JPS6169671U - - Google Patents
Info
- Publication number
- JPS6169671U JPS6169671U JP15049284U JP15049284U JPS6169671U JP S6169671 U JPS6169671 U JP S6169671U JP 15049284 U JP15049284 U JP 15049284U JP 15049284 U JP15049284 U JP 15049284U JP S6169671 U JPS6169671 U JP S6169671U
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- chamber
- premixing
- gas turbine
- premixing chamber
- 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.)
- Pending
Links
- 239000000446 fuel Substances 0.000 claims description 14
- 238000002485 combustion reaction Methods 0.000 claims description 11
- 239000007789 gas Substances 0.000 claims 8
- 239000000567 combustion gas Substances 0.000 claims 4
- 238000001816 cooling Methods 0.000 claims 2
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 2
Description
第１図は本考案に係るガスタービン用燃焼器の
一実施例を示す断面図、第２図ａ，ｂは作用を説
明するための線図、第３図は他の実施例を示す断
面図、第４図は従来の燃焼器を示す断面図、第５
図ａ，ｂおよび第６図ａ，ｂは従来例の作用を説
明するための系統図である。
２３……パイロツト燃焼室、２４……メイン燃
焼室、２６……予混合室、２７……注入口、２８
……空気流路、２９……空気供給部、３８，５１
……予混合燃料配管（燃料供給部）。
FIG. 1 is a cross-sectional view showing one embodiment of a gas turbine combustor according to the present invention, FIGS. 2 a and b are line diagrams for explaining the operation, and FIG. 3 is a cross-sectional view showing another embodiment. , Figure 4 is a sectional view showing a conventional combustor, Figure 5 is a sectional view showing a conventional combustor.
Figures a and b and Figures 6a and b are system diagrams for explaining the operation of the conventional example. 23...Pilot combustion chamber, 24...Main combustion chamber, 26...Premixing chamber, 27...Inlet, 28
... Air flow path, 29 ... Air supply section, 38, 51
...Premixed fuel piping (fuel supply section).
Claims (1)
・空気の予混合室を有し、前記パイロツト燃焼室
で燃焼されメイン燃焼室に吐出される高温の燃焼
ガスに予混合室からの燃料希薄な予混合気を注入
して燃焼させるガスタービン用燃焼器において、
予混合室をメイン燃焼室周囲に環状に形成すると
ともに、その予混合室に空気を燃焼ガスの流れと
反対方向に沿つて供給する空気供給部を設け、か
つ前記予混合室からメイン燃焼室に予混合気を注
入する注入口を燃焼ガスの流れ方向に沿つて複数
、間隔的に設ける一方、予混合室に燃料を供給す
る燃料供給部を燃料流量に対応して空気流れ方向
に位置調整可能に設けたことを特徴とするガスタ
ービン用燃焼器。 ２ 予混合気のメイン燃焼室への注入口は燃焼ガ
スの下流側に向つて次第に大口径とされている実
用新案登録請求の範囲第１項記載のガスタービン
用燃焼器。 ３ 予混合室に燃料を供給する燃料供給部は、そ
の各供給端がそれぞれ予混合室の空気流れ方向に
位置を異ならせて設けた複数の予混合燃料配管と
、その各管に供給燃料を選択的に分配する分配弁
とを有してなる実用新案登録請求の範囲第１項記
載のガスタービン用燃焼器。 ４ 予混合室に燃料を供給する燃料供給部は、そ
の供給端が予混合室の空気流れ方向に位置調整可
能な可動予混合燃料ノズルを有してなる実用新案
登録請求の範囲第１項記載のガスタービン用燃焼
器。 ５ 予混合室とメイン燃焼室との間に環状の冷却
空気流路が形成されている実用新案登録請求の範
囲第１項記載のガスタービン用燃焼器。 ６ 冷却空気流路はパイロツト燃焼用のスワラー
空気供給部を兼用してなる実用新案登録請求の範
囲第４項記載のガスタービン用燃焼器。[Scope of Claim for Utility Model Registration] 1. A vehicle having a pilot combustion chamber, a main combustion chamber, and a fuel/air premixing chamber, and a premixing chamber for high-temperature combustion gas that is combusted in the pilot combustion chamber and discharged to the main combustion chamber. In a gas turbine combustor that injects and burns a lean premixture of fuel from
A premixing chamber is formed in an annular shape around the main combustion chamber, and an air supply section is provided for supplying air to the premixing chamber along a direction opposite to the flow of combustion gas, and the premixing chamber is connected to the main combustion chamber. Multiple inlets for injecting the premixture are provided at intervals along the direction of flow of combustion gas, while the position of the fuel supply section that supplies fuel to the premixing chamber can be adjusted in the direction of air flow according to the fuel flow rate. A combustor for a gas turbine, characterized in that it is provided with a combustor for a gas turbine. 2. The gas turbine combustor according to claim 1, wherein the diameter of the injection port for the premixture into the main combustion chamber gradually increases toward the downstream side of the combustion gas. 3. The fuel supply unit that supplies fuel to the premixing chamber has a plurality of premixed fuel pipes whose respective supply ends are provided at different positions in the air flow direction of the premixing chamber, and supplies fuel to each of the pipes. A combustor for a gas turbine according to claim 1, comprising a distribution valve for selectively distributing distribution. 4. The fuel supply section that supplies fuel to the premixing chamber has a movable premixing fuel nozzle whose supply end is adjustable in the air flow direction of the premixing chamber, as described in claim 1 of the utility model registration. combustor for gas turbines. 5. The gas turbine combustor according to claim 1, wherein an annular cooling air flow path is formed between the premixing chamber and the main combustion chamber. 6. The gas turbine combustor according to claim 4, wherein the cooling air passage also serves as a swirler air supply section for pilot combustion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15049284U JPS6169671U (en) | 1984-10-04 | 1984-10-04 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP15049284U JPS6169671U (en) | 1984-10-04 | 1984-10-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6169671U true JPS6169671U (en) | 1986-05-13 |
Family
ID=30708638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP15049284U Pending JPS6169671U (en) | 1984-10-04 | 1984-10-04 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6169671U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0498014A (en) * | 1990-08-14 | 1992-03-30 | Toshiba Corp | Gas turbine combustion apparatus |
-
1984
- 1984-10-04 JP JP15049284U patent/JPS6169671U/ja active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0498014A (en) * | 1990-08-14 | 1992-03-30 | Toshiba Corp | Gas turbine combustion apparatus |
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