200928075 九、發明說明： 【發明所屬之技術領域】 本發明係關於用於一燃氣渦輪機之澆鑄旋轉葉片，且特 別係關於考慮到葉片之可製造性的該葉片内之二冷卻結構 的設計。 【先前技術】 用於燃氣渦輪機之渦輪葉片經設計與製造以經得起該燃 氣渦輪機操作期間的高溫。這樣的渦輪葉片包括一内冷卻 © 結構，而一冷卻流體（一般為空氣）係通過此内冷卻結構。 冷卻二乳般疋自該燃氣渴輪機發動機之一壓縮機内抽 出。然而如此萃取空氣會減少發動機之總體性能。為藉由 減少空氣消耗量且仍確保葉片之充分冷卻以減少對該發動 機性能之影響，内葉片冷卻結構經設計為最佳的冷卻效 率。這樣的設計舉例而言係揭示於美國專利第6，139 269 號與美國專利第5,403,159號中。美國專利第6，139, 269號 談揭不一具有數個通道之螺旋形冷卻結構，該等通道係在葉 片之縱向方向延伸’且連接至在該葉片根部處之一進口或 連接至該葉片尖端之出口，或者藉由一大約180。的轉向處 或彎曲而連接至一另一縱向通道。該冷卻結構進一步包括 多個在該等縱向通道之壁上的脫扣條帶（trip strip)，該等 脫扣條帶定位在與流過該通道的方向成大約45。。在美國 專利第6,139,269號之特殊構造此外包括在接近該葉片根部 之每個180。轉向處之一空氣再供應通道，其允許空氣由該 葉片根部進入該通道内。 133517.doc 200928075 具有這樣類型的内冷卻結構之满輪葉片通常是藉由一炼 模鑄造製程予以濟铸，而此溶模鎮造製程係使用定義該冷 卻結構的模芯。該模芯是由一可遽出材料（諸如陶幻所製 成在成里製程後，該陶究模芯係經由一遞據製程予以移 除。 該瀝濾製程對於在180。轉向處之區域内的之模芯材料之 • 料是困難的，且仍有—風險即剩餘的模芯材料遺留在該 冷卻通道内’且因此阻礙冷卻介質流過該冷卻通道。 為了減少此風險’係於冷卻結構壁的18〇。轉向處區域内提 供一開口，以瀝濾出剩餘的模芯材料。在一些已知的燃氣 渦輪機葉片内，此開口是藉由一如揭示於舉例而言美國專 利第6,634,858號之板或塞予以再次封閉。 【發明内容】 本發明之目的是提供具有一内冷卻結構之燃氣渦輪機旋 轉葉片，該内冷卻結構具有一允許在此等最新科技方面之 φ 經改良的可製造性，同時至少保持該内冷卻結構之既有冷 卻性能之設計。 一燃氣渦輪機旋轉葉片包括一内冷卻結構，該内冷卻結 構具有至少二個在葉片縱向方向延伸之冷卻通道，至少一 進口在該葉片根部之區域，及至少一出口在該葉片尖端之 區域從一冷卻通道至該葉片外。該葉片進一步包括一在其 根部區域之用於冷卻空氣的充氣腔，該進口自此充氣腔延 伸至一冷卻通道。該第一冷卻通道沿著冷卻流體之方向自 該葉片根部區域延伸至該葉片尖端區域。該第二冷卻通道 133517.doc 200928075 自該尖端延伸至該根部區域。第一與第二冷卻通道藉由在 該葉片尖端區域内一弯曲或轉向處而在該葉片尖端區域彼 此流體連接。該第三冷卻通道再由該根部延伸至該尖端， 而第二與第三冷卻通道藉由該葉片根部區域内一轉向處或 彎曲而彼此流體連接。 為了經由瀝濾以從該彎曲上移除—模芯材料且減少模芯 材料殘留在該彎曲内之風危，一開口是被提供在該冷卻结 構壁内，自該充氣腔延伸至在該葉片根部區域内之從該第 一到第二冷卻通道之該彎曲或轉向處。該開口提供一從該 彎曲至該葉片之根部並至該葉片之外部的直接流體連接。 特別地，該開口與該葉片之根部區域是如此的以允許一液 態//IL體直接且實質在該葉片内冷卻結構之外的縱向葉片方 向上流動。此允許該液體的模芯材料完全地離開該葉片， 而無需穿過任何反轉或靜滯區。因此，可防止液體的模芯 材料殘留在該結構内成為剩餘流體。因此，可確保在該葉 片操作時通過該内冷卻結構的冷卻空氣之流動。 為了簡化並從而划算地製造該燃氣渦輪機旋轉葉片，在 該内結構的彎曲或i 8 〇。轉向處之開口在該渦輪機内的該葉 片操作前並不再關閉。由於在18〇。轉向處之該開口會影響 該内冷卻結構之空氣動力學與冷卻空氣之分佈，因此該冷 卻通道之設計是考慮到冷卻功能與效率而予以調適及最佳 化。 根據本發明，在冷卻流體方向上從在該根部區域内之充 氣腔延伸到葉片尖端區域的該第一冷卻通道包括與該冷卻 133517.doc 200928075 流體之流動方向成90±1〇。之一角度的紊流器或脫扣條帶。 另外’藉由一轉彎處與該第一冷卻通道流體連接的該第二 冷卻通道包括複數個脫扣條帶或紊流器。最後，結合在該 第一冷卻通道内的特定方位之脫扣條帶，在該第一與第二 冷卻通道内之脫扣條帶是予以配置且按規定尺寸形成的， 而使其高度與相鄰脫扣條帶之間的距離之比率為1〇±2。 在本發明之一例示性實施例中’在該第二冷卻通道之該 等脫扣條帶經配置為與該流動方向成45。±丨〇。之角度。在 ® 另一例不性實施例中，該第三冷卻通道包括複數個脫扣條 帶，該等脫扣條帶經配置為從該流動方向至該脫扣條帶之 方向成45°士 10°之一角度。 如上所述，在從該第二至該第三通道的轉向處之開口會 影響在該冷卻結構内的冷卻空氣之分配。特別地，在該位 置之一非封閉開口將導致自該根部區域之充氣腔内通過該 第一與第二通道的氣流之減少，及自該充氣腔内通過該開 Q 口直接至該第二通道的氣流之增加。根據本發明之設計方 法以特別配置於該第一與第二通道内之脫扣條帶的形式， 允許該冷卻氣流之最佳化與通過該第一與第二通道之氣流 的重建。其從而確保該整個葉片之充分與均勻的冷卻。根 據本發明的脫扣條帶之設計允許補償從該第一通道開頭至 該第三通道開頭的非常小之液壓損失。補償該低壓損失是 藉由在該第一與第二通道内的泵唧力而達到，而此泵唧力 是歸因於沿著此等通道之冷卻空氣的對流溫度的增加。 該冷卻空氣之流動動力是連同以下圖示而予以詳細說 133517.doc -9- 200928075 明。 如上所述’根據本發明的葉片冷卻結構之設計由於在接 近該葉另的根部之轉向處的開口而允許最佳化的製造。該 設計在澆鑄後不需方法以關閉該開口。在該冷卻通道内的 該等脫扣條帶之特定設計補償液壓損失並從而確保該第一 與第二通道内之充分冷卻。此設計在維持冷卻性能的同 •時，進而允許改良與簡化的製造。 【實施方式】 圖1顯示從一根部2縱向延伸至一尖端部分3之旋轉燃氣 渦輪機葉片1 » 圖2顯示葉片之冷卻結構，該葉片具有一在其根部區域 内用於冷卻進入該冷卻結構内的空氣之充氣腔4,複數個 至少二個分別自該根部2之充氣腔4延伸至該尖端3且自該 尖端3延伸至該根部2之縱向冷卻通道5_7。該等縱向通道 係藉由大約180。之轉向處而彼此流體連接。 〇 該氣流（如箭頭所標示）從該充氣腔4穿過在該第一冷卻 通道5的開頭之進π8至在該葉片尖端的第—通道之末端， 並繞過-大約18〇。之轉向處。其接著沿著該第二冷卻通道 6流向另一連接該第二冷卻通道6與該第三冷卻通道7的 180。轉向處1〇。該冷卻空氣最終流經該第三冷卻通道7至 ^葉片並絰由在該葉片尖端上之出口。離開該冷 構。 、 在接近該葉片的根部之轉向^1Λ Ba丄 将问處10，係提供一開口或通道 12以在澆鑄之後瀝濾出模芯 果〜材枓，並允許所有已溶解的模 133517.doc 200928075 心材料經由s亥充氣腔4而離開該冷卻結構，使得模芯材料 不會殘留在轉向處10内。