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11.发明授权
公开(公告)号：US6050777A
公开(公告)日：2000-04-18
申请号：US992322
申请日：1997-12-17
CPC分类号： F01D5/186 , Y10T29/49341
摘要： A hollow airfoil is provided which includes a body, a trench, and a plurality of cooling apertures disposed within the trench. The body extends chordwise between a leading edge and a trailing edge, and spanwise between an outer radial surface and an inner radial surface, and includes an external wall surrounding a cavity. The trench is disposed in the external wall along the leading edge, extends in a spanwise direction, and is aligned with a stagnation line extending along the leading edge.
摘要翻译： 提供了一种空心翼片，其包括主体，沟槽和设置在沟槽内的多个冷却孔。 主体在前缘和后缘之间沿翼弦方向延伸，并且在外径向表面和内径向表面之间展开，并且包括围绕腔的外壁。 沟槽沿着前缘设置在外壁中，沿翼展方向延伸，并且与沿着前缘延伸的停滞线对齐。
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公开(公告)号：US5486093A
公开(公告)日：1996-01-23
申请号：US118158
申请日：1993-09-08
申请人： Thomas A. Auxier , Kenneth B. Hall
发明人： Thomas A. Auxier , Kenneth B. Hall
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/121 , F05D2240/303 , F05D2250/25 , F05D2260/202 , F05D2260/221 , Y02T50/676
摘要： The leading edge of the turbine airfoil of a turbine blade for a gas turbine engine is cooled by utilizing helix shaped holes that are rectangular in cross-section and curved to produce film holes egressing at low angles adjacent the outer surface of the leading edge. The helix holes extend from the root to the tip of the blade and are parallelly and longitudinally spaced.
摘要翻译： 用于燃气涡轮发动机的涡轮机叶片的涡轮叶片的前缘通过利用截面矩形的弯曲形状的孔来冷却，并弯曲以产生邻近前缘的外表面以低角度出射的薄膜孔。 螺旋孔从叶片的根部延伸到尖端并且平行且纵向间隔开。
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13.发明授权
公开(公告)号：US5419039A
公开(公告)日：1995-05-30
申请号：US207692
申请日：1994-02-25
CPC分类号： B23P15/04 , F01D5/147 , F01D5/186 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49893
摘要： The method of manufacturing an air cooled stator vane for a gas turbine engine by casting an inner shell with suction side wall and pressure side wall of the airfoil, stamp forming from a blank sheet metal a pair of sheaths and attaching one sheath of the pair of sheaths to the suction side wall and the other sheath of the pair of sheaths to the pressure side wall. Forming in the step of stamp forming pockets with a slot at the end of each pocket for flowing a film of cooling air over the exterior of each of the pair of sheaths and drilling holes in the end of the pocket remote from the slot prior to the step of joining to fluidly connect the pocket with cooling air. The method includes in another embodiment sheet metal blank stamp formed with a corrugated member and attaching it between the cast pressure side wall and one sheath of the pair sheaths and between the suction side wall and the other sheath of the pair of sheaths and drilling holes prior to the step of attaching in the high points of the corrugated member. In another embodiment the method includes forming perforated cylindrically shaped inserts and attaching the inserts in the central passageway formed in the cast inner shell.
摘要翻译： 通过铸造具有翼型的吸力侧壁和压力侧壁的内壳来制造用于燃气涡轮发动机的空气冷却定子叶片的方法，从坯料金属板形成一对护套并附接一对护套的一个护套 护套连接到吸力侧壁，另一侧护套连接到压力侧壁。 在每个口袋的端部形成具有狭槽的口袋的步骤中形成凹槽的步骤，用于在一个护套中的每一个的外部上流动冷却空气的膜，并且在该口袋的端部之前的钻孔远离槽 将口袋与冷却空气流畅连接的步骤。 该方法在另一实施例中包括形成有波纹构件的金属板坯印模，并将其附接在铸造压力侧壁和一对护套的一个护套之间，并且在一对护套和钻孔之前的吸入侧壁和另一个护套之前 到连接在波纹部件的高点的步骤。 在另一个实施例中，该方法包括形成穿孔的圆柱形插入件并将插入件附接到形成在铸造内壳中的中心通道中。
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公开(公告)号：US5405242A
公开(公告)日：1995-04-11
申请号：US550008
申请日：1990-07-09
CPC分类号： B23P15/04 , F01D5/147 , F01D5/186 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49893
摘要： An air cooled stator vane or the like for a gas turbine engine is constructed to include a plurality of axially and radially spaced pockets formed on the outer surfaces of the airfoil sections. Air is directed into the pocket on one end of a passage defined by the pocket to impinge on the back wall of the pocket, change directions and flow through the passage and discharge into the gas path as a film of cooling air coalesced by slots formed at the end of the pocket. The outer wall can be cast in its entirety or fabricated from sheet metal sheaths supported to a cast inner shell. The pockets are fed cooling air through a central passage in the stator vane or through impingement inserts disposed in the central passage.
