JPH0228964U - - Google Patents
Info
- Publication number
- JPH0228964U JPH0228964U JP10348688U JP10348688U JPH0228964U JP H0228964 U JPH0228964 U JP H0228964U JP 10348688 U JP10348688 U JP 10348688U JP 10348688 U JP10348688 U JP 10348688U JP H0228964 U JPH0228964 U JP H0228964U
- Authority
- JP
- Japan
- Prior art keywords
- inner cylinder
- air
- fuel injection
- injection nozzle
- gas turbine
- 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 9
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 238000010790 dilution Methods 0.000 claims description 3
- 239000012895 dilution Substances 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 1
Description
第１図は本考案のガスタービン用燃焼器の一実
施例を示す縦断面説明図、第２図は第１図におけ
る予混合部および燃焼領域の詳細および流体の流
れを示す拡大説明図、第３図は本考案の燃焼器に
おける、空気・燃料比と燃焼ガス中のＣＯ，ＮＯ
ｘ、全圧損失係数との関係を示す線図、第４図は
本考案の燃焼器および従来の燃焼器における、空
気・燃料比と燃焼ガス中のＣＯ，ＮＯｘ、可変機
構開度との関係を示す線図、第５図は従来の燃焼
器の一例を示す説明図である。
１…旋回羽根、２…予混合部、３…燃焼領域、
４…一次燃料噴射ノズル、５…ノズルステータ、
６…外筒、７…内筒、８…加圧空気通路、１０…
空気取入口、１１…主燃料噴射ノズル、１２…仕
切板、１３…空気通路、１４…シールエア取入管
、１５…シールエア取入口、１６…ライナヘツド
、１７…空気室、１８…小孔、２０…希釈領域、
２１…開口、２２…可変機構、２３…可変ポート
、２４…希釈孔、２５…点火プラグ。
FIG. 1 is an explanatory longitudinal cross-sectional view showing one embodiment of a gas turbine combustor of the present invention, FIG. 2 is an enlarged explanatory view showing details of the premixing section and combustion region in FIG. Figure 3 shows the air/fuel ratio and CO and NO in the combustion gas in the combustor of the present invention.
x, a diagram showing the relationship with the total pressure loss coefficient, and Figure 4 shows the relationship between the air/fuel ratio, CO and NOx in the combustion gas, and the opening degree of the variable mechanism in the combustor of the present invention and the conventional combustor. FIG. 5 is an explanatory diagram showing an example of a conventional combustor. 1... Swirling vane, 2... Premixing section, 3... Combustion region,
4...Primary fuel injection nozzle, 5...Nozzle stator,
6... Outer cylinder, 7... Inner cylinder, 8... Pressurized air passage, 10...
Air intake, 11... Main fuel injection nozzle, 12... Partition plate, 13... Air passage, 14... Seal air intake pipe, 15... Seal air intake, 16... Liner head, 17... Air chamber, 18... Small hole, 20... Dilution region,
21... Opening, 22... Variable mechanism, 23... Variable port, 24... Dilution hole, 25... Spark plug.
