1356123 九、發明說明： 【發明所屬之技術領域】 本發明係關於一種具有高溫及高耐磨性之密封件，且係 關於該密封件在氣體渦輪機之燃燒器中或在氣體渦輪機中 之葉片平臺之間之特定應用。 【先前技術】 要求應用於諸如氣體渦輪機之燃燒器、工業氣體渦輪機 技術、蒸汽渦輪機技術及航空宇宙技術之高溫環境中之密 封件能抵抗高溫一給定持續時間。在許多情況下，由於此 等系統中存在振動，因而亦要求其在變化距離及高耐磨性 上提供一密封件。 氣體渦輪機之燃燒器包括沿著燃燒器外殼之内壁之内圓 周置放之熱保護襯墊。此燃燒器通常具有圓錐或圓柱形 狀襯墊在區段中沿著内壁排列。燃燒器内之溫度上升至 1200 C或1400°C，使得必須冷卻襯墊區段及外殼壁以確保 顯者之壽命。例如，藉由内料殼壁與襯塾區段之間的空 氣循環實現冷卻^控制冷卻介質之流動及/或限制所必要 之冷卻介質之體積（因為冷卻介質昂貴），將密封件置放於鄰 近襯塾區段之間。在發電或航行器之氣體渴輪機中，冷卻 ^質可為空氣或蒸汽。 體期間且特別是在以低發射水平之運作期間會在氣 輪機之燃燒器中發生大的振動。為此原因，使用彈簧 負载密封件，因为ι 1 @派 稱距離㈣提供大_之密封效 果。為抵抗對鄰近組件之摩擦，1 此外具有一耐磨塗層。 96462-960920.doc 13561231356123 IX. Description of the Invention: [Technical Field] The present invention relates to a seal having high temperature and high wear resistance, and relates to a blade platform of the seal in a gas turbine burner or in a gas turbine The specific application between. [Prior Art] Seals required for use in high temperature environments such as gas turbine burners, industrial gas turbine technology, steam turbine technology, and aerospace technology are resistant to high temperatures for a given duration. In many cases, due to the presence of vibration in such systems, it is also required to provide a seal over varying distances and high wear resistance. The gas turbine combustor includes a thermal protective liner disposed circumferentially along the inner wall of the combustor casing. This burner typically has a conical or cylindrical gasket aligned along the inner wall in the section. The temperature in the burner rises to 1200 C or 1400 ° C, making it necessary to cool the liner section and the casing wall to ensure a significant life. For example, cooling is achieved by air circulation between the inner casing wall and the lining section to control the flow of the cooling medium and/or to limit the volume of cooling medium necessary (because the cooling medium is expensive), placing the seal on Near the lining section. In gas thirteen turbines for power generation or aircraft, the cooling may be air or steam. Large vibrations occur in the burner of the turbine during the operation of the body and especially during operation at low emission levels. For this reason, a spring-loaded seal is used, since ι 1 @派距距离 (4) provides a large sealing effect. To resist friction against adjacent components, 1 additionally has a wear resistant coating. 96462-960920.doc 1356123
該等密封件之壽命由+爲 I 可畎由塗層之哥命決定，該塗層之壽 塗層被機械地捧掉之味門七 ^ 化及/… 等密封件之壽命因諸如氧 化及/或腐蝕之其它因素而被耗盡。 在設計該等密封件時所遇到之另—問題係有限之時間， 肩有限之時間’材料在曝露於高溫期間維持一彈菁負載。 ，，在氣體渦輪機中，密封件應用於固定葉片或定子葉片之 :臺之間以為s亥等葉片自冷卻區域密封熱氣區域。需要 向效能之密封件’以使冷卻流體體積最小化並以防止任何 熱氣進入冷卻通道。該等密封件必須抵抗氣體渦輪機中之 普遍的高溫以及在具有個別組件之大的熱膨脹及大的振動 之情況下執行。 EP 1 306 589揭示了-詩抵抗高溫應力鬆他之環形高 溫密封件。其包括-具有單層或兩層系統之組件，其中該 等兩層於該密封件之整個長度上延伸。此一組件之材料或 多種材料為固溶體硬化合金、澱積硬化金屬合金或分散硬 化合金中之一。 US 3,761，1〇2揭示了一密封環，詳言之係一墊片（gasket) 或墊圈（washer)，其橫截面為"C"形，其具有—置放於”c" 之内臂之間的彈簧構件。 【發明内容】 考慮到所描述之背景技術，本發明之一目的係提供一用 於高溫及高磨損應用之密封件，其與該技術狀態下所描述 之密封件相比特別具有更長之壽命。其特別適用於氣體渦 輪機中及氣體渦輪機之燃燒室中。 96462-960920.doc 根據第—獨 蜀6月求項之密封件包括第―：笛 第-組件具有-基本上為平面之形狀第及第二組件，該 ㈣分’此等兩部分各附著至該第1且該第二組件包括 端。第一組件包括-具有高耐熱性、= 牛之-側之相對末 第一材料，且笫_ 耐巩化性及耐磨性之 箬备哉 件包括一與第-材料不同且且* 簧負載維持性之第二材料。 不门且具有高彈 根據第二獨立請求項之 件，該第一纟且件 匕括第一組件及第二組 、且件係形成拱形，其中該 表面密封接觸。第_ 八 卜末端與組件 著至拱形第一龟### 第一組件之末端附 π弟·址件之内側之相對末端 有高耐熱性、耐氧化性及耐磨性之第一材料，，且^括一具 包括-與第-材料不同且具有高彈簧負載维一組件 料。 令㈣黃負載維持性之第二材 件根二第'獨株立請求項之密封件包括第-組件及第二組 第1件且：具有—平面或槽形之形狀，且該密封件之 第…件/、有-拱形形狀，其附著至該第一組件之中心。 (該形狀之密封件通常被稱為’’Κ形密封件，,。)如在第一及第 二獨立請求項中，第—組件包括-具有高耐熱性、对氧f匕 性及耐磨性之第-材料’且第二組件包括一與第一材料不 同且具有高彈簧負載維持性之第二材料。 最優化第-組件之材料以抵抗高溫氧化環境以及高磨損 度。第一組件之高耐磨性允許使用無耐磨塗層之該組件。 因此’密封件之壽命為該材料之内在壽命之函數，且其不 再取決於耐磨塗層之壽命或其藉由機械擦掉或其它手段而 96462-960920.doc 被耗盡之時間。The life of the seals is determined by the hardness of the coating, and the life of the seal is mechanically removed. / or other factors of corrosion are exhausted. Another problem encountered in designing such seals is the limited time that the shoulders are limited in time to maintain an elastomeric load during exposure to high temperatures. In the gas turbine, the seal is applied to the fixed vane or the stator vane: between the stages, the vane self-cooling area seals the hot gas area. A seal to performance is required to minimize the volume of cooling fluid and to prevent any hot gases from entering the cooling passage. These seals must be resistant to the high temperatures prevailing in gas