JPH01151062U - - Google Patents
Info
- Publication number
- JPH01151062U JPH01151062U JP4322488U JP4322488U JPH01151062U JP H01151062 U JPH01151062 U JP H01151062U JP 4322488 U JP4322488 U JP 4322488U JP 4322488 U JP4322488 U JP 4322488U JP H01151062 U JPH01151062 U JP H01151062U
- Authority
- JP
- Japan
- Prior art keywords
- air
- gas fuel
- tertiary
- combustor
- combustion
- 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.)
- Granted
Links
- 239000000446 fuel Substances 0.000 claims description 11
- 238000002485 combustion reaction Methods 0.000 claims 6
- 238000013459 approach Methods 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 2
Description
第１図及び第２図は本考案の実施例を示し、第
１図は全体概念図、第２図は要部断面図である。
第３図は従来例の概念図である。第４図は実験結
果を示すグラフである。
１……燃焼器、３……コンプレツサー、４……
燃料供給路、６……ガスタービン、１４ａ……ガ
ス燃料吐出口、１８……一次空気口、１９……二
次空気口、２０……三次空気口、Ｐ……ガス燃料
流の中心。
FIGS. 1 and 2 show an embodiment of the present invention, with FIG. 1 being an overall conceptual diagram and FIG. 2 being a sectional view of a main part.
FIG. 3 is a conceptual diagram of a conventional example. FIG. 4 is a graph showing the experimental results. 1...Combustor, 3...Compressor, 4...
Fuel supply path, 6...Gas turbine, 14a...Gas fuel discharge port, 18...Primary air port, 19...Secondary air port, 20...Tertiary air port, P...Center of gas fuel flow.
Claims (1)
４からのガス燃料を燃焼させて燃焼器１設け、そ
の燃焼器１からの熱風で駆動されるガスタービン
６を前記コンプレツサー３に連動させたターボ式
燃焼装置であつて、前記燃焼器１において、実質
的に環状のガス燃料用の吐出口１４ａの内側に、
一次燃焼用空気を噴出する一次空気口１８を、ガ
ス燃料と一次燃焼用空気がほぼ平行流になるよう
に配置し、前記ガス燃料用吐出口１４ａからのガ
ス燃料流にその外周側から二次燃焼用空気と三次
燃焼用空気を供給する多数の二次空気口１９と三
次空気口２０を、夫々分散配置した状態で、かつ
、前記二次空気口１９よりも前記三次空気口２０
が下流側に位置する状態で設け、前記二次空気口
１９を、前記ガス燃料流の中心Ｐに対して近付く
ほど下流側になる傾斜方向に向け、前記三次空気
口２０を前記ガス燃料流の中心Ｐに対してほぼ直
交方向に向けてあるターボ式燃焼装置。 A turbo-type combustion system in which a combustor 1 is provided in which gas fuel from a fuel supply path 4 is combusted with pressurized air from a compressor 3, and a gas turbine 6 driven by hot air from the combustor 1 is linked to the compressor 3. In the combustor 1, inside the substantially annular gas fuel outlet 14a, the apparatus includes:
The primary air port 18 that blows out the primary combustion air is arranged so that the gas fuel and the primary combustion air flow approximately parallel to each other, and the gas fuel flow from the gas fuel discharge port 14a is A large number of secondary air ports 19 and tertiary air ports 20 that supply combustion air and tertiary combustion air are arranged in a distributed manner, and the tertiary air ports 20 are arranged in a manner that the secondary air ports 19 are larger than the tertiary air ports 20.
is located on the downstream side, the secondary air port 19 is oriented in an inclined direction that becomes more downstream as it approaches the center P of the gas fuel flow, and the tertiary air port 20 is located on the downstream side of the gas fuel flow. A turbo combustion device oriented almost perpendicular to the center P.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1988043224U JP2513191Y2 (en) | 1988-03-30 | 1988-03-30 | Turbo Combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1988043224U JP2513191Y2 (en) | 1988-03-30 | 1988-03-30 | Turbo Combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01151062U true JPH01151062U (en) | 1989-10-18 |
| JP2513191Y2 JP2513191Y2 (en) | 1996-10-02 |
Family
ID=31269630
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1988043224U Expired - Lifetime JP2513191Y2 (en) | 1988-03-30 | 1988-03-30 | Turbo Combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2513191Y2 (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57192729A (en) * | 1981-05-11 | 1982-11-26 | Rolls Royce | Annular combustor for gas turbine-engine |
-
1988
- 1988-03-30 JP JP1988043224U patent/JP2513191Y2/en not_active Expired - Lifetime
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS57192729A (en) * | 1981-05-11 | 1982-11-26 | Rolls Royce | Annular combustor for gas turbine-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2513191Y2 (en) | 1996-10-02 |
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