Cooled airfoil structure

Patent metadata

Field	Value
Publication number	US-10494929-B2
Application number	US-201514804424-A
Country	US
Kind code	B2
Filing date	Jul 21, 2015
Priority date	Jul 24, 2014
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

An airfoil structure for a gas turbine engine includes an airfoil that includes a suction side cooling circuit with at least two segments that are connected by at least one impingement passage.

First claim

What is claimed is:

1. An airfoil structure for a gas turbine engine comprising:
a platform including a radially inner side and a radially outer side;
a root portion extending from the radially inner side of the platform; and
an airfoil extending from the radially outer side of the platform, the airfoil including a suction side cooling circuit with at least two radially spaced segmented passages connected by at least one impingement passage, wherein the airfoil includes a central wall and a pressure side cooling circuit with the central wall dividing the pressure side cooling circuit and the suction side cooling circuit.

2. The airfoil structure of claim 1 , wherein the at least one impingement passage defines a centerline with a first component directed toward a suction side of the airfoil and a second component directed in a radially direction.

3. The airfoil structure of claim 2 , wherein the at least one impingement passage includes an inlet and an outlet and the inlet is spaced a first distance from the suction side of the airfoil and the outlet is spaced a second distance from the suction side of the airfoil with the first distance being greater than the second distance.

4. The airfoil structure of claim 3 , wherein a suction side wall of the airfoil at least partially defines the at least two radially spaced segments.

5. The airfoil structure of claim 1 , wherein the suction side cooling circuit includes at least one section extending longitudinally along a suction side of the airfoil.

6. The airfoil structure of claim 5 , wherein the at least one section includes the at least two radially spaced segmented passages.

7. The airfoil structure of claim 6 , wherein the at least one section includes multiple sections connected by u-shaped bends to form a serpentine pattern along the suction side of the airfoil.

8. The airfoil structure of claim 1 , wherein an outlet of the impingement passage is directed radially inward from an inlet of the impingement passage toward a suction side of the airfoil.

9. The airfoil structure of claim 1 , wherein the pressure side cooling circuit extends along a pressure side of the airfoil, a leading edge cooling circuit extending along a leading edge of the airfoil, and a trailing edge cooling circuit extending along a trailing edge of the airfoil.

10. A gas turbine engine section comprising:
a rotor configured to rotate about an axis of rotation;
an airfoil structure including:
a root portion configured to engage the rotor;
an airfoil including a suction side cooling circuit having multiple radially spaced segmented passages connected by at least one impingement passage; and
a pressure side cooling circuit extending along a pressure side of the airfoil, a leading edge cooling circuit extending along a leading edge of the airfoil, a trailing edge cooling circuit extending along a trailing edge of the airfoil and a central wall dividing the pressure side cooling circuit from the suction side cooling circuit.

11. The gas turbine engine section of claim 10 , wherein the at least one impingement passage defines a centerline with a first component extending in a direction of rotation of the rotor and a second component extending radially.

12. The gas turbine engine section of claim 10 , wherein the at least one impingement passage includes an inlet and an outlet, and the inlet is spaced a first distance from a suction side of the airfoil and the outlet is spaced a second distance from the suction side of the airfoil with the first distance being greater than the second distance.

13. The gas turbine engine section of claim 10 , wherein the suction side cooling circuit includes multiple longitudinally extending passages connected by u-shaped bends to form a serpentine pattern adjacent a suction side of the airfoil and at least one of the longitudinally extending passages includes the multiple radially spaced segmented passages connected by the at least one impingement passage.

14. A method of cooling an airfoil for a gas turbine engine comprising:
directing a cooling fluid into multiple passages extending through a suction side of an airfoil, wherein the airfoil includes a pressure side cooling circuit extending along a pressure side of the airfoil, a leading edge cooling circuit extending along a leading edge of the airfoil, a trailing edge cooling circuit extending along a trailing edge of the airfoil and a central wall dividing the pressure side cooling circuit from the suction side cooling circuit;
directing the cooling fluid from a first one of the multiple passages through at least one impingement passage directed toward a suction side of the airfoil and into a second one of the multiple passages spaced radially from the first one of the multiple passages.

15. The method as recited in claim 14 , wherein the at least one impingement passage includes an inlet and an outlet and the inlet is spaced a first distance from the suction side of the airfoil and the outlet is spaced a second distance from the suction side of the airfoil with the first distance being greater than the second distance.

16. The method as recited in claim 15 , wherein between 20% and 70% of the cooling fluid is directed in the direction of rotation of the gas turbine engine.

17. The method of claim 15 , further comprising directing the cooling fluid through the first one of the multiple passages and the second one of the multiple passages in a serpentine pattern with a u-shaped bend connecting the first one of the multiple passages and the second one of the multiple passages, wherein the first one of the multiple passages and the second one of the multiple passages extend longitudinally between opposing radial ends of the airfoil.

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Snyder Brooks E
• Burdick Andrew D

Classifications

• F01D5/187 Primary

  Convection cooling · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2240/306

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

• Y02T50/676

  Cross-Sectional Technologies · mapped topic