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公开(公告)号：US4926633A
公开(公告)日：1990-05-22
申请号：US372416
申请日：1989-06-27
CPC分类号： F02K1/822 , F01D25/12 , F02C7/18 , F23R3/06 , F23R3/26 , Y02T50/671 , Y02T50/675
摘要： A coolant pressure regulating appartus having a predetermined number of coolant pressure regulating valves which rotate against a spring bias to divert coolant flow and excess pressure from the coolant air fan duct into the engine core exhaust flow. The pressure regulator valve regulates the pressure within a closed cavity suppressor to the pressure level within the core without any affect upon the upstream fan duct pressure.
摘要翻译： 具有预定数量的冷却剂压力调节阀的冷却剂压力调节阀，其克服弹簧偏压旋转，以将冷却剂流和过冷压从冷却剂空气风扇导管转移到发动机芯排气流中。 压力调节阀将闭合的腔体抑制器内的压力调节到芯内的压力水平，而不影响上游风机管道压力。
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公开(公告)号：US4192633A
公开(公告)日：1980-03-11
申请号：US865343
申请日：1977-12-28
申请人： Frederick C. Herzner
发明人： Frederick C. Herzner
CPC分类号： F01D5/22 , F01D11/006 , F01D5/10 , F01D5/3007 , Y10S416/50 , Y10T464/50
摘要： A segmented damper is provided with a lower dovetail portion which is insertable into a dovetail slot for radial retention and which is engageable on its face by a blade retainer for axial retention, such that the damper is pivotable in an axial plane. The damper upper portion has on its one side a flange for engaging the blade shank rail and on its other side a flange for shifting the damper center of gravity axially outward from the lower pivot point. Centrifugal force, occasioned by rotation of the disk and damper, then causes the damper to pivot and impart an axial force against the blade to thereby dampen vibrations.
摘要翻译： 分段阻尼器设置有下部燕尾部分，该下部燕尾部分可插入到燕尾槽中用于径向保持，并且可通过用于轴向保持的叶片保持器在其表面上接合，使得阻尼器可在轴向平面中枢转。 阻尼器上部在其一侧具有用于接合叶片柄杆的凸缘，并且在另一侧上具有用于将阻尼器重心从下枢转点轴向向外移动的凸缘。 离心力通过盘和阻尼器的旋转而产生，然后使阻尼器枢转并且赋予对刀片的轴向力，从而抑制振动。
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公开(公告)号：US5141401A
公开(公告)日：1992-08-25
申请号：US589152
申请日：1990-09-27
CPC分类号： F01D5/3007 , F05D2250/711 , Y02T50/671
摘要： To eliminate stress peaking at the bearing surface interface of the blade and disk slot dovetails in a gas turbine engine, the slot dovetail in undercut to remove disk material from contact with the blade dovetail radially inner edges where surface stress peaking would otherwise occur. The undercut contour radially inward of the blade dovetail is determined by analysis based on each engine design such as to achieve a substantially uniform distribution of surfaces stress along the dovetail slot fillet radius.
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4.发明授权
公开(公告)号：US3982852A
公开(公告)日：1976-09-28
申请号：US528023
申请日：1974-11-29
CPC分类号： F01D5/087 , Y02T50/673 , Y02T50/676
摘要： A bore vane assembly is adapted to be received within the annular passage formed between two axially displaced turbine disc halves so as to provide axial columnar support therebetween during high centrifugal loading. The bore vane assembly includes a plurality of axially extending vanes which provide the required support and which also serve to pump cooling fluid from a plenum into the turbine disc.
摘要翻译： 孔形叶片组件适于容纳在形成在两个轴向移位的涡轮盘半部之间的环形通道内，以便在高离心加载期间在其间提供轴向柱状支撑。 膛孔叶片组件包括多个轴向延伸的叶片，其提供所需的支撑并且还用于将冷却流体从气室泵送到涡轮机盘中。
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