由於此開口 12，冷卻空氣可更容 易地從該充氣腔4直接通過該第三冷卻通道7,而無需通過 第一與第二冷卻通道5與6。然而，由於根據本發明之第一 與第二冷卻通道之特殊設計，在位置A與位置b之間的壓 '降會確保一冷卻氣流通過通道5與6。 一壓力損失是歸因於流體阻力，並取決於空氣速度之二 次方、該通道之形狀、該通道壁之光滑度以及紊流器或脫 ® 扣條帶之形狀。所有根據本發明之這些特點會使得在該第 二通道7的開頭位置B的氣壓是低於在該第一通道$的開頭 位置A的氣壓。 另外’因著葉片之旋轉而產生一抽取作用。該氣壓因該 抽取作用而隨著增加的該通道半徑而增加，特別在一給定 之角速度下與半授的一次方之差成比例。因此在該第一通 道5内，壓力隨著自位置A至位置B之遞增的半徑而增加。 Q 在該第二通道6内，壓力隨著自位置B至位置c之遞減的半 徑而減少’以其在通道5内增加的相同量而減少。該最終 效果因此將為零。此外，然而，冷卻空氣會從通道之熱對 流壁獲得一熱流量，以增加冷卻空氣之溫度。因此，在該 第二通道6内的冷卻空氣之溫度是高於其在第一通道5内之 溫度。此溫度變化同樣影響該在第一與第二通道内之抽取 作用。在該第二通道内之較高溫度使得沿著該第二通道6 之抽取作用小於其在第一通道5内之作用。因此，相較於 在位置A之壓力，在位置B之壓力是較低的導致一沿著 1335I7.doc -11 - 200928075 通道5與6之有效冷卻氣流。 —所述^^卩通道之流體阻力取決於（特別是）該通道 十尤其疋紊流器或脫扣條帶13之設計。圖2顯示本 、之f施例，其包括在該第一冷卻通道5内之紊流器 .&脫4條帶〗3該等奈流器或脫扣條帶係配置在與冷卻流 的方向成90±1〇。（如箭頭所標示）。圖3a顯示該等脫扣條帶 ‘ 找置與相對尺寸的剖面。每-脫扣條帶具有—從該通道 5之㈣測量之高b ’且每一脫扣條扣是配置在與相鄰 脫扣條帶間隔—距離4處。該高度11與距離d是成-ι〇±2的 比率。該等脫扣條帶顯示為具有一矩形形狀。然而，其亦 可為任何其他空氣動力學上適合的剖面形狀。圖3b顯示該 等脫扣條帶相對於冷卻氣流方向之方位。該角度《為90。± 10〇 ° 圖2進一步顯示該具有脫扣條帶15之第二冷卻通道6。類 似於在通道5中，在通道6内的脫扣條帶㈣設計為具有一 Ο 從該通道6之壁16測量之高度h與在該等脫扣條帶之間的距 離d，使得該高度h與距離0之比率為1〇±2，如圖^所示。 高度h是從通道之W丨量，而距離d是沿著冷卻氣流之 方向在相鄰脫扣條帶之間予以測量。 如圖2所示，相較於通道5内之相鄰脫扣條帶13之間的距 離’冷卻通道6内之該等脫扣條帶15彼此間的距離較大。 然而’為了保證一充分冷卻氣流通過通道5與6,冷卻通道 之基本設計特點包含在通道5内的脫扣條帶之特定定位， 且在通道5與6二者内之高度h與相鄰脫扣條帶間之距離㈣ 133517.doc -12- 200928075 比率為10±2。-另-增加此作用之設計特點包括在通道6 内之脫扣條帶較位。料脫扣條㈣配置為與氣流之方 向成45±10〇之傾斜角β，如圖3d所顯示。該角度是在逆時 針方向上從該等脫扣條帶之方向至氣流方向予以測量。 該第三通道7可同樣具有為任何設計之紊流器17，以增 加沿著該通道之冷卻效果》在所示之例示性實施例中，^ 係配置為與該氣流方向成一傾斜角度δ，該角度相對於該 氣流方向為45±10。。 【圖式簡單說明】 圖1顯示本發明可應用之一例示性燃氣渦輪機葉片之側 視圖； 圖2顯示沿著圖的葉片之剖面視圖，其顯示根據 本發明的内葉片冷卻結構； 圖3a與3b分別顯示沿著圖2之111&_111&之脫扣條帶的剖 面示圖與該脫扣條帶之細節，特別是在葉片冷卻結構之第 一冷卻通道内之紊流器之配置與相對尺寸； 圖3c與3d分別顯示沿著圖2之IIIc_Inc之脫扣條帶的气 面示圖與該脫扣條帶之細節，特別是在葉片冷卻結構之第 二冷卻通道内的紊流器之配置與相對尺寸。 【主要元件符號說明】 旋轉葉片 葉片根部 葉片尖端 充氣腔 133517.doc 13· 200928075200928075 IX. INSTRUCTIONS OF THE INVENTION: FIELD OF THE INVENTION The present invention relates to casting rotary blades for use in a gas turbine, and in particular to the design of two cooling structures within the blade that take into account the manufacturability of the blade. [Prior Art] Turbine blades for gas turbines are designed and manufactured to withstand the high temperatures during operation of the gas turbine. Such turbine blades include an internal cooling structure and a cooling fluid (typically air) passes through the internal cooling structure. The cooled milk is extracted from the compressor of one of the gas turbine engines. However, extracting air in this way reduces the overall performance of the engine. To reduce the impact on the performance of the engine by reducing air consumption and still ensuring adequate cooling of the blades, the inner blade cooling structure is designed for optimum cooling efficiency. Such a design is disclosed, for example, in U.S. Patent No. 6,139,269 and U.S. Patent No. 5,403,159. U.S. Patent No. 6,139,269 discloses a spiral cooling structure having a plurality of passages extending in the longitudinal direction of the blade and connected to or connected to one of the blade roots. The tip of the exit, or by approximately 180. The turn