembly Interfacing said dome subassembly, said outer panel subassembly including: six rows of first effusion holes proximate to said dome subassembly a
1. A combustor liner, comprising:a dome subassembly; a modular inner panel subassembly interfacing said dome subassembly; a modular outer panel subassembly Interfacing said dome subassembly, said outer panel subassembly including: six rows of first effusion holes proximate to said dome subassembly and wherein at least one of said six rows includes 239 first effusion holes; and five rows of second effusion holes distal to said dome subassembly and wherein at least one of said five rows includes 281 second effusion holes. 2. The combustor liner of claim 1, wherein said modular inner panel subassembly is removeably affixed to the dome subassembly.3. The combustor liner of claim 1, wherein said modular outer panel subassembly is removeably affixed to the dome subassembly.4. The combustor liner of claim 2, wherein said modular inner panel subassembly includes a plurality of inner panels affixed to one another.5. The combustor liner of claim 3, wherein said modular outer panel subassembly includes a plurality of outer panels removeable affixed to one another.6. The combustor liner of claim 2, wherein said modular inner panel subassembly includes:four rows of third effusion holes on one inner panel; and five rows of fourth effusion holes on another inner panel. 7. The combustor liner of claim 3, wherein:said six rows are on one outer panel; and said five rows are on another outer panel. 8. A The combustor liner of claim 6, wherein each of four rows of the inner panel subassembly includes 181 third effusion holes.9. The combustor liner of claim 6, wherein each of five rows of the inner panel subassembly includes 206 fourth effusion holes.10. The combustor liner of claim 7, wherein each of six rows of the outer panel subassembly includes 239 first effusion holes.11. The combustor liner of claim 7, wherein each of five rows of the outer panel subassembly includes 281 second effusion holes.12. A combustor liner, comprising:a dome subassembly; a plurality of inner panels removeably affixed to said dome subassembly, said inner panels including: four rows of first effusion holes proximate to said dome subassembly and wherein at least one of said four rows includes 181 first effusion holes; and five rows of second effusion holes distal to said dome subassembly and wherein at least one of said five rows includes 206 second effusion holes; wherein at least three of said first and second effusion holes are arranged in an equilateral triangle configuration; a plurality of outer panels removeably affixed to said dome subassembly, said outer panels including: six rows of third effusion holes proximate to said dome subassembly and wherein at least one of said six rows includes 239 first effusion holes; and five rows of fourth effusion holes distal to said dome subassembly and wherein at least one of said five rows includes 281 second effusion holes; wherein at least three of said third and fourth effusion holes are arranged in an equilateral triangle configuration. 13. The combustor liner of claim 12, wherein at least one of said first and second effusion holes is characterized by an angle between about 15 and 25 degrees.14. The combustor liner of claim 12, wherein at least one of said first and second effusion holes is characterized by a diameter about {fraction (17/1000)} and {fraction (23/1000)} inches.15. The combustor liner of claim 12, wherein at least two of said first and second effusion holes are separated by about {fraction (200/1000)} inches.16. A turbine engine, comprising:a compressor section; a turbine section; a combustor liner intermediate said compressor and turbine sections, said combustor liner including: an modular outer panel subassembly having: a first group of six rows of first effusion holes, wherein each of said six rows has at least 239 first effusion holes therein and a second group of five rows of second effusion holes, wherein each of said five rows has at least 281 second effusion holes therein, wherein said first and second effusion holes are configured in a plurality of equilateral triangles. 17. The turbine engine of claim 16, wherein the combustor liner further comprises a modular inner panel subassembly.18. The turbine engine of claim 16, wherein the combustor liner further comprises a dome subassembly that interfaces said modular inner and modular outer panel subassemblies.19. The turbine engine of claim 16, wherein said inner panel subassembly includes a plurality of inner panels removeably affixed to one another by one of welding and brazing.20. The turbine engine of claim 16, wherein said outer panel subassembly includes a plurality of outer panels removeably affixed to one another by one of welding and brazing.21. The turbine engine of claim 16, wherein said modular inner panel subassembly interfaces with and is supported by the turbine section.22. The turbine engine of claim 16, wherein said modular outer panel subassembly interfaces with and is supported by an outer transition liner, which directs gas flow to the turbine section.23. The turbine engine of claim 16, wherein said modular outer panel subassembly includes an angled portion characterized by an angle between about 6.99 to 11.54 degrees.24. The turbine engine of claim 17, wherein said modular inner panel subassembly includes an angled portion characterized by an angle between about 4.85 to 9.41 degrees.25. A method for reducing carbon build-up in a combustor liner, comprising the steps of:providing in a modular outer panel subassembly eleven rows of effusion holes proximate to a dome subassembly, dividing said eleven rows into a first group of six rows and a second group of five rows, said six rows being closest to said dome subassembly wherein at least one of said six rows has at least 239 effusion holes therein, said five rows being farthest from said dome subassembly wherein at least one of said five rows has at least 281 effusion holes therein; moving air through said effusion holes of the outer panel subassembly; providing in a modular inner panel subassembly nine rows of effusion holes proximate to said dome subassembly, dividing said nine rows into a first group of four rows and a second group of five rows, said four rows being closest to said dome subassembly wherein at least one of said four rows has at least 181 effusion holes therein, said five rows being farthest from said dome subassembly wherein at least one of said five rows has at least 206 effusion holes therein; and moving air through said effusion holes of said inner panel subassembly. 26. The method of claim 25, wherein at least three of said effusion holes are arranged in an equilateral triangle configuration.27. The method of claim 25, wherein at least one of said effusion holes is characterized by an angle between about 15 and 25 degrees.28. The method of claim 25, wherein at least one of said effusion holes is characterized by a diameter of about {fraction (17/1000)} and {fraction (23/1000)} inches.29. The method of claim 25, wherein at least two of said effusion holes are separated by about {fraction (200/1000)} inches.
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