Turbine stage platform with endwall contouring incorporating wavy mate face
A turbine stage includes a first airfoil and a second airfoil extending respectively from a first platform and a second platform that form an endwall for a flow passage. The endwall has a nominal surface that is axisymmetric about an axis of the turbine stage. The endwall further includes at least one contoured region that is non-axisymmetric with respect to the axis. The at least one contoured region extends from the first platform to the second platform across a platform splitline. The global maximum variation in elevation ΔEW of the endwall is at least 3% of an axial chord length L of the airfoils on the endwall. The maximum variation in elevation ΔMF at the mate facea of the platforms lies in the range 15-60% ΔEW.
1. A turbine stage comprising:
a first airfoil extending from a first platform and a second airfoil spaced circumferentially from the first airfoil and extending from a second platform,
wherein a flow passage of a working medium is defined between the first and second airfoils, the first and second platforms defining an endwall for said flow passage,
wherein the first and second platforms comprise respective mate faces that interface along a platform splitline,
wherein the endwall has a nominal surface that is axisymmetric about an axis of the turbine stage, the endwall further comprising at least one contoured region that is non-axisymmetric with respect to said axis, the at least one contoured region extending from the first platform to the second platform across the platform splitline,
wherein a global maximum variation in elevation ΔEW of the endwall is at least 3% of an axial chord length L of the airfoils on said endwall,
wherein a maximum variation in elevation ΔMF at any of said mate faces lies in the range 30-45% ΔEW,
wherein the at least one contoured region comprises a first region comprising a bulge and a second region comprising a depression,
wherein the global maximum variation in elevation ΔEW of the endwall is defined as a difference in elevation between a peak of the bulge and a depth d of a bottom point of the depression in relation to the nominal surface,
wherein the bulge is along a pressure side surface on a leading edge of one of the first and second airfoils,
wherein the depression is along a suction side surface and extends from a downstream of the bulge in the flow passage toward a trailing edge of the one of the first and second airfoils, and
wherein the depression and the bulge do not overlap in a plane perpendicular to the axial direction.
2. The turbine stage according to claim 1 , wherein the global maximum variation in elevation ΔEW of the endwall is at least 5% of the axial chord length L of the airfoils on said endwall.
3. The turbine stage according to claim 1 ,
wherein the airfoils belong to a row of rotating blades, and
wherein the endwall is an inner endwall located at the hub side of the airfoils.
4. The turbine stage according to claim 1 ,
wherein the airfoils belong to a row of stationary vanes, and
wherein the endwall is an inner endwall located at the hub side of the airfoils.
5. The turbine stage according to claim 1 ,
wherein the airfoils belong to a row of stationary vanes, and
wherein the endwall is an outer endwall located at the tip side of the airfoils.