Power turbine blade airfoil profile

• US 9,458,723 B2
• Filed: 02/28/2014
• Issued: 10/04/2016
• Est. Priority Date: 02/28/2014
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Lecuyer, Daniel J, Moradi, Niloofar
• Primary Examiner(s): Edgar, Richard
• Assistant Examiner(s): BROCKMAN, ELDON T
• Application Number:
  US14/192,984
• Publication Number:
  US 20150247407A1
• Time in Patent Office: 949 Days
• Field of Search: None
• US Class Current: 1/1
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2220/3212 the first stage of a turbine
• CPC Class Codes: F05D 2250/712 concave
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A power turbine includes a first stage blade having an airfoil with a cold un-coated nominal profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Claims

1. A turbine blade of a gas turbine engine having a gaspath, the turbine blade comprising an airfoil having an intermediate portion contained within the gaspath and defined by a nominal un-coated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 2 to 13 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine blade, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z, wherein X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile section, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape of the intermediate portion, wherein the turbine blade has a manufacturing tolerance of ±

0.015 inches in a direction perpendicular to the airfoil.

2. The turbine blade as defined in claim 1, wherein the turbine blade is a power turbine blade of the gas turbine engine.

3. The turbine blade as defined in claim 2, wherein the power turbine blade is a first stage power turbine blade of a multi-stage power turbine.

4. A turbine blade for a gas turbine engine having a gaspath, the turbine blade having an intermediate airfoil portion contained within the gaspath and defined by a cold un-coated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 2 to 13 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine blade, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z, wherein the turbine blade has a manufacturing tolerance of ±

0.015 inches.

5. The turbine blade as defined in claim 4, wherein the turbine blade is a power turbine blade of the gas turbine engine.

6. The turbine blade as defined in claim 5, wherein the power turbine blade is a first stage power turbine blade of a multi-stage power turbine.

7. A turbine rotor assembly for a gas turbine engine having a gaspath, the assembly comprising a plurality of blades, each blade including an airfoil having an intermediate portion contained within the gaspath and defined by a cold un-coated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 2 to 13 set forth in Table 2, wherein the point of origin of the orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine blade, the Z values are radial distances measured along the stacking line, the X and Y are coordinate values defining the profile at each distance Z.

8. A power turbine blade comprising at least one airfoil having a surface lying substantially on the points of Table 2, the airfoil extending from a platform defined generally by at least some of the coordinate values of the inner gaspath wall given in Table 1, wherein a fillet radius is applied around the airfoil between the airfoil and platform.