is either bent or connected to another longitudinal passage. The cooling structure further includes a plurality of trip strips on the walls of the longitudinal channels, the trip strips being positioned at about 45 in a direction through the passage. . The particular configuration of U.S. Patent No. 6,139,269 is further included in each of the 180 adjacent the blade root. An air resupply channel at the turn that allows air to enter the channel from the root of the blade. 133517.doc 200928075 A full-wheel blade having such an internal cooling structure is usually cast by a mold-casting process using a core defining the cooling structure. The core is removed by a removable material (such as a ceramic illusion), and the ceramic core is removed via a delivery process. The leaching process is for the area at 180. The material of the core material is difficult and there is still a risk that the remaining core material remains in the cooling channel' and thus hinders the flow of cooling medium through the cooling channel. To reduce this risk, it is cooled 18 结构 of the structural wall. An opening is provided in the region of the turn to leaching out the remaining core material. In some known gas turbine blades, this opening is by way of example, for example, US Patent No. The plate or plug of 6,634,858 is again closed. SUMMARY OF THE INVENTION It is an object of the present invention to provide a gas turbine rotary blade having an internal cooling structure having an improved φ that allows for the latest scientific and technological aspects. Manufacturability while maintaining at least the design of the existing cooling performance of the internal cooling structure. A gas turbine rotating blade includes an internal cooling structure having at least two a cooling passage extending in a longitudinal direction of the blade, at least one inlet in the region of the blade root, and at least one outlet in the region of the blade tip from a cooling passage to the outside of the blade. The blade further includes a portion in the root region thereof An plenum for cooling air, the inlet extending from the plenum to a cooling passage. The first cooling passage extends from the blade root region to the blade tip region along a direction of the cooling fluid. The second cooling passage 133517.doc 200928075 Extending from the tip to the root region. The first and second cooling passages are fluidly connected to each other at a tip end region of the blade by a bend or turn in the blade tip region. The third cooling passage is further extended from the root to The tip end, and the second and third cooling passages are fluidly connected to each other by a turn or bend in the blade root region. To remove the core material from the bend via leaching and to reduce residual core material In the wind of the bend, an opening is provided in the wall of the cooling structure, extending from the plenum to the root region of the blade The bend or turn from the first to the second cooling passages. The opening