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1. 发明授权

US06419446B1 Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine 有权
标题翻译：用于抑制燃气涡轮发动机的核心气体流动路径内的核心气体流的径向传递的装置和方法
公开(公告)号：US06419446B1
公开(公告)日：2002-07-16
申请号：US09468751
申请日：1999-12-21
申请人： William A. Kvasnak , Friedrich O. Soechting , Karen A. Thole , Gary A. Zess
发明人： William A. Kvasnak , Friedrich O. Soechting , Karen A. Thole , Gary A. Zess
IPC分类号： F01D904
CPC分类号： F01D9/041 , F01D5/145 , Y10S415/914
摘要： A method for inhibiting radial transfer of core gas flow away from a center radial region and toward the inner and outer radial boundaries of a core gas flow path within a gas turbine engine is provided that includes the steps of: (1) providing a flow directing structure that includes an airfoil that abuts a wall surface, said airfoil having a leading edge, a pressure side, and a suction side; and (2) increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall. Increasing the velocity of the core gas flow in the area where the leading edge of the airfoil abuts the wall impedes the formation of a pressure gradient along the surface of the airfoil that forces core gas from the center region of the core gas toward the wall. The apparatus includes apparatus for diverting core gas flow away from the area where the airfoil abuts the wall.
摘要翻译：提供了一种用于抑制核心气体流离开中心径向区域并朝向燃气涡轮发动机内的核心气体流动路径的内部和外部径向边界的径向转移的方法，其包括以下步骤：（1）提供流动导向包括邻接壁面的翼型的结构，所述翼型具有前缘，压力侧和吸力侧; 和（2）增加翼型件的前缘邻接壁的区域中的核心气流的速度。增加翼型件的前缘邻接壁的区域中的核心气流的速度阻碍沿着翼型的表面形成压力梯度，该压力梯度迫使核心气体从核心气体的中心区域朝向壁。该装置包括用于使核心气体流离开机翼抵靠壁的区域的装置。

2. 发明授权

US06280140B1 Method and apparatus for cooling an airfoil 有权
标题翻译：用于冷却机翼的方法和装置
公开(公告)号：US06280140B1
公开(公告)日：2001-08-28
申请号：US09442922
申请日：1999-11-18
申请人： Friedrich O. Soechting , William A. Kvasnak , Thomas A. Auxier , James P. Downs , William H. Calhoun , Douglas A. Hayes
发明人： Friedrich O. Soechting , William A. Kvasnak , Thomas A. Auxier , James P. Downs , William H. Calhoun , Douglas A. Hayes
IPC分类号： F01D518
CPC分类号： F23R3/002 , F01D5/184 , F01D5/186 , F05D2250/70 , F05D2260/221 , F05D2260/2214
摘要： An apparatus and method for cooling a wall for use in a gas turbine engine is provided that includes a cooling air passage having a plurality of segments connected in series by one or more chambers, an inlet aperture, and an exit aperture. The inlet aperture connects the cooling air passage to one side of the wall. The exit aperture connects the cooling air passage to the opposite side of the wall. Cooling air on the inlet aperture side of the wall enters the cooling air passage through the inlet aperture and exits through the exit aperture.
摘要翻译：提供一种用于冷却用于燃气涡轮发动机的壁的装置和方法，其包括具有通过一个或多个室串联连接的多个段的冷却空气通道，入口孔和出口孔。入口孔将冷却空气通道连接到墙的一侧。出口孔将冷却空气通道连接到壁的相对侧。壁的入口孔侧的冷却空气通过入口孔进入冷却空气通道，并通过出口孔离开。

3. 发明授权

US06210112B1 Apparatus for cooling an airfoil for a gas turbine engine 有权
标题翻译：用于冷却用于燃气涡轮发动机的翼型件的装置
公开(公告)号：US06210112B1
公开(公告)日：2001-04-03
申请号：US09480956
申请日：2000-01-11
申请人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier
发明人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier
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。

4. 发明授权

US5392515A Method of manufacturing an air cooled vane with film cooling pocket construction 失效
标题翻译：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
申请人： Thomas A. Auxier , Hans R. Przirembel , Friedrich O. Soechting
发明人： Thomas A. Auxier , Hans R. Przirembel , Friedrich O. Soechting
IPC分类号： B23P15/04 , F01D5/14 , F01D5/18 , B23P15/00
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。

5. 发明授权

US6164912A Hollow airfoil for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的空心翼型
公开(公告)号：US6164912A
公开(公告)日：2000-12-26
申请号：US217697
申请日：1998-12-21
申请人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier , Frederick Steinbauer, Jr.
发明人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier , Frederick Steinbauer, Jr.
IPC分类号： F02C7/00 , F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/25
摘要： A hollow airfoil is provided which includes a body having an external wall and an internal cavity. The external wall includes a suction side portion and a pressure side portion. The portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. A stagnation line extends along the leading edge. A plurality of cooling apertures, disposed spanwise along the leading edge. According to one aspect of the present invention, the apertures extend through the external wall along a helical path. According to another aspect of the present invention, the apertures are alternately directed towards the suction side portion and the pressure side portions of the airfoil.
摘要翻译：提供了一种空心翼片，其包括具有外壁和内腔的主体。外壁包括吸力侧部分和压力侧部分。这些部分在前缘和后缘之间并行延伸，并且在内径向表面和外径向表面之间展开。停滞线沿着前缘延伸。沿着前缘沿翼展方向设置的多个冷却孔。根据本发明的一个方面，孔径沿着螺旋路径延伸穿过外壁。根据本发明的另一方面，所述孔交替地指向翼型的吸入侧部分和压力侧部分。

