TWI376484B - Venturi cooling system - Google Patents
Venturi cooling system Download PDFInfo
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- TWI376484B TWI376484B TW098115593A TW98115593A TWI376484B TW I376484 B TWI376484 B TW I376484B TW 098115593 A TW098115593 A TW 098115593A TW 98115593 A TW98115593 A TW 98115593A TW I376484 B TWI376484 B TW I376484B
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- venturi
- passage
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Classifications
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- 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
- F23R3/002—Wall structures
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- 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
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- 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
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gas Burners (AREA)
- Spray-Type Burners (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Description
1376484 六、發明說明: 【發明所屬之技術領域】 本發明係關於可用於燃氣渦輪機中之燃燒器。# 言,本發明係關於一種用於冷卻在一級與二級燃燒室 之間 的文氏管喉區域之系統。 【先前技術】 燃氣渦輪機在若干個應用’例如飛機推進、船用 、 号隹進、 發電及驅動過程(例如泵及壓縮機)中發揮一重要作用。' 吊’一燃氣渴輪機包括一屢縮機、一燃燒器及一渴卜 作業中,將空氣饋送至系統中,在該系統處空氣由壓縮2 壓縮且在燃燒器中與燃料混合。隨後,將壓縮空氣與燃料 混合物在燃燒器内燃燒以導致一負責驅動渦輪機之空氣沪 膨脹。 机 燃燒襯界定燃燒器之内部容積且用來保護燃燒器外殼及 剩餘之引擎部分免受存在於燃燒器内之極端溫度。為減少 NOj#放物及延長引擎組件之壽命,需要將退出壓縮機之 壓縮空氣之一部分用於冷卻各種燃燒器組件,包括燃燒 概0 燃燒襯通常包括一用於影響燃燒器内之火焰位置及穩定 喉m在此等配置中’該等Ν〇χ排放 物之一降低係藉由透過燃燒燃料與空氣之一貧、均勻混合 物降低峰值火焰溫度而達成。均勾性通常係藉由在文氏管 上游處於燃燒器中預混合燃料與空氣且隨後在文氏管之邊 緣或頂點下游處點燃進入至二級燃燒室中之混合物而達 139536.doc 1376484 成。藉助在候部之前加速流動,該文氏管組態意欲阻止火 焰在文氏管喉上游處回火至預混合區域或一級燃燒室中。 • 在某些運作條件下亦需要冷卻文氏管下游處之火焰保持區 V 域。由於火焰可駐留於文氏管之每一側上,故兩個側皆需 • 要冷卻。然而’若在文氏管下游處釋放之冷卻空氣流太大 或太靠迎文氏管釋放冷卻空氣流,則其可不利地影響燃燒 效能。 φ US 5,117,636顯示文氏管内之一冷卻通路,該冷卻通路 自文氏管頂點或喉向下游延伸,使得冷卻空氣不再次進入 二級燃燒室内之火焰保持區。