turbines and with large thermal expansion and large vibrations of individual components. EP 1 306 589 reveals that poetry resists high temperature stress and looses its ring-shaped high temperature seal. It comprises - an assembly having a single layer or a two layer system, wherein the two layers extend over the entire length of the seal. The material or materials of this component are one of a solid solution hardening alloy, a deposited hardened metal alloy or a dispersed hard alloy. US 3,761,1 〇 2 discloses a sealing ring, in particular a gasket or washer, having a cross section of the shape "C" having the inner arm placed on the "c" BACKGROUND OF THE INVENTION In view of the described background, it is an object of the present invention to provide a seal for high temperature and high wear applications that is comparable to the seals described in this state of the art. It has a particularly long life. It is especially suitable for use in gas turbines and in the combustion chambers of gas turbines. 96462-960920.doc According to the first - June June seals include: - flute - components have - basic The upper portion is a planar shape and a second component, the (four) minutes 'the two portions are each attached to the first and the second component includes an end. The first component includes - having high heat resistance, = cow-side relative The first material, and the 笫_ resistance to sclerosis and wear resistance, includes a second material that is different from the first material and has a spring load-maintaining property. The first item of the request item, the first part And the second group, and the part is arched, wherein the surface is in sealing contact. The end of the first _ VIII and the component are opposite to the inner side of the arched first turtle ### The first material having high heat resistance, oxidation resistance and wear resistance at the end, and includes a component material comprising - different from the first material and having a high spring load dimension. (4) second load of yellow load maintenance The seal of the material root two of the 'single request' includes the first component and the second set of the first component and has a shape of a plane or a groove, and the first member of the seal member has an arched shape a shape that is attached to the center of the first component. (The seal of this shape is commonly referred to as a ''ring seal,.). As in the first and second independent claims, the first component includes - has The second material comprising high heat resistance, oxygen resistance and wear resistance and the second component comprises a second material different from the first material and having high spring load maintenance. The material of the first component is optimized to resist High temperature oxidation environment and high wear resistance. The high wear resistance of the first component allows the use of no wear resistance The component of the layer. Thus the 'life of the seal is a function of the intrinsic life of the material and it no longer depends on the life of the wear resistant coating or it is consumed by mechanical rubbing or other means 96462-960920.doc Do your best.
惑個别組仵之功能而被最佳地選擇。It is best chosen by confusing the functions of individual groups.
耐磨及耐熱材料且主要係一 ’密封件之第一組件包括—高 展現氧化物分散增強特徵之鈷 -錄合金。 較佳地，第一組件由高溫耐氧化之鎳或基於鈷之超合金 (super alloy)組成，例如Ren0 41TM(UNS編號N07041 :重量 百分比為 19.0Cr、5 5.0Ni、ll.OCo、lO.OMo、3.1Ti、1.5A1、 <0.3Fe、0.09C、0.01B)、Haynes 188(UNS 編號 R30188 :重 量百分比為22.0Cr、22.0Ni、37.0C〇、14.5W、至多 3.0 Fe、 0.1〇、0.901^)、1^)^1168 214(1^8編號]^07214:重量百分比 為 16.0Cr、76.5Ni、4.5A卜 3.0Fe、0.03C)、Haynes 230(UNS 編號N06230 :重量百分比為22.0Cr、55.0Ni、至多5.0C〇、 2.0M〇、14.0W、0.35A卜至多 3.0Fe、0.1C、至多 0.015B、 0.02La)及 Ultimet™(UNS編號 31233 :重量百分比為 26Cr ' 2W、5Mo、0.06C、3Fe、9Ni、0.03Si、〇·8Μη、0.08N、餘 量為Co)。 在本發明之一較佳實施例中，第二組件包括一具有高彈 簧負載維持性之材料。歸因於獲得此彈簧負載所需之形成 96462-960920.doc 1356123 水平，殺積硬化之錄-鉻合金係最合適的。較佳地，第二組 件包括一鎳超合金’諸如Alloy 718/Inconel 718™(UNS編號 N07718 :重量百分比為 i9.0Cr、52.5Ni、3.0M〇、5.1Nb、 〇.9Ti、0.5A1、18.5Fe、至多 0.08C、至多 〇.15Cu)、 Waspaloy(UNS編號N07001 :重量百分比為 i9.5Cr、57.0Ni、 13.5Co、4.3Mo、3.0Ti、1.4A 卜至多 2.〇Fe、〇.〇7C、0.006B、 0.09Zr )或 Ren6 41TM。 在本發明之一較佳實施例中，藉由滾軋成形具有一或多 個迴旋之彈簧負載組件。以此方式應用於具有兩部分之第 _ 一組件，其中每一部分皆具有一或多個迴旋，或應用於具 有一部分之第二組件。 在第一變體中，以過延伸之"u"成形彈簧負載組件。在另 一變體中，將彈簧負載組件滾軋成具有若干曲線。