Airfoil having pedestals in trailing edge cavity

Patent metadata

Field	Value
Publication number	US-10337332-B2
Application number	US-201615053682-A
Country	US
Kind code	B2
Filing date	Feb 25, 2016
Priority date	Feb 25, 2016
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

An airfoil of a gas turbine engine includes an airfoil body having a leading edge and a trailing edge extending in a radial direction, a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge, at least one set of blocking pedestals located within the trailing edge cavity, a set of circular pedestals located aftward from the at least one blocking set of pedestals, and a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body.

First claim

What is claimed is:

1. An airfoil of a gas turbine engine comprising:
an airfoil body having a leading edge and a trailing edge extending in a radial direction;
a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge;
at least one set of blocking pedestals located within the trailing edge cavity, wherein each blocking pedestal of the set of blocking pedestals has a length (Lr) extending in an axial direction and a width (Wr) in the radial direction, wherein the width is greater than the length, thus forming a racetrack geometry such that each pedestal has a constant width and has curved ends;
a set of circular pedestals located aftward from the at least one blocking set of pedestals; and
a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body,
wherein the blocking pedestals, the circular pedestals, and the spear pedestals are integrally clocked with an adjacent set of pedestals to provide even distribution of flow between each set of the pedestals and out the trailing edge of the airfoil,
wherein the blocking pedestals block a flow path of air through the trailing edge cavity and generate a feed pressure and backflow margin for cooling holes within the airfoil.

2. The airfoil of claim 1 , wherein the at least one set of blocking pedestals comprises two sets of blocking pedestals.

3. The airfoil of claim 2 , wherein a spacing between a first set of blocking pedestals and a second set of blocking pedestals is between 0.025 inches and 0.100 inches (0.064-0.254 cm) and a space between the second set of blocking pedestals and the set of circular pedestals is between 0.025 inches and 0.100 inches (0.064-0.254 cm).

4. The airfoil of claim 1 , wherein each of the at least one set of blocking pedestals, the set of circular pedestals, and the set of spear pedestals are arranged along a respective pedestal axis extending in a radial direction, wherein each of the respective pedestal axes of the blocking pedestals, the circular pedestals, and the spear pedestals is parallel with the other respective pedestal axes of the blocking pedestals, the circular pedestals, and the spear pedestals.

5. The airfoil of claim 1 , wherein a width to length ratio for the pedestals of the at least one set of blocking pedestals is between 0.75 and 0.90.

6. The airfoil of claim 1 , wherein the length of each pedestal of the at least one set of blocking pedestals is between 0.036 inches and 0.144 inches (0.091-0.366 cm) and the width of each pedestal of the at least one set of blocking pedestals is between 0.013 inches and 0.050 inches (0.033-0.127 cm).

7. The gas turbine engine of claim 1 , wherein the at least one set of blocking pedestals blocks between 65% and 80% of flow through the trailing edge cavity and the set of circular pedestals and spear pedestals block between 45% and 60% of flow through the trailing edge cavity.

8. A gas turbine engine comprising:
an airfoil having:
an airfoil body having a leading edge and a trailing edge extending in a radial direction;
a trailing edge cavity formed within the airfoil and proximate to the trailing edge of the airfoil, the trailing edge cavity extending from the trailing edge in a forward direction toward the leading edge;
at least one set of blocking pedestals located within the trailing edge cavity, wherein each blocking pedestal of the set of blocking pedestals has a length (Lr) extending in an axial direction and a width (Wr) in the radial direction, wherein the width is greater than the length, thus forming a racetrack geometry such that each pedestal has a constant width and has curved ends;
a set of circular pedestals located aftward from the at least one blocking set of pedestals; and
a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body,
wherein the blocking pedestals, the circular pedestals, and the spear pedestals are integrally clocked with an adjacent set of pedestals to provide even distribution of flow between each set of the pedestals and out the trailing edge of the airfoil,
wherein the blocking pedestals block a flow path of air through the trailing edge cavity and generate a feed pressure and backflow margin for cooling holes within the airfoil.

9. The gas turbine engine of claim 8 , wherein the at least one set of blocking pedestals comprises two sets of blocking pedestals.

10. The gas turbine engine of claim 9 , wherein a spacing between a first set of blocking pedestals and a second set of blocking pedestals is between 0.025 inches and 0.100 inches (0.064-0.254 cm) and a space between the second set of blocking pedestals and the set of circular pedestals is between 0.025 inches and 0.100 inches (0.064-0.254 cm).

11. The gas turbine engine of claim 8 , wherein each of the at least one set of blocking pedestals, the set of circular pedestals, and the set of spear pedestals are arranged along a respective pedestal axis extending in a radial direction, wherein each of the respective pedestal axes of the blocking pedestals, the circular pedestals, and the spear pedestals is parallel with the other respective pedestal axes of the blocking pedestals, the circular pedestals, and the spear pedestals.

12. The gas turbine engine of claim 8 , wherein a width to length ratio for the pedestals of the at least one set of blocking pedestals is between 0.75 and 0.90.

13. The gas turbine engine of claim 8 , wherein the length of each pedestal of the at least one set of blocking pedestals is between 0.036 inches and 0.144 inches (0.091-0.366 cm) and the width of each pedestal of the at least one set of blocking pedestals is between 0.013 inches and 0.050 inches (0.033-0.127 cm).

14. The airfoil of claim 8 , wherein the at least one set of blocking pedestals blocks between 65% and 80% of flow through the trailing edge cavity and the set of circular pedestals and spear pedestals block between 45% and 60% of flow through the trailing edge cavity.

15. A core for manufacturing an airfoil of a gas turbine engine, the core comprising:
a core body having core body and a plurality of apertures and voids therein configured to enable manufacture of an airfoil, the core body having a leading edge and a trailing edge extending in a radial direction; and
a trailing edge structure proximate to the trailing edge of the core body, the trailing edge structure configured to form a trailing edge cavity in an airfoil, the trailing edge structure extending from the trailing edge in a forward direction toward the leading edge, the trailing edge structure comprising:
at least one first set of apertures configured to form at least one set of blocking pedestals located within the trailing edge cavity, wherein each blocking pedestal of the set of blocking pedestals has a length (Lr) extending in an axial direction and a width (Wr) in the radial direction, wherein the width is greater than the length, thus forming a racetrack geometry such that each pedestal has a constant width and has curved ends;
at least one second set of apertures configured to form a set of circular pedestals located aftward from the at least one blocking set of pedestals; and
at least one third set of apertures configured to form a set of spear pedestals located aftward from the set of circular pedestals and closest to the trailing edge of the airfoil body,
wherein the blocking pedestals, the circular pedestals, and the spear pedestals are integral

Assignees

• United Technologies Corp

Inventors

• Auxier James Tilsley
• Teller Bret M

Classifications

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• B22C9/101

  Permanent cores · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title