此意欲分離火焰保持功能與 文氏管冷卻功能。US 6,430,932顯示一文氏管内之一冷卻 室,該冷卻室與燃燒流相反地引導冷卻流且於文氏管上游 處傾瀉冷卻空氣。 已確定文氏管上游及下游側上之熱負載係不同且在任一 側上於文氏管附近傾瀉冷卻空氣皆對燃燒器之作業具有一 φ 影響。在其_將對文氏管之兩個側之冷卻聯繫在一起之先 前技術設計中’文氏管壁内尚未存在一熱拾取平衡,或冷 卻通路内尚未存在有利於壓力降之調節機能。 【發明内容】 ' 提供一種用於一如下類型之燃氣渦輪引擎之燃燒器:具 有一位於該燃燒器之一第一端處之喷嘴總成及—在該喷嘴 下游處界定於該燃燒器之一第二端處之燃燒室。一文氏管 • 定位於該喷嘴與該燃燒室之間。該文氏管界定—該燃燒器 • 之該第一端與該燃燒器之該第二端之間的過渡區域。該文 139536.doc 1376484 氏官包括一於其中用於接收一冷卻空氣流之通路。該通路 具有一面向該噴嘴之第一側及一面向該燃燒室之第二側。 一壓縮空氣源係藉助與該文氏管通路之該第一及第二側兩 者連通之流入口而被引導至該通路中。該文氏管通路於該 文氏官内沿相反方向引導來自該源之壓縮空氣。因而,該 通路之該第一側與第二側中之空氣流係沿相反之方向。 本發明之另一態樣可包括一於該文氏管通路之第二側之 上游處延伸之二級通路。此外,該冷卻流入口可更靠近該 喷嘴或更靠近該文氏管頂點之上游側定位。 【實施方式】 在圖式中,顯示本發明之一典型燃燒器及若干實施例之 一圖形表示。該燃燒器通常由編號丨0表示且涵蓋被併入至 一燃氣渦輪機(未顯示)中。在圖1中,燃燒器10包括一至少 部分地由一熱屏蔽或導流套14環繞之燃燒襯丨2。壓縮空氣 係自一上游壓縮機(未顯示)提供且被饋送至一形成於熱屏 蔽14與燃燒襯12之間的環繞通道16中。 在燃燒襯12界線内提供有複數個一級燃料噴嘴18及一二 級燃料喷嘴20,提供-燃燒器導流套22,其環繞二級燃料 噴嘴20,使得二級噴嘴20與一級噴嘴1 8分離。燃料24係引 入至一控制器26中且被饋送至噴嘴18、20。燃燒襯12與燃 燒器導流套22之間的面積界定一上游或一級燃燒室28。二 級喷嘴20之下游係一文氏管30,該文氏管在燃燒襯12界定 之面積内界定一環形限制部。文氏管30包括一界定一文氏 管喉部之頂點32。頂點32定位於喷嘴18 ' 20之下游處。一 139536.doc 1376484 30之冷卻空氣與兩個通道4〇及42流體連通,通道4〇及42通 常平行於文氏管30之一第一或上游側41及文氏管30之一第 二或下游側43。引導至通道40之冷卻空氣36沿與引導至通 道42中之冷卻空氣之一相反方向轉向。穿過文氏管3〇之上 游側41上之上游通道40之空氣流經引導穿過一上游出口 44 並進入至一級燃燒室28中。穿過下游通道42且沿下游側43 傳遞之冷卻流經引導而穿過毗鄰燃燒襯12定位之出口 46且 進入至下游燃燒室34中。用於文氏管空氣之若干個特定形 式之排氣出口在先前技術中係習知且可併入至當前所描述 之文氏管30中。 於圖3中,顯示本發明之結構之一變化。冷卻空氣%係 自通道16引導至一入口充氣室138中,該入口充氣室具有 一毗鄰文氏管30之下游侧43定位之出口。入口充氣室138 與下游通道142直接流體連通。冷卻空氣係沿一下游方向 經引導而朝.向下游出口 46穿過通道142。一額外冷卻空氣 流係在下游通道部分142a内沿與下游出口钧之相反方向引 導。冷卻通道部分142&與定位於文氏管3〇之上游側“後方 之上游通道140連通。上游通道14〇内之冷卻空氣經引導而 穿過上游出口 44且進入至上游燃燒室28中。將冷卻通道定 位於文氏管之下游面上減少文氏管之下游部分所需之冷 卻。另一選擇為’人口充氣室138可晚鄰文氏管3〇之上游 側41定位。 因而’該文氏管界定該燃燒器之第_與第二端之間的一 過渡區域。該文氏管内之内部通路包括位於該文氏管之一 139536-1010416.doc 1376484 頂點之相對側上的一第一側及—第二側。用於壓縮空氣流 之冷卻入口與該文氏管通路之第一及第二側流體連通且來 自該冷卻入口之壓縮空氣經引導而在第—側及第二側内沿 相反方向穿過文氏管通路。該冷卻入口可在與該文氏管之 頂點成直線或自該文氏管之頂點偏移的一位置處與文氏管 通路連通。