公开(公告)号：WO1997044569A1

公开(公告)日：1997-11-27

申请号：PCT/US1997004368

申请日：1997-03-19

Applicant: WESTINGHOUSE ELECTRIC CORPORATION

Inventor： WESTINGHOUSE ELECTRIC CORPORATION ,  HULTGREN, Kent, G. ,  MCLAURIN, Leroy, D. ,  BERTSCH, Oran, L. ,  LOWE, Perry, E.

IPC: F01D05/08

CPC classification number: F01D5/085 ,  F02C7/185 ,  F05D2260/205

Abstract: A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn.

Abstract translation: 燃气轮机转子具有基本上为闭环的冷却空气方案，其中从压缩机抽出的冷却空气被供应到燃烧室被进一步压缩，冷却，然后被引导到涡轮转子的后端。 附接到每个转子盘的下游表面的下游密封环将冷却空气引导到下游盘表面上，从而将其冷却，然后冷却形成在旋转叶片中的冷却空气通道。 附接到每个盘的上游面的上游密封环将加热的冷却空气从叶片根部导向，同时保持盘与加热的冷却空气热隔离。 从每个上游密封环，加热的冷却空气流过上游盘中的通道，然后被组合并返回到被抽吸的燃烧室。

公开(公告)号：EP0206683A3

公开(公告)日：1988-08-03

申请号：EP86304556

申请日：1986-06-13

Applicant: UNIVERSITY OF DAYTON

Inventor： Minardi, John E. ,  von Ohain, Hans P. ,  Lawson, Maurice O.

IPC: F02C07/18 ,  F01D05/08

CPC classification number: F01D5/08 ,  F02C7/125 ,  F02C7/18 ,  Y02T50/672 ,  Y02T50/676

Abstract: In relation to Fig. 2 of the drawing, a gas turbine with a compressor (18) and a turbine (20), bypasses a portion of the cool air from the compressor (18) into the turbine (20) through a conduit (30, 32), which conduit delivers the cool air to the inlet (33) of the turbine blades (26) so that the cool air (36) flows along the suction side of the turbine blades and maintains a stable flow condition with respect to the hot gases (37) along the pressure side of the turbine blades, with the result that the turbine blades are cooled by the cool air through the conduit (30).

Abstract translation: 关于图1。 如图2所示，具有压缩机（18）和涡轮机（20）的燃气涡轮机通过导管（30,32）将来自压缩机（18）的冷空气的一部分旁路到涡轮机（20）中， 导管将冷空气输送到涡轮叶片（26）的入口（33），使得冷空气（36）沿着涡轮叶片的吸力侧流动并且相对于热气体（37）保持稳定的流动状态， 沿着涡轮叶片的压力侧，结果涡轮叶片被冷空气通过导管（30）冷却。

公开(公告)号：EP0192185A3

公开(公告)日：1988-06-08

申请号：EP86101799

申请日：1986-02-13

Applicant: MTU MOTOREN- UND TURBINEN-UNION MÜNCHEN GMBH

Inventor： Eidenschink, Hans

IPC: F01D11/08 ,  F01D05/08 ,  F01D25/08

CPC classification number: F01D25/12 ,  F01D11/24 ,  Y02T50/675

公开(公告)号：WO1998013584A1

公开(公告)日：1998-04-02

申请号：PCT/DE1997002059

申请日：1997-09-12

Applicant: SIEMENS AKTIENGESELLSCHAFT ,  GROSS, Heinz-Jürgen

Inventor： SIEMENS AKTIENGESELLSCHAFT

IPC: F01D05/08

CPC classification number: F01D5/08 ,  F02C7/18 ,  F05D2260/607 ,  Y02T50/676

Abstract: The invention concerns an energetically advantageous method of cooling a component in a gas turbine plant and a gas turbine plant designed according to the invention. After compression by a compressor (6) in the gas turbine plant, a partial air mass flow (3) is branched off a main air mass flow (2) and is guided in a closed duct (9) to the component to be cooled, the partial air mass flow (3) being subjected, independently of the main air mass flow (2), to additional compression which is carried out using the rotational energy of a turbomachine shaft of the gas turbine plant. To that end, according to the invention, a correspondingly designed gas turbine plant comprises a secondary compressor (10). The invention is suitable in particular for use in stationary gas turbine plants.

