JP6544736B2 - 燃焼システムの中の燃焼ダイナミックスの制御のためのシステムおよび方法 - Google Patents
燃焼システムの中の燃焼ダイナミックスの制御のためのシステムおよび方法 Download PDFInfo
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- 238000002485 combustion reaction Methods 0.000 title claims description 139
- 238000000034 method Methods 0.000 title claims description 13
- 239000007800 oxidant agent Substances 0.000 claims description 231
- 230000001590 oxidative effect Effects 0.000 claims description 225
- 239000000446 fuel Substances 0.000 claims description 63
- 239000007789 gas Substances 0.000 claims description 62
- 230000008878 coupling Effects 0.000 claims description 26
- 238000010168 coupling process Methods 0.000 claims description 26
- 238000005859 coupling reaction Methods 0.000 claims description 26
- 238000011144 upstream manufacturing Methods 0.000 claims description 24
- 230000008859 change Effects 0.000 claims description 20
- 239000012530 fluid Substances 0.000 claims description 9
- 230000007704 transition Effects 0.000 claims description 9
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 230000004044 response Effects 0.000 description 20
- 239000000203 mixture Substances 0.000 description 10
- 239000000567 combustion gas Substances 0.000 description 9
- 230000001788 irregular Effects 0.000 description 9
- 230000008901 benefit Effects 0.000 description 3
- 230000001427 coherent effect Effects 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000003085 diluting agent Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 239000003570 air Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000003534 oscillatory effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Description
12 ガスタービン燃焼器
12a 燃焼器
12b 燃焼器
13 燃焼器有孔構造体
14 圧縮機
16 タービン
18 燃料ノズル
19 燃焼室
24 高温加圧燃焼ガス
26 シャフト
28 排気出口部
30 負荷
32 空気取り入れ口
34 加圧空気
36 オキシダント流路
42 軸線方向
44 半径方向
46 円周方向
50 ヘッドエンド
51 ヘッドエンドチャンバー
52 エンドカバー
53 壁部
54 燃焼器キャップアッセンブリ
58 フロースリーブ
59 インピンジメントスリーブ
60 内側壁部、燃焼器ライナー
61 穿孔
62 一次燃焼ゾーン
64 フロー通路
66 トランジションピース
67 オキシダントフロー
68 圧縮機流出部
69 下流方向
70 第1の燃焼器
71 第2の燃焼器
72 上流面
74 下流面
76 オキシダントポート
79 直径
96 第1の距離
98 第2の距離
Claims (16)
- システムであって、前記システムは、
ガスタービンエンジンを含み、前記ガスタービンエンジンは、
第1の燃焼器であって、前記第1の燃焼器は、
