Blade/vane cooling passages

Patent metadata

Field	Value
Publication number	US-10871074-B2
Application number	US-201916289341-A
Country	US
Kind code	B2
Filing date	Feb 28, 2019
Priority date	Feb 28, 2019
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

Abstract

An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.

First claim

What is claimed is:

1. An airfoil, comprising:
a leading edge;
a trailing edge;
a pressure side wall;
a suction side wall;
a first plurality of ribs, comprising:
a first pressure side rib extending from the pressure side wall away from the leading edge;
a first suction side rib extending from the suction side wall away from the leading edge and forming a first vertex with the first pressure side rib;
a second pressure side rib aft of the first pressure side rib and extending from the pressure side wall away from the trailing edge;
a second suction side rib disposed aft of the first suction side rib and extending from the suction side wall away from the trailing edge and forming a second vertex with the second pressure side rib; and
a first internal rib extending from the first vertex to the second vertex; and

a second plurality of ribs, the second plurality of ribs comprising:
a third pressure side rib disposed aft of the second pressure side rib and extending from the pressure side wall away from the leading edge;
a third suction side rib disposed aft of the second suction side rib and extending from the suction side wall away from the leading edge and forming a third vertex with the third pressure side rib;
a fourth pressure side rib disposed aft of the third pressure side rib and extending from the pressure side wall away from the trailing edge;
a fourth suction side rib disposed aft of the third suction side rib and extending from the suction side wall away from the trailing edge and forming a fourth vertex with the fourth pressure side rib; and
a second internal rib extending from the third vertex to the fourth vertex, wherein the second pressure side rib, the second suction side rib, the third pressure side rib, the third suction side rib, the pressure side wall, and the suction side wall form a hexagonal shaped cavity in a radial airfoil cross section of the airfoil.

2. The airfoil of claim 1 , wherein the first pressure side rib, the second pressure side rib, the first internal rib, and the pressure side wall define a discrete quadrilateral shaped cavity in the radial airfoil cross section of the airfoil.

3. The airfoil of claim 2 , wherein the discrete quadrilateral shaped cavity is trapezoidal shaped in the radial airfoil cross section.

4. A blade, comprising:
an attachment having a radial attachment plane;
an airfoil disposed radially outward from the attachment, the airfoil comprising:
a leading edge;
a trailing edge;
a pressure side wall;
a suction side wall;
a first plurality of ribs, comprising:
a first pressure side rib extending from the pressure side wall away from the leading edge;
a first suction side rib extending from the suction side wall away from the leading edge and forming a first vertex with the first pressure side rib;
a second pressure side rib aft of the first pressure side rib and extending from the pressure side wall away from the trailing edge;
a second suction side rib disposed aft of the first suction side rib and extending from the suction side wall away from the trailing edge and forming a second vertex with the second pressure side rib; and
a first internal rib extending from the first vertex to the second vertex; and

a second plurality of ribs, the second plurality of ribs comprising:
a third pressure side rib disposed aft of the second pressure side rib and extending from the pressure side wall away from the leading edge;
a third suction side rib disposed aft of the second suction side rib and extending from the suction side wall away from the leading edge and forming a third vertex with the third pressure side rib;
a fourth pressure side rib disposed aft of the third pressure side rib and extending from the pressure side wall away from the trailing edge;
a fourth suction side rib disposed aft of the third suction side rib and extending from the suction side wall away from the trailing edge and forming a fourth vertex with the fourth pressure side rib; and
a second internal rib extending from the third vertex to the fourth vertex, wherein a first end of the second pressure side rib and a first end of the third pressure side rib intersect in a radial airfoil plane and separate as the second pressure side rib and the third pressure side rib transition from the radial airfoil plane to the radial attachment plane.

5. The blade of claim 4 , wherein the first pressure side rib, the second pressure side rib, the first internal rib, and the pressure side wall define a discrete quadrilateral shaped cavity in a radial airfoil cross section of the airfoil.

6. The blade of claim 5 , wherein the discrete quadrilateral shaped cavity is trapezoidal shaped in the radial airfoil cross section.

7. The blade of claim 4 , wherein the second pressure side rib, the second suction side rib, the third pressure side rib, and the third suction side rib form a quadrilateral shaped cavity in a radial airfoil cross section of the airfoil.

8. The blade of claim 4 , wherein the second pressure side rib, the second suction side rib, the third pressure side rib, the third suction side rib, the pressure side wall, and the suction side wall form a hexagonal shaped cavity in a radial airfoil cross section of the airfoil.

9. The blade of claim 4 , wherein the first pressure side rib and the first internal rib form a first angle, wherein the first angle transitions from an obtuse angle in the radial airfoil plane to a right angle in the radial attachment plane.

10. The blade of claim 4 , wherein the third pressure side rib and third suction side rib form a second angle that increases to 180 degrees as the third pressure side rib and the third suction side rib transition from the radial airfoil plane to the radial attachment plane.

11. A gas turbine engine, comprising:
a turbine rotor comprising:
a blade comprising:
an attachment having a radial attachment plane;
an airfoil disposed radially outward from the attachment, the airfoil comprising:
a leading edge;
a trailing edge;
a pressure side wall;
a suction side wall;
a first plurality of ribs, comprising:
a first pressure side rib extending from the pressure side wall away from the leading edge;
a first suction side rib extending from the suction side wall away from the leading edge and forming a first vertex with the first pressure side rib;
a second pressure side rib aft of the first pressure side rib and extending from the pressure side wall away from the trailing edge;
a second suction side rib disposed aft of the first suction side rib and extending from the suction side wall away from the trailing edge and forming a second vertex with the second pressure side rib; and
a first internal rib extending from the first vertex to the second vertex, wherein the first pressure side rib and the first internal rib form a first angle, wherein the first angle transitions from an obtuse angle in a radial airfoil plane to a right angle in the radial attachment plane.

12. The gas turbine engine of claim 11 , wherein the airfoil further comprises a second plurality of ribs, the second plurality of ribs comprising:
a third pressure side rib disposed aft of the second pressure side rib and extending from the pressure side wall away from the leading edge;
a third suction side rib disposed aft of the second suction side rib and extending from the suction side wall away from the leading edge and forming a third vertex with the third pressure side rib;
a fourth pressure side rib disposed aft of the third pressure side rib and extending from the pressure side wall away from the trailing edge;
a fourth suction side rib disposed aft of the third suction side rib an

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Spangler Brandon W
• Pack David R

Classifications

• Y02T50/60

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

• F01D5/181 Primary

  Blades having a closed internal cavity containing a cooling medium, e.g. sodium · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F05D2250/13

  trapezoidal · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title