在一特 定變體中，將第二組件滾軋成三個或三個以上迴旋。 在本發明之另一較佳實施例中，第二組件由兩部分組 成，該等兩部分各以過延伸之，，u”成形或具有若干迴旋，且 其附著至第一組件之一側上之相對末端。 · 在本發明之一特定實施例中，具有基本上為平面形狀之 第一組件具有—較佳地置放於基本上為+面之組件中心之 微槽形狀。該組件之總體形狀保持基本上平面（與具有"碗 形狀相對）。該形狀允許第一組件之熱膨服，使得與鄰近 組件之密封接觸之品質不會減少。 在本發明之另一較佳實施例中，使第一組件之厚度最佳 地適應其耐氧化性功能，且使第二組件之厚度最佳地適應 96462-960920.doc -10- 比6123 其具有彈簧負載之功能。為此，密封件包括-在〇.5至5範 圍内之第一挺件之厚度與第二組件之厚度的最佳比率。 在本發m較佳實施例中’密封件包括用於使冷卻 質通過之-或若干開口。該等開口被置放（取決於其用途） 於第-組件或第^組件i或於第一肖第二組件i。在第二 組件為迴旋形狀之情況下，肖口排列於迴旋部分之平面、 非彎曲部分上。 對密封件、周圍區域及鄰近組件之冷卻減少了密封件上 =熱負載，且進-步改良了第二組件之彈簧負載維持性。 兩彈簧負載維持性及耐熱性係僅藉由使用一材料而難以達 成之兩特徵。然而，因為彈簧負載維持性係溫度之函數， 所以熱負載之減少會增加經過更長時間時期維持彈簧之能 力。 在上文所提到之實施例中，鎢惰性氣體焊接使第一與第 二組件彼此附著。由該類型之焊接所產生之超合金展現良 好的均一機械特性，但其可藉由諸如雷射焊接之其它焊接 技術而被接合。 根據本發月之&、封件適當地應用於氣體渦輪機之燃燒器 中’且特別係應用於與燃《器外殼壁平行排列以提供外殼 壁之熱保護的兩鄰近襯墊區段之間。冑封件被排列成使得 第一組件於兩鄰近襯墊區段之間延伸且接觸襯墊區段之面 對外殼壁之表面。所實現之第二組件具有兩迴旋部分該 等部分附著至第一組件之相反側、特別是附著至與襯墊區 段之表面相接觸之侧。該等兩部分各遠離第一組件及概墊 96462-960920.doc -11 - 1356123 區段之表面廷伸至燃燒器外殼壁。第一組件及第二組件之 兩部分與燃燒器外殼壁共同形成一空間，冷卻介質藉由通 過排列於迴旋部分中之冷卻孔進入且藉由第一組件中之冷 卻孔退出而流過該空間。 根據本發明之密封件進一步適當地應用於固定葉片之平 臺中之凹槽’以用於密封氣體渦輪機及涡輪機外殼（平臺排 列於其上）中之熱氣空間。 【實施方式】 根據本發明之密封件可應用於任何兩組件之間之密封， 其中一組件曝露於高溫，例如氣體渦輪機之燃燒器中高達 1400 C之高溫。該密封件之其它應用係應用於航天工業 中，例如對於喷嘴密封件。 圖1中展示本發明之一特定實施例之橫截面。根據本發明 之密封件1應用於氣體渦輪機之燃燒器。具有圓形橫戴面之 燃燒器外殼壁3包圍燃燒器室2。燃燒器外殼壁3填充有一系 列圓周排列之襯墊區段4,其保護燃燒器外殼壁3免受燃燒 器至2中之兩溫氣體。溫度達到高達14〇〇它。 (該密封件同樣可應用於具有其它形狀之燃燒器，例㈣ 形形狀之燃燒器）。 槪塾區段4具有與燃燒器外殼壁之彎曲-致之略微彎曲 之形狀。為便利對燃燒器壁進行附著，每一區段4係沿著其 每一側成形，使得其在面對心之側上提供—凹槽。夹甜帶 6排列在每1槽中且藉由螺栓細附著至燃燒器壁3之襯 96462-960920.doc 1356123 襯墊區段4由耐熱材料製成以保護燃燒室壁3。為進一步 熱保護’此外可藉由一諸如空氣或蒸汽之冷卻介質來冷卻 燃燒室’該冷卻介質絲自壓_及/或被外部地饋入並被 引導至燃燒室壁3與襯墊區段4之間β為防止高溫氣體通過 鄰近觀塾區段間具有給定寬度之間隙到達燃燒室壁，將密 封件1排列在鄰近襯墊區段4之間且其沿著燃燒室之長度在 某長度上延伸（在圖式之平面外之方向中）。考慮到使冷卻所 必要之流體體積最小化，密封件丨進一步控制冷卻流體之流 動及體積。 圖2以詳細之細知展示了置放於鄰近襯墊區段4之間的密 封件1。岔封件之中心部分7或第一組件與襯墊區段4之面對 燃燒器外殼壁3的表面8相接觸。密封件之第二組件之兩部 分（彈簧負載部分9)與燃燒器外殼壁3之表面1〇相接觸。彈簧 負載部分9分別對襯墊區段4與外殼壁3之表面8與1〇提供密 封接觸，使得在密封件丨與燃燒器外殼壁3之間形成一密封 空間丨1。自空間17於箭頭12之方向中通過夾鉗帶6引導之通 道13，將取自壓縮機之冷卻空氣引導至襯墊區段々與燃燒器 外殼壁3之間。（夾鉗帶6藉由螺栓20固定至燃燒器壁3)。冷 部空氣經由通道13到達夾鉗帶6與密封件丨之彈簧負載部分 9之間的空間14。自該處，冷卻空氣通過置放於迴旋彈簧負 載部分9之平坦區中的冷卻孔15且到達至密封件内之空間 11中’自内部對流性地冷卻該密封件且最終通過密封件i之 中心部分中的沖洗孔丨6退出而進入燃燒室2中。 選擇用於襯墊區段之材料以抵抗燃燒室2内高達14〇(rc 96462-960920.doc 13 1356123 之典型溫度。密封件1之中心部分7曝露於大約llOOt之溫 度歸因於达、封件為其自身所創造之分離熱氣與冷卻流體 之熱屏蔽效果，密封件之彈簧負載部分9曝露於更低之溫 度。空間11内之溫度在40(rc之600。0之範圍内。在燃燒室 壁3與襯塾區段4之間的空間17中，溫度可大約為55代。歸 因於一壓力差，冷卻氣體不會自空間14到達空間1 7 ^ 密封件之主要功能係防止空氣自空間14直接到達至燃燒 室2中且替代地進人空間。藉此減少了用於冷卻之所必 要之空氣體積。此密封在燃燒室中在燃燒器之某些運作點 處之振動的情況下特別困難。燃燒室壁1〇與襯墊區段之表 面8之間的標稱距離在若干毫米之範圍内。因低循環疲乏而 造成之移動可導致標稱距離產生25%之變化，而因振動而 造成之移動可進一步導致標稱距離產生高達7%之變化。因 此，彈簧負載部分9在其所曝露之溫度下在全部延長時間中 具有維持其彈簧負載之最佳能力係重要的。另一方面，中 心部分7必須具有高耐熱性以及高耐磨性，因為振動在靠著 襯墊區段4之表面8的密封點處會導致大範圍的磨損。因為 該等原因’所以彈簧負載部分由在高達大約63〇。〇之溫度下 具有高彈簧負載維持性的材料製成。中心部分7由高耐熱材 料以及耐磨材料製成’但未必提供高彈簧負載維持性。 較佳地’中心部分7由一諸如UltimetTMi钻-鎳合金製 成。另外可能之材料為Haynes 25 (UNS編號R3 0605 :重量百 分比為 20.0Cr、lO.ONi、50.0C〇、15.0W、3.0Fe、〇.i〇c、 0·15Μη) ' PM100〇tm(dIN 2.4869 :重量百分比為 〇 3A1、 96462-960920.doc -14- 1356123 20Cr、至多 3Fe、75.6-78.9Ni、〇.5Ti、0.6Y2O3)、 PM2000TM(DIN 1.4768 :重量百分比為 5 5Ah 19Cr、74 5Fe、 〇.5Ti、0.5Y2O3)、PK33tm(英國標準DTD 5〇57 :重量百分 比為1_7-2.5人卜至多〇.〇〇53、至多0〇7(：、12_16(：〇、16_2〇(：1>、 至多 0.2Cu、至多 IFe、至多 〇.5Mn、5-9Mo、至多 0.015S、 至多 0.5Si、1·5-3Τι、至多 〇.〇6ζΓ、剩餘為 Ni)、Rend 41福之 版本。 因為該材料在耐磨性以及耐熱性與耐氧化性方面係較好 的，所以在第一組件上無需保護性塗層。較佳地，彈簧負 籲 載部分9由因在咼達630°C之溫度下具有較好的彈簧負載維 持性而已知之Inconel 7i8(UNS編號N〇7718 :重量百分比為 19,0Cr、52,5Ni、3.0M〇、5.1Nb、0.9Ti、0.5A卜 18.5Fe、 至多0.08C、至多〇.i5Cu)或鎳·鉻合金製成β 作為一選項，第一組件可塗佈有一耐磨塗層以進一步增 加其壽命。 作為另一選項，密封件之第一組件亦可塗佈有一耐氧化 塗層以在燃燒室中進一步增加其抗氧化介質之抗性。 籲 圖3展示根據本發明之密封件i之一區。其可沿著燃燒室 壁之長度延伸。密封件之第—或中心部分7在其橫截面中以 類似於一角形槽而成形’該角形槽沿著其平行於與密封件 之第一組件之兩部分9相接觸之線而行進的中線對稱。該形 狀之優點在於：其允許因密肖件及/或接觸密封件之周圍組 件之振動或熱膨脹而造成之變形。或者，槽形狀亦可彎曲。 在-變體中’若振動及尺寸之潛在變化較不嚴重，則中心 96462-960920.doc 15 1356123 部分亦可（例如）具有一平坦之形狀。中心部分7沿著其中線 具有一系列沖洗孔16，用於使冷卻空氣通過其中退出而至 燃燒室2。 迴旋彈簣負載部分9具有三個或三個以上迴旋，且冷卻孔 15適當地置放於該等迴旋之平坦區上，其未被機械地負載。 藉由一經脈衝之鎢惰性氣體（TIG)焊接18附著彈簧負載 部分9與第一部分7之兩不同材料。該類型之焊接會產生一 作為mtimet™(UNS編號31233 :重量百分比為26Cr、2W、 5Mo、0.06C、3Fe、9Ni、〇.〇3Si、〇.8Mn、〇.