Turbine component with dust tolerant cooling system

Patent metadata

Field	Value
Publication number	US-11230929-B2
Application number	US-201916674527-A
Country	US
Kind code	B2
Filing date	Nov 5, 2019
Priority date	Nov 5, 2019
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

A turbine component includes a hot wall, a cold wall spaced apart from the hot wall and a conduit defined between the hot wall and the cold wall. A cooling system is defined in the conduit. The cooling system includes a plurality of cooling pins, each including a first end having a first cross-sectional area and a second end having a second cross-sectional area. Each cooling pin includes a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end. The pin leading edge is defined by a first diameter and a pin trailing edge is defined by a second diameter. At least one first cooling pin has the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

First claim

What is claimed is:

1. A turbine component, comprising:
a hot wall;
a cold wall spaced apart from the hot wall;
a conduit defined between the hot wall and the cold wall; and
a cooling system defined in the conduit between the hot wall and the cold wall, the cooling system including a plurality of cooling pins, each cooling pin of the plurality of cooling pins comprising a first end having a first cross-sectional area, a second end having a second cross-sectional area, the first cross-sectional area less than the second cross-sectional area, and a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end, the pin leading edge opposite a pin trailing edge, the pin leading edge defined by a first diameter and the pin trailing edge defined by a second diameter, the second diameter greater than the first diameter, with at least one first cooling pin of the plurality of cooling pins having the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

2. The turbine component of claim 1 , wherein the turbine component has a pressure side opposite a suction side, a rib that extends between the pressure side and the suction side and the cold wall is defined by the rib.

3. The turbine component of claim 1 , wherein at least one second pin of the plurality of cooling pins has the second end coupled to the hot wall with the fillet and the first end coupled to the cold wall.

4. The turbine component of claim 1 , wherein each of the plurality of cooling pins has the first end coupled to the hot wall and the second end coupled to the cold wall with the fillet.

5. The turbine component of claim 1 , wherein the fillet further comprises a first fillet defined along the leading edge and a second fillet defined along the trailing edge, and a first fillet arc of the first fillet is greater than a second fillet arc of the second fillet.

6. The turbine component of claim 1 , wherein the turbine component comprises an airfoil that extends from an inner diameter to an outer diameter and from a leading edge to a trailing edge, with an inner platform coupled to the airfoil at the inner diameter, the conduit is in proximity to the leading edge to cool the leading edge, the conduit having an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform, the hot wall of the conduit opposite the leading edge, and the cooling system further comprises a second conduit to cool the trailing edge.

7. The turbine component of claim 6 , wherein the outlet portion includes at least one outlet in fluid communication with the second conduit.

8. The turbine component of claim 6 , wherein the outlet portion is in fluid communication with a plurality of film cooling holes defined through a portion of the inner platform that spans between the airfoil and a second airfoil, the second airfoil coupled to the inner platform and spaced apart from the airfoil.

9. The turbine component of claim 6 , wherein downstream from the inner platform, the outlet portion is defined through a portion of the airfoil such that the outlet portion is in fluid communication with the trailing edge.

10. The turbine component of claim 1 , wherein the plurality of cooling pins includes a first pair of the plurality of cooling pins extending substantially along a first longitudinal axis and having the first end of each of the first pair of the plurality of cooling pins coupled to the hot wall and the second end of each of the first pair of the plurality of cooling pins coupled to the cold wall, and a second pair of the plurality of cooling pins, with at least one second pin of the second pair of the plurality of cooling pins having a third end coupled to the hot wall and a fourth end coupled to the cold wall such that the fourth end is offset from an axis that extends through the third end of the at least one second pin of the second pair of the plurality of cooling pins and the third end has a greater cross-sectional area than the fourth end.

11. The turbine component of claim 1 , wherein the cooling system further comprises a rib that extends from the hot wall to the cold wall to divide the conduit into a plurality of flow passages.

12. A turbine component, comprising:
an airfoil having a pressure side opposite a suction side and a rib that extends between the pressure side and the suction side;
a hot wall;
a cold wall spaced apart from the hot wall defined by the rib;
a conduit defined in the airfoil between the hot wall and the cold wall; and
a cooling system defined in the conduit between the hot wall and the cold wall, the cooling system including a plurality of cooling pins, each cooling pin of the plurality of cooling pins comprising a first end having a first cross-sectional area, a second end having a second cross-sectional area, the first cross-sectional area less than the second cross-sectional area, and a body extending between the first end and the second end, with a pin leading edge defined along the body from the first end to the second end, the pin leading edge opposite a pin trailing edge, the pin leading edge defined by a first diameter and the pin trailing edge defined by a second diameter, the second diameter greater than the first diameter, with at least one first cooling pin of the plurality of cooling pins having the first end coupled to the hot wall and the second end coupled to the cold wall with a fillet.

13. The turbine component of claim 12 , wherein at least one second pin of the plurality of cooling pins has the second end coupled to the hot wall with the fillet and the first end coupled to the cold wall.

Assignees

• Honeywell Int Inc

Inventors

• Whitaker Steven
• Crites Daniel
• Kollati Vighneswara
• Morris Mark
• Kamrath Benjamin Dosland

Classifications

• F05D2240/303

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2240/121

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

• F05D2260/2214

  by increasing the heat transfer surface · CPC title

• F05D2260/2212

  by creating turbulence · CPC title