Claims
- 1. In a gas turbine having a compressor for producing compressed air, a combustor for heating said compressed air comprising:
- a) a first substantially cylindrical liner forming a chamber therein for containing a combustion zone, a second substantially cylindrical liner forming an outer annular passage encircling said first liner;
- b) a flow guide forming a first inlet passage having first and second portions, said first portion extending axially and being concentric with said liner, said second portion extending radially and encircling said first portion;
- c) a plurality of fuel discharge means extending radially into said outer annular passage, each of said fuel discharge means having a plurality of fuel discharge ports formed therein;
- d) a second inlet passage for said chamber, said second inlet passage having first and second portions, said first portion of said second inlet passage formed between said fuel nozzle and said flow guide and extending axially and being concentric with said first portion of said first inlet passage, said second portion of said second inlet passage extending radially and encircling said first portion of said second inlet passage;
- e) a plurality of first swirl vanes disposed in said second portion of said first inlet passage; and
- f) a plurality of second swirl vanes disposed in said second portion of said second inlet passage.
- 2. The combustor according to claim 1, further comprising means for rotating said first and second swirl vanes.
- 3. The combustor according to claim 1, further comprising a third substantially cylindrical liner enclosed by said second liner, said outer annular passage formed between said second and third liners, said first and second liners forming an inner annular passage therebetween.
- 4. The combustor according to claim 3, further comprising means for introducing cooling air into said inner annular passage.
- 5. The combustor according to claim 4, further comprising a circumferentially extending baffle disposed in said inner annular passage.
- 6. The combustor according to claim 5, wherein said baffle has means for directing cooling air introduced into said inner annular passage to flow over said first liner.
- 7. The combustor according to claim 6, wherein said baffle has means for reducing vibration of said inner liner.
- 8. The combustor according to claim 7, further comprising means for rotating said first and second swirl vanes.
- 9. In a gas turbine having a compressor for producing compressed air, a combustor for heating said compressed air comprising:
- a) a first liner forming a chamber therein for containing a combustion zone, a second liner encircling said first liner and a third liner enclosed by said second liner, an outer annular passage being formed between said second and third liners, and an inner annular passage being formed between said first and second liners;
- b) a flow guide forming a first inlet passage having first and second portions, said first portion extending axially and being concentric with said liner, said second portion extending radially and encircling said first portion;
- c) a centrally disposed fuel nozzle in fuel flow communication with said chamber;
- d) a second inlet passage for said chamber, said second inlet passage having first and second portions, said first portion of said second inlet passage formed between said fuel nozzle and said flow guide and extending axially and being concentric with said first portion of said first inlet passage, said second portion of said second inlet passage extending radially and encircling said first portion of said second inlet passage;
- e) a plurality of first swirl vanes disposed in said second portion of said first inlet passage; and
- f) a plurality of second swirl vanes disposed in said second portion of said second inlet passage.
- 10. The combustor according to claim 9, further comprising means for rotating said first and second swirl vanes.
- 11. The combustor according to claim 9, further comprising means for introducing cooling air into said inner annular passage.
- 12. The combustor according to claim 11, further comprising a circumferentially extending baffle disposed in said inner annular passage.
- 13. The combustor according to claim 12, wherein said baffle has means for directing cooling air introduced into said inner annular passage to flow over said first liner.
- 14. The combustor according to claim 12, wherein said baffle has means for reducing vibration of said inner liner.
Parent Case Info
This is a division of application Ser. No. 08/141,757 filed Oct. 27, 1993 now U.S. Pat. No. 5,394,688.
US Referenced Citations (11)
Foreign Referenced Citations (1)
Number |
Date |
Country |
2085147 |
Apr 1982 |
GBX |
Divisions (1)
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Number |
Date |
Country |
Parent |
141757 |
Oct 1993 |
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