〇8N、餘量為Abrasion resistant and heat resistant materials and primarily a first component of the 'seal' include a high cobalt-recording alloy exhibiting oxide dispersion enhancing characteristics. Preferably, the first component consists of high temperature oxidation resistant nickel or a cobalt based super alloy, such as Ren0 41TM (UNS No. N07041: weight percent 19.0Cr, 5 5.0Ni, ll.OCo, lO.OMo) , 3.1Ti, 1.5A1, <0.3Fe, 0.09C, 0.01B), Haynes 188 (UNS No. R30188: weight percentage is 22.0Cr, 22.0Ni, 37.0C〇, 14.5W, up to 3.0 Fe, 0.1〇, 0.901 ^), 1^)^1168 214(1^8号]^07214: Weight percent is 16.0Cr, 76.5Ni, 4.5A Bu 3.0Fe, 0.03C), Haynes 230 (UNS No. N06230: 22.0Cr by weight, 55.0Ni, up to 5.0C 〇, 2.0M 〇, 14.0W, 0.35A 卜 up to 3.0Fe, 0.1C, up to 0.015B, 0.02La) and UltimetTM (UNS No. 31233: weight percentage 26Cr ' 2W, 5Mo, 0.06 C, 3Fe, 9Ni, 0.03Si, 〇·8Μη, 0.08N, and the balance is Co). In a preferred embodiment of the invention, the second component includes a material having a high spring load retention. Due to the formation required to obtain this spring load 96462-960920.doc 1356123 level, the sclerotherapy-chromium alloy system is most suitable. Preferably, the second component comprises a nickel superalloy such as Alloy 718/Inconel 718TM (UNS No. N07718: weight percent i9.0Cr, 52.5Ni, 3.0M 〇, 5.1 Nb, 〇.9Ti, 0.5A1, 18.5 Fe, up to 0.08C, up to 〇.15Cu), Waspaloy (UNS No. N07001: weight percentage is i9.5Cr, 57.0Ni, 13.5Co, 4.3Mo, 3.0Ti, 1.4A, up to 2. 〇Fe, 〇.〇7C , 0.006B, 0.09Zr ) or Ren6 41TM. In a preferred embodiment of the invention, a spring loaded assembly having one or more convolutions is formed by roll forming. In this way, it is applied to a first component having two parts, each of which has one or more convolutions, or is applied to a second component having a portion. In the first variant, the over-extended "u" shaped spring load assembly. In another variation, the spring loaded assembly is rolled to have a number of curves. In a particular variation, the second component is rolled into three or more convolutions. In another preferred embodiment of the invention, the second component is comprised of two parts, each of which is over-extended, u" shaped or has a plurality of convolutions, and which are attached to one side of the first component The opposite end. In a particular embodiment of the invention, the first component having a substantially planar shape has a microgroove shape that is preferably placed in the center of the substantially +-sided component. The shape remains substantially planar (as opposed to having a "bowl shape). This shape allows thermal expansion of the first component such that the quality of the sealing contact with adjacent components is not reduced. In another preferred embodiment of the invention The thickness of the first component is optimally adapted to its oxidation resistance function, and the thickness of the second component is optimally adapted to 96462-960920.doc -10- than 6123, which has a spring load function. Including - an optimum ratio of the thickness of the first member in the range of 〇.5 to 5 to the thickness of the second component. In the preferred embodiment of the present invention, 'the seal includes means for passing the cooling mass - or a number of openings. The openings are placed (depending on its use) in the first component or the second component i or in the first second component i. In the case where the second component is in a convoluted shape, the opening is arranged on the planar, non-curved portion of the convoluted portion. Cooling of the seal, surrounding area and adjacent components reduces the seal on the heat load and further improves the spring load maintenance of the second component. The two spring load maintainability and heat resistance are only by using a material However, because of the spring load maintaining the temperature of the system, the reduction in thermal load increases the ability to maintain the spring over a longer period of time. In the above-mentioned embodiments, the tungsten inert gas The welding causes the first and second components to adhere to each other. The superalloy produced by this type of welding exhibits good uniform mechanical properties, but it can be joined by other welding techniques such as laser welding. &, the seal is suitably used in the burner of a gas turbine' and in particular for the two adjacent sides arranged in parallel with the fuel casing wall to provide thermal protection of the casing wall Between the gasket segments, the dam seals are arranged such that the first component extends between the two adjacent liner segments and contacts the surface of the liner segment facing the outer casing wall. The second