Fan blade tip as a cutting tool

Patent metadata

Field	Value
Publication number	US-10876415-B2
Application number	US-201514623670-A
Country	US
Kind code	B2
Filing date	Feb 17, 2015
Priority date	Jun 4, 2014
Publication date	Dec 29, 2020
Grant date	Dec 29, 2020

Abstract

An airfoil for a gas turbine engine is disclosed. The airfoil may include a first side, and a second side opposite the first side. The first side and the second side may extend axially from a leading edge to a trailing edge and radially from a base to a tip. The tip may include an oblique surface between the first side and the second side.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, comprising:
a pressure side; and
a suction side opposite the pressure side, the pressure side and the suction side extending axially from a leading edge to a trailing edge and radially from a base to a tip, the tip including a flat surface a first oblique surface descending directly from the flat surface towards the pressure side at a first clearance angle and a second oblique surface and a second oblique surface descending directly from the flat surface toward the suction side at a second clearance angle different from the first clearance angle;
wherein a circumferential width of the flat surface varies along its length; and
wherein the flat surface extends only partially between the leading edge to the trailing edge, such that proximate the leading edge and the trailing edge, there is no flat surface.

2. The airfoil of claim 1 , wherein a width of the flat surface is at least 2.54 mm (0.1 in).

3. The airfoil of claim 1 , wherein the first clearance angle of the first oblique surface is between zero to five degrees (0-5°).

4. A gas turbine engine, comprising:
a fan section;
a compressor section downstream of the fan section;
a combustor section downstream of the compressor section; and
a turbine section downstream of the combustor section, at least one of the fan section, compressor section, and the turbine section including:
a rotor,
a plurality of airfoils extending radially from the rotor, and
a fan case surrounding the rotor and the plurality of airfoils, each of the plurality of airfoils having a tip extending between a pressure side, a suction side, a leading edge, and a trailing edge, the tip including:
a flat surface facing the fan case, and
a first oblique surface directly adjacent to the flat surface and extending toward the pressure side at a first oblique angle angled away from the fan case, and a second oblique surface directly adjacent to the flat surface and extending toward the suction side at a second oblique angle different from the first oblique angle;
wherein a circumferential width of the flat surface varies along its length; and
wherein the flat surface extends only partially between the leading edge to the trailing edge, such that proximate the leading edge and the trailing edge, there is no flat surface.

5. The gas turbine engine of claim 4 , wherein the flat surfaces of the tips of the airfoils and the fan case are in sealing contact.

6. The gas turbine engine of claim 4 , wherein the oblique surfaces of the tips of the airfoils reduce frictional heating between the airfoils and the fan case during operation.

7. The gas turbine engine of claim 4 , wherein the fan case includes an abradable seal on an inner surface of the fan case.

8. The gas turbine engine of claim 7 , wherein the flat surface and the oblique surface on the tip of each of the airfoils are designed to cut through the abradable seal of the fan case.

9. The gas turbine engine of claim 4 , wherein the flat surface and the oblique surface of each of the tips of the airfoils undergo treatment for increased wear resistance.

10. A method for reducing frictional heating between airfoils and a casing of a gas turbine engine, the method comprising:
providing a flat surface on a tip of each of the airfoils, the flat surface in sealing contact with the casing;
providing a first oblique surface on the tip of each of the airfoils, the first oblique surface slanted away from the casing and descending directly from the flat surface towards the pressure side at a first clearance angle;
providing a second oblique surface on the tip of each of the airfoils, the second oblique surface slanted away from the casing and descending directly from the flat surface towards the suction side at a second clearance angle different from the first clearance angle; and
operating the gas turbine engine using the oblique surfaces;
wherein a circumferential width of the flat surface varies along its length; and
wherein the flat surface extends only partially between a leading edge to a trailing edge of the airfoil, such that proximate the leading edge and the trailing edge, there is no flat surface.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Hansen James O
• Guo Changsheng

Classifications

• F05D2250/192

  bevelled · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F04D29/164

  of an axial flow wheel · CPC title

• Y02T50/60

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