provides a direct fluid connection from the bend to the root of the blade and to the exterior of the blade. In particular, the opening and the blade The root region is such that a liquid//IL body is allowed to flow directly and substantially in the direction of the longitudinal vanes outside the cooling structure within the blade. This allows the core material of the liquid to completely exit the blade without passing through any Inverting or stagnation zone. Therefore, it is possible to prevent the core material of the liquid from remaining in the structure as the remaining fluid. Therefore, the flow of the cooling air passing through the internal cooling structure during the operation of the blade can be ensured. The gas turbine rotating blade is fabricated, and the inner structure is bent or i 8 〇. The opening of the steering is no longer closed before the blade operation in the turbine. Since the opening at the turn is affected at 18 〇 The aerodynamics of the internal cooling structure and the distribution of the cooling air, so the design of the cooling channel is adapted and optimized in consideration of cooling function and efficiency.According to the present invention, the first cooling passage extending from the inflation chamber in the root region to the blade tip region in the direction of the cooling fluid includes 90 ± 1 Torr with the flow direction of the cooling 133517.doc 200928075 fluid. One angle of turbulence or trip strip. Further, the second cooling passage fluidly coupled to the first cooling passage by a turn includes a plurality of trip strips or turbulators. Finally, in combination with the specific orientation of the trip strips in the first cooling passage, the trip strips in the first and second cooling passages are configured and formed in a predetermined size to have a height and phase The ratio of the distance between the adjacent trip strips is 1 〇 ± 2 . In an exemplary embodiment of the invention, the trip strips in the second cooling passage are configured to be 45 with the flow direction. ±丨〇. The angle. In another exemplary embodiment, the third cooling passage includes a plurality of trip strips configured to be 45° ± 10° from the flow direction to the direction of the trip strip One angle. As noted above, the opening at the turn from the second to the third passage affects the distribution of cooling air within the cooling structure. In particular, a non-closed opening at one of the locations will result in a reduction in airflow through the first and second passages from the inflation chamber of the root region, and from the inflation chamber through the open Q port directly to the second The increase in airflow through the channel. The design in accordance with the present invention allows the optimization of the cooling airflow and the reconstruction of the airflow through the first and second passages in the form of trip strips that are specifically disposed within the first and second passages. It thus ensures sufficient and uniform