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ENDWALL CONTOURING FOR A CONICAL ENDWALL
ENDWALL CONTOURING FOR A CONICAL ENDWALL
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机译:端壁轮廓为锥形端墙
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摘要
A turbine stage includes an array of airfoils spaced apart circumferentially to define a flow passage therebetween for channeling a working medium. The airfoils extend radially outward from an inner endwall located at a hub side thereof. The inner endwall is inclined at an angle to an engine axis such that the flow passage is divergent from an upstream side to a downstream side. The inner endwall is non-axisymmetric about the engine axis, having a mid-passage bulge located between circumferentially adjacent first and second airfoils. The bulge has a peak at a position between 20-60% CaxID and at a position between 30-70% pitchID.
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机译:涡轮级包括围绕间隔开的翼型阵列,以便在其间限定用于引导工作介质的流动通道。翼型从位于其轮毂侧的内端壁径向向外延伸。内端壁与发动机轴线成一定角度倾斜,使得流动通道从上游侧发散到下游侧。内端壁围绕发动机轴线是非轴对称的,其中中间通道凸起位于周向相邻的第一和第二翼型之间。凸起在20-60%CAX ID 的位置处具有峰值,并且在30-70%间距 id 之间的位置。
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