Abstract translation: 本发明涉及用于冷却燃气涡轮机设备的一个组件的高能效的方法和一个根据本发明设计的燃气轮机装置。 的空气质量流量（3）由压缩机压缩后分支出来的主空气质量流量的燃气轮机装置（6）（2），并在同一个组件的封闭通道（9）被引导至被冷却。 的空气质量流（3）经历独立于主空气质量流量（2）额外的压缩，这通过利用燃气轮机设备的涡轮发动机轴的旋转能量发生的。 因此，根据本发明的相应配置的燃气涡轮机组包括辅助压缩机（10）。 本发明特别适合于在固定式燃气轮机设备中使用。

公开(公告)号：WO1998011326A1

公开(公告)日：1998-03-19

申请号：PCT/US1997018234

申请日：1997-08-29

Applicant: AERODYNE RESEARCH, INC.

Inventor： AERODYNE RESEARCH, INC. ,  STICKLER, David, B. ,  KERREBROCK, Jack, L.

IPC: F01D05/08

CPC classification number: F01D5/181 ,  F01D5/088 ,  F01D5/185 ,  Y02T50/676

Abstract: An evaporatively cooled rotor for a gas turbine engine. Each rotor defines an internal cavity which includes a vaporization section that corresponds generally to the blade section of the rotor and a condensing section that corresponds generally to the hub section of the rotor. A radial array of circumferentially disposed capture shelves is provided in the vaporization section for capturing cooling fluid contained within the internal cavity and flowing radially outward under the centrifugal field generated during rotation of the rotor. A barrier disposed along the inner surface of the rotor wall in the condensing section slows or temporarily stops the flow of cooling fluid prior to reaching the vaporization section and a perforated baffle attached to the capture shelves prevents cooling fluid from splashing out of the shelves.

Abstract translation: 用于燃气涡轮发动机的蒸发冷却转子。 每个转子限定内部空腔，其包括大致对应于转子的叶片部分的蒸发部分和大致对应于转子的毂部分的冷凝部分。 在蒸发部分中设置有圆周设置的捕获搁架的径向阵列，用于捕获内部空腔内的冷却流体，并且在转子旋转期间产生的离心场下径向向外流动。 沿着冷凝部分的转子壁的内表面设置的阻挡件在到达蒸发部分之前减慢或暂时停止冷却流体的流动，并且附接到捕获架的穿孔挡板防止冷却流体从搁架中溅出。

公开(公告)号：WO1994016200A1

公开(公告)日：1994-07-21

申请号：PCT/US1994000414

申请日：1994-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  GRANT, Parker, A. ,  HOYT, Stephen, D.

IPC: F01D05/08

CPC classification number: F01D5/3015 ,  F01D5/082 ,  F01D11/005

Abstract: A gas turbine engine having a turbine rotor assembly with a free standing sideplate assembly is disclosed. Various construction details are developed which provide a sideplate assembly which is not radially or axially supported by the web or rim of the adjacent disk. In one particular embodiment, a rotor assembly includes a rotor disk, having a rim, a web (44), and a bore (46) and a sideplate assembly, having a web (54) and a bore (52). The web of the sideplate is radially supported by the bore of the sideplate and includes a disk seal means (62, 86) and an aperture (66). The disk seal means (62, 86) is engaged with the rotor disk and has an axially directed seal force provided by an axially interfering fit between the sideplate and rotor disk. The aperture (68) provides means for fluid communication between a source of cooling fluid and the rotor disk.