cooling of the entire blade. The design of the trip strip according to the present invention allows compensation for very small hydraulic losses from the beginning of the first passage to the beginning of the third passage. Compensating for this low pressure loss is achieved by pumping forces in the first and second passages, which are due to an increase in the convective temperature of the cooling air along the passages. The flow of the cooling air is detailed in the following diagram 133517.doc -9- 200928075. As described above, the design of the blade cooling structure according to the present invention allows for optimal manufacturing due to the opening at the turn of the root adjacent to the blade. The design does not require a method to close the opening after casting. The particular design of the trip strips within the cooling passage compensates for hydraulic losses and thereby ensures adequate cooling within the first and second passages. This design allows for improved and simplified manufacturing while maintaining the same cooling performance. [Embodiment] Figure 1 shows a rotary gas turbine blade 1 extending longitudinally from a portion 2 to a tip portion 3. Figure 2 shows a cooling structure for a blade having a cooling region into the cooling structure in its root region. The inner air plenum 4, a plurality of at least two longitudinal cooling passages 5_7 extending from the plenum 4 of the root 2 to the tip 3 and extending from the tip 3 to the root 2. The longitudinal channels are approximately 180 degrees. The turns are fluidly connected to each other. 〇 The air flow (as indicated by the arrow) passes from the plenum 4 through the beginning of the first cooling passage 5 to the end of the first passage of the blade tip and bypasses - about 18 。. The turning point. It then flows along the second cooling passage 6 to another 180 that connects the second cooling passage 6 with the third cooling passage 7. Turn at 1〇. The cooling air eventually flows through the third cooling passage 7 to the vanes and exits the outlet on the tip of the vane. Leave the cold structure. At a point close to the root of the blade, the ^1Λ Ba丄 will be asked 10 to provide an opening or passage 12 to leaching out the core fruit to the material after casting, and to allow all dissolved molds 133517.doc 200928075 The core material exits the cooling structure via the swell plenum 4 such that the core material does not remain within the turn 10. Due to this opening 12, the cooling air can more easily pass directly from the plenum chamber 4 through the third cooling passage 7 without passing through the first and second cooling passages 5 and 6. However, due to the special design of the first and second cooling passages in accordance with the present invention, the pressure drop between position A and position b ensures a passage of cooling air through passages 5 and 6. A pressure loss is due to fluid resistance and depends on the second dimension of the air velocity, the shape of the