第1の燃焼室を囲む第1の内壁、
前記第1の内壁の少なくとも一部の周りに配置される第1の外壁、
前記第1の燃焼室に酸素及び燃料を供給するように構成された少なくとも1つの第1 の燃料ノズルを含む第1のヘッドエンドチャンバー、
前記第1の内壁の少なくとも一部の周りに配置される第1の外壁、
前記第1の内壁と前記第1の外壁の間に延在し、前記第1のヘッドエンドチャンバー内に連通する第1のオキシダント流路、および、
第1の複数のオキシダントポートを含む第1の有孔構造体であって、前記第1の有孔構造体は、前記少なくとも1つの第1の燃料ノズルの上流で前記第1のオキシダント流路に沿って配設されている、第1の有孔構造体
を含む、第1の燃焼器と、
第2の燃焼器であって、前記第2の燃焼器は、
第2の燃焼室を囲む第3の壁部、
前記第3の壁部の少なくとも一部の周りに配置される第4の壁部、
前記第2の燃焼室に酸素及び燃料を供給するように構成された少なくとも1つの第2 の燃料ノズルを含む第2のヘッドエンドチャンバー、
前記第3の壁部と前記第4の壁部の間に延在し、前記第2のヘッドエンドチャンバー内に連通する第2のオキシダント流路、および、
第2の複数のオキシダントポートを含む第2の有孔構造体であって、前記第2の有孔構造体は、前記少なくとも1つの第1の燃料ノズルの上流で前記第2のオキシダント流路に沿って配設されており、前記第1の有孔構造体は、前記第2の有孔構造体に対して少なくとも1つの相違を有している、第2の有孔構造体
を含む、第2の燃焼器と
を含む、システム。 - 前記少なくとも1つの相違が、前記第1の燃焼器と前記第2の燃焼器との間の燃焼ダイナミックスのモードカップリングを低減させることを助けるように構成されている、請求項1記載のシステム。
- 前記第1の有孔構造体が、前記第1の外壁の少なくとも一部を構成する第1のフロースリーブと前記第1の燃焼器の前記第1の内壁の少なくとも一部を構成する第1の燃焼ライナーとの間、前記第1の燃焼器の第1のインピンジメントスリーブを備える前記第1の内壁と前記第1の燃焼器の第1のトランジションピースとの間、もしくは、前記第1の燃焼器の第1のヘッドエンドチャンバーの中、または、それらの任意の組み合わせのうちの少なくとも1つに配設されている第1の有孔構造体を含み、前記第2の有孔構造体が、前記第2の燃焼器の第2のフロースリーブを備える前記第4の壁部と前記第2の燃焼器の第2の燃焼ライナーを備える前記第3の壁部との間、前記第2の燃焼器の第2のインピンジメントスリーブを備える前記第4の壁部と前記第2の燃焼器の第2のトランジションピースを備える前記第3の壁部との間、もしくは、前記第2の燃焼器の第2のヘッドエンドチャンバーの中、または、それらの任意の組み合わせのうちの少なくとも1つに配設されている第2の有孔構造体を含む、請求項1または2に記載のシステム。
- 前記第1の有孔構造体が、前記第1の燃焼器の前記第1の外壁の少なくとも一部を構成する第1のフロースリーブ、もしくは、第1のインピンジメントスリーブ、または、それらの任意の組み合わせのうちの少なくとも1つを含み、
前記第2の有孔構造体が、前記第2の燃焼器の前記第4の壁部の少なくとも一部を構成する第2のフロースリーブ、もしくは、第2のインピンジメントスリーブ、または、それらの任意の組み合わせのうちの少なくとも1つを含む、請求項1乃至3のいずれかに記載のシステム。 - 前記少なくとも1つの相違が、前記第2の複数のオキシダントポートに対して、前記第1の複数のオキシダントポートにおいて、異なる数のオキシダントポートを含む、請求項1乃至4のいずれかに記載のシステム。
- 前記少なくとも1つの相違が、前記第2の複数のオキシダントポートに対して、前記第1の複数のオキシダントポートにおいて、オキシダントポートの異なる幾何学的な配置を含む、請求項1乃至5のいずれかに記載のシステム。
- 前記少なくとも1つの相違が、前記第2の複数のオキシダントポートに対して、前記第1の複数のオキシダントポートにおいて、オキシダントポートの異なる直径を含む、請求項1乃至6のいずれかに記載のシステム。
- 前記少なくとも1つの相違が、前記第2の複数のオキシダントポートに対して、前記第1の複数のオキシダントポートにおいて、隣接するオキシダントポート同士の間の異なる距離を含む、請求項1記載のシステム。
- 前記少なくとも1つの相違が、前記第2の複数のオキシダントポートに対して、前記第1の複数のオキシダントポートにおいて、オキシダントポートの異なる形状を含む、請求項1乃至8のいずれかに記載のシステム。
- 前記少なくとも1つの相違が、前記第2の有孔構造体に対して、前記第1の有孔構造体の異なる全オキシダント有効フロー面積を含む、請求項1乃至9のいずれかに記載のシステム。
