Turbine blade airfoil profile

Patent metadata

Field	Value
Publication number	US-11156096-B2
Application number	US-202016784811-A
Country	US
Kind code	B2
Filing date	Feb 7, 2020
Priority date	Feb 7, 2020
Publication date	Oct 26, 2021
Grant date	Oct 26, 2021

Abstract

Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

First claim

We claim:

1. A turbine blade comprising:
an airfoil having a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and
an endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge;
wherein at least one of a suction side or a pressure side of the airfoil has a shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the Cartesian coordinate values are non-dimensional percentage values from 0% to 100%, wherein the values are convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at each Z distance being joined smoothly with one another to form the nominal profile,
wherein the shape having the nominal profile substantially in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 5% and 95% of the height of the airfoil.

2. The turbine blade of claim 1 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.

3. The turbine blade of claim 1 , wherein the turbine blade is a fourth stage blade.

4. The turbine blade of claim 1 , wherein the shape having the nominal profile substantially in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil.

5. A rotor blade section for a turbine, the rotor blade section comprising:
a set of rotating blades, the set of rotating blades including at least one blade having:
an airfoil having a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and

an endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge;
wherein at least one of a suction side or a pressure side of the airfoil has a shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the Cartesian coordinate values are non-dimensional percentage values of from 0% to 100%, wherein the values are convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at each Z distance being joined smoothly with one another to form the nominal profile,
wherein the shape having the nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 5% and 95% of the height of the airfoil.

6. The rotor blade section of claim 5 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.

7. The rotor blade section of claim 5 , wherein the rotor blade section is a fourth stage blade section.

8. The rotor blade section of claim 5 , wherein the shape having the nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil.

9. A turbine comprising a plurality of rotor blades, each of the plurality of rotor blades comprising:
an airfoil having a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and
an endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge;
wherein at least one of a suction side or a pressure side of the airfoil has a shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I, wherein the Cartesian coordinate values are non-dimensional percentage values of from 0% to 100%, wherein the values are convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at each Z distance being joined smoothly with one another to form the nominal profile,
wherein the shape having the nominal profile substantially in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 5% and 95% of the height of the airfoil.

10. The turbine of claim 9 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.

11. The turbine of claim 9 , wherein the turbine rotor blade is a fourth stage rotor blade.

12. The turbine of claim 9 , wherein the shape having the nominal profile substantially in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil.

Assignees

• Gen Electric

Inventors

• Ristau Neil Devin
• Wondrasek Michael Anthony
• Agudo Jan Emeric

Classifications

• Y02E20/16

  Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT] · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2240/306

  related to the suction side of a rotor blade · CPC title

• F04D29/544

  Blade shapes · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title