Fan blade anti-icing concept

Patent metadata

Field	Value
Publication number	US-11073082-B2
Application number	US-201916683552-A
Country	US
Kind code	B2
Filing date	Nov 14, 2019
Priority date	Oct 25, 2019
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.

First claim

What is claimed is:

1. A fan blade anti-icing system for a gas turbine engine comprising:
a fan hub mounted for rotation about an axis; and
a fan blade extending radially outwardly from the fan hub, the fan blade having a base and an airfoil extending radially outwardly from the base, the airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge, the fan blade further having a radial passage extending from a blade air inlet in the base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil, wherein the rearwardly directed passage comprises a recessed pocket in the concave side surface or the convex side surface of the airfoil, the recessed pocket being in communication with the radial passage, the recessed pocket being covered with a cover defining an internal plenum within the airfoil, and wherein the blade air outlet communicates with the internal plenum.

2. The fan blade anti-icing system according to claim 1 comprising a plurality of rearwardly directed passages in communication with the radial passage and a plurality of blade air outlets in the concave side surface of the airfoil.

3. The fan blade anti-icing system according to claim 2 wherein the plurality of rearwardly directed passages and the plurality of blade air outlets are oriented towards the trailing edge.

4. The fan blade anti-icing system according to claim 3 wherein the plurality of rearwardly directed passages and the plurality of blade air outlets are radially spaced apart.

5. The fan blade anti-icing system according to claim 4 wherein the plurality of blade air outlets are radially aligned.

6. The fan blade anti-icing system according to claim 5 wherein the plurality of blade air outlets are disposed in an area of the concave side surface, wherein the area is disposed an offset distance X from the blade platform.

7. The fan blade anti-icing system according to claim 1 comprising a plurality of blade air outlets disposed: through the cover; in an edge of the cover; and in an edge of the recessed pocket.

8. The fan blade anti-icing system according to claim 1 wherein the cover is sealed to the recessed pocket by one of: adhesive bonding; welding; and diffusion bonding.

9. A fan blade for a gas turbine engine comprising:
a fan blade having a base and an airfoil with a radially outward axis, the airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge, the fan blade further having a radial passage extending from a blade air inlet in the base for communication with a source of heated air, a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or the concave side surface of the airfoil, wherein the rearwardly directed passage comprises a recessed pocket in the concave side surface, the recessed pocket being in communication with the radial passage, the recessed pocket being covered with a cover defining an internal plenum within the airfoil, and wherein the blade air outlet communicates with the internal plenum.

10. The fan blade according to claim 9 comprising a plurality of rearwardly directed passages in communication with the radial passage and a plurality of blade air outlets in the concave side surface of the airfoil.

11. The fan blade according to claim 10 wherein the plurality of rearwardly directed passages and the plurality of blade air outlets are oriented in a rearward direction parallel to a blade platform.

12. The fan blade according to claim 11 wherein the plurality of rearwardly directed passages and the plurality of blade air outlets are radially spaced apart.

13. The fan blade according to claim 12 wherein the plurality of blade air outlets are radially aligned.

14. The fan blade according to claim 13 wherein the plurality of blade air outlets are disposed in an area of the concave side surface, wherein the area is disposed an offset distance from the blade platform.

15. The fan blade according to claim 9 comprising a plurality of blade air outlets disposed: through the cover; in an edge of the cover; and in an edge of the recessed pocket.

16. The fan blade according to claim 9 wherein the cover is sealed to the recessed pocket by one of: adhesive bonding; welding; and diffusion bonding.

17. The fan blade anti-icing system according to claim 1 , wherein the blade air outlet is disposed within an upstream half of the airfoil.

18. The fan blade according to claim 9 , wherein the blade air outlet is disposed within an upstream half of the airfoil.

Assignees

• Pratt & Whitney Canada

Inventors

• Ivakitch Richard
• Menheere David
• Stone Paul

Classifications

• F05D2240/306

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

• F05D2240/305

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

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F01D5/08

  Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title