該冷卻入口可形成為一定位於該文氏管後方之 徑向充氣室或可呈任一數目之其他形式。 在圖4中,提供一文氏管冷卻系統之再一實施例。冷卻 空氣36係自通道16引導至一入口充氣室238中。入口充氣 至238將冷卻空氣引導至文氏管3〇之後側上之通道、 242中。如所圖解說明,入口充氣室238毗鄰文氏管3〇之頂 點32之後方定位,其中上游通道240沿上游側41引導冷卻 空氣且下游通道242沿下游側43引導冷卻空氣。通道242之 下游端與一二級通路248流體連通。通道242内之冷卻空氣 在其進入二級通路248時在方向上反轉。二級通路248朝燃 燒益之上游側延伸且與毗鄰一排氣通道25〇之上游通道24〇 接。。來自上游通道24〇及二級通路248之組合流穿過排氣 通道250傳遞且穿過上游出口 244排放至文氏管30之上游側 上之燃燒室2 8中。 在圖4中顯不之實施例中(及在上文所描述之實施例 中),涵蓋入口充氣室238可包含除一連續狹槽或環形通道 之外之其他組件。入口充氣室238及二級通路248可由一系 列彼此交越之管形成。因而,入口充氣室238在交越形成 通路248之該系列管之後饋入文氏管3〇之背側。亦可利用 139536.doc 1376484 相對於文氏管30之頂點32之軸位置再定位入口充氣室238 來調節對文氏管30之冷卻效應。另外,如在本文所論述之 所有實施例中’通道及通路之相對大小及形成可變化以在 空氣流於文氏管壁内移動且隨後被引導至燃燒室中時調節 空氣流及冷卻空氣之壓力降。 在審閱本揭示内容之後’熟習此項技術者將顯而易見對 所描述之實施例之多種修改。因而,可在不背離本發明之 精神或實質屬性之情形下以其它特定形式體現本發明,且 因此’當指示本發明範疇時應參考隨附申請專利範圍而非 上述說明書。 【圖式簡單說明】 在圖式中,圖解說明若干當前較佳實施例。 圖1顯示一併入有本發明之一實施例之燃氣渦輪燃燒系 統之一簡化剖視圖。 圖2係圖1中圖解說明之燃燒系統之文氏管喉區域之一部 分剖視圖。 圖3係一供在一燃燒系統中使用的一文氏管系統之一另 一實施例之部分剖視圖。 圖4係一供在一燃燒系統中使用的一文氏管系統之再一 實施例之部分剖視圖。 【主要元件符號說明】 10 燃燒器 12 燃燒襯 14 熱屏蔽/導流套 139536.doc 1376484 16 18 20 22 24 26 28 30
34 36 38 40 41 42
44 46 138 140 142 142a 238 240 環繞通道 一級燃料喷嘴 二級燃料噴嘴 燃燒器導流套 燃料 控制器 上游/一級燃燒室 文氏管 頂點 下游/二級燃燒室 壓縮空氣 入口充氣室 通道 第一 /上游側 通道 第二/下游側 上游出口 下游出口 入口充氣室 上游通道 下游通道 下游通道部分 入口充氣室 通道 139536.doc -11 - 1376484 242 通道 244 上游通道 248 二級通路 250 排氣通道
139536.doc -12-
Claims (1)
1376484 七、申請專利範圍: 1. 一種用於一燃氣渦輪機之燃燒器,其包含: 一位於該燃燒器之—第一端處之噴嘴總成; % 一在該噴嘴之下游處界定於該燃燒器内之燃燒室、; 一定位於該燃燒器内且界定該第一端與該燃燒室之間 的一過渡區域之文氏管,該文氏管在其中昊有一 ^内部通 路’該通路具有一面向該噴嘴之第一側及一面向該燃燒 室之第二侧;及 一被引導至一冷卻入口中之壓縮空氣源,該冷卻入口 與該文氏管通路之該第一及第二側流體連通, 該通路於該第一側及第二側内沿相反方向引導來自該 源之該壓縮空氣以冷卻該文氏管。 2_如請求項丨之燃燒器,其進一步包含一與該文氏管通路 之該第二側之一下游端連通之二級通路,其中穿過該通 路之該第二側移動至該二級通路中之空氣流在方向上反 轉且經引導而朝向該文氏管之該第一側。 3.如請求項2之燃燒器,其進一步包含一定位於該文氏管 通路之該第一側之一端處之冷卻空氣出口,以用於將該 冷卻空氣引導至該燃燒器之該第一端中。 4·如請求項3之燃燒器’其中該二級通路與該通路之該第 一侧係各自與該冷卻空氣出口流體連通。 5.