Abstract translation: 公开了具有具有独立侧板组件的涡轮转子组件的燃气涡轮发动机。 开发出各种构造细节，其提供侧板组件，其不被相邻盘的腹板或边缘径向或轴向地支撑。 在一个具体实施例中，转子组件包括转子盘，其具有轮缘，腹板（44）和具有腹板（54）和孔（52）的孔（46）和侧板组件。 侧板的腹板由侧板的孔径向支撑，并且包括盘密封装置（62,86）和孔（66）。 圆盘密封装置（62,86）与转子盘接合并且具有通过侧板和转子盘之间的轴向干涉配合提供的轴向定向的密封力。 孔（68）提供用于冷却流体源和转子盘之间的流体连通的装置。

公开(公告)号：WO1993006340A1

公开(公告)日：1993-04-01

申请号：PCT/US1992007987

申请日：1992-09-18

Applicant: BENTON, Christopher, E.

IPC: F01D05/08

CPC classification number: H01L23/467 ,  F28F13/08 ,  H01L2924/0002 ,  H01L2924/00

Abstract: An object (6, 8) to be cooled is placed within the constricted chamber region (18) of a cooling chamber (12) that has first and second open ends communicating with first and second chamber regions (14, 16) communicating with the constricted chamber region disposed therebetween. A mechanism (22, 22') for transporting a cooling medium is coupled to the first chamber end, and/or a second such transport mechanism (24, 24') is coupled to the second chamber end, the mechanisms being operated in push-pull fashion. These transport mechanisms and Venturi-like chamber cause the cooling medium entering the first chamber region to be compressed upon approaching the constricted chamber region, and to expand upon exiting the constricted chamber region and entering the second chamber region. Cooling medium velocity in the constricted chamber region is maximized, thereby promoting removal of heat from the object to be cooled.

Abstract translation: 要冷却的物体（6,8）被放置在冷却室（12）的收缩室区域（18）内，该冷却室（12）具有第一和第二开放端，与第一和第二室区域（14,16）连通， 腔室区域。 用于输送冷却介质的机构（22,22'）联接到第一室端部，和/或第二这样的输送机构（24,24'）联接到第二室端部， 拉时尚。 这些传送机构和文氏管状室使得进入第一室区域的冷却介质在接近收缩室区域时被压缩，并且在离开收缩室区域并进入第二室区域时膨胀。 收缩室区域中的冷却介质速度最大化，从而促进从被冷却物体中除去热量。

公开(公告)号：WO1982001033A1

公开(公告)日：1982-04-01

申请号：PCT/US1980001278

申请日：1980-09-24

Applicant: KARSTENSEN K

IPC: F01D05/08

CPC classification number: F01D9/042 ,  F01D5/189

Abstract: An improved gas turbine cooling system for a modularized gas turbine is provided by mounting a hollow nozzle vane (18) on an outer shroud (32) to extend inwardly to an inner shroud (36) in which they are slidingly engaged. Cooling air is directed through an annulus (24) into the hollow nozzle vanes (18) which are formed with vent holes (56) on the trailing edge thereof. Both the outer (32) and inner (36) shroud portions are contained in one of the engine modules (12) while the other of the engine modules (14) is sealingly associated with the one module (12) by sealing rings (26, 28) having a greater coefficient of thermal expansion than the outer shroud (32).

Abstract translation: 通过将中空喷嘴叶片（18）安装在外部护罩（32）上以向内延伸到内部护罩（36），提供用于模块化燃气轮机的改进的燃气轮机冷却系统，在该内部护罩36滑动地接合。 冷却空气通过环（24）引导到中空喷嘴叶片（18）中，中空喷嘴叶片（18）在其后缘形成有通气孔（56）。 外部（32）和内部（36）护罩部分都被包含在一个发动机模块（12）中，而另一个发动机模块（14）通过密封环（26）密封地与一个模块（12） 28）具有比外护罩（32）更大的热膨胀系数。

公开(公告)号：WO1998023851A1

公开(公告)日：1998-06-04

申请号：PCT/JP1996003503

申请日：1996-11-29

Applicant: HITACHI, LTD. ,  MARUSHIMA, Shinya ,  MATSUMOTO, Manabu ,  KAWAIKE, Kazuhiko ,  IKEGUCHI, Takashi ,  MACHIDA, Takashi ,  SEKIHARA, Masaru

Inventor： HITACHI, LTD.