component is realized with two turns A portion of the portions are attached to opposite sides of the first component, particularly to the side in contact with the surface of the pad section. The two portions are each remote from the first component and the pads 96462-960920.doc -11 - 1356123 The surface of the section extends to the wall of the burner casing. The two parts of the first component and the second component together with the wall of the burner casing form a space through which the cooling medium enters through the cooling holes arranged in the swirling portion The cooling holes in an assembly exit and flow through the space. The seal according to the invention is further suitably applied to the grooves in the platform of the fixed blade for sealing the gas turbine and the turbine casing (on which the platform is arranged) The hot air space. [Embodiment] The seal according to the present invention can be applied to the seal between any two components, one of which is exposed to high temperatures, such as a high temperature of 1400 C in a gas turbine burner. Other applications of the seal are used in the aerospace industry, such as for nozzle seals. A cross section of a particular embodiment of the invention is shown in FIG. The seal 1 according to the invention is applied to a burner of a gas turbine. A burner casing wall 3 having a circular cross-face surrounds the burner chamber 2. The burner housing wall 3 is filled with a series of circumferentially arranged pad segments 4 that protect the burner housing wall 3 from the two gases in the burner to two. The temperature reaches up to 14 〇〇 it. (The seal is equally applicable to burners having other shapes, such as (four) shaped burners). The weir section 4 has a shape that is slightly curved from the curvature of the burner casing wall. To facilitate attachment of the burner walls, each section 4 is formed along each of its sides such that it provides a groove on the side facing the heart. The strips 6 are arranged in each of the slots and are finely attached to the liner of the burner wall 3 by bolts. 96462-960920.doc 1356123 The gasket section 4 is made of a heat resistant material to protect the combustion chamber wall 3. For further thermal protection 'moreover the combustion chamber can be cooled by a cooling medium such as air or steam. The cooling medium wire is self-pressed and/or externally fed and guided to the combustion chamber wall 3 and the gasket section. Between 4, to prevent high temperature gas from reaching the combustion chamber wall through a gap having a given width between adjacent viewing pockets, the sealing member 1 is arranged between adjacent gasket segments 4 and along the length of the combustion chamber at a certain Extends in length (in the direction out of the plane of the drawing). The seal further controls the flow and volume of the cooling fluid in view of minimizing the volume of fluid necessary to cool. Figure 2 shows in detail the seal 1 placed between adjacent liner segments 4. The central portion 7 or the first component of the crucible seal is in contact with the surface 8 of the gasket section 4 facing the burner casing wall 3. The two parts of the second component of the seal (spring load portion 9) are in contact with the surface 1 of the burner casing wall 3. The spring load portion 9 provides sealing contact to the surfaces 8 and 1 of the liner section 4 and the outer wall 3, respectively, such that a sealed space 形成1 is formed between the seal 丨 and the burner casing wall 3. From the space 17 in the direction of the arrow 12, the passage 13 guided by the clamp belt 6 guides the cooling air taken from the compressor between the gasket section 々 and the burner casing wall 3. (The clamp band 6 is fixed to the burner wall 3 by bolts 20). The cold air reaches the space 14 between the clamp band 6 and the spring loaded portion 9 of the seal jaw via the passage 13. From there, the cooling air passes through the cooling holes 15 placed in the flat zone of the convoluted spring load portion 9 and reaches the space 11 in the seal 'cooling the seal from the inside convectively and finally through the seal i The flushing port 6 in the center portion exits and enters the combustion chamber 2. The material used for the liner section is selected to withstand a typical temperature of 14 〇 in the combustion chamber 2 (rc 96462-960920.doc 13 1356123. The central portion 7 of the seal 1 is exposed to a temperature of about llOOt due to the seal The thermal shielding effect of the separated hot gas and cooling fluid created by itself, the spring loaded portion 9 of the seal is exposed to a lower temperature. The temperature in the space 11 is in the range of 40 (rc 600. 