摘要翻译： 用于燃气涡轮发动机的空气冷却的定子叶片等被构造成包括形成在翼型部分的外表面上的多个轴向和径向隔开的袋。 空气被引导到由口袋限定的通道的一端上的口袋中以撞击在口袋的后壁上，改变方向并流过通道，并且当冷却空气的膜由形成在 口袋的尽头。 外壁可以整体铸造或由支撑到铸造内壳的金属板制成。 凹穴通过定子叶片中的中心通道或设置在中心通道中的冲击插入件供给冷却空气。
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公开(公告)号：US4887663A
公开(公告)日：1989-12-19
申请号：US200489
申请日：1988-05-31
CPC分类号： F02K1/822 , F23R3/002 , F05D2260/202 , Y02T50/675
摘要： Overlapping liner plates 12, 14, 16 are secured at the upstream end to support surface 22. Cooling air 26 supplied through compartmental plenums 24 passes between (54) the plates and over (56) the plate surface. Complementary elongated depressions 40, 46 selectively guide the airflow and provide flexibility to absorb transverse expansions.
摘要翻译： 重叠的衬板12,14,16固定在上游端以支撑表面22。通过隔室增压室24供应的冷却空气26在板之间穿过（54）并在板表面上方穿过（56）。 互补的细长凹陷40,46选择性地引导气流并提供弹性以吸收横向膨胀。
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公开(公告)号：US4753575A
公开(公告)日：1988-06-28
申请号：US082402
申请日：1987-08-06
IPC分类号： F01D5/18
摘要： A hollow, cooled airfoil has a pair of nested, coolant channels therein which carry separate coolant flows back and forth across the span of the airfoil in adjacent parallel paths. The coolant in both channels flows from a rearward to forward location within the airfoil allowing the coolant to be ejected from the airfoil near the leading edge through film coolant holes.
摘要翻译： 中空的冷却翼型件在其中具有一对嵌套的冷却剂通道，所述一对嵌套的冷却剂通道在相邻的平行路径中携带分离的冷却剂来回跨越翼型跨度。 两个通道中的冷却剂从翼型中的向后位置流动，允许冷却剂从前缘附近的翼型件通过薄膜冷却剂孔喷出。
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公开(公告)号：US06210112B1
公开(公告)日：2001-04-03
申请号：US09480956
申请日：2000-01-11
IPC分类号： F01D518
CPC分类号： F01D5/186 , Y10T29/49341
摘要： A hollow airfoil is provided which includes a body, a trench, and a plurality of cooling apertures disposed within the trench. The body extends chordwise between a leading edge and a trailing edge, and spanwise between an outer radial surface and an inner radial surface, and includes an external wall surrounding a cavity. The trench is disposed in the external wall along the leading edge, extends in a spanwise direction, and is aligned with a stagnation line extending along the leading edge.