- 前記第1の有孔構造体が、前記第1の燃焼器の中の第1の燃焼ダイナミックスを少なくとも部分的に変更させるように構成されており、前記第2の有孔構造体が、前記第2の燃焼器の中の第2の燃焼ダイナミックスを少なくとも部分的に変更させるように構成されており、前記第1および第2の有孔構造体の間の前記少なくとも1つの幾何学的な相違が、前記第1および第2の燃焼ダイナミックスの間の相違を引き起こす、請求項1乃至10のいずれかに記載のシステム。
- 前記第1の有孔構造体が、前記第1のタービン燃焼器の第1の外壁の少なくとも一部を構成する第1のフロースリーブと前記第1のタービン燃焼器の第1の燃焼ライナーとの間、前記第1のタービン燃焼器の第1の外壁の少なくとも一部を構成する第1のインピンジメントスリーブと前記第1のタービン燃焼器の第1のトランジションピースとの間、もしくは、前記第1の燃焼器の第1のヘッドエンドチャンバーの中、または、それらの任意の組み合わせのうちの少なくとも1つに配設されている第1の有孔構造体を含む、請求項1乃至11のいずれかに記載のシステム。
- 第1の複数のオキシダントポートを含む第1の有孔構造体を備える第1の燃焼器の中の第1の燃焼ダイナミックスを制御するステップであって、前記第1の有孔構造体は、前記第1の燃焼器の第1の内壁と第1の外壁との間に延在する第1のオキシダント流路に沿って配設され、前記第1の内壁が第1の燃焼室の周りに配置され、前記第1の外壁が前記第1の内壁の少なくとも一部の周りに配置され、前記第1のオキシダント流路が、前記第1の燃焼器の第1のヘッドエンド内に延在する、ステップと、
第2の複数のオキシダントポートを含む第2の有孔構造体を備える第2の燃焼器の中の第2の燃焼ダイナミックスを制御するステップであって、前記第2の有孔構造体は、前記第2の燃焼器の第2の内壁と第2の外壁との間に延在する第2のオキシダント流路に沿って配設され、前記第2の内壁が第2の燃焼室の周りに配置され、前記第2の外壁が前記第2の内壁の少なくとも一部の周りに配置され、前記第2のオキシダント流路が、前記第2の燃焼器の第2のヘッドエンド内に延在しており、前記第1および第2の有孔構造体は、少なくとも1つの相違を有しており、前記第1の燃焼ダイナミックスに対して前記第2の燃焼ダイナミックスを変化させる、ステップと
を含み、
前記第1の有孔構造体は、前記燃焼器の第1のヘッドエンド内に配置された第1の燃料ノズルの上流に配置され、
前記第2の有孔構造体は、前記燃焼器の第2のヘッドエンド内に配置された第2の燃料ノズルの上流に配置される、方法。 - 前記第1および第2の有孔構造体の間の前記少なくとも1つの相違を介して、前記第1および第2の燃焼器の間のモードカップリングを低減させるステップを含む、請求項13記載の方法。
- 前記第1および第2の有孔構造体の間の前記少なくとも1つの相違が、オキシダントポートの数、オキシダントポートの直径、オキシダントポートの形状、隣接するオキシダントポート同士の間の距離、全オキシダント有効フロー面積、幾何学的配置、もしくは、幾何学的特性、または、それらの任意の組み合わせのうちの少なくとも1つの相違を含む、請求項13または14に記載の方法。
- 前記第1の燃焼器の第1の燃料−オキシダント比率を、前記第2の燃焼器の第2の燃料−オキシダント比率の範囲内に維持するために、前記第1の燃焼器への第1の燃料流量、および、前記第2の燃焼器への第2の燃料流量を制御するステップを含む、請求項13乃至15のいずれかに記載の方法。
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US14/192,687 | 2014-02-27 | ||
US14/192,687 US9709279B2 (en) | 2014-02-27 | 2014-02-27 | System and method for control of combustion dynamics in combustion system |
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US10663170B2 (en) * | 2017-01-19 | 2020-05-26 | Doosan Heavy Industries Construction Co., Ltd. | Flow conditioner to reduce combustion dynamics in a combustion system |
US20180209650A1 (en) * | 2017-01-24 | 2018-07-26 | Doosan Heavy Industries Construction Co., Ltd. | Resonator for damping acoustic frequencies in combustion systems by optimizing impingement holes and shell volume |
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