0. In the space 17 between the chamber wall 3 and the lining section 4, the temperature can be about 55 generations. Due to a pressure difference, the cooling gas does not reach the space from the space 14 7 ^ The main function of the seal is to prevent air From space 14 directly into combustion chamber 2 and instead into the space, thereby reducing the volume of air necessary for cooling. This seal is vibrating in the combustion chamber at certain operating points of the burner. This is particularly difficult. The nominal distance between the wall of the combustion chamber 1 and the surface 8 of the pad section is in the range of a few millimeters. Movement due to low cycle fatigue can result in a 25% change in the nominal distance. Movement due to vibration The step causes the nominal distance to produce a variation of up to 7%. Therefore, it is important that the spring loaded portion 9 has the optimum ability to maintain its spring load for all of its extended time at the temperature it is exposed to. It is necessary to have high heat resistance and high wear resistance because the vibration causes a wide range of wear at the sealing point against the surface 8 of the pad section 4. For these reasons, the spring load portion is up to about 63 〇. Made of a material with high spring load retention at the temperature of the crucible. The central portion 7 is made of a highly heat resistant material and a wear resistant material 'but does not necessarily provide high spring load maintenance. Preferably the 'central portion 7' consists of an element such as UltimetTMi Made of drill-nickel alloy. Another possible material is Haynes 25 (UNS No. R3 0605: 20.0Cr, lO.ONi, 50.0C〇, 15.0W, 3.0Fe, 〇.i〇c, 0·15Μη) ' PM100〇tm (dIN 2.4869: weight percentage is 〇3A1, 96462-960920.doc -14-1356123 20Cr, up to 3Fe, 75.6-78.9Ni, 〇.5Ti, 0.6Y2O3), PM2000TM (DIN 1.4768: weight percentage 5 5Ah 19Cr, 74 5F e, 〇.5Ti, 0.5Y2O3), PK33tm (British standard DTD 5〇57: weight percentage is 1_7-2.5 person to most 〇.〇〇53, up to 0〇7 (:, 12_16(:〇, 16_2〇(: 1>, at most 0.2 Cu, at most IFe, at most 〇.5 Mn, 5-9 Mo, at most 0.015 S, at most 0.5 Si, 1-5-3 Τι, at most 〇.〇6 ζΓ, remaining Ni), Rend 41 Fu version. Since the material is superior in abrasion resistance as well as heat resistance and oxidation resistance, no protective coating is required on the first component. Preferably, the spring negative load-bearing portion 9 is known as Inconel 7i8 (UNS number N〇7718: weight percent 19,0Cr, 52, 5Ni) due to better spring load maintenance at a temperature of 630 ° C. , 3.0M 〇, 5.1Nb, 0.9Ti, 0.5A 卜 18.5Fe, up to 0.08C, up to 〇.i5Cu) or nickel·chromium alloy made of β as an option, the first component may be coated with a wear resistant coating Further increase its life. As a further option, the first component of the seal may also be coated with an oxidation resistant coating to further increase its resistance to oxidation media in the combustion chamber. 3 shows a region of the seal i according to the present invention. It can extend along the length of the combustion chamber wall. The first or central portion 7 of the seal is shaped in its cross-section like an angular groove. The angular groove travels along its line parallel to the two portions 9 of the first component of the seal. Line symmetry. The advantage of this shape is that it allows deformation due to vibration or thermal expansion of the components of the slanting member and/or the contact seal. Alternatively, the groove shape can also be curved. In the -variant, if the potential change in vibration and size is less severe, the portion of the center 96462-960920.doc 15 1356123 may, for example, have a flat shape. The central portion 7 has a series of flushing holes 16 along the center line for allowing cooling air to exit therethrough to the combustion chamber 2. The convoluted magazine load portion 9 has three or more convolutions, and the cooling holes 15 are suitably placed on the flat areas of the convolutions, which are not mechanically loaded. Two different materials are attached to the first portion 7 by a pulsed tungsten inert gas (TIG) weld 18 attached to the spring. This type of welding will produce one as mtimetTM (UNS No. 31233: weight percentage is 26Cr, 2W, 5Mo, 0.06C, 3Fe, 9Ni, 〇.〇3Si, 〇.8Mn, 〇.〇8N, balance is