channel, the smoothness of the channel wall, and the shape of the turbulence or strip. All of these features in accordance with the present invention cause the air pressure at the beginning position B of the second passage 7 to be lower than the air pressure at the beginning position A of the first passage $. In addition, an extraction action is produced due to the rotation of the blade. The gas pressure increases with increasing the radius of the channel due to the extraction, particularly at a given angular velocity proportional to the difference between the half-ordered squares. Therefore, in the first passage 5, the pressure increases with increasing radius from position A to position B. Q In this second passage 6, the pressure decreases as the radius from the position B to the position c decreases, by the same amount that it increases within the passage 5. This final effect will therefore be zero. In addition, however, the cooling air obtains a heat flow from the heat convection wall of the passage to increase the temperature of the cooling air. Therefore, the temperature of the cooling air in the second passage 6 is higher than the temperature in the first passage 5. This temperature change also affects the extraction in the first and second channels. The higher temperature within the second passage causes the extraction along the second passage 6 to be less than its effect within the first passage 5. Therefore, compared to the pressure at position A, the pressure at position B is lower resulting in an effective cooling airflow along channels 5 and 6 along 1335I7.doc -11 - 200928075. The fluid resistance of the channel depends on, in particular, the design of the channel, in particular the turbulence or trip strip 13. Figure 2 shows an embodiment of the present invention, which includes a turbulator in the first cooling passage 5. < 4 strips of the strips 3 are arranged in the flow with the cooling stream The direction is 90±1〇. (as indicated by the arrow). Figure 3a shows the section of the trip strip ‘find and relative size. Each trip strip has - a height b' measured from (4) of the channel 5 and each trip bar is disposed at a distance - distance 4 from the adjacent trip strip. The height 11 and the distance d are ratios of -ι 〇 ± 2. The trip strips are shown as having a rectangular shape. However, it can also be any other aerodynamically suitable profile shape. Figure 3b shows the orientation of the trip strips relative to the direction of the cooling airflow. The angle is "90. ± 10 〇 ° Figure 2 further shows the second cooling channel 6 with the trip strip 15 . Similar to in the channel 5, the trip strip (4) in the channel 6 is designed to have a height h measured from the wall 16 of the channel 6 and a distance d between the trip strips such that the height The ratio of h to distance 0 is 1〇±2, as shown in Figure 2. The height h is the amount of W from the channel, and the distance d is measured between adjacent trip strips along the direction of the cooling airflow. As