This point, referenced as point 2, is also the origin of a new coordinate system. With this radial location, the point on the turbine bucket airfoil 10 that has the minimum axial location is used to define this point in space. The topmost point 2 is intended to be high along the turbine bucket airfoil 10, but be kept below the tip shelf to avoid any fillets and cooling holes. The first two points of the plane are located along the leading edge, as seen in FIG. 2 is oriented such that it is generally aligned with the leading edge and the chord line of the turbine bucket airfoil 10, as embodied by the invention. Each defined airfoil section in the X, Y plane is joined smoothly with adjacent airfoil sections in the Z direction to form the complete airfoil shape. The X, Y, and Z coordinates are given in distance dimensions, e.g., units of inches, and are joined smoothly at each Z location to form a smooth continuous airfoil cross-section. The positive X, Y and Z directions are axial toward the exhaust end of the turbine, tangential in the direction of engine rotation and radially outwardly toward the static case, respectively. The points for the coordinate values shown in Table 1 relative to the engine centerline and for a cold, i.e., room temperature bucket at various cross-sections of the bucket's airfoil along its length. These unique loci of points define the nominal airfoil profile and are identified by the X, Y and Z Cartesian coordinates of various Tables that follow. The rotor bucket airfoil profile, as embodied by the invention, is defined by unique loci of points to achieve the necessary efficiency and loading requirements whereby improved performance is obtained. Y10S416/00- Fluid reaction surfaces, i.e.Y10S- TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS AND DIGESTS.Y10- TECHNICAL SUBJECTS COVERED BY FORMER USPC.Y- GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS AND DIGESTS.F01D5/00- Blades Blade-carrying members Heating, heat-insulating, cooling or antivibration means on the blades or the members.F01D- NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g.F01- MACHINES OR ENGINES IN GENERAL ENGINE PLANTS IN GENERAL STEAM ENGINES.F- MECHANICAL ENGINEERING LIGHTING HEATING WEAPONS BLASTING.238000004519 manufacturing process Methods 0.000 claims abstract description 8.Assignors: VANDEPUTTE, THOMAS W., GRAFITTI, ANDREW D., VELTRE, LOUIS Publication of US20110076150A1 publication Critical patent/US20110076150A1/en Application granted granted Critical Publication of US8133030B2 publication Critical patent/US8133030B2/en Status Active legal-status Critical Current Adjusted expiration legal-status Critical Links Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Application filed by General Electric Co filed Critical General Electric Co Priority to US12/570,265 priority Critical patent/US8133030B2/en Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Original Assignee General Electric Co Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Vandeputte Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Active, expires Application number US12/570,265 Other versions US20110076150A1
AIRFOIL SHAPE PDF
Google Patents US8133030B2 - Airfoil shapeÄownload PDF Info Publication number US8133030B2 US8133030B2 US12/570,265 US57026509A US8133030B2 US 8133030 B2 US8133030 B2 US 8133030B2 US 57026509 A US57026509 A US 57026509A US 8133030 B2 US8133030 B2 US 8133030B2 Authority US United States Prior art keywords airfoil profile inches bucket turbine Prior art date Legal status (The legal status is an assumption and is not a legal conclusion.