Gas turbine engine airfoil

Patent metadata

Field	Value
Publication number	US-11041507-B2
Application number	US-201916591046-A
Country	US
Kind code	B2
Filing date	Oct 2, 2019
Priority date	Feb 19, 2014
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A compressor airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction. A positive sweep angle is in the rearward direction. The airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.

First claim

What is claimed is:

1. A compressor airfoil of a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span, wherein a negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction, wherein the airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.

2. A compressor airfoil of a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span, wherein a negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction, wherein the airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is positive at 0% span and has a decrease in trailing edge sweep angle of greater than 10° from 0% span to 40% span, wherein the trailing edge sweep angle is strictly decreasing from 0% span to 40% span.

3. The compressor airfoil according to claim 2 , wherein the curve crosses to the negative leading edge sweep angle at a span position less than 75% span.

4. The compressor airfoil according to claim 3 , wherein the curve crosses to the negative leading edge sweep angle in a range of 60% span to less than 75% span.

5. The compressor airfoil according to claim 2 , wherein the curve crosses to the negative leading edge sweep angle at a span position less than 40% span.

6. The compressor airfoil according to claim 2 , wherein the positive trailing edge sweep angle indicates an airfoil edge that is oriented in the same direction as the velocity vector of an incoming gas flow relative to the leading or trailing edge of the airfoil.

7. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged immediately upstream of the combustor section;
a fan section having an array of twenty-six or fewer fan blades, wherein the low pressure compressor is immediately downstream from the fan section, wherein the low pressure compressor is counter-rotating relative to the fan blades; and
an airfoil arranged in the compressor section outside the high pressure compressor, and the airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span, wherein a negative leading edge sweep angle is in the forward direction, and a positive leading edge sweep angle is in the rearward direction.

8. The gas turbine engine according to claim 7 , wherein the gas turbine engine is a two-spool configuration.

9. The gas turbine engine according to claim 7 , wherein the airfoil is rotatable relative to an engine axis of an engine static structure.

10. The gas turbine engine according to claim 7 , wherein the curve crosses to the negative leading edge sweep angle at a span position less than 75% span.

11. The gas turbine engine according to claim 10 , wherein the curve crosses to the negative leading edge sweep angle in a range of 60% span to less than 75% span.

12. The gas turbine engine according to claim 10 , wherein the curve crosses to the negative leading edge sweep angle at a span position less than 40% span.

13. The gas turbine engine according to claim 7 , wherein the airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.

14. The gas turbine engine according to claim 7 , wherein the airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is positive at 0% span and has a decrease in trailing edge sweep angle of greater than 10° from 0% span to 40% span.

15. The gas turbine engine according to claim 7 , wherein the positive leading edge sweep angle is in the aftward direction along the gas turbine engine's axis of rotation.

Assignees

• Raytheon Tech Corp

Inventors

• Gallagher Edward J
• Brilliant Lisa I
• Straccia Joseph C
• Balamucki Stanley J
• Stephens Mark A
• Hudon Kate

Classifications

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title

• F04D29/324

  Blades · CPC title

• F04D29/384 Primary

  characterised by form · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2220/3217

  for the first stage of a compressor or a low pressure compressor · CPC title