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公开(公告)号：US07581923B2
公开(公告)日：2009-09-01
申请号：US11159686
申请日：2005-06-23
IPC分类号： F01D11/02
CPC分类号： F01D11/04 , F01D5/082 , F01D9/023 , Y02T50/676
摘要： A pump/flow guide is positioned in a gas turbine engine and attached to a transition duct to face a turbine disk. The pump/flow guide provides a smooth path for guiding purge flow to resist the ingestion of hot gas. One leg of the pump/flow guide extends radially outwardly and contacts the radially inner section of the transition duct that forms a “fish mouth.” Spaced tabs on the pump/flow guide receive bolts to secure the pump/flow guide to the transition duct. The pump/flow guide thus provides a relatively smooth flow passage for purge gas flow.
摘要翻译： 泵/流动引导件定位在燃气涡轮发动机中并且附接到过渡管道以面对涡轮盘。 泵/流动导向器提供了一个平滑的路径，用于引导吹扫流动以抵抗热气体的摄取。 泵/流动引导件的一条腿径向向外延伸并接触形成“鱼嘴”的过渡管道的径向内部。 泵/导流板上的间隔的接头接收螺栓，以将泵/流动导向器固定到过渡管道上。 因此，泵/流动引导器提供用于吹扫气体流动的相对平滑的流动通道。
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公开(公告)号：US07708520B2
公开(公告)日：2010-05-04
申请号：US11605678
申请日：2006-11-29
IPC分类号： F01D11/02
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.
摘要翻译： 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。 凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。
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公开(公告)号：US4513567A
公开(公告)日：1985-04-30
申请号：US576770
申请日：1984-02-03
CPC分类号： F01D11/08
摘要： Method for controlling the clearance between rotating and stationary components of a gas turbine engine are disclosed. Techniques for achieving close correspondence between the radial position of rotor blade tips and the circumscribing outer air seals are disclosed. In one embodiment turbine case temperature modifying air is provided in flow rate, pressure and temperature varied as a function of engine operating condition. The modifying air is scheduled from a modulating and mixing valve supplied with dual source compressor air. One source supplies relatively low pressure, low temperature air and the other source supplies relatively high pressure, high temperature air. After the air has been used for the active clearance control (cooling the high pressure turbine case) it is then used for cooling the structure that supports the outer air seal and other high pressure turbine component parts.
摘要翻译： 公开了一种用于控制燃气涡轮发动机的旋转和静止部件之间的间隙的方法。 公开了用于实现转子叶片尖端的径向位置与外接外部空气密封件之间紧密对应的技术。 在一个实施例中，涡轮壳体提供温度改变空气，其流量，压力和温度随发动机工作条件而变化。 改装空气由配有双源压缩机空气的调节和混合阀调度。 一个来源提供相对低压，低温空气，另一个来源提供相对高压，高温空气。 在空气用于主动间隙控制（冷却高压涡轮机壳体）之后，然后将其用于冷却支撑外部空气密封和其它高压涡轮机部件的结构。
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公开(公告)号：US20090067997A1
公开(公告)日：2009-03-12
申请号：US11714019
申请日：2007-03-05
IPC分类号： F04D29/08
CPC分类号： F01D11/02 , F01D11/001 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and a spaced radially outer surface. The control pockets and their associated knife edge seals create a difficult flow path to prevent leakage into radially inner portions of the turbine section.
摘要翻译： 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的控制腔相关联。 控制袋及其相关的刀刃密封件产生困难的流动路径，以防止泄漏到涡轮部分的径向内部。
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公开(公告)号：US08167547B2
公开(公告)日：2012-05-01
申请号：US11714019
申请日：2007-03-05
IPC分类号： F01D11/02
CPC分类号： F01D11/02 , F01D11/001 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and a spaced radially outer surface. The control pockets and their associated knife edge seals create a difficult flow path to prevent leakage into radially inner portions of the turbine section.
摘要翻译： 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的控制腔相关联。 控制袋及其相关的刀刃密封件产生困难的流动路径，以防止泄漏到涡轮部分的径向内部。
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公开(公告)号：US20080124215A1
公开(公告)日：2008-05-29
申请号：US11605678
申请日：2006-11-29
IPC分类号： F01D25/00
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.
摘要翻译： 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。 凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。
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