Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the first stage of a turbine
First Claim
1. An aerodynamic profile for a turbine blade, the profile being, when cold and in a non-coated state, substantially identical to a nominal profile determined by Cartesian coordinates X,Y,Z′
- given in Table 1, in which the coordinate Z′
is a quotient D/H, where D is a distance of a point under consideration from a first reference X,Y plane situated at a base of the nominal profile, and H is a height of said profile measured from said first reference plane that is an intersection of a stacking axis of a set of blades and an axisymmetric surface of a hub, out to a second reference plane that is an intersection of said stacking axis with an axisymmetric surface of a casing, the measurements D and H being taken radially relative to an axis of a turbine, and the coordinate X is measured in an axial direction of the turbine.
3 Assignments
0 Petitions
Accused Products
Abstract
When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
16 Citations
10 Claims
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1. An aerodynamic profile for a turbine blade, the profile being, when cold and in a non-coated state, substantially identical to a nominal profile determined by Cartesian coordinates X,Y,Z′
- given in Table 1, in which the coordinate Z′
is a quotient D/H, where D is a distance of a point under consideration from a first reference X,Y plane situated at a base of the nominal profile, and H is a height of said profile measured from said first reference plane that is an intersection of a stacking axis of a set of blades and an axisymmetric surface of a hub, out to a second reference plane that is an intersection of said stacking axis with an axisymmetric surface of a casing, the measurements D and H being taken radially relative to an axis of a turbine, and the coordinate X is measured in an axial direction of the turbine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
- given in Table 1, in which the coordinate Z′
Specification
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- Resources
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Current AssigneeSafran Aircraft Engine Company
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Original AssigneeSnecma (Safran SA)
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InventorsMartet, Renaud, Routier, Pascal, Royan, Renaud, Bleuzen, Jean
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Primary Examiner(s)EDGAR, RICHARD A
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Application NumberUS13/171,734Publication NumberTime in Patent Office993 DaysField of SearchNoneUS Class Current416/223.ACPC Class CodesF01D 5/141 Shape, i.e. outer, aerodyna...F05D 2250/74 given by a set or table of ...Y02T 50/60 Efficient propulsion techno...