摘要翻译： 提供了一种空心翼片，其包括主体，沟槽和设置在沟槽内的多个冷却孔。 主体在前缘和后缘之间沿翼弦方向延伸，并且在外径向表面和内径向表面之间展开，并且包括围绕腔的外壁。 沟槽沿着前缘设置在外壁中，沿翼展方向延伸，并且与沿着前缘延伸的停滞线对齐。
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公开(公告)号：US5674050A
公开(公告)日：1997-10-07
申请号：US279632
申请日：1988-12-05
申请人： Kenneth B. Hall , Thomas A. Auxier
发明人： Kenneth B. Hall , Thomas A. Auxier
CPC分类号： F01D5/187 , F01D5/147 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： A bulkhead in the form of a rib extending spanwise adjacent the leading edge of the airfoil of a turbine blade of a gas turbine engine serves to stiffen the airfoil to attain protection from impact by foreign objects, but doesn't materially affect cooling effectiveness in the event of a puncture of the skin. Holes extending spanwise in the rib reduce the mass, allow radial flow, and restrict flow into the leading edge. This construct allows a reduction in the thickness of the skin of the airfoil, and hence a weight reduction.
摘要翻译： 以与燃气涡轮发动机的涡轮机叶片的翼型的前缘相邻的凸肋的形式的隔板的形式用于加强翼型件，以防止受到外来物体的冲击，但不会实质上影响冷却效果 皮肤穿刺的事件。 在翼肋中延伸的孔减少质量，允许径向流动，并限制流入前缘。 该构造允许翼型件的皮肤的厚度减小，并因此减轻重量。
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公开(公告)号：US5403158A
公开(公告)日：1995-04-04
申请号：US173531
申请日：1993-12-23
申请人： Thomas A. Auxier
发明人： Thomas A. Auxier
摘要： Passive clearance control is attained for rotor blades for gas turbine engines in environments where the airfoil of the rotor is solid or where coolant is unavailable or is available but not at sufficient quantity to provide passive clearance control. In this situation a judiciously located curved slot extending from the tip of the blade adjacent the pressure side and terminating at the pressure side at a location where there is sufficient static pressure so that the pressure drop across the slot induces a pumping action. In embodiments where there is sufficient coolant for tip cooling, the curved slot is judiciously located to be in communication with the film cooling hole discharging on the pressure side of the blade and the tip of the blade adjacent the pressure side of the blade.
摘要翻译： 转子叶片在转子的翼型是固体或者冷却剂不可用或可用但不足够数量以提供被动间隙控制的环境中，用于燃气涡轮发动机的转子叶片被动间隙控制。 在这种情况下，从位于压力侧的叶片的尖端延伸并且在压力侧终止于具有足够的静压力的位置处的明智定位的弯曲槽口使得穿过狭槽的压降引起泵送作用。 在具有足够的冷却剂用于尖端冷却的实施例中，弯曲的狭槽被明智地定位成与在叶片的压力侧上排放的薄膜冷却孔和叶片的尖端邻近叶片的压力侧连通。
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20.发明授权Method of manufacturing an air cooled vane with film cooling pocket construction 失效制造具有薄膜冷却口袋结构的风冷叶片的方法
公开(公告)号：US5392515A
公开(公告)日：1995-02-28
申请号：US842289
申请日：1992-02-10
CPC分类号： B23P15/04 , F01D5/147 , F01D5/186 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49893
摘要： An air cooled stator vane for a gas turbine engine is fabricated by casting the suction side wall and pressure side wall of the airfoil into separate halves and joining both halves at complementary sides and ribs, and forming pockets with a slot at the end of each pocket for flowing a film of cooling air over the exterior wall and drilling holes in the end of the pocket remote from the slot to fluidly connect the pocket with cooling air. The method includes in another embodiment a sheet metal sheath with pockets and slots identical to the pockets and slots in the shell configuration formed over the shell. Another embodiment includes perforated inserts extending in the cavity formed by the shell.
摘要翻译： 用于燃气涡轮发动机的空气冷却定子叶片通过将翼型的吸力侧壁和压力侧壁浇铸成分开的半部并且在互补的侧面和肋部处连接两半并且在每个口袋的端部处形成具有狭槽的袋 用于将冷却空气的膜流过外壁并在远离槽的孔的端部钻孔，以将空腔与冷却空气流体连接。 该方法在另一个实施例中包括金属板护套，其具有与在外壳上形成的壳体构造中的凹穴和狭槽相同的凹穴和狭槽。 另一个实施例包括在由壳形成的空腔中延伸的穿孔插入件。
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