6. 发明授权

US5645397A Turbine vane assembly with multiple passage cooled vanes 失效
标题翻译：具有多通道冷却叶片的涡轮叶片组件
公开(公告)号：US5645397A
公开(公告)日：1997-07-08
申请号：US541854
申请日：1995-10-10
申请人： Friedrich O. Soechting , William L. Plank , Kenneth B. Hall
发明人： Friedrich O. Soechting , William L. Plank , Kenneth B. Hall
IPC分类号： F01D9/02 , F01D5/18 , F01D9/04 , F01D25/12 , F02C7/18 , F01D9/06
CPC分类号： F01D5/187 , F01D25/12 , Y02T50/676
摘要： A vane assembly for a gas turbine engine is provided, which includes a plurality of vanes, an inner vane support, a casing, and apparatus for maintaining a pressure difference. Each vane has a leading edge, a trailing edge, an outer radial end, an inner radial end, and an internal cavity. The internal cavity includes a forward compartment adjacent the leading edge and an aft compartment adjacent the trailing edge. The casing, which includes an annulus, is positioned radially outside of the vanes. The vanes extend between the inner vane support and the casing. The apparatus for maintaining a pressure difference maintains a difference in the cooling air pressure within the forward and aft compartments of the vane cavity under operating conditions.
摘要翻译：提供了一种用于燃气涡轮发动机的叶片组件，其包括多个叶片，内叶片支撑件，壳体和用于保持压力差的装置。每个叶片具有前缘，后缘，外径向端，内径向端和内腔。内腔包括邻近前缘的前隔室和邻近后缘的后舱。包括环形的壳体位于叶片的径向外侧。叶片在内叶片支撑件和壳体之间延伸。用于维持压力差的装置在操作条件下保持叶片腔的前后间隔室内的冷却空气压力差。

7. 发明授权

US5599166A Core for fabrication of gas turbine engine airfoils 失效
标题翻译：用于制造燃气涡轮发动机翼型的核心
公开(公告)号：US5599166A
公开(公告)日：1997-02-04
申请号：US333157
申请日：1994-11-01
申请人： Donald L. Deptowicz , Friedrich O. Soechting
发明人： Donald L. Deptowicz , Friedrich O. Soechting
IPC分类号： B22C9/04 , B22C9/10 , F01D5/18
CPC分类号： B22C9/103 , B22C9/04 , F01D5/18
摘要： An airfoil (20) for a gas turbine engine (10) includes cooling passages (40), (50) extending radially within the airfoil to circulate cooling air therethrough. Pluralities of small crossover holes (48), (66), (72) are formed within the walls (50), (68), (74), respectively, to allow cooling air to flow between the cooling passages. Optimum stiffness parameters are provided to improve producability of the airfoils with small geometric features, such as the crossover holes, as well as to improve the overall cooling scheme without jeopardizing manufacturability of airfoils.
摘要翻译：用于燃气涡轮发动机（10）的翼型件（20）包括在翼型件内径向延伸以使冷却空气通过其中的冷却通道（40），（50）。多个小交叉孔（48），（66），（72）分别形成在壁（50），（68），（74）内，以允许冷却空气在冷却通道之间流动。提供最佳刚度参数以提高具有小几何特征（例如交叉孔）的翼型件的可生产性，以及改善整体冷却方案而不损害翼型件的可制造性。

8. 发明授权

US06247896B1 Method and apparatus for cooling an airfoil 有权
标题翻译：用于冷却机翼的方法和装置
公开(公告)号：US06247896B1
公开(公告)日：2001-06-19
申请号：US09338376
申请日：1999-06-23
申请人： Thomas A. Auxier , James P. Downs , William S. Kvasnak , Friedrich O. Soechting , William H. Calhoun , Douglas A. Hayes
发明人： Thomas A. Auxier , James P. Downs , William S. Kvasnak , Friedrich O. Soechting , William H. Calhoun , Douglas A. Hayes
IPC分类号： F01D518
CPC分类号： F01D5/18 , F01D5/187 , F05D2230/14 , F05D2250/15 , F05D2250/70 , F05D2260/2214
摘要： A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.
摘要翻译：提供了一种用于冷却燃气涡轮发动机内的壁的方法和装置，其包括以下步骤：（1）提供具有内表面和外表面的壁; （2）在所述壁内提供具有在所述内表面和所述外表面之间延伸的用于冷却空气的通道的所述壁内的冷却微电路; 和（3）通过增加微电路内的每单位流动的平均热传递系数来增加从通道内的壁到流体流的传热。根据一个方面，本发明的方法和装置可以被调整以使手上的壁的热分布基本匹配。

9. 发明授权

US6050777A Apparatus and method for cooling an airfoil for a gas turbine engine 失效
标题翻译：一种用于冷却燃气涡轮发动机翼型的装置和方法
公开(公告)号：US6050777A
公开(公告)日：2000-04-18
申请号：US992322
申请日：1997-12-17
申请人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier
发明人： Martin G. Tabbita , James P. Downs , Friedrich O. Soechting , Thomas A. Auxier
IPC分类号： F01D5/18 , F01D9/06
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。

10. 发明授权

US5419039A Method of making an air cooled vane with film cooling pocket construction 失效
标题翻译：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：US5419039A
公开(公告)日：1995-05-30
申请号：US207692
申请日：1994-02-25
申请人： Thomas A. Auxier , Hans R. Przirembel , Friedrich O. Soechting
发明人： Thomas A. Auxier , Hans R. Przirembel , Friedrich O. Soechting
IPC分类号： B23P15/04 , F01D5/14 , F01D5/18 , B23P15/00
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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