IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0282520
(2002-10-29)
|
발명자
/ 주소 |
- Stumpf, James Anthony
- Duncan, Beverly Stephenson
- Burrus, David Louis
- Cooper, Clayton Stuart
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
9 |
초록
▼
A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of the combustor, includes: a first portion positioned adjacent and connected to the dome plate, wherein the first liner portion extends downstream from and
A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of the combustor, includes: a first portion positioned adjacent and connected to the dome plate, wherein the first liner portion extends downstream from and substantially perpendicular to the dome plate; a second portion extending substantially perpendicular to the first liner portion and substantially parallel to the dome plate; a first arcuate portion having a predetermined radius located between the first and second liner portions; a third portion extending downstream and substantially perpendicular to the second liner portion; and, a second arcuate portion located between the second and third liner portions; wherein the first liner portion, the second liner portion, the first arcuate liner portion and a portion of the dome plate form the trapped vortex cavity.
대표청구항
▼
1. A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of said combustor, said liner comprising:(a) a first portion positioned adjacent and connected to said dome plate, wherein said first liner portion exten
1. A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of said combustor, said liner comprising:(a) a first portion positioned adjacent and connected to said dome plate, wherein said first liner portion extends downstream from and substantially perpendicular to said dome plate; (b) a second portion extending substantially perpendicular to said first liner portion and substantially parallel to said dome plate; (c) a first arcuate portion having a predetermined radius located between said first and second liner portions, wherein said predetermined radius of said first arcuate liner portion is at least approximately 3-5 times a thickness for said first and second liner portions; (d) a third portion extending downstream and substantially perpendicular to said second liner portion; and, (e) a second arcuate portion located between said second and third liner portions; wherein said first liner portion, said second liner portion, said first arcuate liner portion and a portion of said dome plate form said trapped vortex cavity.2. The liner of claim 1, wherein said liner is made of metal.3. The liner of claim 1, wherein said liner is made of Ceramic Matrix Composite material.4. The liner of claim 1, wherein said liner is an outer liner of said combustor.5. The liner of claim 1, wherein said liner is an inner liner of said combustor.6. The liner of claim 1, wherein said predetermined radius of said first arcuate liner portion is no greater than a length of said first line portion.7. The liner of claim 1, wherein said predetermined radius of said first arcuate liner portion is no greater than a height of said second liner portion.8. The liner of claim 1, wherein a centerpoint for said predetermined radius of said first arcuate liner portion is located along a radial plane positioned between said dome plate and a radial plane through said first liner portion.9. The liner of claim 1, wherein a centerpoint for said predetermined radius of said first arcuate liner portion is located along a radial plane positioned between said dome plate and approximately one-half a length of said first liner portion.10. The liner of claim 1, wherein said first arcuate liner portion includes a multihole cooling pattern formed therein.11. The liner of claim 1, wherein said second arcuate liner portion has a predetermined radius in a range of approximately 3-5 times said thickness for said first and second liner portions.12. The liner of claim 1, wherein said predetermined radius of said first arcuate portion is in a range of approximately 6-12 times said thickness for said first and second liner portions.13. A gas turbine engine combustor having at least one trapped vortex cavity located adjacent a combustion chamber thereof, comprising:(a) an annular dome plate positioned at an upstream end of said combustion chamber, said dome plate having a plurality of circumferentially spaced flow passages formed therein; (b) a device positioned between adjacent flow passages of said dome plate for injecting fuel in said flow passages and said trapped vortex cavity; (c) an outer liner connected at an upstream end to said dome plate; and (d) an inner liner connected at an upstream end to said dome plate, at least one of said outer and inner liners further comprising: (1) a first portion extending downstream from and substantially perpendicular to said dome plate; (2) a second portion extending substantially perpendicular to said first liner portion and substantially parallel to said dome plate; (3) a first arcuate portion having a predetermined radius located between said first and second liner portions, wherein said predetermined radius of said first arcuate liner portion is at least approximately 3-5 times a thickness for said first and second liner potions; (4) a third portion extending downstream and substantially perpendicular to said second liner portion; and, (5) a second arcuate portion located between said second and third liner portions; wherein said first liner portion, said second liner portion, said first arcuate liner portion and a portion of said dome plate form said trapped vortex cavity.14. The combustor of claim 13, said trapped vortex cavity being formed by a first portion of said outer liner, a second portion of said outer liner, a first arcuate portion of said outer liner, and a portion of said dome pate located radially outside said flow passages.15. The combustor of claim 13, said vortex cavity being formed by a first portion of said inner liner, a second portion of said inner liner, a first arcuate portion of said inner liner, and a portion of said dome plate located radially inside said flow passages.16. The combustor of claim 13, wherein said liner is made of metal.17. The combustor of claim 13, wherein said liner is made of Ceramic Matrix Composite material.18. The combustor of claim 17, wherein said inner and outer liners are connected to said dome plate so as to allow radial expansion of said dome plate.19. The combustor of claim 13, wherein said predetermined radius of said first arcuate liner portion is in a range of approximately 6-12 times said thickness of said first and second liner portions.20. A liner for a gas turbine engine combustor having a trapped vortex cavity formed therein, wherein a dome plate is positioned at an upstream end of said combustor, said liner comprising:(a) a first portion positioned adjacent and connected to said dome plate, wherein said first line portion extends downstream from and substantially perpendicular to said dome plate; (b) a second portion extending substantially perpendicular to said first liner portion and substantially parallel to said dome plate; (c) a first arcuate portion located between said first and second liner portions configured to have a predetermined radius which limits stress on said second liner portion to a predetermined level; (d) a third portion extending downstream and substantially perpendicular to said second liner portion; and, (e) a second arcuate portion located between said second and third liner portions; wherein said first liner portion, said second liner portion, said first arcuate liner portion and a portion of said dome plate form said trapped vortex cavity.
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