Turbine airfoil with optimized airfoil element angles

Patent metadata

Field	Value
Publication number	US-9797267-B2
Application number	US-201514949991-A
Country	US
Kind code	B2
Filing date	Nov 24, 2015
Priority date	Dec 19, 2014
Publication date	Oct 24, 2017
Grant date	Oct 24, 2017

Abstract

A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 2, 3, and 4.

First claim

What is claimed is:

1. A turbine airfoil assembly for installation in a gas turbine engine having a longitudinal axis, the turbine airfoil assembly including an endwall for defining an inner boundary for an axially extending hot working gas path, and an airfoil extending radially outwardly from the endwall, the airfoil having an outer wall comprising a pressure sidewall and a suction sidewall joined together at chordally spaced apart leading and trailing edges of the airfoil, an airfoil mean line is defined extending chordally and located centrally between the pressure and suction sidewalls, airfoil inlet and exit angles are defined at the airfoil leading and trailing edges that are substantially in accordance with inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 2, 3, and 4, where the inlet and exit angle values are generally defined as angles between a line parallel to the longitudinal axis and the airfoil mean line lying in an X-Y place of an X, Y, Z Cartesian coordinate system in which Z is a dimension perpendicular to the X-Y plane and extends radially relative to the longitudinal axis, and wherein each of the inlet and exit angle values is defined with respect to a distance from the endwall corresponding to a Z value that is a distance of a total span of the airfoil from the endwall with the distances being joined smoothly with one another to form a complete airfoil shape.

2. The turbine airfoil assembly of claim 1 , wherein the airfoil comprises an airfoil for a third stage vane in a turbine engine, and the one of Tables 1, 2, 3, and 4 defining the airfoil inlet and exit angles is Table 1.

3. The turbine airfoil assembly according to claim 1 , wherein the airfoil comprises an airfoil for third stage blade in a turbine engine, and the one of Tables 1, 2, 3, and 4 defining the airfoil inlet and exit angles is Table 2.

4. The turbine airfoil assembly of claim 1 , wherein the airfoil comprises an airfoil for a fourth stage vane in a turbine engine, and the one of Tables 1, 2, 3, and 4 defining the airfoil inlet and exit angles is Table 3.

5. The turbine airfoil assembly according to claim 1 , wherein the airfoil comprises an airfoil for fourth stage blade in a turbine engine, and the one of Tables 1, 2, 3, and 4 defining the airfoil inlet and exit angles is Table 4.

6. The turbine airfoil assembly of claim 1 , including four airfoils comprising, in succession, an airfoil for a third stage vane having the airfoil inlet and exit angles defined by Table 1, an airfoil for a third stage blade having the airfoil inlet and exit angles defined by Table 2, an airfoil for a fourth stage vane having the airfoil inlet and exit angles defined by Table 3 and an airfoil for a fourth stage blade having the airfoil inlet and exit angles defined by Table 4.

7. Third and fourth stage vane and blade airfoil assemblies in a gas turbine engine having a longitudinal axis, each airfoil assembly including:
an endwall for defining an inner boundary for an axially extending hot working gas path, and an airfoil extending radially outwardly from the endwall, the airfoil having an outer wall comprising a pressure sidewall and a suction sidewall joined together at chordally spaced apart leading and trailing edges of the airfoil, an airfoil mean line is defined extending chordally and located centrally between the pressure and suction sidewalls, airfoil inlet and exit angles are defined at the airfoil leading and trailing edges that are substantially in accordance with inlet angle values, α, and exit angle values, β, where the inlet and exit angle values are generally defined as angles between a line parallel to the longitudinal axis and the airfoil mean line lying in an X-Y plane of an X, Y, Z Cartesian coordinate system in which Z is a dimension perpendicular to the X-Y plane and extends radially relative to the longitudinal axis, and wherein each of the inlet and exit angle values is defined with respect to a distance from the endwall corresponding to a Z value that is a percentage of the total span of the airfoil from the endwall, wherein:
a) the inlet angle values, α, and exit angle values, β, for the third stage vane are as set forth in Table 1;
b) the inlet angle values, α, and exit angle values, β, for the third stage blade are as set forth in Table 2;
c) the inlet angle values, α, and exit angle values, β, for the fourth stage vane are as set forth in Table 3;
d) the inlet angle values, α, and exit angle values, β, for the fourth stage blade are as set forth in Table 4.

8. A turbine airfoil assembly for installation in a gas turbine engine having a longitudinal axis, the turbine airfoil assembly including an endwall for defining an inner boundary for an axially extending hot working gas path, and an airfoil extending radially outwardly from the endwall, the airfoil having an outer wall comprising a pressure sidewall and a suction sidewall joined together at chordally spaced apart leading and trailing edges of the airfoil, an airfoil mean line is defined extending chordally and located centrally between the pressure and suction sidewalls, airfoil exit angles are defined at the airfoil trailing edge that are substantially in accordance with exit angle values, β, set forth in one of Tables 1, 2, 3, and 4, where the exit angle values are generally defined as angles between a line parallel to the longitudinal axis and the airfoil mean line lying in an X-Y plane of an X, Y, Z Cartesian coordinate system in which Z is a dimension perpendicular to the X-Y plane and extends radially relative to the longitudinal axis, wherein each the exit angle value is defined with respect to a distance from the endwall corresponding to a Z value that is a distance of a total span of the airfoil from the endwall with the distances being joined smoothly with one another to form a complete airfoil shape, and wherein each the airfoil exit angle is within about 1% of a respective value set forth in one of Tables 1, 2, 3, and 4.

9. The turbine airfoil assembly of claim 8 , wherein the airfoil comprises an airfoil for a third stage vane in a turbine engine, and one of Tables 1, 2, 3, and 4 defining the airfoil exit angles is Table 1.

10. The turbine airfoil assembly of claim 8 , wherein the airfoil comprises an airfoil for a third stage blade in a turbine engine, and one of Tables 1, 2, 3, and 4 defining the airfoil exit angles is Table 2.

11. The turbine airfoil assembly of claim 8 , wherein the airfoil comprises an airfoil for a fourth stage vane in a turbine engine, and one of Tables 1, 2, 3, and 4 defining the airfoil exit angles is Table 3.

12. The turbine airfoil assembly of claim 8 , wherein the airfoil comprises an airfoil for a fourth stage blade in a turbine engine, and one of Tables 1, 2, 3, and 4 defining the airfoil exit angles is Table 4.

13. The turbine airfoil assembly of claim 8 , including four of the airfoils comprising, in succession, an airfoil for a third stage vane having airfoil exit angles defined by Table 1, an airfoil for a third stage blade having airfoil exit angles defined by Table 2, an airfoil for a fourth stage vane having airfoil exit angles defined by Table 3 and an airfoil for a fourth stage blade having airfoil exit angles defined by Table 4.

14. The turbine airfoil assembly of claim 8 , including at least two of the airfoils comprising, in succession, an airfoil for a third stage blade having airfoil exit angles defined by Table 2, and an airfoil for a fourth stage vane having airfoil exit angles defined by Table 3.

Assignees

• Siemens Energy Inc

Inventors

• Lohaus Andrew S
• Malandra Anthony J
• Scribner Carmen Andrew
• Taremi Farzad
• Flitan Horia
• Lee Ching-Pang
• Azad Gm Salam
• Buchal Tobias

Classifications

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F05D2250/74

  given by a set or table of xyz-coordinates · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title