shown in Fig. 2, the distance between the trip strips 15 in the cooling passage 6 is larger than the distance between adjacent trip strips 13 in the passage 5. However, in order to ensure a sufficient cooling airflow through passages 5 and 6, the basic design features of the cooling passages include the specific positioning of the trip strips within the passages 5, and the heights h and adjacent ones within the passages 5 and 6 The distance between the buckle strips (4) 133517.doc -12- 200928075 The ratio is 10±2. - Another - Design features that add to this effect include the release of the trip strip in channel 6. The material trip strip (4) is configured to have an inclination angle β of 45 ± 10 与 to the direction of the air flow, as shown in Figure 3d. The angle is measured in the counterclockwise direction from the direction of the trip strips to the direction of the air flow. The third passage 7 can likewise have a turbulator 17 of any design to increase the cooling effect along the passage. In the illustrated exemplary embodiment, the system is configured to be at an oblique angle δ to the direction of the airflow. This angle is 45 ± 10 with respect to the direction of the gas flow. . BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 shows a side view of an exemplary gas turbine blade to which the present invention is applicable; Figure 2 shows a cross-sectional view of the blade along the Figure showing the inner blade cooling structure in accordance with the present invention; Figure 3a And 3b respectively show a cross-sectional view of the trip strip along 111 & _111 & and the details of the trip strip, in particular the arrangement of the turbulators in the first cooling passage of the blade cooling structure Figures 3c and 3d respectively show a gas-surface view of the trip strip along IIIc_Inc of Figure 2 and details of the trip strip, particularly a turbulator in a second cooling passage of the blade cooling structure Configuration and relative size. [Main component symbol description] Rotating blade Blade root Blade tip Inflating chamber 133517.doc 13· 200928075
5 第一冷卻空氣通道 6 第二冷卻空氣通道 7 第三冷卻空氣通道 8 進口 9 轉向處 10 轉向處 11 出口 12 開口 13 第一通道内之脫扣條帶 14 冷卻通道壁 15 第二通道内之脫扣條帶 16 第二冷卻通道壁 17 第三通道内之脫扣條帶 A 在冷卻通道5的開頭之位置 B 在冷卻通道5的末端之位置 C 在第二通道6至第三通道7彎曲之 位置 d 相鄰脫扣條帶之距離 h 脫扣條帶之高度 a 脫扣條帶13之定位角度 β 脫扣條帶15之定位角度 δ 脫扣條帶17之定位角度 133517.doc -14-5 First cooling air channel 6 Second cooling air channel 7 Third cooling air channel 8 Inlet 9 Turning point 10 Turning point 11 Outlet 12 Opening 13 Tripping strip 14 in the first channel Cooling channel wall 15 In the second channel Trip strip 16 second cooling channel wall 17 trip strip A in the third channel at position B at the beginning of cooling channel 5 at position C at the end of cooling channel 5 is curved in second channel 6 to third channel 7 Position d Distance of adjacent trip strips h Height of trip strips a Positioning angle of trip strips 13 Positioning angle of trip strips δ Positioning angle of trip strips 133517.doc -14 -