Claims (1)
に加圧空気通路８を形成し、内筒の端部の中心に
一次燃料噴射ノズル４を取り付け、内筒の端部の
周辺部に加圧空気を取り入れるための空気取入口
１０を設け、この空気取入口内に多数の旋回羽根
１を取り付けるとともに、これらの旋回羽根の間
に主燃料噴射ノズル１１を挿入し、一次燃料噴射
ノズル４の外側周囲に空気取入口１０に連通する
予混合部２を形成したガスタービン用燃焼器にお
いて、 予混合部２内に仕切板１２を設けて予混合部を
分割し、さらに一次燃料噴射ノズル４の外側のノ
ズルステータ５と予混合部２との間にシールエア
を流すための空気通路１３を形成したことを特徴
とするガスタービン用燃焼器。 ２ 一次燃料噴射ノズル４の下流側に隣接するラ
イナヘツド１６の表面を被覆するように、扁平な
空気室１７を形成した請求項１記載のガスタービ
ン用燃焼器。 ３ 燃焼領域３の下流側の希釈領域２０における
加圧空気通路８に、内筒７内へ空気を流入させる
開口２１を設け、この開口を開閉して内筒内への
流入空気量を調節するための可変機構２２を加圧
空気通路に設けた請求項１または２記載のガスタ
ービン用燃焼器。[Claims for Utility Model Registration] 1. An inner cylinder 7 is provided within the outer cylinder 6 to form a pressurized air passage 8 between the outer cylinder and the inner cylinder, and a primary fuel injection nozzle is provided at the center of the end of the inner cylinder. 4, an air intake 10 is provided around the end of the inner cylinder to take in pressurized air, and a large number of swirling vanes 1 are mounted inside this air intake, and a main In a gas turbine combustor in which a fuel injection nozzle 11 is inserted and a premixing section 2 that communicates with an air intake port 10 is formed around the outside of the primary fuel injection nozzle 4, a partition plate 12 is provided in the premixing section 2. A combustor for a gas turbine, characterized in that a premixing section is divided, and an air passage 13 for flowing seal air between a nozzle stator 5 outside a primary fuel injection nozzle 4 and the premixing section 2 is formed. 2. The combustor for a gas turbine according to claim 1, wherein the flat air chamber 17 is formed so as to cover the surface of the liner head 16 adjacent to the downstream side of the primary fuel injection nozzle 4. 3. The pressurized air passage 8 in the dilution region 20 on the downstream side of the combustion region 3 is provided with an opening 21 that allows air to flow into the inner cylinder 7, and the amount of air flowing into the inner cylinder is adjusted by opening and closing this opening. The gas turbine combustor according to claim 1 or 2, further comprising a variable mechanism (22) provided in the pressurized air passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1988103486U JP2516822Y2 (en) | 1988-08-04 | 1988-08-04 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1988103486U JP2516822Y2 (en) | 1988-08-04 | 1988-08-04 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0228964U true JPH0228964U (en) | 1990-02-23 |
| JP2516822Y2 JP2516822Y2 (en) | 1996-11-13 |
Family
ID=31334363
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1988103486U Expired - Lifetime JP2516822Y2 (en) | 1988-08-04 | 1988-08-04 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2516822Y2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04187909A (en) * | 1990-11-21 | 1992-07-06 | Nkk Corp | Method of premixing in gas turbine combustor and premixing device |
| EP2613084A3 (en) * | 2012-01-09 | 2018-01-10 | Rolls-Royce plc | A combustor for a gas turbine engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50140716A (en) * | 1974-02-04 | 1975-11-12 | ||
| JPS55148151A (en) * | 1979-05-01 | 1980-11-18 | Rolls Royce | Porous laminated wood |
| JPS6139273U (en) * | 1984-08-14 | 1986-03-12 | 三菱重工業株式会社 | combustor |
| JPS62218732A (en) * | 1986-03-20 | 1987-09-26 | Hitachi Ltd | Gas turbine combustor |
-
1988
- 1988-08-04 JP JP1988103486U patent/JP2516822Y2/en not_active Expired - Lifetime
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50140716A (en) * | 1974-02-04 | 1975-11-12 | ||
| JPS55148151A (en) * | 1979-05-01 | 1980-11-18 | Rolls Royce | Porous laminated wood |
| JPS6139273U (en) * | 1984-08-14 | 1986-03-12 | 三菱重工業株式会社 | combustor |
| JPS62218732A (en) * | 1986-03-20 | 1987-09-26 | Hitachi Ltd | Gas turbine combustor |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04187909A (en) * | 1990-11-21 | 1992-07-06 | Nkk Corp | Method of premixing in gas turbine combustor and premixing device |
| EP2613084A3 (en) * | 2012-01-09 | 2018-01-10 | Rolls-Royce plc | A combustor for a gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2516822Y2 (en) | 1996-11-13 |
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