如請求項4之燃燒器,其中該冷卻空氣出口將該空氣流 自該二級通路及該文氏管通路之該第一側引導至該文氏 管之上游處該燃燒器之該第一端中。 139536.doc 1376484 6. 7. 8. 9. 10. 11. 如請求項1之燃燒器,其中該冷卻入口係在該燃燒器内 該文氏管之該上游側後方之一位置處與該文氏管通路之 該第一側連通。 如請求項1之燃燒器,其進一步包含一定位於該文氏管 後方之徑向充氣室。 一種用於一燃氣渦輪機之燃燒器,其包含: 一位於該燃燒器之一第一端處之喷嘴總成; 一在S玄喷嘴之下游處界定於該燃燒器内之燃燒室; 疋位於該燃燒器内且界定該第一端與該燃燒室之間 的一過渡區域之文氏管·,該文氏管在其中具有一内部通 路’該文氏管通路具有位於該文氏管之一頂點之相對側 上的一第一側及一第二侧;及 用於壓縮空氣流之冷卻入口,該冷卻入口與該文 氏管通路之該第一及第二側流體連通,且來自該冷卻入 口之該壓縮空氣經引導而在該第一惻及第二側内沿相反 方向穿過該文氏管通路以冷卻該文氏管。 如凊求項8之燃燒器,其中該冷卻入口係在該燃燒器内 自該文氏管之該頂點偏移之一位置處與該文氏管通路之 該第—側或第二側連通。 如請求項8之燃燒器,其中該冷卻入口包含一定位於該 文氏管後方之徑向充氣室。 如請求項8之燃燒器,其進—步包含—與該文氏管通路 之該第二側之一下游端連通之二級通路,其中穿過該通 路之該第二側移動至該二級通路之該空氣流在方向上反 139536.doc -2- ^76484 轉且經引導而朝向該文氏管之該第一側。 12·如請求項11之燃燒器,其進一步包含一定位於該文氏管 通路之該第一侧之一端處之冷卻空氣出口,以用於將該 " 冷卻空氣引導至該燃燒器之該第一端中。 • 13,如請求項12之燃燒器,其中該二級通路與該通路之該第 ,- 一側係各自與該冷卻空氣ώ ΰ流鎧連通。 • 14.如請求項13之燃燒器’其中該冷卻空氣出口將該空氣流 φ 自該二級通路及該文氏管通路之該第一側引導至該文氏 管之上游處之該燃燒器之該第一端中。 15.—種在一燃氣渦輪機燃燒器内之文氏管其包含: 一上游傾斜側、一下游傾斜側、一定位於該上游與下 游側之間的頂點及一在傾斜側之間用於在最接近該頂點 處供應冷卻空氣之冷卻空氣入口; 一用於自该入口沿下游傾斜側之内表面且隨後沿一襯 在其上游引導冷卻空氣之第一通路; • -用於自該入口沿上游傾斜側引導冷卻空氣之第二通 路;及 一用於在該文氏管之該馆駐夕& & 貝點之上游處將冷钟空氣自該 第二通道引導至燃燒器之冷卻排出管。 16. 如請求項15之文氏管,其谁一半 丹進步包含在該文氏管内圍繞 該燃燒器徑向延伸之中心充氣g。 17. 如請求項15之文氏管,复中兮、人 • "宁δ亥冷部排出管定位於該文氏 管之該上游傾斜側之上游處。 139536.doc
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-
2009
- 2009-01-21 US US12/357,029 patent/US7712314B1/en active Active
- 2009-04-01 EP EP09004835.6A patent/EP2211104B1/en active Active
- 2009-04-02 CA CA2661248A patent/CA2661248C/en active Active
- 2009-04-02 SG SG200902292-2A patent/SG163466A1/en unknown
- 2009-04-02 SG SG2011091501A patent/SG177888A1/en unknown
- 2009-04-08 AU AU2009201420A patent/AU2009201420B8/en active Active
- 2009-04-22 MX MX2009004301A patent/MX2009004301A/es active IP Right Grant
- 2009-04-28 JP JP2009110007A patent/JP4933578B2/ja active Active
- 2009-05-05 CN CN2009101359487A patent/CN101782232B/zh active Active