Co)與Inc〇nel 718(UNS編號N〇7718 :重量百分比為i9 〇心、 52.5Ni、3.0M〇、5.1Nb、0.9Ti、0.5A卜 18.5Fe、至多 〇.08C、 至夕0.15 Cu)間之過渡金屬而特別適用於該應用之超合 金。沿著密封件之兩側置放焊接18之優點在於：其曝露於 一與中心部分7之十線處溫度相比更低的溫度。因此，該焊 接曝露於由熱膨脹所導致之更小的力。 或者，密封件之第一及第二組件可藉由雷射焊接而彼此 附著。 圖4展不了與圖1中所示之類型相同之類型之燃燒器襯墊 區段4的橫截面，其沿著燃燒器外殼壁之内圓周排列。其藉 由夾鉗帶6而固定至燃燒器室壁3。圖4展示了 一特別安置於 燃燒器分裂線之軸向末端處的襯墊區段4。一密封件丨，置放 於襯墊區段4之表面8與燃燒器壁3之表面1〇之間。密封件厂 具有分離包括熱氣之燃燒器室中空間2與冷卻流體之主要 功能’該冷卻流體在箭頭22之方向於襯墊區段4之間流動且 96462-960920.doc -16- 1356123 流過通過夾鉗帶6之通道13。密封件Γ包括形成棋形形狀之 第一組件21及一具有彈簧負載之第二組件9。拱形形狀之組 件21之外末端與表面8及10相接觸，且彈簧負載組件9|在組 件21之拱形的内末端之間延伸。彈簧負載組件9,包括三個迴 旋，其類似於圖丨至3中之密封件丨之彈簧負載組件9。第二 組件9’之彈簧負載分別為第一組件21與襯墊區段4及燃燒器 壁1〇的表面8及Η)之間的密封提供良好之預負载接觸。彈菁 元件可含有適當地置放於迴旋之平坦區上的冷卻沖洗孔 15’其為了更大之冷卻流動而未被機械地負載。在兩表面8 與之間因振動及低循環疲之移動而造成之變化距離的情 況下亦特別地提供密封接觸。第一組件21由一具有高耐熱 ，、耐氧化性及耐磨性之材料製造，且第二組件9,由一具有 高彈簧負載維持性之材料製造，適當之材料與結合圖⑴ 之密封件1之組件7與9所描述之材料相同。 __圖5展示了排列在-具有固定葉片31之渦輪機外殼(未圖 :)上之葉片列中的兩固定葉片平臺3〇。葉片平臺％間隔了 J間隙32 ’熱氣除非被阻擋否則可流過該間隙。葉片平 臺3〇各在其面對鄰近葉片平臺之面（enfaee)上包括一延伸 過該面長度之較大部分的凹槽33,且在此情況下，該凹槽 沿著彎曲部分延伸。 、，圖以展示了沿著圖5tlv_lv線之平臺且特別使每—鄰近 平臺〇之凹槽33彼此面對的橫截面。根據本發明之密封件 34係置放於凹槽33甲且延伸穿過間隙u，且因此自密封件 另側上之外殼密封渦輪機之熱氣空間35。在第一變 96462-960920.doc 1356123 體中以一類似於圖2中密封件之方式建構密封件34,其具有 一基本上為平面之第一組件36及一具有若干迴旋之第二組 件37。第一組件36包括用於使冷卻流動39通過之冷卻孔％。 圖6b展不了置放於葉片平臺3〇之凹槽”中之密封件狗的 第二變體。以類似於圖6a中之方式的方式成形第一組件 41，而第二組件42僅包括一形成過延伸之"u"形狀的迴旋❶ 該變體不含有冷卻孔。 原則上，所展示之所有密封件根據其在渦輪機中之置放 及該位置之冷卻需要而含有冷卻孔或無冷卻孔。 作為一選項，對於所揭示之所有密封件而言，第一組件 可塗佈有一耐磨塗層，以進一步增加其壽命。 作為另-選項，密封件之第—組件亦可塗佈有—耐氧化 塗層，以進-步增加其在燃燒室或氣體渦輪機中抗氧化介 質之抗性。 【圖式簡單說明】 圖1展示氣體渴輪機燃燒室及排列在室壁之内圓周周圍 之襯墊區段的橫截面。 圖2展示兩鄰近襯墊區段之詳細圖，其中根據本發明之密 封件排列於兩襯塾區段之間。 圖3展示根據本發明之圖丨及2之密封件的透視圖。 圖4展示根據本發明之具有拱形形狀之第一組件及延伸 於拱形之内末端之間之第二組件的另一密封件。 圖5展示用於在凹槽中應用根據本發明之密封件之固定 葉片平臺。 96462-960920.doc • 18· 1356123 圖6a及6b分別展示根據本發明之應用於氣體渦輪機葉片 平臺中之凹槽之密封件的第一與第二變體。 【主要元件符號說明】 1，1' , 34, 40 密封件 2 燃燒室/燃燒器室 3 燃燒器外殼壁 4 襯塾區段 6 夾甜帶 7 第一組件/中心部分 8 表面 9 彈簧負載部分/第二組件 9'，37, 42 第二組件 10 表面/燃燒室壁 11 密封空間 12 箭頭 13 通道 14, 17 空間 15, 15' , 38 冷卻孔 16 沖洗孔 18 焊接 20 螺栓 21, 36, 41 第一組件 22 箭頭 30 葉片平臺 31 固定葉片 32 間隙 96462-960920.doc -19· 1356123 33 凹槽 35 熱氣空間 39 冷卻流動 96462-960920.docCo) and Inc〇 nel 718 (UNS No. N〇7718: weight percentage is i9 〇 heart, 52.5Ni, 3.0M 〇, 5.1Nb, 0.9Ti, 0.5A 卜 18.5Fe, up to 〇.08C, 0.15 Cu) The transition metal between them is particularly suitable for the superalloys of this application. The advantage of placing the weld 18 along both sides of the seal is that it is exposed to a lower temperature than the temperature at the ten line of the central portion 7. Therefore, the solder joint is exposed to a smaller force caused by thermal expansion. Alternatively, the first and second components of the seal may be attached to each other by laser welding. Figure 4 shows a cross section of a combustor liner section 4 of the same type as that shown in Figure 1, which is arranged along the inner circumference of the burner casing wall. It is fixed to the burner chamber wall 3 by means of a clamp belt 6. Figure 4 illustrates a pad section 4 that is specifically disposed at the axial end of the burner split line. A seal member is placed between the surface 8 of the liner section 4 and the surface 1 of the burner wall 3. The seal factory has the primary function of separating the space 2 and the cooling fluid in the burner chamber including hot gas. The cooling fluid flows between the gasket segments 4 in the direction of the arrow 22 and flows 96462-960920.doc -16 - 1356123 Pass the channel 13 of the clamp belt 6. The seal Γ includes a first component 21 that forms a chevron shape and a second component 9 that has a spring load. The outer end of the arched shape member 21 is in contact with the surfaces 8 and 10, and the spring loaded assembly 9| extends between the arcuate inner ends of the assembly 21. The spring loaded assembly 9, comprising three convolutions, is similar to the spring loaded