Modified structural truss for airfoils

Patent metadata

Field	Value
Publication number	US-10378364-B2
Application number	US-201715806224-A
Country	US
Kind code	B2
Filing date	Nov 7, 2017
Priority date	Nov 7, 2017
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.

First claim

The invention claimed is:

1. A gas turbine engine, comprising:
a compressor section configured to compress a gas;
a combustor section configured to receive a fuel and the gas and to combust the fuel and the gas to generate exhaust;
a turbine section configured to receive the exhaust and to generate mechanical power from the exhaust to drive the compressor section; and
an airfoil located in at least one of the compressor section or the turbine section and having:
a pressure side wall,
a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine, and
a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.

2. The gas turbine engine of claim 1 , wherein the multiple air passages include a first plurality of triangular air passages including the at least one triangular air passage, each of the first plurality of triangular air passages being partially defined by the pressure side wall, and a second plurality of triangular air passages partially defined by the suction side wall.

3. An airfoil for use with a gas turbine engine, the airfoil comprising:
a pressure side wall;
a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine; and
a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.

4. The airfoil of claim 3 , wherein the multiple air passages include a first plurality of triangular air passages including the at least one triangular air passage, each of the first plurality of triangular air passages being partially defined by the pressure side wall, and a second plurality of triangular air passages partially defined by the suction side wall.

5. The airfoil of claim 3 , wherein the plurality of ribs include a first plurality of ribs extending from the pressure side wall to the suction side wall, and a second plurality of ribs extending from the pressure side wall to the suction side wall and each forming an angle with at least one of the first plurality of ribs.

6. The airfoil of claim 3 , wherein the plurality of ribs are oriented to facilitate expansion of the pressure side wall and the suction side wall due to exposure to heat during operation of the gas turbine engine.

7. The airfoil of claim 3 , wherein the at least one internal air passage resembles a diamond and is bound on all sides by the plurality of ribs.

8. The airfoil of claim 3 , wherein the at least one internal air passage is a tip feed passage configured to transport air to an outer diameter edge or an inner diameter edge of the airfoil.

9. The airfoil of claim 3 , wherein the airfoil is configured for use as at least one of a blade or a vane in a compressor section or a turbine section of the gas turbine engine.

10. The airfoil of claim 3 , wherein the multiple air passages further include a leading edge cavity located at a leading edge of the airfoil, and a trailing edge cavity located at a trailing edge of the airfoil.

11. The airfoil of claim 3 , wherein the plurality of ribs further define an opening between two of the multiple air passages to facilitate air transfer therebetween.

12. An airfoil for use with a gas turbine engine, the airfoil comprising:
a pressure side wall;
a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine; and
a plurality of ribs defining multiple air passages including a first triangular air passage partially defined by the pressure side wall and a second triangular air passage partially defined by the suction side wall.

13. The airfoil of claim 12 , wherein the plurality of ribs include a first plurality of ribs extending from the pressure side wall to the suction side wall, and a second plurality of ribs extending from the pressure side wall to the suction side wall and each forming an angle with at least one of the first plurality of ribs.

14. The airfoil of claim 12 , wherein the plurality of ribs are oriented to facilitate expansion of the pressure side wall and the suction side wall due to exposure to heat during operation of the gas turbine engine.

15. The airfoil of claim 12 , wherein the multiple air passages includes at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.

16. The airfoil of claim 12 , wherein the multiple air passages include at least one internal air passage that resembles a diamond and is bound on all sides by the plurality of ribs.

17. The airfoil of claim 12 , wherein the multiple air passages include at least one tip feed passage configured to transport air to an outer diameter edge or an inner diameter edge of the airfoil.

18. The airfoil of claim 12 , wherein the airfoil is configured for use as at least one of a blade or a vane in a compressor section or a turbine section of the gas turbine engine.

19. The airfoil of claim 12 , wherein the multiple air passages further include a leading edge cavity located at a leading edge of the airfoil, and a trailing edge cavity located at a trailing edge of the airfoil.

20. The airfoil of claim 12 , wherein the plurality of ribs further define an opening between two of the multiple air passages to facilitate air transfer therebetween.

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W
• Otero Edwin
• Pack David R

Classifications

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F04D29/324

  Blades · CPC title

• F05D2250/11

  triangular · CPC title

• F05D2240/126

  Baffles or ribs · CPC title