- 2009-05-05 AR ARP090101612A patent/AR072358A1/es active IP Right Grant
- 2009-05-07 IL IL198653A patent/IL198653A/en active IP Right Grant
- 2009-05-07 BR BRPI0901605-8A patent/BRPI0901605A2/pt not_active Application Discontinuation
- 2009-05-07 CL CL2009001101A patent/CL2009001101A1/es unknown
- 2009-05-07 MY MYPI20091855A patent/MY149412A/en unknown
- 2009-05-08 KR KR1020090040209A patent/KR101131646B1/ko active IP Right Grant
- 2009-05-11 TW TW098115593A patent/TWI376484B/zh active
- 2009-05-11 TW TW101113646A patent/TWI452242B/zh active
- 2009-08-06 US US12/536,861 patent/US7707836B1/en active Active
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Also Published As
Publication number | Publication date |
---|---|
EP2211104B1 (en) | 2017-06-14 |
US7707836B1 (en) | 2010-05-04 |
JP4933578B2 (ja) | 2012-05-16 |
EP2211104A2 (en) | 2010-07-28 |
TW201028622A (en) | 2010-08-01 |
SG163466A1 (en) | 2010-08-30 |
MY149412A (en) | 2013-08-30 |
CN101782232A (zh) | 2010-07-21 |
JP2010169076A (ja) | 2010-08-05 |
TW201241369A (en) | 2012-10-16 |
HK1146108A1 (en) | 2011-05-13 |
US7712314B1 (en) | 2010-05-11 |
SG177888A1 (en) | 2012-02-28 |
KR20100085810A (ko) | 2010-07-29 |
MX2009004301A (es) | 2010-07-20 |
AR072358A1 (es) | 2010-08-25 |
AU2009201420B8 (en) | 2011-02-17 |
EP2211104A3 (en) | 2014-08-06 |
AU2009201420A1 (en) | 2010-08-05 |
CN101782232B (zh) | 2012-11-28 |
KR101131646B1 (ko) | 2012-03-28 |
IL198653A (en) | 2013-01-31 |
CL2009001101A1 (es) | 2011-08-19 |
IL198653A0 (en) | 2010-02-17 |
CA2661248C (en) | 2011-02-08 |
AU2009201420B2 (en) | 2011-01-27 |
CA2661248A1 (en) | 2010-07-21 |
TWI452242B (zh) | 2014-09-11 |
BRPI0901605A2 (pt) | 2010-12-21 |
AR092910A2 (es) | 2015-05-06 |
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