assembly 9 of the seals of Figures 3 through 3. The spring load of the second component 9' provides good preload contact for the seal between the first component 21 and the pad section 4 and the surfaces 8 and Η of the burner wall 1 分别, respectively. The elastomeric element may contain a cooling rinsing hole 15' suitably placed on the flattened area of the convolution which is not mechanically loaded for greater cooling flow. Sealing contact is also provided in particular in the case of varying distances between the two surfaces 8 and due to the movement of vibration and low cycle fatigue. The first component 21 is made of a material having high heat resistance, oxidation resistance and wear resistance, and the second component 9 is made of a material having high spring load maintenance, and a suitable material and a seal of the combination (1) The components 7 and 9 are the same as described in 9. __ Figure 5 shows two fixed blade platforms 3〇 arranged in a row of blades on a turbine casing (not shown) having fixed blades 31. The blade platform % is spaced J gap 32 'hot air can flow through the gap unless it is blocked. The vane platform 3 includes a recess 33 extending over a larger portion of the length of the face on its face facing the adjacent vane platform, and in this case, the recess extends along the curved portion. The figure shows a cross section along the platform of the Figure 5tlv_lv line and in particular the grooves 33 of each of the adjacent platform turns facing each other. The seal 34 according to the present invention is placed in the recess 33 and extends through the gap u, and thus the outer casing on the other side of the seal seals the hot gas space 35 of the turbine. In the first variation 96626-960920.doc 1356123, a seal 34 is constructed in a manner similar to the seal of FIG. 2, having a substantially planar first component 36 and a second component 37 having a plurality of convolutions. . The first component 36 includes a cooling hole % for passing the cooling flow 39. Figure 6b shows a second variant of the seal dog placed in the groove of the blade platform 3. The first component 41 is shaped in a manner similar to that of Figure 6a, while the second component 42 includes only one Forming an extended "u" shape of the turret ❶ This variant does not contain cooling holes. In principle, all of the seals shown contain cooling holes or no cooling depending on their placement in the turbine and the cooling requirements at that location. As an option, for all of the disclosed seals, the first component may be coated with a wear resistant coating to further increase its life. As an alternative, the first component of the seal may also be coated with - an oxidation resistant coating to further increase its resistance to oxidation media in a combustion chamber or gas turbine. [Simplified Schematic] Figure 1 shows a gas turbine combustion chamber and is arranged around the inner circumference of the chamber wall. Cross section of the pad section. Figure 2 shows a detailed view of two adjacent pad sections, wherein the seal according to the invention is arranged between the two pad segments. Figure 3 shows a figure 2 and 2 according to the invention. A perspective view of the seal. 4 shows a further assembly of the first component having an arched shape and a second component extending between the inner ends of the arch according to the invention. Figure 5 shows a seal for applying the seal according to the invention in a groove Fixed blade platform. 96462-960920.doc • 18· 1356123 Figures 6a and 6b show first and second variants of a seal applied to a groove in a gas turbine blade platform, respectively, according to the present invention. Description] 1,1' , 34, 40 Seal 2 Combustion Chamber / Burner Chamber 3 Burner Housing Wall 4 Lining Section 6 Sandwich Ribbon 7 First Assembly / Center Section 8 Surface 9 Spring Load Section / Second Assembly 9',37, 42 Second assembly 10 Surface/combustion chamber wall 11 Sealed space 12 Arrow 13 Channel 14, 17 Space 15, 15', 38 Cooling hole 16 Flush hole 18 Welding 20 Bolt 21, 36, 41 First component 22 Arrow 30 Blade platform 31 Fixed blade 32 Clearance 96462-960920.doc -19· 1356123 33 Groove 35 Hot air space 39 Cooling flow 96462-960920.doc