IPC: F01D05/08

CPC classification number: F01D5/085 ,  F01D5/084 ,  F05D2260/205

Abstract: To improve reliability in operation of a gas turbine by suppressing thermal stresses applied onto a rotor of the gas turbine and thermal displacement thereof. In the gas turbine, a plurality of disks (12a) having a plurality of moving blades (7a), which are driven by combustion gas, annularly arranged on an outer periphery thereof, and spacers (11a) disposed between the disks (12a) are successively arranged in an axial direction to form a rotor (1a) shaft. A gap is formed between that area of the disk (12a) on a side of an axis of the rotor, which faces the spacer (11a), and the adjacent spacer (11a), and contact surfaces (16a) contacting both that area of the disk (12a) on a side of an outer periphery of the rotor, which faces the spacer (11a), and the adjacent spacer (11a) are formed. Further, third flow passages (10a) are provided on the disks (12a) for conducting a fluid to the gap.

Abstract translation: 通过抑制施加在燃气轮机的转子上的热应力及其热位移来提高燃气轮机运转的可靠性。 在燃气轮机中，具有环形地设置在其外周上的由燃烧气体驱动的多个活动叶片（7a）的多个盘（12a）和设置在盘（12a）之间的间隔件（11a） 依次布置在轴向上以形成转子（1a）轴。 在转子的面向间隔件（11a）的一侧的盘（12a）的区域与相邻的间隔件（11a）之间形成有间隙，以及接触表面（16a） 形成面向间隔件（11a）的转子的外周侧的盘（12a）和相邻的间隔件（11a）。 此外，第三流动通道（10a）设置在盘（12a）上，用于将流体传导到间隙。

公开(公告)号：WO1997049902A1

公开(公告)日：1997-12-31

申请号：PCT/US1997008107

申请日：1997-05-12

Applicant: WESTINGHOUSE ELECTRIC CORPORATION

Inventor： WESTINGHOUSE ELECTRIC CORPORATION ,  PFEIFER, Nathan, R. ,  DIAKUNCHAK, Ihor, S. ,  HUBER, David, J.

IPC: F01D05/08

CPC classification number: F01D5/081 ,  F05D2260/205

Abstract: The design of compressors for the cooling systems for combustion turbines is disclosed. Closed-loop air cooling systems and combustion turbines with ultra-low NOx emission combustion systems require nearly all of the compressor air to be pre-mixed with fuel. In either of these systems, it is necessary to extract a portion of the compressor delivery air, cool it, compress it and then re-introduce it into the combustion turbine. In the prior art, this was accomplished using an outside compressor. However, in accordance with the present invention, a compressor that supplies the required amount of increased pressure air for cooling hot end components is provided that is "on-board" or internal to the combustion turbine system. In preferred embodiments, an axial compressor receives a portion of compressor delivery air, is diverted at the compressor exit inner diameter and then compressed in one or more reduced height axial compressor stages located below the inner wall of the main compressor exit diffuser that is itself located directly downstream from the auxiliary compressor. Methods of cooling combustion turbines are also disclosed.

Abstract translation: 公开了用于燃烧涡轮机的冷却系统的压缩机的设计。 具有超低NOx排放燃烧系统的闭环空气冷却系统和燃烧涡轮机需要几乎所有的压缩机空气与燃料预混合。 在这些系统中的任何一个中，必须提取压缩机输送空气的一部分，将其冷却，压缩，然后将其重新引入燃气轮机。 在现有技术中，这是使用外部压缩机完成的。 然而，根据本发明，提供了“车载”或燃烧涡轮机系统内部的用于冷却热端部件所需量的增压空气的压缩机。 在优选实施例中，轴向压缩机接收压缩机输送空气的一部分，在压缩机出口内径处转向，然后在位于主压缩机出口扩散器的内壁下方的一个或多个减小高度的轴向压缩机级中被压缩，本体位于 直接从辅助压缩机的下游。 还公开了冷却燃烧涡轮机的方法。